everts air cargo revision transmittal sheetevertsair.com/vendors/dc-9 maintenance manual.pdfboeing...

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14 CFR REGULATIONS REQUIRE THAT COMPANY MANUALS BE MAINTAINED CURRENT.MANUAL HOLDERS NEED TO SIGN BELOW. YOUR SIGNATURE ATTESTS THAT YOU HAVERECEIVED, REVIEWED, UNDERSTAND, AND INSERTED THIS REVISION.

REPLACED PAGES WILL BE DESTROYED.

NAME OF MANUAL HOLDER/USER MANUAL #

PLACE A CHECK HERE TO INDICATE THAT YOU HAVE MADE ANENTRY ON THE REVISION CONTROL PAGE (INTRO-3):

SIGNATURE OF MANUAL HOLDER/USER DATE

Please return this signature page no later than seven (7) days from issued revi-sion to:

EVERTS AIR CARGOPUBLICATIONS DEPARTMENTP.O. BOX 61680FAIRBANKS, AK 99706FAX: 907-450-2320

Everts Air Cargo Revision Transmittal SheetREVISION NUMBER

DATE

Rev 3 04 March 2014

303/04/2014

The following revisions apply to your EVERTS AIR CARGO DC-9 MAINTENANCE MANUAL, datedFebruary 21, 2011. These changes have been incorporated into the Everts Air electronic manual system.Please review the changes below.

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Intentionally Left Blank

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CHAPTER PAGE DESCRIPTION OF CHANGES INSTRUCTIONS

LEP Updated List of Effective Pages.Replaced ‘Accepted’ with ‘Approved’ in FAA Signature.

Remove LEP-1 to LEP-4.Insert LEP-1 to LEP-4.

TOC Updated Table of Contents. Remove TOC-1 to TOC-4.Insert TOC-1 to TOC-4.

Preface Intro-1 Added ‘Revision procedures for all Everts...’.

Remove pages Intro-1 to Intro-2.Insert pages Intro-1 to Intro-2.

Chapter 1 1-1, 1-2, 1-4, 1-13 to 1-15

Pagination for chapter 1 has changed.1.1 EffectivityChanged ‘AX’ to ‘CE’ in first and second item in table.Added additional row for ‘N935CE’.1.3 Source DocumentsReplaced ‘On-Aircraft Maintenance Planning’ with ‘Maintenance Planning Document’ and ‘ME9-001’ with ‘ME9-007’.Replaced ‘AC 121-22A’ with ‘AC 121-22 (Current Revision)’.1.11.1 Special InspectionsAdded ‘Special inspections accomplished...’ to end of paragraph.Added ‘NOTE’ section below paragraph.1.21 DefinitionsAdded ‘Out Of Service’ row to table.1.23 Clock StoppageReplaced reference to obsolete ‘Maintenance Check Manual’ with ‘EAC DC-9 Mainatenance Manual...’.1.25 Short-Term Inspection EscalationReplaced ‘D76’ with ‘D076’.1.29 Routine Checks Occuring at Intervals at 4 Months or GreaterAdded ‘In the event the aircraft exceeds...’ to end of paragraph.1.31 Accomplishment of Scheduled InspectionsReplaced reference to ‘Maintenance Check Manual’ with ‘Task Card Manual’.

Remove pages 1-1 to 1-14.Insert pages 1-1 to 1-16.

Chapter 2 2-2, 2-3, 2-4, 2-5, 2-9, 2-10, 2-12, 2-22

Pagination for chapter 2 has changed.2.4.1 Enging Receiving Inspection...Added new section.2.4.2 Incoming Engine Component...Added new section.2.5 Electrical Wiring Interconnection...Added ‘OpSpec D097’ to end of title.2.6 Fuel Tank System (SFAR 88)...Added ‘OpSpec D097’ to end of title.2.8.1 GeneralRemoved ‘or F800’ after ‘F1000’.2.8.2 System DescriptionAdded ‘The data is not filtered...’.2.8.4 Data ConversionRemoved ‘or F 800’ before ‘F 1000’.Changed ‘L-3 Communications’ to ‘a vendor’.

Remove pages 2-1 to 2-40.Insert pages 2-1 to 2-32.

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Chapter 2 (continued)

2.9.2 Scheduled Maintenance TasksReplaced ‘091C-001’ with ‘23-071-01-02’.2.10 Systems and Powerplant Master...Corrected sorting of indices.Changed 1A task card number from ‘33-042-04-12’ to ‘33-042-04-02’Added 1A task card items ‘51-01EAC’, ‘52-01EAC’, and ‘52-02EAC’.Changed 1A task card numbers from ‘79-003-03-01’ to ‘79-001-03-01’ and 79-003-03-02’ to ‘79-001-03-02’.Removed task cards ‘73-04EAC’ and ‘73-05EAC’ from this index.2.11 Systems and Powerplant Maint...Corrected format and sorting of list.Changed ‘FC’ to ‘Flight Cycles’ in ‘73-001-02’ Description.

Chapter 3 3-3, 3-4, 3-5, 3-7, 3-8, 3-9

Pagination has been corrected.3.8 Structural Maintenance Program...Corrected format and sorting of list.Removed task card 53-704-02 from this index.Changed all instances of ‘FC’ in the Interval column to ‘Flight Cycles’.

Remove pages 3-3 to 3-13 (entire chapter) - incorrectly paginated.Insert pages 3-3 to 3-10.

NOTE: All pages/chapters after page 3-3 will need to be removed due to incorrect pagination. This can be done now.

Chapter 4 Pagination has been corrected.4.3 Zonal Inspection TasksCorrected format and sorting of list.

Remove entire chapter 4 - incorrectly paginated.Insert pages 4-1 to 4-4.

Chapter 5 5-1, 5-2 Pagination has been corrected.5.3 EAC Supplemental Inspection...Corrected format and sorting of list.Replaced ‘05-01’ with ‘05-01EAC’ and ‘09LM-001EAC’ with ‘05-001-00-01’.Replaced ‘05-02’ with ‘05-02EAC’ and ‘09LM-002EAC’ with ‘05-001-00-02’.Removed task card ‘32-02EAC’ from list.Replaced ‘14-04EAC/35-05EAC’ with ‘34-04EAC’, and added ‘34-04EAC’ to end of line item.Added ‘1675 Flight Cycles’ to Interval column of task number ‘34-05EAC’.Added ‘34-05EAC’ to end of ‘34-05EAC’ line item.Added ‘As Req.’ to Interval column of task card ‘71-01EAC’.Added ‘71-01EAC’ to Task Card column of Task Number ‘71-01EAC’.


Chapter 6 6-6, 6-7, 6-9 Pagination has been corrected.6.5 Preweighing Checklist - Form M-9ARemoved items 42 and 43 from the ‘Verify That’ table.6.6 Form M-9EAdded ‘30’ to ‘Cargo Straps’ in table.6.8 Change to Basic...Form M-9HAdded items 6 and 7.


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Chapter 7 7-1 Pagination has been corrected.Section 7 DC-9 Equipment Inventory List - Form M-9BReplaced ‘N904AX’ with ‘N904CE’ and ‘N930AX’ with ‘N930CE’ and ‘N935AX’ with ‘N930CE’.


Task Cards TC-1, TC-2, TC-3, TC-5 to TC-9, TC-13, TC-27, TC-55 to TC-59, TC-61 to TC-64,

Pagination has changed for the Task Card chapter.TC 05-01EACChanged ‘09LM001EAC’ to ‘05-01EAC’ in ‘EAC CARD NO.’ field on all three task cards of this card set.TC 05-02EACReplaced ‘09LM-002EAC’ with ‘05-02EAC’ on all 5 task cards in this set.Removed ‘Every’ from the ‘REPEAT’ section of this card series.Removed item ‘7-E’ from task card TC-7 referring to recording APU hours.TC 08-02-EACAdded BOW Index Unit information to form on page TC-13, below the picture of the aircraft.TC 25-15EACAdded ‘(Stud P/N...)’ to item 1 in table.Added ‘(P/N MS24693S272)’ to item 4.Added NOTE below item 8.TC 34-04EACMoved up from end of chapter.TC 34-05EACAdded ‘1675 Flight Cycles’ to the ‘REPEAT’ section of this card set.Removed item ‘v’ on card 2 of 5. This has caused subsequent numerals on the card to shift (pg. TC-56).Added ‘Proceed to Step 4’ to item ‘B’ on card 2 of 5 (pg. TC-56).Added ‘(Alternate Method)’ to item 3 title (pg. TC-56).TC 34-08EACChanged ‘097C028...’ with ‘34-054-01-01’ in Related Card section of this card set.TC 35-04-EACInserted ‘and Courier’ into ‘TITLE’ section of cards.Replaced ‘Verify that all of the avionics...’ with ‘Check last test date...’ in item ‘1’ in the ‘Procedure’ section.Added item ‘2’ to the ‘Procedure’ section of card 2 of 2.

Remove entire Task Card chapter - incorrectly paginated.Insert pages TC-1 to TC-138.

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Task Cards continued

TC-69 to TC-91, TC-93,

TC 51-01EACAdded new task card set 51-01EAC.TC 52-01-EACAdded new task card set 52-01EAC.TC 52-02-EACAdded new task card set 52-02EAC.TC 52-03-EACAdded new task card set 52-03EAC.TC 71-01EACAdded ‘See Below / Compliance Required’ to ‘Related Card’ field.Added ‘Related Task Cards...’ above first NOTE.TC 34-04EACRemoved duplicate entry of task card 34-04EAC from end of chapter (out of place).

Revision Control Entry Record the insertion of this revision on the Revision Control Page on INTRO-3.

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DC-9 MAINTENANCE MANUAL

DC-9 Maintenance Manual

THIS MANUAL IS THE PROPERTY OF EVERTS AIR CARGO

The person, or office, this manual has been assigned to will be responsible for the general maintenance and insertion of revisions.

This document has EAR data with Export Control Classification Numbers (ECCN) of:

9E991

Export of this technology is controlled under the Untited States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreing persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright 2010 The Boeing Company

Unpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyright-able subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one of more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

MANUAL NUMBER ___________________________

ASSIGNED TO ___________________________

POSITION ___________________________

DATE ___________________________

Rev 2 17 April 2012

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Table of ContentsChapter Preface- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -INTRO-1

Chapter 1 Introduction - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-1

1.1 Effectivity - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-11.2 General - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-11.3 Source Documents - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-11.4 DC-9 Maintenance Manual Responsibility - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-21.5 Manual Format - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-31.6 Manual Control and Revision Instructions- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-31.7 Aircraft Records - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-31.8 Maintenance Manual Revision - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-41.9 Aircraft Systems & Components - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-41.10 Aircraft Structures- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-41.11 Winter Operations- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-4

1.11.1 Special Inspections - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-41.12 Ground Handling - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-41.13 RVSM Equipment- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-41.14 Periodic Aircraft Weighing- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-41.15 Aircraft Test Flight Requirements - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-5

1.15.1 Engines- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-51.15.2 Aircraft - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-5

1.16 Engines - Pratt & Whitney JT8D - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-61.16.1 "On Condition" Program - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-61.16.2 Engine Condition Monitoring Program - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-6

1.16.2.1 General Concepts - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-61.16.2.2 Authority - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-6

1.16.3 Fuel Nozzle Maintenance- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-71.16.4 Decision Process - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-71.16.5 Technical Support- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-71.16.6 Maintenance Action Procedures - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-7

1.17 Auxiliary Power Unit- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-71.18 Landing Gear - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-81.19 MSG-3 Training Requirements - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-81.20 Acronyms (DC-9 Maintenance Review Board) - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-91.21 Definitions- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-121.22 Inspection Schedule- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-141.23 Clock Stoppage - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-141.24 Out of Cycle Items - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-151.25 Short -Term Inspection Escalation - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-151.26 Maintenance and Inspection Package Development - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-151.27 Airworthiness Directives, Time Limit Control, and Airworthiness Limitations - - - - - - - - - 1-151.28 Routine Checks Occurring at Intervals Less Than 4 months. - - - - - - - - - - - - - - - - - - - - - 1-151.29 Routine Checks Occurring at Intervals at 4 Months or Greater.- - - - - - - - - - - - - - - - - - - - 1-151.30 Assembly of Check Work Packages - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-151.31 Accomplishment of Scheduled Inspections - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1-15

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Table of ContentsChapter 2 Systems and Powerplant Program - - - - - - - - - - - - - - - - - - - - - - - - - -2-1

2.1 Purpose - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-12.2 General- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-12.3 Systems and Powerplant Maintenance Program- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-12.4 Systems and Powerplant Maintenance Requirement Rules - - - - - - - - - - - - - - - - - - - - - - - 2-1

2.4.2 Incoming Engine Component Inventory - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-32.5 Electrical Wiring Interconnection Systems (EWIS) Maintenance Program OpSpec D097 - - 2-42.6 Fuel Tank System (SFAR 88) Maintenance Program OpSpec D097 - - - - - - - - - - - - - - - - - 2-42.7 Systems Maintenance Significant Items (MSI) - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-42.8 DFDR Maintenance Program - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-4

2.8.1 General - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-42.8.2 System Description - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-42.8.3 Scheduled Maintenance Tasks - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-42.8.4 Data Conversion - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-5

2.9 Cockpit Voice Recorder Maintenance Program- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-52.9.1 General - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-52.9.2 Scheduled Maintenance Tasks - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-5

2.10 Systems and Powerplant Master Control Forms - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-52.11 Systems and Powerplant Maintenance Tasks - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 2-16

Chapter 3 Structural Maintenance Program - - - - - - - - - - - - - - - - - - - - - - - - - -3-1

3.1 Purpose - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 3-13.2 Supplemental Inspection Document (SID) - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 3-13.3 Corrosion Prevention and Control Program (AD 92-22-08R2)- - - - - - - - - - - - - - - - - - - - - 3-23.4 Program Rules - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 3-23.5 General- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 3-23.6 Introduction- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 3-23.7 Notes - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 3-33.8 Structural Maintenance Program Tasks - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 3-3

Chapter 4 Zonal Inspection Program (ZIP) - - - - - - - - - - - - - - - - - - - - - - - - - - -4-1

4.1 Program Rules - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 4-14.2 Zonal Reanalysis - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 4-14.3 Zonal Inspection Tasks - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 4-1

Chapter 5 EAC Supplemental Inspection Tasks - - - - - - - - - - - - - - - - - - - - - - - -5-1

5.1 General- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 5-15.2 EAC Developed Task Cards- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 5-15.3 EAC Supplemental Inspection Tasks - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 5-1

Chapter 6 Weight and Balance Procedures - - - - - - - - - - - - - - - - - - - - - - - - - - -6-1

6.1 Policies- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-16.1.1 General - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-16.1.2 Responsibilities - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-16.1.3 Controlling Documents- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-1

6.2 Weight and Balance Control - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-1

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Table of Contents6.2.1 Individual Aircraft Weight and Balance Control - - - - - - - - - - - - - - - - - - - - - - - - - - 6-16.2.2 Responsibility - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-1

6.3 Terms and Definitions - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-26.3.1 Arm - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-26.3.2 Center of Gravity (CG) - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-26.3.3 Center of Gravity Limits - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-26.3.4 Center of Gravity Range - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-26.3.5 Datum (REF. Datum) - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-26.3.6 Equipment Check List - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-26.3.7 Required Equipment List - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-26.3.8 Moment - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-26.3.9 Moment Index (or Index) - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-26.3.10 Station - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-36.3.11 Basic Weight - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-36.3.12 Empty Weight - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-36.3.13 Basic Operating Weight- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-36.3.14 Basic Operating Index - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-36.3.15 Operating Index - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-3

6.4 Weight and Balance Forms: M-9, M-9A, M-9B, M-9E, M-9G, and M-9H - - - - - - - - - - - - - 6-36.4.1 Pre-Weighing Check List (Form M-9A) - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-36.4.2 Aircraft Equipment List (Form M-9B) - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-36.4.3 Aircraft Actual Weight and Balance (Task Card 08-02 EAC): - - - - - - - - - - - - - - - - - 6-36.4.4 Accumulative Weight Change Record (Form M-9G) - - - - - - - - - - - - - - - - - - - - - - - 6-46.4.5 Change to Basic Operating Weight (BOW) (Form M-9H) - - - - - - - - - - - - - - - - - - - - 6-4

6.5 Preweighing Checklist - Form M-9A - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-56.6 Form M-9E - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-7

Deviations of Basic Empty Weight (BEW) 7Calculation of Basic Operating Weight (BOW) 7

6.7 Accumulative Weight Change Record (Form M-9G) - - - - - - - - - - - - - - - - - - - - - - - - - - - 6-86.8 Change to Basic Operating Weight (BOW) Form M-9H - - - - - - - - - - - - - - - - - - - - - - - - - 6-9

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PREFACEThis manual remains the property of Everts Air Cargo.

As required by, Title 14 CFR Part 121.137, the person to whom this manual is issued shall be responsible for keeping the manual in usable form and in current condition, inserting revisions when received and recording insertion dates on the revision control page.

This manual must be returned to Everts Air Cargo Maintenance Office in the event of termination of employment.

This manual contains instructions, information and data necessary to guide operations personnel in the per-formance of their assigned duties with the highest degree of safety possible.

All information contained herein is in accordance with the various FARs pertaining thereto and as required by the provisions of Title 14 CFR Parts 119 and 121: Certification and Operations: Domestic, Flag and Supplemental Air Carriers and Commercial Operators of Large Aircraft. This manual must be used in con-junction with the FAR's which are referenced throughout the manual. In the event there appears to be a conflict between this manual and the FAR’s, the regulations will preside.

The company will issue a copy of this manual to company employees and such other persons as may be required to ensure the proper performance of their duties and functions. The company will provide revision service for its manual holders to keep them in current status. Each manual holder is responsible for keeping his copy up to date with the revision service provided.

Revision procedures for all Everts Air Cargo manuals are found in the GOM, Volume I, Chapter 1, Page 1.

Whenever a revision is issued, the revisions will be numbered consecutively for each volume and will indi-cate the volume affected by the revision material. The revision letter will contain instructions for adding, removing and replacing revised pages.

Upon completion of the revision, the old pages will be destroyed and the person making the revision will enter the date and his name, for the appropriate revision on the Revision Record page located in the front of the affected volume.

Errors or comments regarding the content of this manual should be brought to the attention of the Director of Maintenance.

Everts Air Cargo is referred to as the abbreviation EAC throughout this manual.

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Rev 2 17 April 2012

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Revision RecordsMAKE ENTRIES WHEN INSERTING REVISIONS IN THIS MANUAL.

REVISION NO BY DATE REVISION NO BY DATE

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Everts Air Cargo Revision Transmittal Sheet

The following revisions apply to your EVERTS AIR CARGO DC-9 MAINTENANCE MANUAL, dated _______________. These changes have been incorporated into the Everts Air Cargo electronic manual system. Please review the changes below.

14 CFR REGULATIONS REQUIRE THAT COMPANY MANUALS BE MAINTAINED CURRENT. MANUAL HOLDERS NEED TO SIGN BELOW. YOUR SIGNATURE ATTESTS THAT YOU HAVE RECEIVED, REVIEWED, UNDERSTAND, AND INSERTED THIS REVISION.

REPLACED PAGES WILL BE DESTROYED.

NAME OF MANUAL HOLDER/USER __________________________________MANUAL # _______

SIGNATURE OF MANUAL HOLDER/USER _____________________________ DATE __________

UPON COMPLETION, MAIL/FAX TO:

EVERTS AIR CARGOPUBLICATIONS MANAGERP.O. BOX 61680FAIRBANKS, AK 99706 907-450-2320

REVISION NUMBERDATE

CHAPTER PAGE DESCRIPTION OF CHANGES INSTRUCTIONS

For future reference it is recommended that you copy this page.

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CHAPTER: 1 INTRODUCTION

1.1 Effectivity

This report ME9-006 was created by Boeing, Maintenance Engineering, Long Beach and is valid for the DC-9 aircraft operated by Everts Air Cargo, Inc. (hereafter known as EAC).

Irrespective of the type of operation environment, the limitations that are described and specified in the Maintenance Specification Document will be adhered to as applicable to the following aircraft:

The aircraft and its component parts, accessories, and appliances shall be maintained in an airworthy con-dition in accordance with the maximum time limits, as authorized in this document for the accomplishment of the maintenance tasks, periodic inspections, and routine checks. The maintenance will be accomplished using the specific maintenance task cards and the DC-9 Aircraft Maintenance Manual (AMM) or other approved sources.

1.2 General

The EAC DC-9 listed in paragraph 1.1 shall be maintained in an airworthy condition in accordance with the inspections and procedures outlined in this inspection program, the approved Boeing technical manu-als, standard practices, and in accordance with Title 14 CFR Part 121 Subpart L. Maintenance, Preventive Maintenance, and Alterations.

The aircraft structure, power plants, systems, and components are to be inspected and serviced periodi-cally, not to exceed the time intervals mentioned in this inspection program.

The EAC DC-9 Maintenance Manual is considered a "Living Document," in that it will be revised to assure that the aircraft continues to be maintained in an airworthy condition. This will be accomplished through revision procedures.

1.3 Source Documents

The DC-9 aircraft operated by EVERTS AIR CARGO, Inc. shall be serviced and maintained in accordance with procedures detailed in relevant chapters of this manual. This manual complies with the requirements of current Federal Aviation Regulations. The following manuals are to be used in conjunction with the EAC General Maintenance Manual and the EAC DC-9 Maintenance Manual:

These manuals may be found at www.myboeingfleet.com or other relevant sources

• DC-9 FAA MSG-3 Maintenance Review Board (MRB) Report - (ME-MRB-9) - Latest Revision

• DC-9 Task Cards (TBC) - (ME9-008) - Latest Revision

• DC-9 Supplemental Inspection Document (SID) - (DM-IS-SID-9)

• DC-9/MD-80/MD-90/717 Special Compliance Item (SCI) - MDC-92K9145

• DC-9 Maintenance Implementation Document (MID) - ME9-005

• Boeing DC-9 Service Bulletins (SB)*

A/C Registration Fuselage No. Manufacturer S/N BUN Delivery Date Model

N904CE 0172 47040 33A102 06-OCT-1967 DC9-32F

N930CE 0445 47363 32A001 09-FEB-1969 DC9-33F

N932CE 0584 47465 33A401 17-APR-1970 DC9-33F

N935CE 0521 47413 33A301 14-JUL-1969 DC9-33F

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• Boeing DC-9 Service Letters (SL)*

• DC-9 FAA Airworthiness Directives (AD's)*

• P&W (Maintenance Manual PN 48167, Engine Manual PN 481672, IPC PN 481675, SPM PN 585005, Component Maintenance Manual, Service Bulletin List)

• Boeing, (DC, MD, 717 Non-Destructive Test Standard Practices Manual (Noncustomized) TP-MDC-93K0393

• DC, MD, 717 Standard Wiring Practices Manual (Noncustomized) D6-82481,

• DC-9 Aircraft Illustrated Parts Catalog (ABX) TP-9IPC-GB-084,

• EAC DC-9 Illustrated Parts Catalog

• EAC DC-9 Aircraft Maintenance Manual

• DC-9 Aircraft Maintenance Manual TP-9MMM,

• DC-9 Cargo Loading Manual (BAL) TP-9CL-BAL,

• DC-9 Component Description and Location List (Noncustomized) ME-761-68,

• DC-9 Maintenance Planning Document (Noncustomized) ME9-007,

• DC-9 Supplemental Inspection Document (Noncustomized) DM-IS-SID-9,

• DC-9, MD-80 Structural Repair Manual (Noncustomized) TP-9SRM,

• DC-9/MD-80 Corrosion Prevention Control Program (Noncustomized) MDC-K4606,

• DC-9/MD-80 Safe-Life Limits (Noncustomized) MDC-J0005,

• Listed STCs (individual list found in each aircraft file)

These requirements are in compliance with Appendix H to 14 CFR, Part 25, Instructions for Continued Airworthiness as described in AC 121-22 (Current Revision).

NOTE: This program meets the requirements of Title 14 CFR 121 Subpart AA - Continued Air-worthiness and Safety Improvements.

NOTE: *Service Letters, Service Bulletins and Airworthiness Directives are reviewed by EAC and integrated into the maintenance program where they are applicable and effective.

1.4 DC-9 Maintenance Manual Responsibility

The person responsible for the administration of this Continuous Airworthiness Maintenance Program and the scheduling of inspections contained herein shall be the Director of Maintenance of Everts Air Cargo.

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1.5 Manual Format

This manual is divided into the following sections:

1.6 Manual Control and Revision Instructions

Requirements for revision of this manual will be handled in accordance with EAC GOM.

Everts Air Cargo will issue a copy of its approved manuals to company employees and such other persons as may be required to ensure the proper performance of duties and functions. Everts Air Cargo will provide revision service for its manuals to keep them in current status. Each manual holder is responsible for keep-ing his copy up-to-date with the revision service provided. However the technical publications manager is responsible for and will monitor the manual revision service and status of the manuals.

Whenever revisions are issued, they will be numbered consecutively and will indicate each chapter and page affected by the revised material. The revision letter will contain instructions for adding, removing and replacing revised pages.

Upon receipt of the revision, the new pages will be inserted, the old pages removed, and the person making the changes will enter the revision on the Revision Record Sheet, sign the transmittal sheet and return to the Technical Publications Manager. Removed pages must be destroyed locally.

On the text portion of the manual, a line to the left of the sentence, paragraph or section indicates the revised material. In the data portion there will be an "R" to the left of the requirement number, which will indicate that task has been revised. When the page is reprinted or revised again the revision bar or "R" for the previous revision will be deleted.

1.7 Aircraft Records

All maintenance records shall be maintained in accordance with Title 14 CFR Part 121 Subpart V - Records and Reports and GMM chapter 4.

Section Title Description

Section 1 Introduction General information pertaining to the Continuous Airworthiness Maintenance Program format, content, and how it is controlled. The inspection schedule to be followed is also specified in this section.

Section 2 Systems and Powerplant Program

The outline of the scheduled maintenance tasks for the Systems and Powerplant Maintenance Program.

Section 3 Structural Maintenance Program

This section provides the basic scheduled tasks and intervals applicable to the aircraft structure.

Section 4 Zonal Inspection Program (ZIP)

This section provides the intervals for the General Visual Inspections (GVI) of each aircraft zone to check system/powerplant installations and structure for security and general condition.

Section 5 EAC Supplemental Inspection Tasks

The Supplemental Inspection Tasks are those requirements that are mandated by modifications. Airworthiness Directives and operator specific requirements.

Section 6 Weight and Balance Procedures

Describes weight and balance procedures.

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1-4


1.8 Maintenance Manual Revision

The Director of Maintenance will review the information and, in conjunction with the Chief Inspector, make appropriate changes to the program through the revision process as stated in GOM chapter 1.

1.9 Aircraft Systems & Components

Aircraft and engine components are listed in Chapter: 2 Systems and Powerplant Program. The Systems and Powerplant Program provides operating times and limitations for components and is arranged in ATA Chapter sequence. A description of the part is given along with the related task card number and the type of task performed. Aircraft and engine systems and components are tracked by the EAC computer system, and Kardex, for each individual DC-9 aircraft in the Everts Air Cargo fleet.

1.10 Aircraft Structures

Aircraft structural inspections are listed in Chapter: 3 Structural Maintenance Program. The Structures Pro-gram provides operating times and limitations for components and is arranged in ATA Chapter sequence. A description of the part is given along with the related task card number and the type of task performed. Aircraft structural inspections are tracked by the EAC computer system, for each individual DC-9 aircraft in the Everts Air Cargo fleet.

1.11 Winter Operations

Refer to the EAC GMM chapter 5 & DC-9 AMM chapter 12 for the winter operation specifics.

1.11.1 Special Inspections

All special inspections such as but not limited to Lightning Strike, Bird Strike, hard/overweight landing, Overspeed, excessive maneuvers, and severe turbulence inspections will be accomplished per the require-ments of the DC-9 AMM Chapter 5 Unscheduled Maintenance Checks. Special inspections accomplished IAW Chapter 5 are to be accomplished by an Inspector or Designated Inspector.

NOTE: Special inspections require a new Airworthiness Release per GMM 4.8.6.

1.12 Ground Handling

Refer to the EAC General Maintenance Manual (GMM) chapter 5 & the DC-9 AMM chapter 9 for specifics.

1.13 RVSM Equipment

The DC-9 aircraft operated by EAC are all compliant to the requirements for operations within airspace designated as Reduced Vertical Separation Minimum (RVSM) as found in 14 CFR 91.180. EAC aircraft have used STC No ST01136LA for its instructions for compliance with the requirements. This STC con-tains Instructions for Continued Airworthiness (ICA) items. These items are listed in this manual.

1.14 Periodic Aircraft Weighing

The aircraft shall be weighed every 36 months.

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1.15 Aircraft Test Flight Requirements

The purpose of a test flight is to establish the airworthiness of an aircraft or engine that has undergone maintenance, repair, alteration, or which may have changed its flight characteristics appreciably or sub-stantially affected its operation in flight.

A Functional Check Flight (FCF) checklist will be used during the test flight; checklists are located in the DC-9 Operations Manual, Book 1, section 4.4.

Inspector and/or mechanic specialist to accompany test flight if requested by crew. Inspector to accompany any test flight deemed necessary by Chief Inspector.

Cabin load and/or ballast will be as directed by pilot making the test flight.

• Inspection department shall determine when a test flight is required. The Inspector assigned to handling of logbooks and releasing of aircraft shall make an entry in the aircraft log book "Aircraft released for test flight only" and sign the airworthiness release.

• The pilot making the Test Flight shall utilize the appropriate FCF checklist and make a notation with his full name and certificate number in Aircraft Log that he has flown the aircraft and found it satisfactory or unsatisfactory.

The Pilot making the flight is responsible for the safe and efficient conduct of the flight; therefore, no test flight will be originated if, in the opinion of the pilot making the test flight, conditions exist or may develop which will jeopardize the safety of the flight, i.e., weather, visibility or gross weight.

Unless otherwise authorized by the Director of Operations, all test flights shall be - day VFR weather con-ditions or night - 1500 feet ceiling and 3 miles visibility. The following maintenance, repair or alteration operations shall require a test flight outlined below:

1.15.1 Engines

1. Double Engine Change

• After completion of the Test Flight, make visual check of engine, accessory section and accom-plish any necessary adjustments.

• The crew shall be fully informed of the condition surrounding the unit change and shall be instructed to maintain a close check on the involved unit throughout the ensuing flight. The aircraft shall be immediately returned to base for any major discrepancies affecting safety that may be found in flight. All ground checks shall be made in accordance with the Maintenance Manual.

1.15.2 Aircraft

1. Changing any combination of two or more control surfaces (stabilizers and/or primary control surface) shall require a Test Flight.

2. Original FAA. Certification of Aircraft onto the EAC operating certificate.

3. All new aircraft, which have not been test flown prior to acceptance and delivery, aircraft out of over-haul, modification or conversion. Aircraft repaired after major damage has been done, shall require a Test Flight.

• Test Flight to be accomplished empty with ballast weight as requested by the crew.

• Test Flight shall be at least the minimum duration required to ascertain the operation of the system/systems causing the test flight.

4. Correction of serious reported rigging defects.

5. Any condition that can not be reproduced satisfactorily on the ground and determined by the Director of Operations and Director of Maintenance

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1.16 Engines - Pratt & Whitney JT8D

With the exception of life-limited parts, off-wing (in-shop) maintenance tasks are not included herein. Off-wing tasks shall be controlled by EAC, based on their specific maintenance programs and approved manuals.

Limitations of life-limited parts are controlled by the engine manufacturers and are published in the Engine Manuals, Section 5. The declared life of these life-limited parts will be lower than the ultimate Predicted Safe Cycle Life (PSCL). A life sampling program to justify an extension to the declared life up to the PSCL in increments will be an approved method of achieving life extensions.

There are no mandatory threshold inspections required. Engine manufacturers may recommend such inspections in the event that in-service experience would dictate the need to examine specific components of individual engines; if this is required, direct negotiations between applicable operators and the engine manufacturers will be necessary. Results of these inspections should be made available by the engine man-ufacturers to other customer airlines as well as the regulatory authorities.

Opportunity Inspections of certain engine components and accessories may be recommended. No specific list of items will be included; however, if the need exists, operators will be requested by the engine manu-facturers to cooperate in obtaining necessary samples on an "as required" basis. Results of these inspec-tions should be made available by the engine manufacturers to other customer airlines as well as the regulatory authorities.

1.16.1 "On Condition" Program

EAC will operate its P&W JT8D series engines On-Condition. The maintenance program is specified in the P&W Maintenance Manual, and aircraft specific MRB recommendations. EAC is primarily responsi-ble for the airworthiness of its aircraft engines and parts thereof.

The P&W JT8D series On-Condition program, while based on MRB and Pratt & Whitney recommenda-tions, is the property of EAC.

The time or cycle life limits and minimum service bulletin requirements listed in this program may be changed based on requests from EAC that are approved by the FAA.

All Airworthiness Directives applicable to the specific PWJT8D series engine in question will be con-trolled and implemented per the procedures stated in the EAC General Maintenance Manual.

All JT8D series engines, either owned or leased will be placed on the EAC P&W JT8D series On-Condi-tion Maintenance program.

1.16.2 Engine Condition Monitoring Program

1.16.2.1 General Concepts

EAC uses a performance monitoring program including borescope inspections, spectrographic oil analysis, and scheduled tasks at prescribed intervals as tools for economically maintaining engines at a high level of safety. The program provides a means to identify engine deterioration, possible impending component fail-ures, and engine system indicating errors.

1.16.2.2 Authority

The engine trend analyst reviews and analyzes engine performance to determine the current health of each engine being operated under this program. The designated primary and Alternate Engine performance ana-lyst will be qualified by having an A & P certificate and borescope training.

The engine trend analyst will designate an alternate to perform the duties of the engine condition monitor-ing program in his/her absence. The designated primary and alternate engine trend analysis will have the necessary training and will be qualified by the training department. This training will be documented and kept on file by the training manager. The designated alternate will have the same authority and responsibil-ity for the engine condition monitoring program as does the engine trend analyst.

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1.16.3 Fuel Nozzle Maintenance

Fuel nozzle maintenance is a key function in the On-Condition maintenance reliability of the P&W JT8D engine. Any time a fuel nozzle system component is replaced for time change requirements, a complete overhauled unit will be installed. Only P&W authorized overhaul facility will complete these overhauls.

1.16.4 Decision Process

The following logic sequence is used by the Engine Trend Analyst during the application of trend interpre-tation and analysis to determine necessary corrective action.

• All deviations are analyzed for possible explanations or data errors.

• Corrective action may consist of the following:

A. Review of data inputs for accuracy.

B. Review of recent Maintenance Action taken that may have affected trends.

C. Performance of instrumentation tests and checks.

D. Performance of borescope inspections.

E. Performance of ground power runs.

F. In-flight observations by the engine trend analyst.

1.16.5 Technical Support

Additional technical support, if necessary to determine initial and/or subsequent corrective action, may be acquired through the sources identified below:

• Other qualified Engine Trend Monitoring Program Data Trend Analysis personnel for confirma-tion of Trend Analysis interpretation.

• Engine Shop (EAC & vendor) personnel with power plant experience and/or training.

• Maintenance Line and Maintenance Supervisor personnel with aircraft/engine operating experience.

• Engine Manufacturer representatives, including factory representative.

• Engine Manufacturer twenty-four-hour Technical Assistance Hot Line.

• Other Pratt and Whitney Manufacturer's representatives.

• Airframe Manufacturer representatives and factory assistance.

1.16.6 Maintenance Action Procedures

When the Engine Trend Analyst determines that a Maintenance Action is necessary, he/she will complete a Form M-13, Special Inspection Compliance Record. The Engine Trend Analyst will forward the Form M-13 to the Maintenance Supervisor on duty. The Maintenance Supervisor will then schedule the aircraft for the work as required by the Form M-13.

1.17 Auxiliary Power Unit

Tasks have been assigned to the program checks prior to reaching the threshold for each respective task. APU tasks in this group are identified in Chapter: 2 Systems and Powerplant Program. Auxiliary Power Unit tasks and components are tracked by the EAC Computer System and Kardex, for each individual air-craft in the Everts Air Cargo fleet.

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1.18 Landing Gear

The landing gear life limited components are listed in report MDC-J0005 - DC-9/MD-80 Safe Life Limits Report. Landing gear components are tracked by the EAC Computer System and Kardex, for each individ-ual aircraft in the Everts Air Cargo fleet.

1.19 MSG-3 Training Requirements

Everts Air Cargo will give sufficient training to Everts Air Cargo maintenance, inspection and records per-sonnel, including any Everts Air Cargo approved vendors and person(s) who will be accomplishing the tasks contained in this manual. Personnel previously trained under another MSG-3 program do not require further training.

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1.20 Acronyms (DC-9 Maintenance Review Board)

The following is a list of common acronyms referenced in this inspection program manual and/or other associated documentation.

Acronym Definition Acronym Definition

A/C Air Conditioning CDP Compressor Discharge Pressure

A/P Autopilot CPCP Corrosion Prevention and Control Program

A/T Autothrottle CPCS Cabin Pressure Control System

AC Advisory Circular CMR Certification Maintenance Requirement

ACARS ARINC Communications & Reporting System

CT Calendar Time

ACM Air Cycle Machine CY Cycles/Landing

ACMP AC Motor Pumps DAC Douglas Aircraft Company

AD Accidental Damage DADC Digital Air Data Computer

ADC Air Data Computer DFDAU Digital Flight Data Acquisition Unit

ADF Automatic Direction Finder DFGS Digital Flight Guidance System

ALI Airworthiness Limitation Instruction DET Detailed Inspection

AFCS Automatic Flight Control System DME Distance Measuring Equipment

AOA Angle of Attack DS Discard

APU Auxiliary Power Unit DTR Damage Tolerance Rating

ATA Air Transport Association E/E Electrical/Electronic

AUX Auxiliary ED Environmental Deterioration

BIT Built in Test EDP Engine Driven Pump

BITE Built in Test Equipment EGT Exhaust Gas Temperature

BUTE Bent Up Trailing Edge EFIS Electronic Flight Instrument System

CASS Continuous Analysis and Surveillance System

ELT Emergency Locator Transmitter

CB Circuit Breaker ENG Engine

CDCCL Critical Design Configuration Control Limitations

EAPAS Enhanced Airworthiness Program for Airplane Systems

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EPR Engine Pressure Ratio LP Low Pressure

EWIS Electrical Wiring Interconnection Systems

LPT Low Pressure Turbine

EZAP Enhanced Zonal Analysis Procedures LVDT Linear Variable Differential Transformer

FAA Federal Aviation Administration MDC McDonnel Douglas Corporation

FAR Federal Aviation Regulation MEA Maintenance Engineering Analysis

FC Functional Check MEL Minimum Equipment List

FCV Flow Control Valve MFGR Manufacturer

FD Fatigue Damage MID Maintenance Implementation Document

FH Flight Hour MLG Main Landing Gear

FMEA Failure Mode and Effects Analysis MMEL Master Minimum Equipment List

GPWS Ground Proximity Warning System MO Month

GVI General Visual Inspection MOD Modulating

FQIS Fuel Quantity Indicating System MRB Maintenance Review Board Report

FSM Fuel System Management MSG-3 Maintenance Steering Group - 3rd Task Force

HP High Pressure MSI Maintenance Significant Item

HPC High Pressure Compressor MTBF Mean Time Between Failure

HPSOV High Pressure Shutoff Valve MTBUR Mean Time Between Unscheduled Removal

HPT High Pressure Turbine MWCS Master Warning & Caution System

HYD Hydraulic NDI Non-Destructive Inspection

I/B Inboard O/B Outboard

IN Inspection OAMP On Aircraft Maintenance Planning

IRS Inertial Reference System OP Operational Check

ISC Industry Steering Committee PCU Power Control Unit

LB Pound PMMEL Proposed Master Minimum Equipment List

LDG Landing Gear PSE Principal Structural Elements

LDNG Landings PRSOV Pressure Regulation and Shutoff Valve

LH Left Hand PPH Policy & Procedures Handbook

LPC Low Pressure Compressor PRV Pressure Regulation Valve

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QAD Quick Attach Detach TAT Total Air Temperature

RH Right Hand TBD To Be Determined

RMP Reversible Motor Pump TCAS Traffic Collision Avoidance System

RPM Revolutions Per Minute TR Transformer Rectifier

RS Restoration VBV Variable Bypass Valve

SATCOM Satellite Communication VC Visual Check

SCI Special Compliance Items VOR Visual Omni Range

SDI Special Detailed Inspection WOW Weight-on-Wheels

SID Supplemental Inspection Document WXR Weather Radar

SOV Shutoff Valve XFEED Crossfeed

SSI Structural Significant Item XFER Transfer

STA Station YR Year

SV Service ZIP Zonal Inspection Program

SWPM Standard Wiring Practices Manual

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1.21 Definitions

The following list contains definitions of common terms that apply to inspections and maintenance actions referenced in this Continuous Airworthiness Maintenance Program manual and/or other associated docu-mentation.

Term Definition

Accidental Damage Physical deterioration of an item caused by contact or impact with an object or influence, which is not part of the aircraft, or by human error during manufacturing, operation of the aircraft, or maintenance practices.

Corrosion Prevention and Control Program

A program of maintenance tasks implemented at a threshold designed to control an aircraft structure to Corrosion level 1 or better.

Corrosion Level 1 Corrosion damage that does not require structural reinforcement or replacement Or Corrosion occurring between successive inspections exceed allowable limit but is local and can be attributed to an event not typical of operator usage of other aircraft in the same fleet (e.g. Mercury spillage).

Corrosion Level 2 Corrosion damage that requires structural reinforcement or replacement, OrCorrosion occurring between successive inspections is widespread and requires blendout.

Corrosion Level 3 Corrosion found during the first or subsequent inspections, which is determined to be a potential urgent airworthiness concern requiring expeditious action.

Discard The removal from service of an item at a specified life limit.

Environmental Deterioration

Physical deterioration of an item's strength or resistance to failure as a result of chemical interaction with its climate or environment.

Electrical Wiring Interconnection Systems

All wiring related components connecting LRUs such as: Wiring, Cannon Plug, Modular Blocks, Clamps, Terminal Strips, Etc

External Access not limited by restrictions more than opening a door or quick opening panel. The term also means access limited by removing a fairing or opening an access hatch.

Fatigue Damage The initiation of a crack or cracks due to cyclic loading and subsequent propagation.

Functional Check A quantitative check to determine if one or more functions of an item perform(s) within specified limits.

Inspection An examination of an item against a specific standard.

Inspection-Detailed (DET)

An intensive examination of a specific structural area, system, installation or assembly to detect damage, failure, or irregularity.

Inspection-General Visual (GVI)

A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity.

Inspection-Special Detailed (SDI)

An intensive examination of a specific item(s), installation or assembly to detect damage, failure, or irregularity.

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Inspection-Zonal A collective term comprising selected general visual inspections and visual checks that are applied to each zone, defined by access and area, to check system and powerplant installations and structure for security and general condition.

Internal Access by removing access panels, equipment, insulation or furnishings, or required disassembly.

Item Any level of hardware assembly.

Lubrication and Servicing (LUB/SVC)

Any act of lubricating or servicing for the purpose of maintaining inherent design capabilities.

Maintenance Significant Item

Items identified by the manufacturer, whose failure could affect safety, and/or are undetectable during operations, and/or could have significant operational impact, and/or could have significant economic impact.

Operational Check A task to determine that an item is fulfilling its intended purpose.

Out Of Service An aircraft is considered out of service when the aircraft is in the process of maintenance, modification, repair, or storage. The aircraft cannot be dispatched for flight until all applicable maintenance tasks are completed and an airworthiness release is signed off in the aircraft log book. During the out of service phase, the scheduled maintenance intervals, flight hours and/or calendar time may be stopped when appropriate storage requirements are completed.

Principal Structural Element

Details, elements, or assemblies which contribute significantly to carrying flight, ground, pressure or control loads, and whose failure could affect the structural integrity necessary for the safety of the airplane.

Repeat Interval The interval between successive accomplishments of a specific maintenance task after reaching the threshold interval.

Restoration (RST) That work necessary to return an item to a specific standard. Restoration may vary from cleaning or replacement of single parts up to a complete overhaul.

Scheduled Maintenance Check

Packaged inspection tasks that are accomplished on a regular basis.

Structural Significant Item

Any detail, element, or assembly, which contributes significantly to carrying flight, ground, pressure, or control loads and whose failure could affect the structural integrity necessary for the safety of the airplane.

Tasks - Maintenance An action or set of actions required to achieve a desired outcome which restores an item to or maintains an item in serviceable condition, including inspection and determination of condition.

Visual Check An observation to determine that an item is fulfilling its intended purpose. It does not require quantitative tolerances and is a failure-finding task.

Term Definition

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1.22 Inspection Schedule

Utilization Parameter Limits: This program is a Low Utilization Maintenance Program (LUMP) developed by Boeing for EAC. The intervals contained in this document are based on a utilization not to exceed 1,500 FH per year. If the utilization is to exceed 1,500 FH per year then the intervals will need to be reanalyzed and adjusted accordingly.

*NOTE: An "AIRWORTHINESS RELEASE" is required on all checks with the exception of the Daily Check.

1.23 Clock Stoppage

The aircraft may not always be in operation and may be placed into an out of service phase described in the EAC DC-9 Maintenance Manual chapter 1.21. Under these conditions, accumulation of calendar time for the maintenance program's scheduled maintenance checks as described above may be halted. This is referred to as "Clock Stoppage". The clock stoppage will continue until such time the maintenance or mod-ification are completed, appropriate actions are complied with, and the conditions for flight and return to service have been met.

This program is designed to keep the 24 month calendar intervals set for the low utilization maintenance program developed by Boeing for EAC and will only be used during "C" check maintenance. Clock stop-page will require the approval of the Director of Maintenance and The Chief Inspector (or their designated agents) prior to its use. To identify that Clock Stoppage has been used, a log book entry in the mainte-nance discrepancies section of the aircraft log stating "Clock Stoppage" with the DOM & CI initials and date. To release the Clock Stoppage, in the Corrective Action section of the log book, the inspector sign-ing the Airworthiness Release will state "Clock Started" and initial in the inspector block.

Item Description

Daily Check A Daily check shall be accomplished every day, once per day, and may exceed 24 hours elapsed time. This check is normally carried out by the flight crew as a function of the First Flight of Day (FFOD) Daily Check. If maintenance performs this daily check normal company procedures will apply for documentation. Regardless of who accomplishes the check, the log book will be annotated as follows:

• The upper case letter D (or Daily),• The captain/qualified mechanic's initials,• Employee identification number • Time of day, and date• Type inspection accomplished entered in the block at the bottom of the log sheet.

Service Check Is normally accomplished every 3 days at stations where properly trained EAC Maintenance personnel are based. (Service check shall be accomplished every three days, and may exceed 72 hours elapsed time).

“A” Check (Systems & Powerplant)

"A" Check (4 Months or 450 hours, whichever comes first) consists of several task type(s) to assure continued airworthiness of the aircraft's powerplant, systems, components and structures. It also consists of a review of the flight logbook and should be performed at stations where qualified maintenance personnel are available.

“C” Check (Systems & Powerplant)

Interval 24 months.

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The records department upon receipt of the log page will make the required corrections to the records based on the dates from that log page.

1.24 Out of Cycle Items

Out of Cycle items are those tasks that are not incorporated into a scheduled maintenance check. These items shall be scheduled and accomplished on an individual basis or in conjunction with a scheduled main-tenance check as required by Everts Air Cargo.

1.25 Short -Term Inspection Escalation

Escalation of maintenance intervals may be accomplished by following the limits found in the Operations Specifications Paragraph D076. Escalations must be approved by the Chief Inspector.

1.26 Maintenance and Inspection Package Development

Aircraft work packages are made up of several types of documents developed to facilitate the specific nature of the generating item. Documents have been developed to issue routine repetitive tasks or one-time actions that are not practical for inclusion in a repetitive task system. This section will deal primarily with repetitive tasks.

1.27 Airworthiness Directives, Time Limit Control, and Airworthiness Limitations

Work package development for these maintenance and inspection tasks will be tracked and prepared fol-lowing the procedures established in the Everts Air Cargo General Maintenance Manual.

1.28 Routine Checks Occurring at Intervals Less Than 4 months.

The Daily / Service check is carried on-board the aircraft to be used as needed. This form requires no con-trol document to accompany issuance.

1.29 Routine Checks Occurring at Intervals at 4 Months or Greater.

Maintenance and Inspection checks that occur at intervals of 4 months or greater and are of a repetitive non-terminating nature are typically incorporated into this program and identified in this manual. In the event the aircraft exceeds the A or C check interval period, (up to a maximum of 10 percent, with a maxi-mum of 90 days), the aircraft will be allowed to fly directly to the maintenance facility where the mainte-nance is to be performed. The aircraft may make technical stops as needed enroute to the maintenance facility. Everts will inform the Flight Standards District Office (FSDO) in the events this extension is used.

1.30 Assembly of Check Work Packages

The Everts Air Cargo Inspection Department will build the inspection work package as stated in the GMM section 7.37 Check Package Assembly Procedures & Checklist, Form M-38. The completed package will be put together with any work documents generated from other sources like Airworthiness Directive, Ser-vice Bulletins, Modification Orders, or other company required documentation issued for accomplishment.

1.31 Accomplishment of Scheduled Inspections

Documentation of scheduled maintenance will be recorded in accordance with procedures outlined in the Task Card Manual or by use of the M-13 form.

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When a task card is issued during a check, a record of to whom the task was issued will be made on the tally sheet. When the task card is completed, the mechanic or inspector who accomplished the task card will sign off the "completed by" block for that task card.

The tally sheet for each check has empty spaces provided below the list of task cards. These blanks are to be used to record additional task cards that are not listed on the tally sheet. Any unused spaces should have a line drawn across them when the check package is issued. At the completion of the check, the completed cards are inventoried against the tally sheet to assure that all of the task cards are completed and accounted for.

The task cards will be signed for by the appropriate person performing the task. It is not always necessary for both Mech and Insp blocks be signed for. Use GMM section 4.4 Required Inspection Items for a list of items that require both mechanic and inspection signature.

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CHAPTER: 2 SYSTEMS AND POWERPLANT PROGRAM

2.1 Purpose

This section provides the basic scheduled tasks and intervals for the Aircraft Systems, Powerplant and Auxiliary Power Unit.

2.2 General

The Everts Air Cargo MSG-3 maintenance requirements for the McDonnell Douglas DC-9 series airplane are made up of systems & powerplant maintenance inspection tasks, which are individually identified in this section.

2.3 Systems and Powerplant Maintenance Program

This section of the manual outlines the scheduled maintenance tasks for the Systems and Powerplant Main-tenance Program. MSG-3 logic was used to develop these on-airplane scheduled maintenance inspection requirements.

Although MSG-3 defines the basic logic used, because of a long operational history, service experience provided additional guidance in determining proper task application and frequency. With the exception of life-limited parts, this process does not generally include off airplane shop maintenance procedures. Off-airplane detailed procedures are controlled by Everts Air Cargo and are derived from Everts Air Cargo Continuous Analysis and Surveillance program (CAS) for Continued Airworthiness as required by the Local Regulatory Authority.

This section also includes several tasks that were defined through the MSG-3 Zonal Analysis process. These tasks (Restoration, Detailed Inspection and General Visual Inspection) are considered applicable and effective to minimize wiring contamination and to detect wiring installation discrepancies that may not be reliably detected through a zonal inspection. Since these tasks were defined through the Zonal Analysis process, they are not system specific and do not have a Failure Effect Category assigned. These tasks have been included under ATA Chapter 20 Systems Tasks.

2.4 Systems and Powerplant Maintenance Requirement Rules

Crew monitoring of airplane instruments is recognized as an integral part of the flight crew normal duties.

Engine sampling is the responsibility of the engine manufacturer. The opportunity/threshold inspection requirements are items pertaining to and performed within the guidelines of the power plant inspection requirements. Disassembly sample inspections of major engine components provide the means for moni-toring mechanical wear and component durability trends so that an effective ongoing maintenance plan can be established. These will be opportunity inspections that are to be performed within specified limits. Inspection findings and data will be obtained from engine parts and components that are disassembled for any reason, as long as they are disassembled to the extent necessary to accomplish the required inspection.

Program rules will apply to these types of powerplants, although individual tasks and procedures will vary due to their design:

Lubrication tasks are not required on deactivated doors if the door operating mechanism is no longer acces-sible from inside the airplane or if the door has been rendered inoperable from inside and/or outside the air-plane.

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2.4.1 Engine Receiving Inspection checklist (JT8D)

Engine Receiving Inspection checklist (JT8D)

Date:

Mech Insp

1a. Record Engine serial number for engine being received.

Engine serial number______________________

1b. Inspect engine for obvious external damage prior to engine being removed from truck.

NOTE: Notify inspection department of any damage found.

Damage found? ___Yes ___No Date_________ EMP#______ Mech XXX

2. Accomplish external inspection of engine for possible hidden damage after engine has been removed from truck and placed on ground

Date_________________ EMP#_________ Mech XXX

3. Keep this copy of the engine receiving checklist with all engine paperwork from engine vendor.

Date_________________ EMP#_________ Insp XXX

4. If engine is QEC’ed, verify QEC components on engine match what is on inventory sheet from Maintenance Repair Organization (MRO)

Date_________________ EMP#_________

5. Ensure all sign-offs are completed, and route paperwork to Stockroom Supervisor

Date_________________ EMP#_________ Insp XXX

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2.4.2 Incoming Engine Component Inventory

Inspector___________________________________________________

Incoming Engine Component Inventory

Date:Engine Serial number:

Basic Engine

Nomenclature Part Number Serial NumberFuel ControlFuel PumpFuel HeaterFuel Pressure switchOil tankFuel Oil CoolerIgnition ExciterStarter Bleed Valve ControlFuel Heat ValveL/H Anti-Ice ValveR/H Anti-Ice ValvePRBCP&D Valve

QEC

StarterStarter Shut-off ValveCSDGeneratorHydraulic PumpCSD Oil Cooler ValveNose Cowl Anti-Ice ValveOil Pressure TransmitterOil Pressure Warning Light SwitchMain Oil By-Pass SwitchCSD Oil Cooler (Fan or Chin Strap)Oil Quantity UnitN1 TachN2 TachFuel Flow Transmitter6th Stage Check Valve8th Stage Check Valve

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2.5 Electrical Wiring Interconnection Systems (EWIS) Maintenance Program OpSpec D097

The EWIS maintenance program is based on EWIS Instructions for Continued Airworthiness (ICA) and published in the DC-9 Maintenance Implementation Document (MID) (ME9-005). These items are included in this maintenance program.

All EWIS tasks have been identified by adding the notation "EZAP" to the task description.

2.6 Fuel Tank System (SFAR 88) Maintenance Program OpSpec D097

The fuel tank system inspection program was based on fuel tank system Instructions for Continued Air-worthiness (ICA) and published in the DC-9 Maintenance Implementation Document (MID) ME9-005 section 3, and the DC-9/MD-80/MD-90/717 Special Compliance Item (SCI) MDC-92K9145. They have been developed in accordance with the applicable provisions of SFAR 88. These items are included in this maintenance program, this meets the requirements set forth in Title 14 CFR 121.1113.

Those items affected by any Supplemental Type Certificate (STC) will have inspections located in ICA section of that STC and have to be approved by the FAA Oversight Office, and as such will not be covered in this program.

2.7 Systems Maintenance Significant Items (MSI)

All Maintenance Significant Items (MSIs) identified by the manufacturer have been subjected to MSG-3 analysis. This process has resulted in the identification of maintenance inspection tasks, which are con-tained in this section. Hard time requirements for maintenance significant items have been incorporated into Section 2 of this manual

2.8 DFDR Maintenance Program

(14 CFR Part 121.344(a)(b)(c))

2.8.1 General

Everts Air Cargo uses the Fairchild F1000 model DFDR on its DC-9 aircraft. All maintenance operation on this recorder system will be accomplished as outlined in the installed STC ST89CH document and L-3 Communications Installation and Operation Instruction Manual.

2.8.2 System Description

The Fairchild SSDFDR meets or exceeds the requirements of Federal Aviation Administration (FAA) Technical Standard Order TSO-C124a and is capable of storing a minimum of 25 hours of flight data. The data is not filtered and meets requirements of 121.346 (d) (1) and (2).

2.8.3 Scheduled Maintenance Tasks

All scheduled maintenance tasks will be accomplished as required by the EAC DC-9 MM document and tracked by task card. The EAC maintenance program contains the following task cards in support of DFDR maintenance:

Task Card Description Interval

31- 01EAC Verify DFDR system 24 mo

31- 02EAC DFDR ULB Battery 6 yr

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2.8.4 Data Conversion

Data is recorded using the F 1000 DFDR. Every 24 months this data is downloaded removing the flightdata recorder and sending it to a vendor for analysis. A converted document is sent back to EAC for review and if there are any anomalies the necessary maintenance actions will be taken. All downloaded data will be stored in the inspections department.

2.9 Cockpit Voice Recorder Maintenance Program

(14 CFR Part 121.359)

2.9.1 General

Everts Air Cargo uses the FA2100 Cockpit Voice Recorder (CVR) system for the DC-9 aircraft. All main-tenance operations on this unit will be accomplished as outlined in the L-3 Fairchild Aviation Recorders FA2100 Component Maintenance Manual

2.9.2 Scheduled Maintenance Tasks

All scheduled maintenance tasks will be accomplished as required by the EAC DC-9 MM document and tracked by task card. The EAC maintenance program contains the following task cards in support of CVR system maintenance:

Task Card Description Interval

23-071-01-02 CVR recording system 24 mo

23- 01EAC CVR ULB Battery 6 yr

2.10 Systems and Powerplant Master Control Forms

The following pages contain master control forms for 1A, 2A, and 4A maintenance checks on DC-9 air-craft. These forms are a listing of all task cards that are required to be completed and will be used to track completion of these lettered maintenance checks.

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DC-9 Task Card Index1A

Aircraft: Station: Date: Interval Aircraft Total Time:

Aircraft Total Cycles:

1A

Task Number

Task Card(s) AMM Reference

Nomenclature Issued Completed

20-040-01

20-040-01-01 20-40-00-210GVI all exposed EWIS in the left and right

powerplants and cowled hinged doors (EZAP).

1A

20-040-01-02 20-40-00-210GVI all exposed EWIS in the left and right

powerplants and cowled hinged doors (EZAP).

1A

24-001-01

24-001-01-01 24-10-00-212Visual check the CSD charge and scavenge

filter differential pressure indicators.1A

24-001-01-02 24-10-00-212Visual check the CSD charge and scavenge

filter differential pressure indicators. 1A

25-11EAC 25-11EAC Widget Inspection. 1A

25-12EAC 25-12EAC Net Inspection. 1A

25-13EAC 25-13EAC Cargo net inspection. 1A

25-14EAC 25-14EAC Seat track cleaning. 1A

25-15EAC 25-15EAC Protective floor installation, removal. 1A

25-050-01

25-050-01-01 25-50-00-210Do a general visual inspection of the cargo

compartment lining for general condition and security.

1A

25-050-01-02 25-50-00-210Do a general visual inspection of the cargo

compartment lining for general condition and security.

1A

25-060-08 25-060-08-01 25-60-00-210 General visual inspection of the fire axe. 1A

25-060-09 25-060-09-01 25-60-00-212Visual check of the first aid and medical kits

for inspection date and seal.1A

25-060-13 25-060-13-01 25-60-00-212Visual check of the personal breathing equipment (seal) and expiration date.

1A

25-060-15 25-060-15-01 25-60-00-212 Visual check of the survival kit. 1A

Print Name:__________________________ Signature:____________________________ Date:________________

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25-060-19 25-060-19-01 25-60-00-710 Operation check of the flashlights. 1A

26-023-02

26-023-02-01 26-20-00-212Visual check of the halon portable fire

extinguishers for proper pressure.1A

26-023-02-02 26-20-00-212Visual check of the halon portable fire

extinguishers for proper pressure.1A

29-012-0229-012-02-01 29-012-02-02

29-00-00-610 Service accumulator to proper charge. 1A

29-012-03

29-012-03-01 29-10-00-211Detailed inspection of the Delta-P indicator

on hydraulic filters.1A


on hydraulic filters.1A


on hydraulic filters. 1A

29-021-01 29-021-01-01 29-20-00-211Detailed inspection of the auxiliary hydraulic pump seal drain container for fluid due to loss

of seal.1A

29-022-01 29-022-01-01 29-20-00-211Detailed inspection of the transfer pump seal drain container for fluid due to loss of seal.

1A

31-051-02 31-051-02-01 31-50-00-710Operational check the take-off warning

system.1A

32-011-01

32-011-01-01 32-10-00-210Do a general visual inspection of the left main

landing gear shock strut assemblies. 1A

32-011-01-02 32-10-00-210Do a general visual inspection of the right main landing gear shock strut assemblies.

1A

32-011-05

32-011-05-01 12-10-00-610Do a visual check of the left main landing

gear hydraulic dampers for fluid level.1A

32-011-05-02 12-10-00-610Do a visual check of the right main landing

gear hydraulic dampers for fluid level.1A




1A

Task Number




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32-013-02

32-013-02-01 32-10-00-210

Do a general visual inspection of the left main landing gear upper & lower side braces, fixed

side braces, upper & lower lock links, and upper & lower torque links.

1A

32-013-02-02 32-10-00-210

Do a general visual inspection of the right main landing gear upper & lower side braces, fixed side braces, upper & lower lock links,

and upper & lower torque links.

1A

32-021-01 32-021-01-01 32-20-00-210Do a general visual inspection of the nose

landing gear shock strut and housing assembly.

1A

32-022-02 32-022-02-01 32-20-00-210

Do a general visual inspection of the nose landing gear upper & lower side braces, fixed

side braces, upper & lower lock links, and upper & lower torque links.

1A


landing gear retract cylinder, bungee cylinder, and lock pins.

1A

32-041-01

32-041-01-01 32-40-00-210Do a general visual inspection of the left main

landing gear wheels.1A

32-041-01-02 32-40-00-210Do a general visual inspection of the right

main landing gear wheels. 1A


landing gear wheels.1A

32-043-01

32-043-01-01 32-40-00-720Functional check of the left main landing gear

brake pins for brake wear. 1A

32-043-01-02 32-40-00-720Functional check of the right main landing

gear brake pins for brake wear. 1A

32-044-09

32-044-09-01 32-40-00-614Service the brake system accumulator in the

left main wheel well. 1A

32-044-09-02 32-40-00-614Service the brake system accumulator in the

right main wheel well. 1A




1A

Task Number




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32-700-01

32-700-01-01 32-10-00-210Zonal Inspection: Nose landing gear and

landing gear doors.1A

32-700-01-02 32-10-00-210Zonal Inspection: Left main landing gear and

landing gear doors.1A

32-700-01-03 32-10-00-210Zonal Inspection: Right main landing gear

and landing gear doors. 1A

33-032-01 33-032-01-01 33-40-00-710Operational check of the main wheel well

lights using cabin floor switch.1A

33-042-01 33-042-01-01 33-40-00-710 Operational check wing strobe lights. 1A

33-042-02 33-042-02-01 33-40-00-710 Operational check anti-collision lights. 1A

33-042-03 33-042-03-01 33-40-00-710 Operational check position lights. 1A

33-042-04

33-042-04-01 33-40-00-211Do a detailed inspection of the left wing

position light lenses for crazing which causes diffusion of light source.

1A

33-042-04-02 33-40-00-211Do a detailed inspection of the right wing

position light lenses for crazing which causes diffusion of light source.

1A

35-04EAC 35-04EAC

Crew oxygen cylinder hydrostatic test Note: DOT 3HT requires a hydrostatic test

every 3 yrs and has a limited service life of 24 years from date of manufacture. DOT 3AA cylinders require a hydrostatic test every 10

yrs. 3AA have an unlimited service life as set

1A

35-010-02 35-010-02-01 35-10-00-212Visual check of the crew oxygen bottle

pressure gauge for proper pressure. 1A

35-010-08 35-010-08-01 35-10-00-710Operational check of the oxygen mask

microphone. 1A




1A

Task Number




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35-12EAC 35-12EAC

Portable oxygen cylinder hydrostatic test Note: DOT 3HT requires a hydrostatic test

every 3 yrs and has a limited service life of 24 years from date of manufacture. DOT 3AA cylinders require a hydrostatic test every 10

yrs. 3AA have an unlimited service life as set

1A

35-020-07 35-020-07-01 35-20-00-212Visual check of the crew oxygen bottle

pressure gauge for proper pressure. 1A

35-030-0135-030-01-01 35-030-01-02

35-30-00-212Visual inspection of the portable oxygen

bottle for proper pressure. 1A

51-01EAC 51-01EAC Aircraft Wet Wash and Interior Cleaning. 1A

52-01EAC 52-01-EAC 52-30-00 Vent Door Inspection and Lube. 1A

52-02EAC 52-02EAC53-32-00-4 /

12-65-0Main Cargo Door Lubrication. 1A

53-100-01 53-100-01-01 53-50-00-210Zonal Inspection: External - lower fuselage, including radome and lower wing fillets - as

viewed from ground.1A

53-100-05 53-100-05-01 53-50-00-210Zonal Inspection: Internal - forward passenger

door stairwell with stairs extended and includes airstairs.

1A

53-100-08 53-100-08-01 53-40-00-210Zonal Inspection: Internal - nose gear wheel well & unpressurized sidewalls, STA 37 to

STA 110. 1A

53-100-09 53-100-09-01 25-50-00-210Zonal Inspection: Internal - Forward and center cargo compartments with liners

installed. 1A

53-100-14 53-100-14-01 53-50-00-210Zonal Inspection: Internal - l/h & r/h main gear wheel wells and view zone 54 from

wheel wells.1A

53-100-15 53-100-15-01 25-50-00-210Zonal Inspection: Internal - aft cargo compartment; with liners installed.

1A




1A

Task Number




Rev 3 04 March 2014

2-11


53-200-01 53-200-01-01 53-50-00-210Zonal Inspection: External - Upper fuselage -

as viewed from ground. 1A

53-200-03 53-200-03-01 53-40-00-210Zonal Inspection: Internal - cockpit area -

STA 69 - STA 160. 1A

53-200-05

53-200-05-01 53-50-00-210Zonal Inspection: Internal - Forward cabin

area. 1A

53-200-05-02 53-50-00-210 Zonal Inspection: Internal - Aft cabin area. 1A

53-300-01 53-300-01-01 53-60-00-210Zonal Inspection: External - aft fuselage and

empennage - as viewed from ground.1A

53-300-04 53-300-04-01 53-50-00-210Zonal Inspection: Internal - APU

compartment.1A

57-500-01 57-500-01-01 57-20-00-210Zonal Inspection: External - lower surface

from ground, slats and flaps extended.1A

57-600-01 57-600-01-01 57-20-00-210Zonal Inspection: External - lower surface

from ground, slats and flaps extended.1A

71-400-01

71-400-01-01 71-10-00-210Zonal Inspection: External - Left powerplant, pylon, cowl door, inlet area, and nose cowl

from ground level.1A

71-400-01-02 71-10-00-210Zonal Inspection: External - Right

powerplant, pylon, cowl door, inlet area, and nose cowl from ground level.

1A

71-400-05

71-400-05-01 71-10-00-210Zonal Inspection: Internal - Left powerplant

and nacelle doors.1A

71-400-05-02 71-10-00-210Zonal Inspection: Internal - Right powerplant

and nacelle doors. 1A




1A

Task Number




Rev 3 04 March 2014

2-12


72-030-02

72-030-02-01 72-30-00-210Do a general visual inspection of the visible parts of the left engine fan blades and stator

vanes. 1A

72-030-02-02 72-30-00-210Do a general visual inspection of the visible parts of the right engine fan blades and stator

vanes.1A

79-001-03

79-001-03-01 79-20-00-902Clean or replace the left main oil pressure

filter and check for contamination (15 micron).

1A

79-001-03-02 79-20-00-902Clean or replace the right main oil pressure

filter and check for contamination (15 micron).

1A

79-14EAC 79-14EAC Oil S.O.A.P. 1A




1A

Task Number




Rev 3 04 March 2014

2-13





2A

Task Number



21-053-01 21-053-01-01 21-00-00-610 Service the ACM 2A

21-054-01 21-054-01-01 21-70-00-902 Restore the Coalescer Bag 2A

32-010-01

32-010-01-01 12-20-00-640 Lubricate the left main landing gear and doors 2A

32-010-01-02 12-20-00-640Lubricate the right main landing gear and

doors2A

32-020-01 32-020-01-01 12-20-00-640 Lubricate the Nose Landing Gear and Doors 2A

33-051-01 33-051-01-01 33-50-00-710Do an operational check of the Emergency Lighting System operated from the Flight

Deck and flight Attendant position2A

49-030-02 49-030-02-01 49-20-00-210Do an operational check of the Turbine

Plenum Drain2A

49-050-02 49-50-02-01 49-50-00-901Replace the Pneumatic Air System Filter

Element2A

49-090-01 49-090-01-01 49-90-00-901Check for contamination and discard the APU

Oil Filter Element2A

74-001-01

74-001-01-01 74-20-00-211Do a detailed inspection of the left engine

ignitor plugs2A

74-001-01-02 74-20-00-211Do a detailed inspection of the right engine

ignitor plugs2A

80-001-01

80-001-01-01 80-00-00-610 Check the left engine starter oil 2A

80-001-01-02 80-00-00-610 Check the right engine starter oil 2A


Rev 3 04 March 2014

2-14





4A

Task Number



27-011-04

27-011-04-01 12-20-00-640Lubricate the left aileron control tab pushrods,

control mechanism hinges, and control tab hinges

4A

27-011-04-02 12-20-00-640Lubricate the right aileron control tab

pushrods, control mechanism hinges, and control tab hinges

4A

27-011-05

27-011-05-01 12-20-00-640Lubricate the sector and pulley bearing on the

lateral control mixers4A

27-011-05-02 12-20-00-640Lubricate the sector and pulley bearing on the

lateral control mixers4A

27-012-03

27-012-03-01 12-20-00-640Lubricate the left aileron trim tab pushrods,

actuators, and tab hinges4A

27-012-03-02 12-20-00-640Lubricate the right aileron trim tab pushrods,

actuators, and tab hinges4A

27-021-02 27-021-02-01 12-20-00-640Lubricate the Rudder Hinges, Trim Tab Hinges, and Control Mechanism Hinges

4A

27-031-02

27-031-02-01 12-20-00-640 Lubricate the elevator assembly 4A

27-031-02-02 12-20-00-640 Lubricate the elevator assembly 4A

27-055-01 27-055-01-01 12-20-00-640Lubricate the eight Flap Actuating Cylinders, Roller Bearings, Hinge Bearings, and Follow-

up Linkage

4A


Rev 3 04 March 2014

2-15


27-063-04

27-063-04-01 12-20-00-640

Lubricate the left wing ground spoiler actuator cranks, control rod ends, idler links, drive links attach pins and fitting, drive link

assembly bolts, drive hinge fittings, and drive drum axis bearing

4A

27-063-04-02 12-20-00-640

Lubricate the right wing ground spoiler actuator cranks, control rod ends, idler links, drive links attach pins and fitting, drive link

assembly bolts, drive hinge fittings, and drive drum axis bearing

4A

27-067-01

27-067-01-01 12-20-00-640Lubricate the left wing ground spoiler

cylinders and spoiler actuators4A

27-067-01-02 12-20-00-640Lubricate the right wing ground spoiler

cylinders and spoiler actuators4A

27-081-02

27-081-02-01 27-80-00-210Do a general visual inspection of the slat drive

mechanism in the left wing leading edge4A

27-081-02-02 27-80-00-210Do a general visual inspection of the slat drive

mechanism in the right wing leading edge4A

27-081-03

27-081-03-01 12-20-00-640 Lubricate the left wing slat drive system 4A

27-081-03-02 12-20-00-640 Lubricate the right wing slat drive system 4A

34-010-02 34-010-02-01 34-10-00-210Do a general visual inspection of the Rudder

Pitot Probe4A



Rev 3 04 March 2014

2-16


2.11 Systems and Powerplant Maintenance Tasks

The following pages contain a listing of the Systems & Powerplant Maintenance Tasks applicable to this manual.

TASK NUMBER DESCRIPTION INTERVAL CAT. TASK

CODE SOURCE EFF. TASK CARD

20-040-01GVI All Exposed EWIS in the Left and Right Powerplants and Cowl Hinged Doors (EZAP)

1A GVI MID ALL20-040-01-0120-040-01-02

24-001-01Visual Check the CSD Charge and Scavenge

Filter Differential Pressure Indicators1A 7 VC MRB ALL

24-001-01-0124-001-01-02

25-050-01Do a general visual inspection of the Cargo Compartment Lining for general condition

and security1A 8 GVI MRB ALL

25-050-01-0125-050-01-02

25-060-08 General Visual Inspection of the Fire Axe 1A 8 GVI MRB ALL 25-060-08-01

25-060-09Visual Check of the First Aid and Medical

Kits for inspection date and seal1A 9 VC MRB ALL 25-060-09-01

25-060-13Visual Check of the Personal Breathing Equipment (seal) and Expiration Date

1A 6 VC MRB ALL 25-060-13-01

25-060-15 Visual Check of the Survival Kit 1A 8 VC MRB ALL 25-060-15-01

25-060-19 Operational Check of the Flashlights 1A 9 OP MRB ALL 25-060-19-01

26-023-02Visual Check of the Halon Portable Fire

Extinguishers for proper pressure1A 9 VC MRB ALL

26-023-02-0126-023-02-02

29-012-02 Service Accumulator to proper charge 1A 9 SV MRB ALL29-012-02-0129-012-02-02

29-012-03Detailed Inspection of the Delta-P Indicator

on Hydraulic Filters1A 9 DET MRB ALL

29-012-03-0129-012-03-0229-012-03-03

29-021-01Detailed Inspection of the Auxiliary

Hydraulic Pump Seal Drain Container for fluid due to loss of seal

1A 6 DET MRB ALL 29-021-01-01

29-022-01Detailed Inspection of the Transfer Pump

Seal Drain Container for fluid due to loss of seal

1A 9 DET MRB ALL 29-022-01-01

31-051-02Operational Check the Take-off Warning

System1A 8 OP MRB ALL 31-051-02-01

32-011-01Do a general visual inspection of the Main

Landing Gear Shock Strut Assemblies1A 5 GVI MRB ALL

32-011-01-0132-011-01-02

32-011-05Visual Check the Left and Right Main

Landing Gear Hydraulic Dampers for fluid level

1A 6 VC MRB ALL32-011-05-0132-011-05-02

32-013-02

Do a general visual inspection of the Main Landing Gear Upper & Lower Side Braces, Fixed Side Braces, Upper & Lower Lock Links, and Upper & Lower Torque Links

1A 5 GVI MRB ALL32-013-02-0132-013-02-02

32-021-01Do a general visual inspection of the Nose

Landing Gear Shock Strut and Housing Assembly

1A 5 GVI MRB ALL 32-021-01-01

32-022-02

Do a general visual inspection of the Nose Landing Gear Upper & Lower Side Braces, Fixed Side Braces, Upper & Lower Lock Links, and Upper & Lower Torque Links

1A 5 GVI MRB ALL 32-022-02-01

Rev 3 04 March 2014

2-17



Landing Gear Retract Cylinder, Bungee Cylinder, and Lock Pins

1A 6 \ 8 GVI MRB ALL 32-035-01-01

32-041-01Do a general visual inspection of the Main

Landing Gear Wheels1A 5 GVI MRB ALL

32-041-01-0132-041-01-02


Landing Gear Wheels1A 5 GVI MRB ALL 32-042-01-01

32-043-01Functional Check the Main Landing Gear

Brake pins for brake wear1A 8 FC MRB ALL

32-043-01-0132-043-01-02

32-044-09 Service the Brake System Accumulators 1A 9 SV MRB ALL32-044-09-0132-044-09-02

33-032-01Operational Check of the Main Wheel Well

Lights using Cabin Floor Switch1A 8 OP MRB ALL 33-032-01-01

33-042-01 Operational Check Wing Strobe Lights 1A 9 OP MRB ALL 33-042-01-01

33-042-02 Operational Check Anti-Collision Lights 1A 9 OP MRB ALL 33-042-02-01

33-042-03 Operational Check Position Lights 1A 9 OP MRB ALL 33-042-03-01

33-042-04Detailed Inspection of the Position Light

Lenses for crazing which cause diffusion of light source

1A 9 DET MRB ALL33-042-04-0133-042-04-02

35-010-02Visual Check of the Crew Oxygen Bottle

Pressure gauge for proper pressure1A 6 VC MRB ALL 35-010-02-01

35-010-08Operational Check of the Oxygen Mask

Microphone1A 9 OP MRB ALL 35-010-08-01

35-020-07Visual Check of the Crew Oxygen Bottle

Pressure gauge for proper pressure1A 6 VC MRB ALL 35-020-07-01

35-030-01Visual Inspection of the Portable Oxygen

Bottles for proper pressure1A 6 VC MRB ALL

35-030-01-0135-030-01-02

72-030-02General Visual Inspection of the visible parts

of the fan blades and Stator Vanes1A 6 GVI MRB ALL

72-030-02-0172-030-02-02

79-001-03Clean or Replace Main Oil Pressure Filter and check for contamination (15 Micron)

1A 6 RS MRB ALL79-001-03-0179-001-03-02

21-053-01 Service the ACM 2A 6 SV MRB ALL 21-053-01-01

21-054-01 Restore the Coalescer Bag 2A 6 RS MRB ALL 21-054-01-01

32-010-01Lubricate the Left and Right Main Landing

Gear and Doors2A 5 \ 6 \ 8 Lubricate MRB ALL

32-010-01-0132-010-01-02

32-010-01 Lubricate the Main Landing Gear and Doors 2A 5 \ 6 \ 8 Lubricate MRB ALL32-010-01-0132-010-01-02

32-020-01 Lubricate the Nose Landing Gear and Doors 2A 5 \ 6 \ 8 Lubricate MRB ALL 32-020-01-01

33-051-01Operational Check of the Emergency

Lighting System operated from the Flight Deck.

2A 8 OP MRB ALL 33-051-01-01

49-030-02Operational Check of the Turbine Plenum

Drain2A 7 OP MRB ALL 49-030-02-01



Rev 3 04 March 2014

2-18


49-050-02Replace APU Air Pressure Regulator Filter

Element2A 7 DS MRB ALL 49-050-02-01

49-090-01Check for contamination and discard Oil

Filter Element2A 9 DS MRB ALL 49-090-01-01

74-001-01 Detailed Inspection of the Igniter Plugs 2A 9 DET MRB ALL74-001-01-0174-001-01-02

80-001-01 Check Starter Oil 2A 6 GVI MRB ALL80-001-01-0180-001-01-02

27-011-04Lubricate the Left and Right Control Tab Pushrods, Control Mechanism Hinges and

Control Tab Hinges4A 6 Lubricate MRB ALL

27-011-04-0127-011-04-02

27-011-05Lubricate the Sector and Pulley Bearing on

the Lateral Control mixers4A 6 Lubricate MRB ALL

24-011-05-0124-011-05-02

27-012-03Lubricate the Left and Right Trim Tab

Pushrods, Trim Tab Actuators and Trim Tab Hinges

4A 6 Lubricate MRB ALL27-012-03-0127-012-03-02

27-021-02Lubricate Rudder Hinges, Rudder Tab Hinges

and Control Mechanism Hinges4A 6 Lubricate MRB ALL 27-021-02-01

27-031-02 Lubricate the Elevator Assembly 4A 6 Lubricate MRB ALL27-031-02-0127-031-02-02

27-055-01Lubricate the eight actuating cylinders, roller

bearings Hinge Bearings and follow-up linkage


27-063-04

Lubricate Ground Spoiler Actuator Cranks, Control Rod Ends, Idler Links, Drive Links

Attach Pins and Fitting, Drive Link Assembly Bolts Drive Hinge Fittings and Drive Drum

Axis Bearing


27-067-01Lubricate the Ground Spoiler Cylinders and

Spoiler Actuators4A 6 Lubricate MRB ALL

27-067-01-0127-067-01-02

27-081-02General Visual Inspection of the Slat Drive

Mechanism4A 6 DET MRB ALL

27-081-02-0127-081-02-02

27-081-03 Lubrication of the Slat Drive System 4A 6 Lubricate MRB ALL27-081-03-0127-081-03-02

34-010-02General Visual Inspection of the Rudder Pitot

Probe (Zone: 63)4A 6 GVI MRB ALL 34-010-02-01

20-030-01

Detailed Inspection of all wires in the area of the Bleed Air Duct Joints (Aft side of Aft Pressure Bulkhead, Left and Right Side)

(EZAP)

1C DET MRB ALL 20-030-01-01

21-021-03Do an operational check of the forward cabin

attendant panel hinged bypass valve.1C OPC MRB ALL 21-021-03-01

21-022-01Conditioned Air Distribution, Recirculation

& Ground Supply. (ref. Boeing MPD pg D.1-3).

1C 6 RS MRB ALL21-022-01-0121-022-01-02

21-031-01Lubricate the Outflow Valve and Butterfly

Valve Assemblies1C 6 Lubricate MRB ALL 21-031-01-01

21-031-03Clean Outflow Valve and Butterfly Valve

Assemblies1C 6 RS MRB ALL 21-031-03-01

21-031-08 Discard Cabin Pressure Controller Filter 1C 6 DS MRB ALL 21-031-08-01



Rev 3 04 March 2014

2-19


21-062-01Clean Cabin Air Temperature Sensor and Air

Sensor Ejector1C 6 \ 7 RS MRB ALL 21-062-01-01

23-071-01 Operational Check for 4 channel operation 1C 9 OP MRB ALL 23-071-01-01

24-001-07 Restoration of the Main Aircraft Batteries 1C 8 RS MRB ALL 24-001-07-01

24-001-11Operational Check of the APU Generator

Field Disconnect1C 8 OP MRB ALL 24-001-11-01

25-015-01Detailed Inspection of the Crew Seatbelt

connecting links1C 5 DET MRB ALL 25-015-01-01

25-015-02 Lubricate Seats and Seat Tracks 1C 6 Lubricate MRB ALL 25-015-02-01

25-015-03Operational Check of the Captain's and First

Officer's Inertial Reel1C 8 OP MRB ALL 25-015-03-01

25-015-04General Visual Inspection of the Seat belts

and Rotary Buckle Assembly1C 8 GVI MRB ALL 25-015-04-01

25-015-06Functional Check of the Seat Belt Attach Bolt

for proper torque1C 8 FC MRB ALL 25-015-06-01

25-060-11

Detailed Inspection of the Life Vest Expiration Date

P/N AV35 - 30 MOS.P/N AC/2000 - 10 YRS

1C 8 DET MRB ALL 25-060-11-01

26-012-01Operational Check of the APU External Fire

Warning Horn and Remote Panel Light1C 8 OP MRB ALL 26-012-01-01

26-012-02Lubricate the APU Fire Warning Horn (If

applicable)1C 9 Lubricate MRB ALL 26-012-02-01

26-023-01Detailed Inspection of the Portable Fire

Extinguishers for proper weight and condition

1C 9 DET MRB ALL26-023-01-0126-023-01-02

27-011-01Detailed Inspection of the Aileron Control

Cables (Exposed Area)1C 6 DET MRB ALL

27-011-01-0127-011-01-02

27-011-06 Lubricate the Control Wheel Bearings 1C 6 Lubricate MRB ALL 27-011-06-01

27-012-01Detailed Inspection of the Aileron Trim

Cables (Exposed area)1C 6 DET MRB ALL

27-012-01-0127-012-01-02

27-013-01Detailed Inspection of the Aileron Bus Cable

System (Exposed Area)1C 9 DET MRB ALL

27-013-01-0127-013-01-02

27-042-01Operational Check of the Primary Trim

Motor Heater1C 9 OP MRB ALL 27-042-01-01

27-051-01Detailed Inspection of the Flap Cable System

in the exposed area1C 6 DET MRB ALL

27-051-01-0127-051-01-02

27-061-01Operational Check of the “SPOILER

DEPLOYED”, “AUTOSPOILER FAIL” or “AUTOSPOILER DO NOT USE” Indication

1C 8 OP MRB ALL 27-061-01-01

27-061-02Operational Check of the “SPOILER FLAP

EXTEND” Indication1C 9 OP MRB ALL 27-061-02-01

27-061-05Operational Check of the Spoiler Lockout

unlocking function1C 9 OP MRB ALL 27-061-05-01

27-062-01Operational Check of the Autospoiler System

(RTO Function only)1C 7 OP MRB ALL 27-062-01-01



Rev 3 04 March 2014

2-20


27-063-01Detailed Inspection of the Spoiler Speedbrake

and Flight Spoiler cables (exposed area)1C 6 DET MRB ALL

27-063-01-0127-063-01-02

28-022-04Operational Check of the Suction Feed

System1C 8 OP MRB ALL 28-022-04-01

29-032-01Detailed Inspection of the cockpit indication

and reservoir level for accuracy1C 9 DET MRB ALL 29-032-01-01

30-030-01Operational Check of the Alternate Static

Port Heaters1C 9 OP MRB ALL 30-030-01-01

32-031-01Detailed Inspection of the Landing Gear

Control Cables (Exposed Area)1C 6 DET MRB ALL 32-031-01-01

32-031-04Detailed Inspection of the Landing Gear Alternate Control Cables (Exposed Area)

1C 8 DET MRB ALL 32-031-04-01

32-044-02General Visual Inspection of the Brake Pedal

Mechanical Linkage1C 8 GVI MRB ALL 32-044-02-01

32-044-03Detailed Inspection of the Brake Pedal

Control Cables (Exposed Area)1C 5 DET MRB ALL

32-044-03-0132-044-03-02

32-046-01

Do an operational check of the Auto Braking System

INTERVAL NOTE: Perform in conjunction with 27-062-01, Operational Check of the Autospoiler System (RTO Function Only)

1CNOTE

8 OPC MRB ALL 32-046-01-01

32-044-06General Visual Inspection of the Parking

Brake mechanism (Zones: 44 and 45)1C 5 GVI MRB ALL

32-044-06-0132-044-06-02

32-051-02Detailed Inspection of the Steering Wheel,

Drum, cables and rudder pedal steering cables

1C 6 DET MRB ALL32-051-02-0132-051-02-02

33-014-01Operational Check of the Emergency Power

Switch to verify operation Cockpit Flood Lights

1C 8 OP MRB ALL 33-014-01-01

33-014-02Operational Check of Cockpit Flood Lights by pulling Emergency Bus Sensing Circuit

Breaker1C 8 OP MRB ALL 33-014-02-01

33-051-02Replace batteries in Emergency Light Battery

Packs1C 8 RS MRB ALL 33-051-02-01

33-051-04

Functional Check of Self Illuminating Exit Signs by Checking Brightness of Sign Using

a Comparator (If Installed)

1C 8 FC MRB ALL 33-051-04-01

34-010-01Visual Check the Pitot and Static System for

water1C 6 VC MRB ALL

34-010-01-0134-010-01-02

34-010-05 Operational Check of the Air Data Switching 1C 9 OP MRB ALL 34-010-05-01

34-022-01 Operational Check of the Compass Switching 1C 9 OP MRB ALL 34-022-01-01

34-024-01 Operational Check of the Attitude Switching 1C 9 OP MRB ALL 34-024-01-01

34-024-02Operational Check of the AUX VG “INOP”

Display1C 9 OP MRB ALL 34-024-02-01

34-029-01Detailed Inspection of the Standby Compass for leaks and freedom of movement of the

Compass Card1C 8 DET MRB ALL 34-029-01-01



Rev 3 04 March 2014

2-21


34-032-01Operational Check of the VHF NAV

Switching1C 6 OP MRB ALL 34-032-01-01

34-046-01 Functional Check of the TCAS System 1C 8 FC MRB ALL 34-046-01-01

35-010-04Detailed Inspection of the Crew Oxygen

Mask and Mic Assembly1C 6 DET MRB ALL 35-010-04-01

35-010-10Detailed Inspection of the Smoke Goggles,

Smoke Hood, Full Face O2 Mask and Smoke Mask

1C 9 DET MRB ALL 35-010-10-01

35-030-03Detailed Inspection of the Oxygen Mask and

Hose Assembly1C 6 DET MRB ALL

35-030-03-0135-030-03-02

49-080-02General Visual Inspection of the Outside

Exhaust Ducting1C 7 GVI MRB ALL 49-080-02-01

52-011-01 Lubricate the Door Mechanism 1C 6 Lubricate MRB ALL 52-011-01-01

52-011-03 Detailed Inspection of the Door Pressure Seal 1C 6 DET MRB ALL 52-011-03-01

52-012-01Lubricate the Aft Cabin Bulkhead Door

Mechanism1C 8 Lubricate MRB ALL 52-012-01-01




52-030-01 Lubricate the Cargo Door Mechanism 1C 6 Lubricate MRB ALL52-030-01-0152-030-01-02

52-030-03Detailed Inspection of the Cargo Door

Pressure Seal1C 6 DET MRB ALL

52-030-03-0152-030-03-02

52-041-02Detailed Inspection of the Avionics and

Forward Accessory Compartment Door Seals1C 6 DET MRB ALL

52-041-02-0152-041-02-02


52-042-03 Detailed Inspection of the Door Seal 1C 6 DET MRB ALL 52-042-03-01

52-070-01Operational Check of the Door Warning


56-012-02 Lubricate the Clearview Window Assembly 1C 9 Lubricate MRB ALL 56-012-02-01

57-001-00Lubricate the articulated bent-up trailing edge

(BUTE) doors and rollers.1C Lubricate MRB ALL 57-001-00-01

57-002-00Detailed inspection of the articulated bent-up

trailing edge (BUTE) doors and rollers.1C DET MRB ALL 57-002-00-01

71-010-01General Visual Inspection of the internal

Nose Cowl and attachments1C 6 GVI MRB ALL

71-010-01-0171-010-01-02

71-010-02 General Visual Inspection of the Inlet Bullet 1C 6 GVI MRB ALL71-010-02-0171-010-02-02

71-010-14Detailed Inspection of the Fan Cowl Latches

and attaching hardware and attachments1C 9 DET MRB ALL

71-010-14-0171-010-14-02



Rev 3 04 March 2014

2-22


71-020-02Detailed Inspection of the Vibration Isolators

NOTE: Also done during engine change.1C 9 DET MRB ALL

71-020-02-0171-020-02-02

72-040-01Special Detailed Inspection of the Burner

Cans (Borescope)1C 9 SDI MRB ALL

72-040-01-0172-040-01-02

72-050-01Special Detailed Inspection of the 1st Stage

Turbine Vanes, and 1st Stage Turbine Blades (Borescope)

1C 6 \ 9 SDI MRB ALL72-050-01-0172-050-01-02

72-050-03Detailed Inspection of the Turbine Blades

(Viewed from exhaust)1C 6 DET MRB ALL

72-050-03-0172-050-03-02

73-001-02

Inspect for contamination and discard the Main Fuel Filter

NOTE: Check 50 Flight Cycles after fuel maintenance.

1C 6 DS MRB ALL73-001-02-0173-001-02-02

78-010-01Detailed Inspection of the Exhaust Cone

(Zones: 75 and 76)1C 9 DET MRB ALL

78-010-01-0178-010-01-02

78-030-03Functional Check of the Low Pressure

Warning Switch1C 9 FC MRB ALL

78-030-03-0178-030-03-02

20-010-06Clean area of dust, lint and all foreign objects

– Aft Cargo Compartment (Waste Tank Area)(EZAP)

2C RS MRB ALL 20-010-06-01

20-010-11GVI All Exposed EWIS in the Main Landing

Gear Wheel Wells (EZAP)ACCESS NOTE: Gear Doors Open

2C GVI MID ALL20-010-11-0120-010-11-02

20-030-02Inspect (GVI) all exposed EWIS in the APU

compartment. (EZAP)2C GVI MID ALL 20-030-02-01

21-029-01Operational Check of the Ram Air Valve


21-033-01Functional Check of the Cabin Low Pressure

Warning and Indication System2C 8 \ 9 FC MRB ALL 21-033-01-01

21-053-02Clean the Primary and Secondary Heat

Exchangers2C 6 RS MRB ALL 21-053-02-01

21-053-03Functional Check of the Supply Temperature

High System Sensor and Alerts2C 9 FC MRB ALL 21-053-03-01

21-055-02 Clean the Cooling Fan Protection Screen 2C 9 RS MRB ALL 21-055-02-01

21-056-01Functional Check of the Auto Pack Shutdown

System2C 9 FC MRB ALL 21-056-01-01

21-056-02Functional Check of the Cabin Delta-P

Switch2C 9 FC MRB ALL 21-056-02-01

21-056-03Operational Check of the A/C Shutoff and

"OVRD" System2C 9 OP MRB ALL 21-056-03-01

21-056-04Functional Check of the Condition Air

Thermal Switch2C 9 FC MRB ALL 21-056-04-01

21-056-05Functional Check of the Turbine Inlet

Thermal Switch2C 9 FC MRB ALL 21-056-05-01

21-056-06Functional Check of the Compressor

Discharge Thermal Switch2C 9 FC MRB ALL 21-056-06-01

21-062-02Operational Check of the Cockpit Supply

Temperature High System and Alerts2C 6 \ 9 OP MRB ALL 21-062-02-01



Rev 3 04 March 2014

2-23


23-060-01Functional Check of the Discharging

Capability2C 6 FC MRB ALL

23-060-01-0123-060-01-0223-060-01-03

24-001-08Operational Check of the Load Shed for

Generators.2C 9 OP MRB ALL 24-001-08-01

24-001-10Operational Check of the mechanical remote

80 amp. C/B reset2C 9 OP MRB ALL 24-001-10-01

25-015-05

Detailed Inspection of the Crew Seats attachments, tracks and locking to structureNOTE: This task satisfies requirement AD

2004-05-25 & SB DC9-25A350

2C 5 DET MRB ALL 25-015-05-01

25-060-07Detailed Inspection of the Escape Lines

(Cockpit and Cabin)2C 9 DET MRB ALL 25-060-07-01

26-021-01Operational Check of the Firex Bottle Low

Pressure Switches and Lights by manual test2C 9 OP MRB ALL 26-021-01-01

26-021-04Operational Check of the Agent Discharge

System to check Firing Circuit Integrity2C 9 OP MRB ALL 26-021-04-01

26-021-05

Do a general visual inspection of the Deployment Lines for general condition,

security, and integrity.ACCESS NOTE: 8202, 8204, 8206 (-10);

8202A, 8204A, 8206A (-20, -30, -40, -50) 8101, 8103, 8105 (-10); 8101A, 8103A,

8105A (-20, -30, -40, -50)

2C 8 GVI MRB ALL26-021-05-0126-021-05-0226-021-05-03

26-021-06Operational Check of the APU Emergency

Shutdown System from the Cockpit and External Panel

2C 8 OP MRB ALL 26-021-06-01

26-021-08

Perform a leak check of the engine and APU fire extinguishing deployment lines.

INTERVAL NOTE: Not to exceed 48 months.

2CNOTE

FC MRB ALL 26-021-08-01

27-023-01Operational Check of the Rudder Hydraulic Shut off system and manual revision mode

2C 9 OP MRB ALL 27-023-01-01

27-040-03Operational Check of the Brake Override

Switch2C 9 OP MRB ALL 27-040-03-01

27-081-05Detailed Inspection of the Slat Drive Tracks

and Slat Drive Cables2C 6 DET MRB ALL

27-081-05-0127-081-05-02

28-022-02Operational Check of the “FUEL LEVEL

LOW” alert and latching circuit2C 8 OP MRB ALL 28-022-02-01

29-012-01Functional Check of the Main Hydraulic

Reservoirs for internal leakage2C 9 FC MRB ALL

29-012-01-0129-012-01-02

30-010-03Functional Check of the 500 Deg “TEMP

HIGH” Sensors, and alerts2C 9 FC MRB ALL 30-010-03-01

30-010-07Operational Check of the “L/R ICE PROT

TEMP LOW” alerts and inhibit circuit2C 9 OP MRB ALL 30-010-07-01

31-051-01Operational Check the Landing Gear Aural

warning2C 8 OP MRB ALL 31-051-01-01

31-051-04Operational Check the Overspeed Aural

warning2C 8 OP MRB ALL 31-051-04-01

32-031-03Operational Check of the Alternate Gear

Extend System2C 8 OP MRB ALL 32-031-03-01



Rev 3 04 March 2014

2-24


32-044-01Functional Check of the Dual Brake Control

Valves2C 5 FC MRB ALL

32-044-01-0132-044-01-02

32-044-07Functional Check of the Brake De-Spin

System2C 5 FC MRB ALL 32-044-07-01

32-045-01Operational Check of the Dual Anti-Skid

Control Valves2C 8 OP MRB ALL 32-045-01-01

34-010-03Functional Check of the Pitot and Static

System for leakage (High Altitude)2C 6 FC MRB ALL 34-010-03-01

34-010-04Operational Check of the Static Selector


34-010-06Functional Check of the Standby Altimeter/

Airspeed System2C 6 FC MRB ALL 34-010-06-01

34-045-01Functional Check of the Ground Proximity

Warning System (Mark II)2C 8 FC MRB ALL 34-045-01-01

36-015-01Detailed Inspection of the APU Check Valve

Flapper and Hinge Pin2C 6 DET MRB ALL 36-015-01-01

52-011-04Functional Check of the Locking Device for

the Door Set Screws2C 6 IN MRB ALL 52-011-04-01

52-021-04 Operational Check of the Door Mechanism 2C 9 OP MRB ALL 52-021-04-01


the Door Set Screws2C 6 FC MRB ALL

52-030-04-0152-030-04-02

52-041-03Do a functional check of the Avionics

Compartment Door Locking Device for the Door Set Screws

2C 6 FNC MRB ALL 52-041-03-01


the Door Set Screws2C 6 FC MRB ALL 52-042-04-01

52-054-01 Functional Check of the Blowout Panels 2C 8 FC MRB ALL 52-054-01-01

56-011-01Do a detailed inspection of the left, center,

and right Windshield2C 6 DET MRB ALL 56-011-01-01

56-012-01Operational Check of the Sliding Clearview

Window2C 9 OP MRB ALL 56-012-01-01

56-012-03Detailed Inspection of the Clearview Window

Pressure Seal2C 6 DET MRB ALL 56-012-03-01

79-030-01Functional Check of the Oil Strainer

Indication System2C 9 FC MRB ALL

79-030-01-0179-030-01-02

24-001-12Detailed Inspection of the External Power

Receptacle (Internal)3C 9 DET MRB ALL 24-001-12-01

24-001-13Functional Check of the External Power

Receptacle Studs with a GO/NO-GO Gage3C 9 FC MRB ALL 24-001-13-01

30-010-01Operational Check of the 130 Deg Overheat

Sensors3C 9 OP MRB ALL

30-010-01-0130-010-01-02

30-010-02Operational Check of the 180 Deg Overheat

Sensors3C 9 OP MRB ALL 30-010-02-01

30-010-04Functional Check of the 300/390 Deg “TEMP

LOW” Sensors and System Alerts3C 9 FC MRB ALL 30-010-04-01

30-010-05Functional Check of the Tail Low Pressure

Switch and System Alerts3C 9 FC MRB ALL 30-010-05-01



Rev 3 04 March 2014

2-25


36-024-01Operational Check of the Tail Compartment

Overheat System and Alerts3C 9 OP MRB ALL 36-024-01-01

71-020-04Lubrication of Front Yoke Bolts

NOTE: Accomplish at with Task 54-499-02.3C 9 Lubricate MRB ALL

71-020-04-0171-020-04-02

20-010-01Clean area of dust, lint and all foreign objects - E and E Compartment (Do not disturb any

systems installations) (EZAP)4C RST MRB ALL 20-010-01-01

20-010-02

Clean area of dust, lint and all foreign objects – Forward Cargo Compartment Upper

Tunnels and Under Side of Cabin Vents (Cusp Holes)(EZAP)

4C RS MRB ALL 20-010-02-01

20-010-03

Clean area of dust, lint and all foreign objects – Area between Lower Surface of Cabin Floor to Upper Surface of Center Wing

(EZAP)

4C RS MRB ALL 20-010-03-01

20-010-04General Visual Inspection of Vapor Barrier - Area between Lower Surface of Cabin Floor

to Upper Surface of Center Wing (EZAP)4C GVI MRB ALL 20-010-04-01

20-010-07

Clean area of dust, lint and all foreign objects – Aft Cargo Compartment, Upper Tunnels

and Upper Side of Cabin Vents (Cusp Holes)(EZAP)

4C RS MRB ALL 20-010-07-01

20-010-08GVI All EWIS in the Nose Gear Wheel Well

and Unpressurized Sidewalls (EZAP)NOTE: With gear doors open

4C GVI MID ALL 20-010-08-01

20-010-09GVI All EWIS in the Forward Cargo

Compartment (EZAP)4C GVI MID ALL 20-010-09-01

20-010-12

GVI All EWIS in the Aft Cargo Compartment (EZAP)

ACCESS NOTE: With ceiling and sidewall panels removed

4C GVI MID ALL 20-010-12-01

20-010-13Detailed Inspection of the Electrical Main

Feeder Cables and Associated Exposed EWIS (EZAP)

4C DET MID ALL

20-010-13-0120-010-03-0220-010-03-0320-010-03-0420-010-13-0520-010-03-0620-010-03-0720-010-03-0820-010-03-09

20-010-14Inspect (GVI) all EWIS in the E & E

compartment including the aircraft batteries (EZAP)

4C GVI MID ALL 20-010-14-01

20-010-15Clean area of dust, lint and all foreign objects - Forward Accessory Compartment (Do not disturb any systems installations) (EZAP)

4C RST MRB ALL 20-010-15-01

20-020-01Clean area of dust, lint and all foreign objects – Cockpit Area, Lower Sidewalls, Floor Area

and EPC (Fwd Side).4C RS MRB ALL 20-020-02-01

20-020-03Clean Lavatory area of dust, lint and all foreign objects – (Under Sink Deck and

Toilet Shroud)4C RS MRB ALL 20-020-03-01



Rev 3 04 March 2014

2-26


20-020-04

GVI All Exposed EWIS in Cockpit Area (EZAP)

ACCESS NOTE: Remove all panels, including floor, instrument, and EPC

4C GVI MID ALL 20-020-04-01

20-050-02

GVI All Exposed EWIS From Rear Spar to Trailing Edge of Left Wing (EZAP)

ACCESS NOTE: Flaps lowered and Spoilers raised

4C GVI MID ALL 20-050-02-01

20-060-02

GVI All Exposed EWIS From Rear Spar to Trailing Edge of Right Wing (EZAP)

ACCESS NOTE: Flaps lowered and Spoilers raised

4C GVI MID ALL 20-060-02-01

21-021-01Detailed Inspection of the Left Check Valves

Flapper and Hinge Pins4C DET MRB ALL 21-021-01-01

21-021-02Operational Check of the Radio Rack

Cooling System Venturi Mode4C OP MRB ALL 21-021-02-01

21-029-02Detailed Inspection of the Cold Air,

Conditioned Air, Ground Air Connector Check Valves Flapper and Hinge Pins

4C 6 \ 7 \ 9 DET MRB ALL 21-029-02-01

21-029-03Detailed Inspection of the Ground

Conditioned Air Access Door Hinge and Latch Assembly

4C 9 DET MRB ALL 21-029-03-01

21-031-02Detailed Inspection of the Outflow Valve and

Butterfly Valve Assemblies4C 6 DET MRB ALL 21-031-02-01

21-031-04Operational Check of the Outflow Valves

Manual Control System4C 9 OP MRB ALL 21-031-04-01

21-031-05Functional Check of the Outflow Valve

Manual Control Cable System4C 9 FC MRB ALL 21-031-05-01

21-031-06Detailed Inspection of the Outflow Valve

Manual Control Cables4C 9 DET MRB ALL

21-031-06-0121-031-06-0221-031-06-03

21-031-07Operational Check of the Cabin Pressure

Transfer Relay4C 9 OP MRB ALL 21-031-07-01

21-034-01Functional Check of the Cabin Positive

Pressure Relief Valves4C 8 \ 9 FC MRB ALL 21-034-01-01

21-034-02 Operational Check of the Equalization Valves 4C 9 OP MRB ALL21-034-02-0121-034-02-02

21-034-03Operational Check of the Negative Pressure

Relief Valve4C 9 OP MRB ALL 21-034-03-01

21-034-04Detailed Inspection of the Negative Pressure

Relief Valve4C 9 DET MRB ALL 21-034-04-01

21-055-03Detailed Inspection of the Diverter Valves

Flapper and Hinge Pins4C 9 DET MRB ALL 21-055-03-01

24-001-09Operational Check of the AC Crosstie

Lockout Alert4C 9 OP MRB ALL 24-001-09-01

27-011-02Detailed Inspection of the Aileron Control

Cables (Unexposed Area)4C 6 DET MRB ALL

27-011-02-0127-011-02-0227-011-02-03

27-011-03Functional Check of the Torque Tube and

Override Mechanism4C 6 FC MRB ALL 27-011-03-01



Rev 3 04 March 2014

2-27


27-012-02Detailed Inspection of the Aileron Trim

Cables (Unexposed area)4C 6 DET MRB ALL

27-012-02-0127-012-02-0227-012-02-03

27-021-01Detailed Inspection of the Rudder Control Cables and Trim Cables (Unexposed Area)

4C 6 DET MRB ALL

27-021-01-0127-021-01-0227-021-01-0327-021-01-0427-021-01-05

27-023-02Detailed Inspection of the Rudder Shut-off

Actuation Cable and Control Cables (Unexposed Area)

4C 9 DET MRB ALL

27-023-02-0127-023-02-0227-023-02-0327-023-02-0427-023-02-05

27-031-01Detailed Inspection of the Elevator Cable

System (Unexposed Area)4C 6 DET MRB ALL

27-031-01-0127-031-01-0227-031-01-0327-031-01-0427-031-01-0527-031-01-06

27-033-01Functional Check of the Elevator Hydraulic System to maintain pressure without Main

Hydraulic System pressure4C 9 FC MRB ALL 27-033-01-01

27-041-02Detail Inspection of the Horizontal Stabilizer

Control and Indication Cables4C 6 DET MRB ALL

27-041-02-0127-041-02-0227-041-02-0327-041-02-0427-041-02-0527-041-02-06

27-042-02Detailed inspection of the Horizontal

Stabilizer Trim Relay Linkage4C 6 DET MRB ALL 27-042-02-01

27-042-03Detailed Inspection of the Horizontal Stabilizer Position Limiting Linkage

4C 6 DET MRB ALL 27-042-03-01

27-051-02Detailed Inspection of the Flap Cable System

in the unexposed area4C 6 DET MRB ALL

27-051-02-0127-051-02-0227-051-02-03

27-063-02Detailed Inspection of the Spoiler/

Speedbrake cables (Unexposed area)4C 9 DET MRB ALL

27-063-02-0127-063-02-0227-063-02-03

27-081-01Detailed Inspection of the Slat Control Cable

Loop4C 6 DET MRB ALL

27-081-01-0127-081-01-01

28-022-03Operational Check of the "CTR FUEL PRES

LOW " Alert inhibit System4C 8 OP MRB ALL 28-022-03-01

28-024-01 Functional Check of the Fuel Shroud System 4C 9 FC MRB ALL 28-024-01-01

28-024-03Operational Check of the Drain Mast

assembly (Venting)4C 9 OP MRB ALL 28-024-03-01

28-028-01 Operational Check of the Fuel Dump System 4C 9 OP MRB ALL28-028-01-0128-028-01-02

28-028-02Detailed Inspection of the Lever Mechanism

and Control Cables4C 9 DET MRB ALL

28-028-02-0128-028-02-02

32-001-00 Service the tail bumper strut with nitrogen. 4C SV MRB ALL 32-001-00-01



Rev 3 04 March 2014

2-28


32-024-02Detailed Inspection of the Ground Sense

Cable System (Unexposed Area)4C 6 DET MRB ALL

32-024-02-0132-025-02-02


Control Cables (Unexposed Area)4C 6 DET MRB ALL

32-031-02-0132-031-02-0232-031-02-03


Alternate Ccntrol Cables (Unexposed Area)4C 8 DET MRB ALL

32-031-05-0132-031-05-0232-031-05-03

32-044-04Detailed Inspection of the Brake Pedal

Control Cables (Unexposed Area)4C 5 DET MRB ALL

32-044-04-0132-044-04-0232-044-04-03

34-029-02Detailed Inspection of the Standby Compass

clamps and brackets4C 8 DET MRB ALL 34-029-02-01

34-029-03Functional Check of the Standby Compass

for Calibration4C 8 FC MRB ALL

34-029-03-0134-029-03-02

34-032-02Detailed Inspection of the VOR/LOC

Antenna for proper bonding4C 6 DET MRB ALL 34-032-02-01

35-010-03Functional Check of the Demand and Supply

Pressure Regulators4C 6 FC MRB ALL 35-010-03-01

35-020-05Functional Check of the Demand and Supply

Pressure Regulators4C 6 FC MRB ALL 35-020-05-01

36-015-02Detailed Inspection of the Lever Mechanism

for Crossfeed Valve and Cables4C 6 DET MRB ALL 36-015-02-01

52-045-01Functional Check of the Pressure Relief Door

Latches4C 9 FC MRB ALL 52-045-01-01

52-045-02Detailed Inspection of the APU Door Hinges

and Camlock Fastener4C 8 DET MRB ALL 52-045-02-01

76-011-01Detailed Inspection of the left and right throttle cable system (Unexposed Area)

4C 6 DET MRB ALL

76-011-01-0176-011-01-0276-011-01-0376-011-01-04

76-013-01Detailed Inspection of the left and right fuel shutoff lever cable system (Unexposed Area)

4C 6 DET MRB ALL

76-013-01-0176-013-01-0276-013-01-0376-013-01-04

76-021-02Detailed Inspection of the Emergency

Shutdown System Cables (Unexposed Area)4C 8 DET MRB ALL

76-021-02-0176-021-02-0276-021-02-0376-021-02-0476-021-02-0576-021-02-0676-021-02-07

78-030-02Functional Check of the Thrust Reverser

System to hold pressure without Main Hydraulic Pressure

4C 6 FC MRB ALL78-030-02-0178-030-02-02

52-011-02

Detailed Inspection of the Door and Interlock Mechanism, Seal Depressor, Girt Bar

Latches, Pressure Seal, Door Stops and Set Screws (Lining removed)

5C 9 DET MRB ALL 52-011-02-01

52-012-02

Detailed Inspection of the Door Mechanism and structure, Door Seal Depressor, Door Stops, and Emergency Handle Mechanism

(Lining removed)

5C 9 DET MRB ALL 52-012-02-01



Rev 3 04 March 2014

2-29


52-021-02

Do a detailed inspection of the Overwing Emergency Exit Door Mechanism, Pressure Seal Depressor, Door Stops, and Lock Pin

Socket Assembly (Lining removed)

5C 6 DET MRB ALL 52-021-02-01

52-030-02

Detailed Inspection of the Cargo Door Mechanism, Cargo Barrier, Hold Open

Mechanism, Stops and Set Screws (Lining removed)

5C 6 \ 9 DET MRB ALL52-030-02-0152-030-02-02

52-041-01Detailed Inspection of the Door Mechanism, Seal Depressor, Avionics Compartment Door

Stops and Set Screws (Lining removed)5C 6 DET MRB ALL 52-041-01-01

52-042-02Detailed Inspection of the Door Mechanism, Seal Depressor, Girt Bar Latches, Door Stops

and Set Screws (Lining removed)5C 6 \ 8 DET MRB ALL 52-042-02-01

30-010-06Functional Check of the Wing Low Pressure

Switch and System Alerts6C 9 FC MRB ALL 30-010-06-01

30-010-08Functional Check of the Supply Pressure

High Switch and System Alerts6C 9 FC MRB ALL 30-010-08-01

20-010-05Detailed Inspection of Fuel Quantity Wiring –

Center Wing Tank (Analog only, no Task required if system is digital) (EZAP)

8C DET MRB ALL 20-010-05-01

20-010-10GVI All Exposed EWIS in the Center Wing

Section (EZAP)8C GVI MID ALL 20-010-10-01

20-020-02Clean area of dust, lint and all foreign objects

– EPC (Aft Side)8C RS MRB ALL 20-020-03-01

20-050-01

Detailed Inspection of Left Wing Fuel Quantity Wiring (Analog only, no task

required if system is digital) and all exposed EWIS (EZAP)

8C DET MRB ALL 20-050-01-01

20-050-03GVI All Exposed EWIS in the Left Wing

Interspar Box Section (EZAP)8C GVI MID ALL 20-050-30-01

20-060-01

Detailed Inspection of Right Wing Fuel Quantity Wiring (Analog only, no task

required if system is digital) and all exposed EWIS (EZAP)

8C DET MRB ALL 20-060-01-01

20-060-03GVI All Exposed EWIS in the Right Wing

Interspar Box Section (EZAP)8C GVI MID ALL 20-060-03-01

28-011-01Detailed Inspection of the Flapper Check

Valves8C 8 DET MRB ALL

28-011-01-0128-011-01-02

28-011-02General Visual Inspection of the Aux Fuel

Cell Cavity8C 8 GVI MRB ALL

28-011-02-0128-011-02-02

28-011-03Detailed Inspection of the Aux Fuel Cell

Cavity Link and Hanger Assy8C 8 DET MRB ALL

28-011-03-0128-011-03-02

28-012-01Detailed Inspection of the Vent Relief and

Climb Vent Float Valves8C 8 \ 9 DET MRB ALL

28-012-01-0128-012-01-02

28-012-02Detailed Inspection of the Aux Tank Climb

Vent Float Valves8C 9 DET MRB ALL

28-012-02-0128-012-02-02

28-012-03Detailed Inspection of the Vent Drain Swing

Check Valves8C 9 DET MRB ALL

28-012-03-0128-012-03-0228-012-03-03

28-012-04Detailed Inspection of the Aux Tank Vent

Drain Swing Check Valve8C 9 DET MRB ALL

28-012-04-0128-012-04-02



Rev 3 04 March 2014

2-30


28-012-05 Detailed Inspection of the Flame Arrestor 8C 8 \ 9 DET MRB ALL28-012-05-0128-012-05-02

28-013-01Detailed Inspection of the Wing Tank Check

Valves8C 9 DET MRB ALL

28-013-01-0128-013-01-02

28-013-02 Clean the Tank Scavenge Filters 8C 9 RS MRB ALL28-013-02-0128-013-02-0228-013-02-03

28-013-03 Clean the Fuel Scavenge Rakes 8C 9 RS MRB ALL28-013-03-0128-013-03-0228-013-03-03

28-013-04Detailed Inspection of the Center Tank Check

Valve8C 9 DET MRB ALL 28-013-04-01

28-022-01Detailed Inspection of the Engine/APU Fuel

manifold (Fuel Tank Internal)8C 9 DET MRB ALL

28-022-01-0128-022-01-02

32-002-00Service the tail bumper strut with hydraulic

and nitrogen.8C SV MRB ALL 32-002-00-01

56-021-01Detailed Inspection of the Cabin and Door

Acoustic Window Panes8C 8 DET MRB ALL 56-021-01-01

25-060-20 Discard the Flashlight Batteries 1 YR 9 DS MRB ALL 25-060-20-01

32-011-03

Restore the Left and Right Main Landing Gear Shock Struts, Upper Side Brace, Lower Side Brace, Fixed Side Braces, Upper Lock Links, Lower Lock Links, and Upper and

Lower Torque Links

10 YR 5 RS MRB ALL32-011-03-0132-011-03-02

32-021-03

Restore the Nose Landing Gear Shock Strut, Cylinder, Housing, Steering Lever, Piston,

Axle, Upper Drag Brace, Lower Drag Brace, Upper Lock Link, Lower Lock Link, and

Upper and Lower Torque Links

10 YR 5 RS MRB ALL 32-021-03-01

32-045-02 Restore the Dual Anti-Skid Control Valves 10 YR 8 RS MRB ALL32-045-02-0132-045-02-02

25-060-14Restoration the Personal Breathing

Equipment10 YR / MR 6 RS MRB ALL

25-060-14-0125-060-14-02

80-001-02Do a detailed inspection of the Starter S/O

Valve Inline Filter (if installed)2000 FH 6 DET MRB ALL

80-001-02-0180-001-02-02

80-001-03Discard the Starter S/O Valve Inline Filter (if

installed)4000 FH DS MRB ALL

80-001-03-0180-001-03-02

27-041-03 Restoration of the Primary Brake Relay 8000 FH 9 RST MRB ALL 27-041-03-01

27-1Replace the Primary Longitudinal Up / Down

Contactors8000 FH RS SCI ALL 27-001-00-01

49-010-01Detailed Inspection of the APU Engine and

Airframe Mount Assy and Attaching hardware

APU CHG 9 DET MRB ALL 49-010-01-01

49-080-01General Visual Inspection of the inside of the

Exhaust DuctAPU CHG 7 GVI MRB ALL 49-080-01-01

24-001-02Operational Check of the CSD Disconnect

SystemNOTE: At Engine Change

ENG CHG 9 OP MRB ALL 24-001-02-01



Rev 3 04 March 2014

2-31


24-001-03Operational Check of the ENG Generator

Field DisconnectNOTE: At Engine Change

ENG CHG 8 OP MRB ALL 24-001-03-01

71-010-06Detailed Inspection of the Undercowl Pylon

Apron surfaceNOTE: Done during engine change.

ENG CHG 9 DET MRB ALL71-010-06-0171-010-06-02

71-020-01Special Detailed Inspection of the Cone Bolts

NOTE: Done during engine change.ENG CHG 9 SDI MRB ALL

71-020-01-0171-020-01-02

76-021-01Operational Check of the Engine Emergency

Shutdown SystemENG CHG 8 OP MRB ALL 76-021-01-01

25-060-06Restoration of the Life Vests

NOTE: At Manufacturer's RecommendationNOTE 9 RS MRB ALL 25-060-06-05

26-021-03 Discard Discharge Cartridge NOTE 9 DS MRB ALL 26-021-03-01

26-021-07Discard the Engine/APU Firex Bottle

INTERVAL NOTE: Discard per Manufacturer's Life Limits

NOTE 8 DIS MRB ALL 26-021-07-01

26-023-07Discard the Portable Fire Extinguisher Bottle

INTERVAL NOTE: Discard per Manufacturer's Life Limits

NOTE 8 DIS MRB ALL26-023-07-0126-023-07-02

32-010-02

Discard the Main Landing Gear Assembly Components

INTERVAL NOTE: Per DC-9 Report No. MDC-J0005

NOTE 5 DIS MRB ALL32-010-02-0132-010-02-02

32-020-02

Discard Nose Landing Gear Assembly Life Limited Components

INTERVAL NOTE: Per DC-9 Report #MDC-J0005

NOTE 5 DIS MRB ALL 32-020-02-01

72-030-03Discard the Rotor

NOTE: Per Manufacturer's Life LimitsNOTE 6 DS MRB ALL

72-030-03-0172-030-03-02

72-050-02Discard the Hubs, Disks, Blade Retainers,

and Rotating AirsealsNOTE 5 DS MRB ALL

72-050-02-0172-050-02-02



Rev 3 04 March 2014

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Rev 3 04 March 2014

3-1


CHAPTER: 3 STRUCTURAL MAINTENANCE PROGRAM

3.1 Purpose

This section provides the basic scheduled tasks and intervals applicable to the aircraft structure. These tasks have been developed considering the following types of damage sources;

• Accidental Damage (AD)

• Environmental Deterioration (Corrosion) (ED)

• Fatigue Damage (FD)

The Environmental Deterioration (ED) tasks in this section were developed taking into account the con-cerns of a Corrosion Prevention and Control Program (CPCP), with the objective of controlling corrosion on the aircraft to Corrosion Level 1 or better.

3.2 Supplemental Inspection Document (SID)

The DC-9 Supplemental Inspection Document provides information and data for the implementation of a supplemental structural inspection program for the DC-9 airplane as specified in FAA Advisory Circular 91-56, dated 6 May 1981. Development of the DC-9 SID has been carried out under the guidance of an Industry Steering Committee (ISC) and a DC-9 SID Working Group made up of airline, manufacturer and FAA personnel. The program provides continuing structural integrity for aging transport airplanes by eval-uating current structural maintenance programs and by supplementing them, as necessary. The evaluation is based on service experience, a reassessment of the fatigue durability and damage tolerance characteris-tics of the structure, and the availability of state-of-the-art inspection methods.

The SID document contains information that defines the mandatory inspection requirements for the Princi-pal Structural Elements (PSE's) and also provides specific Non-Destructive Inspection (NDI) techniques and procedures for each PSE. NDI is a technology used to detect defects in materials while utilizing tech-niques that do not damage or destroy the items being tested.

Principal Structural Elements are those parts of structure which contribute significantly to carrying flight, ground, and pressurization loads, and whose failure, if left undetected, could lead to the loss of the air-plane.

Continued airworthiness requires the continued update of inspection procedures as experience, data, and technology is increased. The SID document is, therefore, prepared in an incremental fashion. The proce-dures must be sufficiently defined to provide instructions necessary to cover high time/cycle, fleet leader airplanes and are considered complete at the time of publication until subsequent additions are issued

Commercial Airplane Group, Long Beach using the form given on 4.8, Vol 1 of the SID. The inspection findings shall be reported at least once a year (by April 30 for all inspections of the previous year) by each operator who has performed SID directed inspections on one or more PSEs. More than one PSE may be reported on one page of the form. For symmetric PSEs, both sides of the PSE must be inspected to receive credit for the inspection.

MAIL TO:BOEING COMMERCIAL AIRPLANE GROUP, LONG BEACHTECHNICAL AND FLEET SUPPORT SERVICE ENGINEERING --- AGING AIRPLANEDC-9 SID PROGRAM, MAIL STOP: D800-0037 3855 LAKEWOOD BLVD.LONG BEACH, CA 90846

Rev 2 17 April 2012

3-2


3.3 Corrosion Prevention and Control Program (AD 92-22-08R2)

During the MSG-3 analyses Boeing included the environmental damage and as such the FAA Los Angeles Aircraft Certification Office (LAACO) has found that the Environmental Deterioration (ED) tasks in the DC-9 MSG-3 Maintenance Review Board (MRB) Report and have confirmed that the tasks are the same as those in the DC·9 CPCP document (MDC·K4606) as mandated in AD 92-22-08R2

Therefore, the ED tasks in the DC-9 MSG-3 MRB Report are FAA approved as an equivalent program for corrosion prevention and control as specified in paragraph (b) in AD 92-22-08R2.

Structural maintenance requirements are determined on the basis of continual maintenance to preserve or restore the inherent corrosion preventive measures and structural surface finishes. Should corrosion be detected or should the corrosion inhibiting compound exhibit signs of deterioration during the performance of a structural task, the Corrosion Control Handbook (CCH) -- MDC K0805 should be referred to for appropriate corrective action. The CCH provides general information on inspection, detection, and removal of corrosion as well as preventive maintenance practices for corrosion control. Tasks in which periodic application of corrosion inhibiting compounds are recommended or required are contained in this section of this document.

As stated above the Corrosion Prevention and Control Program (CPCP) is an integral part of the Structural Maintenance Program. The objective of the CPCP is to control corrosion found on all structure listed in the Structural Maintenance Program to Level 1 or better.

3.4 Program Rules

Inspection intervals for Accidental Damage (AD) and Environmental Deterioration (ED) are specified in calendar time (months).

Inspection intervals for Fatigue Damage (FD) are specified in landings (cycles).

When inspections indicate evidence of deterioration, appropriate actions must be taken. (e.g., additional samples, decreased intervals, etc…)

All inspections are Zone specific.

Unless otherwise noted, it is understood that the removal or displacement of component/installations/lin-ing/insulation is not required to perform the inspection.

3.5 General

The Structural Inspection requirements for the Douglas Model DC-9 aircraft are presented in ATA sequence/order as shown below:

• ATA 52 - Doors

• ATA 53 - Fuselage

• ATA 54 - Pylons

• ATA 55 - Stabilizers

• ATA 57 - Wings

3.6 Introduction

This section of the maintenance manual identifies scheduled maintenance requirements for the Structures Inspection Program. This program was developed using MSG-3 logic along with service experience, and is designed to provide timely detection of reduced failure resistance caused by accidental and environmental damage which may occur in the fleet during normal operations. This is damage due to corrosion, stress cor-rosion, and minor accidental damage events considered as undetected. Inspection is by visual and/or Non-Destructive Inspection (NDI) procedures. Major accidental damage is not covered in this program.

This structural inspection programs tasks listed herein constitute the minimum scheduled requirements for all Everts Air Cargo DC-9 aircraft. It should be noted that conditions in modification of a subject aircraft may void the effectiveness of this program, which may require an adjustment to task intervals.

Rev 2 17 April 2012

3-3


3.7 Notes

Tasks for detecting damage using visual and/or Non-Destructive Inspection (NDI) procedures are specified in this program.

After discrepancies are found, repair, modification action, inspection program adjustment or reporting to the local regulatory authority may be required to assure continuing airworthiness of the airplane as pre-scribed herein.

3.8 Structural Maintenance Program Tasks

The following pages contain a listing of the Structural Maintenance Program Tasks that are applicable to this manual.



52-101-02 Door, Main Entrance, Internal Structure 48 MO DET MRB ALL 52-101-02-01

52-102-02 Door, Aft Cabin Bulkhead, Internal Structure 60 MO DET MRB ALL 52-102-02-01

52-103-02Emergency Exit, Overwing, Internal

Structure48 MO DET MRB ALL 52-103-02-01

52-104-02Door, Forward Lower Cargo, Internal


52-105-02Internal Structure - (Deactivated Door)

NOTE: Or 15000 Flight Cycles96 MO DET MRB ALL 52-105-02-01

52-105-04 Internal Structure - (Active Door) 36 MO DET MRB ALL 52-105-04-01

52-106-02 Door, Aft Lower Cargo, Internal Structure 72 MO DET MRB ALL 52-106-02-01

52-107-02Door, Electrical / Electronics Compartment,

Internal Structure96 MO DET MRB ALL 52-107-02-01

52-108-02Door, Forward Galley Service, Internal


52-110-02Door, Forward Accessory Compartment,


52-111-02 Door, Main Landing Gear, Internal Structure 48 MO DET MRB ALL52-111-02-0152-111-02-02

52-112-02 Doors, Main Gear Strut, Structure 48 MO DET MRB ALL52-112-02-0152-112-02-02

53-113-02Jamb, Forward Accessory Compartment

Door, Internal Structure72 MO GVI MRB ALL 53-113-02-01

53-114-02Jamb, Electric / Electronic Compartment

Door, Internal Structure36 MO DET MRB ALL 53-114-02-01

53-115-02 Jamb, Main Entrance Door, Internal Structure 48 MO DET MRB ALL 53-115-02-01

53-115-04

Jamb, Electric / Electronic Compartment Door, X-Ray Upper Forward Corner of Main

Entrance Door JambNOTE: Not applicable to FUS 935 & Sub or

after accomplishment of S/B DC9-52-112

1500 Flight Cycles

SDI MRB ALL 53-115-04-01

Rev 3 04 March 2014

3-4


53-116-02Jamb, Forward Galley Service Door, Internal


53-116-04Jamb, Forward Galley Service Door, X-Ray

Upper Forward Corner1500 Flight

CyclesSDI MRB ALL 53-116-04-01

53-117-02Jamb, Fwd Lwr Cargo Compt Door, Internal

Structure, Scuff Plate removed36 MO DET MRB ALL 53-117-02-01

53-118-02Jamb, Upper Cargo Compt Door, Internal

Structure, Scuff Plate removed36 MO DET MRB ALL 53-118-02-01

53-119-02Jamb, Aft Lwr Cargo Compt Door, STA 718 -

756 (-10/20), 897 - 935 (-30) 973 - 1011 (-40), 1068 - 1106 (-50), Internal Structure

36 MO DET MRB ALL 53-119-02-01

53-121-03 Jamb, Aft Cabin Bulkhead Door, Surfaces 60 MO DET MRB ALL 53-121-03-01

53-122-02 Panel, Prapezoidal, Structure 48 MO DET MRB ALL53-122-02-0153-122-02-02

53-123-02Longeron #20, Aft end of Trap Panel,

Structure48 MO DET MRB ALL

53-123-02-0153-123-02-02

53-124-02Longeron #22, Wing to Fuselage Fitting

Including Area Under Fillet Fairing, Internal Structure

48 MO DET MRB ALL53-124-02-0153-124-02-02

53-125-02Fuselage Frames, Overwing, Internal

StructureNOTE: Or 15000 Flight Cycles

96 MO DET MRB ALL 53-125-02-01

53-126-02Fuselage Frame, Over Trapezoidal Panel,


53-126-02-0153-126-02-02

53-127-02

Frames, Aft Cabin Fuselage Ceiling Above Lavs & Galleys, (Lavs & Galleys Removed)

STA 756 - 817 (-10-20), 935 - 996 (-30), 1011 - 1072 (-40), 1100 - 1167 (-50), Internal

Structure

60 MO DET MRB ALL 53-127-02-01

53-128-02 Keel, Underwing Barrel, Internal Structure 48 MO DET MRB ALL 53-128-02-01

53-129-02 Keel, MLG Wheel Well, Structure 48 MO DET MRB ALL53-129-02-0153-129-02-02

53-130-02Pressure Bulkhead, MLG Wheel Well, Aft

Face36 MO DET MRB ALL 53-130-02-01

53-131-02 Pressure Bulkhead Aft Cabin, Structure 60 MO DET MRB ALL53-131-02-0153-131-02-02

53-132-02Bulkhead, Engine Pylon Fwd Support,


53-133-02Bulkhead, Engine Pylon Fwd Support,


53-134-02

Attach Angle, Top Fus to Vert Stab Joint, STA 947.6 - 1012.8 (-10/-20) 1126.6 - 1191.8 (-30), 1202.6 - 1267.8 (-40), 1297.6 - 1362.8

(-50), External Structure

72 MO DET MRB ALL 53-134-02-01

53-135-02Attach Angle, Top Fus to Vert Stab Joint,

External Structure72 MO DET MRB ALL 53-135-02-01



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3-5


53-136-01Canted Frame, STA 895 & 926 (-10/-20),

1074 & 1105 (-30), 1150 & 1181 (-40), 1245 & 1276 (-50), External Structure

1500 Flight Cycles

GVI MRB ALL 53-136-01-01

53-136-02Canted Frame, STA 895 & 926 (-10/-20),

1074 & 1105 (-30), 1150 & 1181 (-40), 1245 & 1276 (-50), Internal Structure

72 MO DET MRB ALL 53-136-02-01

53-137-01Floor Beams & Seat Tracks - (Lavs, Galleys & Floor Panels Removed), Internal Structure

48 MO DET MRB ALL

53-137-01-0153-137-01-0253-137-01-0353-137-01-04

53-138-02Skin Panels, STA 69 - 218, Internal Structure (Longeron 18L - 18R, Above Cabin Floor)

96 MO DET MRB ALL53-138-02-0253-138-02-03

53-138-03Skin Panels, STA 69 - 218, Internal Structure

(Longeron 18L - 27L, 18R - 27R, Below Cabin Floor)

72 MO DET MRB ALL 53-138-03-01

53-138-04Skin Panels, STA 110 - 218, Internal

Structure (Longeron 27L - 27R, Bildge Area)36 MO DET MRB ALL 53-138-04-01

53-138-05Skin Panels, STA 37 - 69, Internal Structure

(Above Pressure Panel, STA 37 to 69)72 MO DET MRB ALL 53-138-05-01

53-138-06Skin Panels, STA 37 - 218, Itnernal Structure

(Nose Wheel Well)48 MO DET MRB ALL 53-138-06-01

53-139-02Skin Panels, STA 218 -908 (-10/-20), -1087

(-30), -1163 (-40), -1258 (-50), Internal Structure excluding areas in tasks below

96 MO DET MRB ALL 53-139-02-01

53-139-03

Internal Structure (Area Under Fillet Fairing, Over Wing Emergency Exit Area, Above

Cabin Floor Splices, Upper & Lower Antenna Cutouts as viewed from the outside & Lower Antenna from the Bilge Area also

(Antenna's removed)

48 MO DET MRB ALL53-139-03-0153-139-03-0253-139-03-03

53-139-04

Skin Panels, STA 218 -817 (-10/-20), -1087 (-30), -1163 (-40), -1258 (-50), Internal

Structure (below Cabin Floor, 18L - 24L, 18R - 24R)

72 MO DET MRB ALL53-139-04-0153-139-04-02

53-139-05Skin Panels, STA 218 -908 (-10/-20), -1087

(-30), -1163 (-40), -1258 (-50), Internal Structure (below Cabin Floor, 24L - 24R)

36 MO DET MRB ALL53-139-05-0153-139-05-02

53-140-02

Skin Panels, STA 817 - 1112 (-10/-20), 996 - 1291 (-30), 1072 - 1367 (-40), 1167 - 1462 (-50), Internal Structure (Upper Fuselage, 18L -

18R)

72 MO DET MRB ALL 53-140-02-01

53-140-03

Skin Panels, STA 817 - 1112 (-10/-20), 996 - 1291 (-30), 1072 - 1367 (-40), 1167 - 1462 (-50), Internal Structure (Lower Fuselage, 18L

- 18R)

48 MO DET MRB ALL 53-140-03-01

53-401-02Fus Frame Joint, to Fwd Aux Fuel Tank Spt

Ftgs, External Tank StructureNOTE: Or 15000 Flight Cycles

120 MO DET MRB ALL 53-401-02-01



Rev 3 04 March 2014

3-6


53-402-02

Fus Frame Joint, to Aft Aux Fuel Tank Spt Ftgs, STA 642 (-10/20), 760 (-30), 798 (-40),

855 (-50), Tank StructureNOTE: Or 15000 Flight Cycles. Task to be complied with at whichever interval occurs

first

120 MO DET MRB ALL 53-402-02-01

53-439-02NLG Retract Cylinder Attach Fitting, STA

110, Structure48 MO DET MRB ALL 53-439-02-01

53-440-02 Fitting, Keel to Rear Wing Spar, Structure 48 MO DET MRB ALL53-440-02-0153-440-02-02

53-441-02Fitting, Retract Cylinder MLG Door,


53-441-02-0153-441-02-02

53-442-02Dorsal Fitting, Vertical Stabilizer, STA - 901.4 (-10/-20), -1080.4 (-30), -1156.4 (-40), -1251 (-50), Internal Structure

72 MO DET MRB ALL 53-442-02-01

53-703-02

Fwd Aux Fuel Tank Aft Bulkhead, Inspect Bulkhead around access hole cutout

NOTE: Or 15000 Flight Cycles. Task to be complied with at whichever interval occurs

first

96 MO DET MRB ALL 53-703-02-01

54-144-02 Front Spar, One Piece, Internal Structure 72 MO DET MRB ALL54-144-02-0154-144-02-02

54-145-02Front Spar, Spar Tangs, STA 786 (-10/-20), 965 (-30), 1041 (-40), 1136 (-50), Internal


54-146-02Rear Spar, Upper and Lower Two Piece Caps

(Pylon), Internal Structure72 MO DET MRB ALL

54-146-02-0154-146-02-02

54-147-02Rear Spar, Upper and Lower Two Piece Caps,


54-448-02 Yoke - Forward Engine Mount, Structure 72 MO DET MRB ALL54-448-02-0154-448-02-02

54-449-02Bolts, Yoke to Front Pylon Spar (Accomplish

with MSI 71-20-00-04)72 MO DET MRB ALL

54-449-02-0154-449-02-02

55-150-02Rear Spar Caps, STA XHR 0 - STA XHR 209.0 (-10, XH 0.0 - XHR 209), Structure

72 MO DET MRB ALL55-150-02-0155-150-02-02

55-152-02Rear Spar - Center Box Caps, STA XH 6.6 Left - STA XH 6.6 Right, Internal Structure

36 MO DET MRB ALL 55-152-02-01

55-153-02Joints, Center Box, STA XH 7.0 - STA XH

7.0 (Left & Right), Internal Structure includes Jackscrew Lug Attach Area

36 MO DET MRB ALL 55-153-02-01

55-154-02Joints, Operating Bulkhead, STA LH 9 - RH

9, Internal Structure36 MO DET MRB ALL 55-154-02-01

55-155-02Plates, Upper, STA XH 7.2 - STA XH 209,


55-257-02Spar Caps, STA XE 3.4 - STA XE 236.0,

Internal Structure48 MO DET MRB ALL

55-257-02-0155-257-02-02

55-258-02Skin Panels, Upper and Lower, STA XE 3.4 -

STA XE 236.0, External Structure72 MO DET MRB ALL 55-258-02-01



Rev 3 04 March 2014

3-7


55-360-02Front Spar (Attachment Tangs), STA 947.6 (-10/-20), 1126.6 (-30), 1202.6 (-40), 1297.6 (-

50), Structure72 MO DET MRB ALL 55-360-02-01

55-361-02Rear Spar (Attachment Tangs), STA 1012.8 (-10/-20), 1191.8 (-30), 1267.8 (-40), 1362.8

(-50), Structure72 MO DET MRB ALL 55-361-02-01

55-362-01Front Spar, STA ZFS 4.7 - STA ZFS 154.8,

Aft Face Structure3000 Flight

CyclesGVI MRB ALL 55-362-01-01

55-362-02Front Spart, STA ZFS 4.7 - STA ZFS 154.8,

Aft Face Structure72 MO DET MRB ALL 55-362-02-01

55-363-01Rear Spar, STA ZFS -5.0 - STA ZFS 170.0,

Forward Face Structure72 MO DET MRB ALL 55-363-02-01

55-363-02Rear Spar, STA ZFS -4.7 - STA ZFS 154.8,

Structure1500 Flight


55-363-03Skin Panels, Vertical Stabilizer, Leading

Edge & Tip Cap, External Structure1500 Flight


55-363-04Skin Panels, Vertical Stabilizer, Leading

Edge & Tip Cap, Internal Structure72 MO DET MRB ALL 55-363-04-01

55-464-01Spar Caps, STA ZR 10.0 - STA ZR 140,


55-464-03Spar Caps, STA ZR 10.0 - STA ZR 140, Tap

Test for Delamination on Composite (External)

1500 Flight Cycles

DET MRB ALL 55-464-03-01

55-464-04

INTERNAL - SPECIAL DETAILED:Rudder - Spar Caps, STA ZR 10.0 - ZR 140. Do a special detailed inspection (X-Ray) of the metal structure of the Rudder Spar Caps

(Internal), STA ZR 10.0 - ZR 140.

3000 Flight Cycles

SDI MRB ALL 55-464-04-01

55-465-02Skin Panels, STA ZR 8.0 - STA ZR 142.0,


55-566-02Pivot Support Fittings, Horizontal Stabilizer,

STA XH 7.2 (Left & Right) & STA ZRS 173.0, Structure

36 MO DET MRB ALL 55-566-02-01

55-567-02 Hinges - Elevator Assembly, Structure 48 MO DET MRB ALL55-567-02-0155-567-02-02

57-168-02 Rear Spar Web, STA XCW 58.5 48 MO DET MRB ALL57-168-02-0157-168-02-02

57-169-02Lower Tee Cap at Bulkhead, STA XCW

58.5, Structure60 MO DET MRB ALL

57-169-02-0157-169-02-02

57-170-01Bulkhead XCW 121.5 at Front Spar Jack

Point, Internal Structure3000 Flight

CyclesGVI MRB ALL

57-170-01-0157-170-01-02

57-170-02Bulkhead XCW 121.5 at Front Spar Jack

Point, External Structure72 MO DET MRB ALL

57-170-02-0157-170-02-02

57-171-02Slat Track Cutouts, STA XIS 83.5 - STA

XOS 580.5, Internal Structure72 MO DET MRB ALL

57-171-02-0157-171-02-02

57-172-02Rear Spar (Outboard), STA XCW 58.5 - STA

XW 536.8, Aft Face48 MO DET MRB ALL

57-172-02-0157-172-02-02

57-172-03Rear Spar (Outboard), STA XCW 58.5 - STA

XW 536.8, Forward Face120 MO DET MRB ALL

57-172-03-0157-172-03-02



Rev 3 04 March 2014

3-8


57-173-02

Attach Angle (Top Wing to Center Fuselage), STA 491 - 642 (-10/-20) 606 - 760 (-30), 644 - 798 (-40), 701 - 855 (-50), Structure, Fillet

removed

48 MO DET MRB ALL57-173-02-0157-173-02-02

57-174-02Rear Spar Web, STA XCW 58.6 Left to

XCW 58.6 Right, Forward Face96 MO DET MRB ALL 57-174-02-01

57-174-03Rear Spar Web, STA XCW 58.6 Left to XCW 58.6 Right, Aft Face, Aft Face,

External Structure60 MO DET MRB ALL

57-174-03-0157-174-03-02

57-176-02Wing Upper Rear Spar Cap (Dog Leg), STA XCW 0.0 - STA XRS 58.6 Left and Right,

Forward Face96 MO DET MRB ALL 57-176-02-01

57-176-03Wing Upper Rear Spar Cap (Dog Leg), STA XCW 0.0 - STA XRS 58.6 Left and Right,

External Structure60 MO DET MRB ALL

57-176-03-0157-176-03-02

57-177-02Fitting, Rear Spar, STA XCW 58.6 at Trap Panel / Rear Spar Intersection, Structure

48 MO DET MRB ALL 57-177-02

57-178-02Splice, Front Spar Cap, STA XCW 58.5,


57-178-02-0157-178-02-02

57-179-02Front Spar Web, STA XCW 58.6 Left - XCW

58.6 Right, Forward Face36 MO DET MRB ALL 57-179-02-01

57-179-03Front Spar Web, STA XCW 58.6 Left - XCW

58.6 Right, Aft Face96 MO DET MRB ALL 57-179-03-01

57-180-03Panel, Upper Skin, Internal Structures STA.

XCW 58.6 to Tip of Tank120 MO DET MRB ALL

57-180-03-0157-180-03-02

57-181-02Panel, Upper Skin, STA XRS 69.0 -536.8

(-10), 560.0 (-30, -40, -50), External Surfaces72 MO DET MRB ALL

57-181-02-0157-181-02-02

57-182-03Cutouts, Upper Wing Door, Internal

Structures STA. XW 58.6 to Tip of Tank.120 MO DET MRB ALL

57-182-03-0157-182-03-02

57-183-02 Panel, Lower Skin, External Structure 48 MO DET MRB ALL57-183-02-0157-183-02-02

57-184-02 Panels, Upper Skin, Internal Structure 96 MO DET MRB ALL 57-184-02-01

57-185-02 Cutouts, Door, Structure 96 MO DET MRB ALL 57-185-02-01

57-186-02 Panel, Lower Skin, Structure 96 MO DET MRB ALL 57-186-02-01

57-187-02 Support Fitting, Main Landing Gear Structure 48 MO DET MRB ALL57-187-02-0157-187-02-02

57-188-02 Hinges, Aft Flap, Structure 48 MO GVI MRB ALL57-188-02-0157-188-02-02

57-189-02 Studs, Wing Flap, Visible Structure 48 MO DET MRB ALL57-189-02-0157-189-02-02

57-190-02 Fitting, Spoiler Drive, Visible Structure 48 MO DET MRB ALL57-190-02-0157-190-02-02

57-191-01 Ailerons, External Structure1500 Flight

CyclesGVI MRB ALL

57-191-01-0157-191-01-02

57-191-02 Ailerons, Tap Test for Delamination 72 MO DET MRB ALL57-191-02-0157-191-02-02



Rev 3 04 March 2014

3-9


57-192-01 Flaps, External Structure 30 MO GVI MRB ALL57-192-01-0157-192-01-02

57-192-03 Flaps, Internal Structure 72 MO DET MRB ALL57-192-03-0157-192-03-02

57-193-01 Fittings, Flap Support 60 MO GVI MRB ALL57-193-01-0157-193-01-02

57-193-03 Fittings, Flap Support 48 MO DET MRB ALL57-193-03-0157-193-03-02

57-194-03 Bracket Attach, Flap Vane, Structure 60 MO DET MRB ALL57-194-03-0157-194-03-02

57-195-01Do a general visual inspection of the external

structure of the Inboard Spoilers.1500 Flight

CyclesGVI MRB ALL

57-195-01-0157-195-01-02

57-195-02Spoilers, Tap Test for Delaminations (Metal

Only)60 MO SDI MRB ALL

57-195-02-0157-195-02-02



Rev 3 04 March 2014

3-10



Rev 3 04 March 2014

4-1


CHAPTER: 4 ZONAL INSPECTION PROGRAM (ZIP)

4.1 Program Rules

Each Zonal Inspection includes a GVI in order to determine the general condition and security of items contained in the Zonal Inspection Program (ZIP). Whenever physically possible, the Zonal Inspections will be conducted within touching distance unless otherwise stated. This includes (but not limited to) checking for evidence of degradation such as corrosion, chafing of tubing, loose duct support, wiring dam-age, cable and pulley wear, fluid leaks, inadequate drainage, and for other conditions which could lead to corrosion/damage.

The extent of a Zonal Inspection is defined by the access required and the instructions provided with the task.

Doors and panels opened or removed during the Zonal Inspection Program, and not having a separate defined zonal task, will receive a GVI. Zones which do not contain system or component installations and which receive adequate inspection from the system/structural programs were not assigned a zonal task.

It is expected that the area to be inspected is clean enough to minimize the possibility that accumulated dirt, lint, fibers or grease might hide unsatisfactory conditions that would otherwise be obvious. Any clean-ing that is considered necessary should be performed in accordance with accepted procedures in order to minimize the possibility of the cleaning process itself introducing anomalies.

4.2 Zonal Reanalysis

The Enhanced Zonal Analysis Procedure (EZAP) permits appropriate attention to be given to electrical wiring installations. Thus, as well as determining zonal inspections, the logic provides a means to identify applicable and effective tasks to minimize contamination and to address significant wiring installation dis-crepancies that may not be reliably detected through the existing zonal inspection program. These dedi-cated tasks were subsequently included in the Systems and Powerplant Section, Chapter 20.

4.3 Zonal Inspection Tasks

The following pages contain a listing of Zonal Tasks applicable to this inspection program.



32-700-01Zonal Inspection: Landing Gear and Landing

Gear Doors1A GVI MRB ALL

32-700-01-0132-700-01-0232-700-01-03

53-100-01Zonal Inspection: External - Lower Fuselage, including Radome and Lower Wing Fillets -

As viewed from Ground1A GVI MRB ALL 52-800-01-01

53-100-05Zonal Inspection: Internal - Forward

Passenger Door Stairwell with stairs extended & includes Airstairs

1A GVI MRB ALL52-800-02-0152-800-02-02

53-100-08Zonal Inspection: Internal - Nose Gear Wheel Well & Unpressurized Sidewalls, STA 37 to

STA 1101A GVI MRB ALL 52-800-03-01

53-100-09Zonal Inspection: Internal - Forward & Center Cargo Compartment with liners

installed1A GVI MRB ALL 53-100-01-01

53-100-14Zonal Inspection: Internal - L/H & R/H Main

Gear Wheel Wells and view Zone 54 from Wheel Wells

1A GVI MRB ALL 53-100-02-01

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53-100-15Zonal Inspection: Internal - Aft Cargo

Compartment, with liners installed1A GVI MRB ALL 53-100-03-01

53-200-01Zonal Inspection: External: Upper Fuselage -

As viewed from ground1A GVI MRB ALL 53-100-04-01

53-200-03Zonal Inspection: Internal: Cockpit Area -

STA 69 - STA 1601A GVI MRB ALL 53-100-05-01

53-200-05Zonal Inspection: Internal: Forward, Mid and

Aft Cabin Area1A GVI MRB ALL 53-100-06-01

53-300-01Zonal Inspection: External Aft Fuselage &

Empennage - As viewed from ground1A GVI MRB ALL 53-100-07-01

53-300-04 Zonal Inspection: Internal APU Compartment 1A GVI MRB ALL 53-100-08-01

57-500-01Zonal Inspection: External - Lower surface

from ground, Slats and Flaps extended1A GVI MRB ALL 53-100-09-01

57-600-01Zonal Inspection: External - Lower surface

from ground, Slats and Flaps extended1A GVI MRB ALL 53-100-10-01

71-400-01Zonal Inspection: External - Powerplants,

Pylons, Cowl Doors, Inlet Areas, and Nose Cowls from ground level

1A GVI MRB ALL 53-100-11-01

71-400-05Zonal Inspection: Internal - Left & Right

Powerplant & Nacelle Doors1A GVI MRB ALL 53-100-12-01

52-800-02Zonal Inspection: External - Lower Cargo

Doors and Surrounding Door Jambs1C GVI MRB ALL 53-100-13-01

53-100-04Zonal Inspection: Internal - Forward

Accessory Compartment, Aft Face of STA 37 to Forward Face of STA 69 Bulkhead

1C GVI MRB ALL 53-100-14-01

53-100-07Zonal Inspection: Internal - E & E Compartment, STA 69 to STA 218

1C GVI MRB ALL 53-100-15-01

53-300-03 Zonal Inspection: Internal Aft Fuselage 1C GVI MRB ALL 53-100-16-01

57-001-00Lubricate the articulated bent-up trailing edge

(BUTE) doors and rollers.1C Lubricate MRB ALL 57-001-00-01

57-002-00Detailed inspection of the articulated bent-up

edge (BUTE) doors and rollers.1C DET MRB ALL 57-002-00-01

57-500-03Zonal Inspection: Internal - Fixed Leading

Edge Compartment1C GVI MRB ALL 53-100-17-01

57-500-07Zonal Inspection: Internal - Fixed Trailing Edge Compartment, including Flap Hinge

Area1C GVI MRB ALL 53-200-01-01

57-600-03Zonal Inspection: Internal - Fixed Leading

Edge Compartment1C GVI MRB ALL 53-200-02-01

57-600-07Zonal Inspection: Internal - Fixed Trailing Edge Compartment, including Flap Hinge

Area1C GVI MRB ALL 53-200-03-01


Powerplant Nose Cowls Inlet Area1C GVI MRB ALL 53-200-04-01


Exhaust Cone & Nozzle Assembly1C GVI MRB ALL

53-200-05-0153-200-05-02



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52-800-01Zonal Inspection: External - Doors

(Passenger/Cargo)2C GVI MRB ALL

53-200-06-0153-500-06-02

52-800-03

Zonal Inspection: External - Passenger Doors and Surrounding Jambs, Including Service Doors, Ventral Stairs, Emergency Exits &

Upper Cargo Door

2C GVI MRB ALL 53-300-01-01

53-100-02Zonal Inspection: External - The Upper

Fuselage to Wing Fillets2C GVI MRB ALL 53-300-02-01

53-100-03Zonal Inspection: Internal - Radome, STA 7

to Forward Face of STA 37 Pressure Bulkhead with Radome open

2C GVI MRB ALL 53-300-03-01

53-100-06

Zonal Inspection: Internal - Forward Passenger Door Stairwell with stairs

extended, access through E & E Compartment

2C GVI MRB ALL 53-300-04-01


Compartment (Aft Area)2C GVI MRB ALL

55-300-05-0155-300-05-02

53-200-02 Zonal Inspection: External: Upper Fuselage 2C GVI MRB ALL55-300-06-0155-300-06-02

53-300-02Zonal Inspection: External - Aft Fuselage &

Empennage2C GVI MRB ALL 55-300-07-01

57-500-02Zonal Inspection: External - Upper and lower surface, including all flight control surfaces

in the extended / deployed position.2C GVI MID ALL

55-300-08-0155-300-08-02

57-600-02Zonal Inspection: External - Upper and lower surface, including all flight control surfaces

in the extended / deployed position.2C GVI MRB ALL 57-500-01-01

71-400-02Zonal Inspection: External - Powerplants,

Pylons, Cowl Doors, Inlet Areas, and Nose Cowls

2C GVI MRB ALL 57-500-02-01


Powerplant Nose Cowls2C GVI MRB ALL 57-500-03-01


Pylons2C GVI MRB ALL 57-500-04-01

53-100-10Zonal Inspection: Internal - Forward Cargo

Compartment, Including Bilge Area and Left & Right Tunnels

4C GVI MRB ALL 57-500-05-01

53-100-11Zonal Inspection: Internal - Area between Lower Surface of Cabin Floor to Upper

Surface of Center Wing4C GVI MRB ALL 57-500-06-01


Compartment, Including Ceiling Area, Bilge Area and Left & Right Tunnels

4C GVI MRB ALL 57-500-07-01

53-200-04Zonal Inspection: Internal: Cockpit Area -

STA 69 - STA 1604C GVI MRB ALL 57-600-01-01

55-300-05Zonal Inspection: Internal Horizontal

Stabilizer Leading Edge4C GVI MRB ALL 57-600-02-01

55-300-06Zonal Inspection: Internal Horizontal

Stabilizer Trailing Edge4C GVI MRB ALL 57-600-03-01



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55-300-07Zonal Inspection: Internal Vertical Stabilizer

Leading Edge and Tip Fairing4C GVI MRB ALL 57-600-04-01

55-300-08Zonal Inspection: Internal - Horizontal Stabilizer Interspar Box Including Tip

4C GVI MRB ALL 57-600-05-01

57-500-06Zonal Inspection: Internal - Left Wing Tip

Assembly4C GVI MRB ALL 57-600-06-01

57-600-06Zonal Inspection: Internal - Right Wing Tip

Assembly4C GVI MRB ALL 57-600-07-01

53-100-12Zonal Inspection: Internal - Center Wing

Section8C GVI MRB ALL

71-400-01-0171-400-01-02

53-100-13Zonal Inspection: Internal - Area below

Center Wing Section8C GVI MRB ALL

70-400-02-0170-400-02-02

53-200-06Zonal Inspection: Internal: Forward, Mid and

Aft Cabin Area8C GVI MRB ALL

71-400-03-0171-400-03-02

57-500-04Zonal Inspection: Internal - Left Wing

Interspar Box Section8C GVI MRB ALL

71-400-04-0171-400-04-02

57-500-05Zonal Inspection: Internal - Left Wing Vent

Box8C GVI MRB ALL

71-400-05-0171-400-05-02

57-600-04Zonal Inspection: Internal - Right Wing

Interspar Box Section8C GVI MRB ALL

71-400-06-0171-400-06-02

57-600-05Zonal Inspection: Internal - Right Wing Vent

Box8C GVI MRB ALL

71-400-07-0171-400-07-02



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CHAPTER: 5 EAC SUPPLEMENTAL INSPECTION TASKS

5.1 General

Supplemental Inspection Tasks are those required items that are mandated by modifications and operator specific requirements. These requirements will include interior installations, avionics upgrades, etc.

The following pages contain a listing of the supplemental inspection tasks applicable to this manual.

5.2 EAC Developed Task Cards

As new tasks are developed by Everts Air Cargo to direct special inspection or maintenance requirements not listed by the MRB, Everts Air Cargo will write its own work card for guidance.

The Director of Maintenance has the responsibility for the creation and content of all EAC developed task cards.

5.3 EAC Supplemental Inspection Tasks

The following pages contain a listing of the EAC Supplemental Inspection Tasks that are applicable to this manual.



05-01EACDaily Check

INTERVAL NOTE: To be performed before the first flight of each day.

1 DY IN DAC ALL 05-001-00-01

25-16EAC

Survival ELT ops check & battery replacement

Replace survival ELT Battery if it will not go until the next ops check

12 MO OP FAR ALL 25-16EAC

25-40EACInventory First Aid Kit

Inspect and replenish every twelve months12 MO GVI FAR ALL 25-40EAC

35-21EACRestore PBE

10 YRS OR PER manufacturer's recommendation

120 MO IN EAC ALL 35-21EAC

25-11EAC Widget Inspection 1A IN EAC ALL 25-11EAC

25-12EAC Net Inspection 1A IN EAC ALL 25-12EAC

25-13EAC Cargo Net Inspection 1A IN EAC ALL 25-13EAC

25-14EAC Seat Track Cleaning 1A SV EAC ALL 25-14EAC

25-15EAC Protective Floor Installation, Removal 1A SV EAC ALL 25-15EAC

35-04EAC

Crew and Courier Oxygen Cylinder Hydrostatic Test

NOTE: DOT 3HT require hydrostatic test each 3 years and have a limited service life of 24 years from date of manufacture and DOT 3AA cylinders require hydrostatic test each

10 years. 3AA have an unlimited service life as set forth in 49 CFR Part 180.209.

1A FC EAC ALL 35-04EAC

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35-12EAC

Portable Oxygen Cylinder Hydrostatic TestNOTE: DOT 3HT require hydrostatic test

each 3 years and have a limited service life of 24 years from date of manufacture and DOT 3AA cylinders require hydrostatic test each

10 years. 3AA have an unlimited service life as set forth in 49 CFR Part 180.209.

1A FC EAC ALL 35-12EAC

79-14EAC Oil S.O.A.P. 1A DET EAC ALL 79-14EAC

31-01EAC

Digital Flight Data RecorderFunctional Check of all required Aircraft

Parameters being recorded properly by the Flight Recorder. NOTE: Recording of

parameters and tolerances specified by Title 14 CFR, Part 121 Appendix B or Local

Regulatory Requirements must be verified.

1C 9 OP EAC ALL 31-01EAC

73-04EAC On wing fuel nozzle clean 1C RS Pratt ALL 73-04EAC

73-05EAC Engine water & detergent washing 1C RS Pratt ALL 73-05EAC

25-10EAC

General Visual Inspection of the Survival Kit, Check Date

NOTE: For contents see section 8.8.1 of GMM

24 MO GVI EAC ALL 25-10EAC

34-01EACRVSM Ground Check

NOTE: Per STC# ST01136LA24 MO IN STC ALL 34-01EAC

34-02EACRVSM Flight Check

NOTE: Per STC# ST01136LA24 MO

Light Check

STC ALL 34-02EAC

34-03EACAltimeter Biennieal Check

NOTE: Per STC# ST01136LA24 MO IN FAR ALL 34-03EAC

34-04EACRVSM Height Keeping Performance

Monitoring24 MO INS STC ALL 34-04EAC

34-08EACTransponder Biennieal Inspection

NOTE: Per STC# ST01136LA24 MO IN FAR ALL 34-08EAC

05-02EAC

Service CheckINTERVAL NOTE: A service check shall be

accomplished every three days, and may exceed 72 hours elapsed time.

3 DY IN DAC ALL 05-001-00-02

08-02EAC

Weight & BalanceDue to the low utilization of this aircraft,

EAC will weight the aircraft every 36 months.

36 MO OP AC ALL 08-02EAC

23-01EAC Voice Recorder Underwater Beacon Battery 6 YR 9 RS EAC ALL 23-01EAC

31-02EAC Flight Data Recorder ULB Battery 6 YR DS EAC ALL 31-02EAC

34-05EACMode-S Transponder Antenna Removal and

Testing1675 Flight

CyclesEAC ALL 34-05EAC

71-01EAC Engine Change As Req. EAC ALL 71-01EAC



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CHAPTER: 6 WEIGHT AND BALANCE PROCEDURES

6.1 Policies

6.1.1 General

The purpose of this Chapter is to set forth methods, procedures and responsibilities for maintaining weight and balance control of EVERTS AIR CARGO's fleet of aircraft.

A complete weight and balance file shall be maintained for each aircraft. Each weight and balance file shall be kept up to date in the maintenance files of the Company, and shall include the following:

1. A current equipment list as weighed.

2. A current copy of the loading schedule in use, and substantiating data thereon.

3. A current copy of the Weight and Balance Report.

4. An empty Weight and Balance Change Record.

5. A signed copy of form M-9H.

6.1.2 Responsibilities

It shall be the responsibility of the Chief Inspector to establish and maintain the procedures and records outlined in this chapter for the control and periodic weighing and weight and balance changes affecting the Company Aircraft.

It shall be the responsibility of the Director of Operations to establish and maintain procedures which will ensure that the aircraft are properly loaded and will not exceed the authorized gross weight and center of gravity limits.

6.1.3 Controlling Documents

1. The Company's Operations Specifications, Part E, "Aircraft Weight and Balance Control."

2. FAA approved Flight Manual appropriate to the type of aircraft.

3. Weight and Balance Control during flight operations (including loading schedule instructions) are contained in the Company's Operations Manual.

6.2 Weight and Balance Control

6.2.1 Individual Aircraft Weight and Balance Control

The individual weight and balance of each aircraft shall be reestablished at the specified reweighing peri-ods. It shall also be reestablished whenever the cumulative changes to the empty weight exceed plus or minus one half of one percent of the maximum landing weight or the cumulative change in CG position exceeds one half of one percent of the CG range.

6.2.2 Responsibility

The Chief Inspector will be responsible for current empty aircraft weight and balance. Prior to release of an aircraft which has undergone a repair or alteration affecting the weight and balance of the aircraft, the Chief Inspector will accomplish the following as applicable:

If the cumulative weight change is less than plus or minus one half of one percent of the CG range, the cumulative change in weight and balance will be recorded on the Aircraft Basic Weight and Balance Report, Form M-9G.

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When the cumulative weight changes to the empty weight exceed plus or minus one half of one percent of the maximum landing weight, recompute the empty weight.

When the cumulative change in the CG position exceeds plus or minus one half of one percent of the CG Range, recompute the empty weight CG.

The recomputed aircraft empty weight and balance shall be forwarded to the Operations Secretary using Form M-9H. Form M-9H must be signed and returned to the Chief Inspector prior to release of the aircraft.

Changes to the aircraft CG, empty weight, or cumulative change to the aircraft weight and balance are the responsibility of the Director of Operations. The effects of these factors upon the current loading schedule are also his responsibility.

6.3 Terms and Definitions

6.3.1 Arm

The horizontal distance in inches from the reference datum line to the center of gravity of the item.

6.3.2 Center of Gravity (CG)

The point about which an aircraft would balance if it were possible to suspend it at that point. It is the mass center of the aircraft, or the theoretical point at which the entire weight of the aircraft is assumed to be con-centrated.

6.3.3 Center of Gravity Limits

The specified forward and aft points beyond which the CG must not be located during flight.

6.3.4 Center of Gravity Range

The distance between the forward and aft CG limits.

6.3.5 Datum (REF. Datum)

An imaginary vertical line from which all measurements of arm are taken. All moment arms and the loca-tion of permissible CG range must be taken with reference to that point.

6.3.6 Equipment Check List

The required equipment list plus equipment included in the aircraft empty weight.

6.3.7 Required Equipment List

The required equipment as prescribed in the applicable airworthiness regulations. (See certification basis, Type Certificate Data Sheet appropriate to the type of aircraft).

6.3.8 Moment

The product of the weight of an item multiplied by its arm. Moments are expressed in pounds-inches, (1 lb-in). Total moment is the weight of the aircraft multiplied by the distance between the datum and CG.

6.3.9 Moment Index (or Index)

A moment divided by a constant such as 100. The moment index is used to simplify weight and balance computations where heavy items and long arms result in large, unmanageable numbers.

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6.3.10 Station

A location in the aircraft which is identified by a number designating its distance in inches from the datum. The datum is identified as station zero. The station and arm are identical. An item located at station +50 would have an arm of 50 inches.

6.3.11 Basic Weight

The weight of the aircraft, engines, and all items of operating equipment that have fixed locations and are permanently installed in the aircraft.

6.3.12 Empty Weight

The empty weight of the aircraft as weighed for weight and balance purposes, plus all items listed on the master equipment checklist.

6.3.13 Basic Operating Weight

The weight of the aircraft, engines and all items of operating equipment that have fixed locations and are permanently installed in the aircraft, plus crew and all the equipment required for flight but not including fuel and payload.

6.3.14 Basic Operating Index

The particular aircraft index with equipment and crew listed in Item 13.

6.3.15 Operating Index

The index for the particular aircraft, ready to operate with crew, fuel and payload and all required equip-ment.

6.4 Weight and Balance Forms: M-9, M-9A, M-9B, M-9E, M-9G, and M-9H

6.4.1 Pre-Weighing Check List (Form M-9A)

This report is used and completed prior to the actual weighing of the aircraft and is attached to the actual Weight and Balance Form for filing. This form shall establish that the aircraft is proper condition to be weighed.

6.4.2 Aircraft Equipment List (Form M-9B)

This form is used to record all permanent equipment installed in the aircraft at the time of weighing. The Chief Inspector is responsible for the accuracy and completeness of this form. It is attached to the actual Weight and Balance Form for retention in the aircraft records.

6.4.3 Aircraft Actual Weight and Balance (Task Card 08-02 EAC):

This report is to record and compute the actual weight, CG location, and moment of each aircraft. It is used when the aircraft is weighed and becomes part of the particular Aircraft Weight and Balance file. Data from this report is entered on the Aircraft Basic Weight and Balance Record Form M-9. The Chief Inspec-tor is responsible for the completion of this form and proper distribution. This form will be used for com-putation of operational index units and percent CG and provides the data required by the flight crews to compute the weight and balance for each flight. M-9E is for an aircraft in Cargo Only configuration and M-9F is for an aircraft in tanker configuration.

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6.4.4 Accumulative Weight Change Record (Form M-9G)

This form shall be used between aircraft weighing to compute the change in CG caused by any removed or installed equipment, or major repairs which will effect the weight and balance of the aircraft. Weight changes totaled on this sheet may not exceed one-half of 1% of the maximum landing weight or % MAC of the aircraft without recomputing the weight and balance. Any of these sheets accumulated between weighing may be discarded at weighing.

6.4.5 Change to Basic Operating Weight (BOW) (Form M-9H)

This form is issued by the Chief Inspector with the new weight and balance of the aircraft to the Operations Secretary. An Operations Bulletin is then generated and sent to appropriate personnel for posting. This form is returned to the Chief Inspector upon issuance of an Operations Bulletin.

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6.5 Preweighing Checklist - Form M-9A

Weighing Condition

Cockpit

STA. ______ DATE________________ A/C NO.N _____________ A/C TYPE ________________

A/C SER. NO. ______________ DATUM _______________ INSPECTOR ____________________

Description YES NO N/A MECH INSP

1. Aircraft in hangar with hangar door closed and leveled

2. Install chocks and release parking brake

3. Install gear pins

4. Landing gear strut serviced

5. Tires inflated at normal pressure

6. All flight control neutral, flap and spoiler retracted

7. All fuel tanks and sumps drained

8. Potable water system drained

9. Toilet and lavatory waste water drained

10. All hydraulic systems filled

11. Engine’s oil tanks filled

12. CSD oil systems filled

13. APU oil tank filled

14. Engine and APU fire extinguisher bottles full

15. Clean and set up cockpit and cabin, appropriate for dispatch


16. Crew oxygen cylinder filled

17. Portable oxygen cylinder in place and filled

18. Hand fire extinguisher in place and filled

19. Oxygen masks in place

20. Life vests installed

21. Hand axe installed

22. First aid kit installed

23. Headphones and microphones installed

24. All radio equipment installed

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6-6


Lower Cargo Compartments

Cargo Configuration Aircraft

Verify That:

25. All seats and seat belts installed

26. All cockpit instruments installed

27. All cockpit manuals removed


28. All containers removed

29. Fly away kits removed

30. All compartments empty


31. Pallet roller system installed

32. Cargo barrier net installed

33. Loading and tie down equipment installed


34. Accessories, electrical and electronic compart-ments units are installed

35. All tools and working equipment from cabin, cockpit and cargo compartments were removed

36. All aircraft emergency doors closed

37. All aircraft doors and cockpit windows closed

38. Nothing interferes with weighing operation in air-craft exterior and interior

39. Airplane equipment in agreement with applicable equipment list (Write down deviation list on page ____ if not)

40. Aircraft leveled and ready for weighing

41. Weight and balance procedure completed

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6.6 Form M-9E

Table 1: Deviations of Basic Empty Weight (BEW)

Table 2: Calculation of Basic Operating Weight (BOW)

REGISTRATION N _______ A/C TYPE _______ LOCATION _____________ DATE ___________DATE OF LAST WEIGHING _________________ REPORT NUMBER_________________________

Description Weight +/- Arm Inches Moment (in-lbs)

Basic Empty Weight (BEW) CG Moment (in-lbs)

Description Weight (+) Arm Inches Moment (in-lbs)

Basic Empty Weight

2 Pilots 380.0 122.0 46360

2 Pilots’ Equipment 50.0 119.0 5950

1 Aircraft Library 30.0 126 3780

30 Cargo Straps 171.3 249.0 42653.7

Pallet Jack 223.5

Cargo Nets (Forward) 52.0 249.0 12948.0

Additional Widgets 36.93 544.275 20100.0758

Cargo Nets (Aft) 52.0 916.5 47658.0

Fuel Drainable (Unusable) 131.0 653.4 85595.4

Floor Panels 1849.0 544.275 1006364.48

Basic Operating Weight CG Moment (in-lbs)

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6.7 Accumulative Weight Change Record (Form M-9G)

Aircraft N_____________________ Date_______________ Station______________________________

List all equipment changes (removed or installed) or major repairs which will affect the weight and balance of the aircraft. Weight changes may accumulate not exceeding one half of 1% of the maximum landing weight, or % MAC, without recomputing the weight and balance.

NOTE: See aircraft AFM for maximum landing weight.

Inspector_______________________________________________ Date__________________________

DATE ITEM INSTALLED WEIGHT +/- ARM MOMENT

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6.8 Change to Basic Operating Weight (BOW) Form M-9H

From: EAC Chief Inspector Date_______________

To: EAC Operations Secretary

Subject: Change to Basic Operating Weight

Instructions:

1. Issue an Operations Bulletin to alert operations of the new weight.

2. Complete the bottom section of this form and return to the Chief Inspector.

TO: Chief Inspector Date_______________

FROM: EAC Operations Secretary

Operations Bulletin issued on ________________________________.

1. Aircraft S/N: ___________________ A/C Reg. No. ___________________

2. Date Weighed: ___________________

3. BOW: ___________________

4. Index: ___________________

5. W&B Folders and Log Book Can updated on ___________________________

6. % MAC ___________________________________

7. C of G ____________________________________

Signature, Chief Inspector

Signature, Operations Secretary

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Rev 3 04 March 2014

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DC-9 Maintenance ManualAircraft No. Station TAT TAC Date

SECTION 7DC-9 EQUIPMENT INVENTORY LIST - Form M-9B

The following Equipment List shall be used to inventory the equipment (appliances) which is required to be installed.

In the upper right corner of each page enter:

A/C NO.: - The Aircraft "N" Number.

Station: - The Station the Equipment Inventory or Weighing is accomplished, as applicable.

TAT: - The Total Airframe Time.

TAC: - The Total Airframe Cycles.

Date: - The date on which the Equipment Inventory or Weighing is accomplished, as applicable.

The headings for the columns are as follows:

ITEM NO. - A sequential numbering system to identify each appliance.

ITEMS - The nomenclature and part number which is applicable for each appliance installed.

CK - The individual who accomplishes the Equipment Inventory will place a "check mark" in this space when it is determined that each item is installed.

REQ APL - The number of identical appliances which are installed.

WEIGHT (LBS) - The weight of each appliance expressed in pounds.

ARM - The distance (expressed in inches) from the appliance location to the datum.

CODE - This column is used to identify aircraft of different configuration by a numerical code. The absence of any information in this column shall mean that the appliance information is standard for the fleet.

EAC Aircraft Codes:

CODE 2 N904CE (31, 32 & 32F SERIES NON-EFIS)

CODE 3 N930CE, N932CE, N935CE (33F SERIES NON-EFIS)

CODE 4 N952AX (41 SERIES NON-EFIS)

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ITEM NO.

ITEMS CK REQ APL

WEIGHT (LBS)

ARM CODE

A Nose CompartmentStation 7 to Station 37

A-1 Antenna, Glideslope(Collins Type 37P-5522-0700-023)

1 5 33.0

A-2 Shell, Radome (DACO 5912445-1) 1 32 8 30.0

A-3 Antenna, Radar (Bendix) 1 23 3 26.0

B Crew CompartmentStation 37 to Station 160

B-1 Gyro, Directional #1 (Sperry 2588302-4) 1 9 0 45.0

B-2 Transformer Rectifier(General Electric 6RW176YN3)

2 11 0 47.0

B-3 Transformer Rectifier(General Electric 6RW176YN3)

2 11 0 54.0

B-4 Inverter, Static (LELAND ASH734-1) 1 22 4 49.0

B-5 Gyro, Directional #2 (Sperry 2588302-4) 1 9 0 56.0

B-6 Transceiver, Radar (RTA4A) 1 26 8 150.0

B-7 Gyro, Vertical (Sperry 2587335-12) 2 14 7 63.0 2,3,4

B-8 Inclinometer Plate (DACO 3916001-1) 1 1 67.0

B-9 Scope, Radar (Bendix 20412220426) 1 15 5 91.0 2,3,4

B-10 Regulator, Pilot & Copilot 02(Bendix 29261-7E-A1)

2 2 7 133.0

B-11 OPEN

B-12 Microphones, Pilot & Copilot (Telex TEL 66T or Telex 38T, or 63999-000)

2 7 106.0

B-13 Headsets, Pilot & Copilot (Telex A1210)or (Telephonics TDH-30)

2 1 1 115.0

B-14 Masks (with microphone), Pilot & Copilot Oxygen (Puritan 114029-25) (114423-21)

2 2 8 140.0

B-15 Handset, Crew (Electro-Voice 625-4122) 1 10 120.0

B-16 Pilot Seat, (Aircraft Mechanics 5925379-501) 1 42 0 129.0

B-17 Seat Copilot (Aircraft Mechanics 5925379-502) 1 42 0 129.0

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B-18 Belt, Pilot & Copilot Shoulder(Pacific Scientific 101110-5)

2 1 4 129.0

B-19 Logbooks, Manuals, & Forms:Emergency Response GuideDeferred Item List (Spare)Log Book & HolderLog Book (Spare)Minimum Equipment List (MEL)Airport Analysis ManualDC-9 ChecklistDC-9 Emergency Checklist

11111122

21 15 129.0

B-20 Harness, Pilot & Copilot Shoulder(Part of Each Seat)

2 6 135.0

B-21 Personal Breathing Equipment (PBE) 1 2 0 148.0

B-22 Mask (with microphone),Observer Oxygen (Puritan 114027-13) or(Puritan 114427-11) or(Puritan 114423-21)

1 2 8 145.0

B-23 Observer Oxygen Bottle(5600-2C1A-F30A) or(5600-2C3A-F30A) or(5600-2C6A-F30A)

2 18 4 144.0

B-24 Cylinder, Crew Oxygen(Scott 6350-A27-CC-C)

1 25 0 160.0

B-25 Regulator, Crew Oxygen (Scott 27660-5) 1 8 160.0

B-26 Extinguisher, Amerex 352(DOT 4B240ET)

1 25 147.0

B-27 First Aid Kit 1 40 126.0

B-28 Microphone, Observers(Telex TEL 66T or Telex 38T, or63999-000)

1 7 106.0

B-29 Headset, Observers (Telex A1210) or(Telephonics TDH-39)

1 11 147.0

B-30 Axe, Emergency (Reuleta 42D8331) 1 2 7 147.0

B-31 Seat, Observers (DACO 5914552-509) 1 12 8 153.0

B-32 Harness, Observers Shoulder(Pacific Scientific 1101440-05)

1 6 157.0

ITEM NO.

ITEMS CK REQ APL

WEIGHT (LBS)

ARM CODE

Rev 3 04 March 2014

7-4


B-33 Belt, Observers Seat(Pacific Scientific 1101011-5)

1 1 4 157.0

B-34 Pitot Heat Indicator (8DW84LAN1) 1 1 0 110.0

B-35 Storage Pouch LG Pins 1 1 0 148.0

B-36 Life Vest (Observers) 1 1 3 129.0

B-37 Life Vest (Captain & Copilot) 2 1 3 129.0

B-38 Courier Seat Assy 1 150 0 160.0

B-39 Life Vest (Courier Seat) 2 1 3 160.0

B-40 Horizontal Situation Indicator(Collins 522-3875-001 or 522-2782-004)

2 4 9 90.0 2,3,4

B-41 Encoding Altimeter (518-16007-333) or(518-28007-201)

2 3 9 90.0 2,3,4

B-42 Standby Altimeter (A40179-10-020, -021) or (A40169-100-021)

1 3 8 90.0 2,3,4

B-43 Vertical Speed Indicator(Specialties SLZ9244)

2 2 2 90.0

B-44 Clock (Aerosonic 87000-1105) 2 1 0 90.0

B-45 Automatic Pilot Indicator(Sperry 2587-554-3)

1 1 5 90.0

B-46 DME Indicator (Collins 522-2604-003) or (522-2604-023)

2 1 1 90.0 2,3,4

B-47 Gyrosyn Compass Indicator(Sperry 1784460-655) or(1784460-355) or (258755-7-901)

2 7 8 90.0

B-48 Radio Altimeter Indicator(Collins 522-4114-003)

2 2 5 90.0 2,3,4

B-49 Flight Director Indicator(Collins 522-3487-010)

2 4 8 90.0 2,3,4

B-50 Mach Airspeed Indicator(Kollsman A39469100-29)

2 2 1 90.0 2,3,4

Mach Airspeed Indicator(Kollsman 35900-A1778)

2 2 4 90.0

B-51 Standby Ram Air Temp Indicator(162BL-710)

1 8 180.0

ITEM NO.

ITEMS CK REQ APL

WEIGHT (LBS)

ARM CODE

Rev 3 04 March 2014

7-5


B-52 Accelerometer (Safeflight 14001) 1 3 5 75.0 2,3,4

B-59 Standby Horizon Indicator (501-1568-14) 1 3 3 90.0 4

B-65 Captain’s VSI/TRA Display 1 3 20 100.00 2,3,4

B-66 F/O’s VSI/TRA Display 1 3 20 100.00 2,3,4

B-67 TCAS Control Panel 1 2 00 110.00 2,3,4

C Cargo CompartmentStation 160 to Station 1019

C Station 160 to 239

C-1 Extinguisher Amerex (369) 1 15 0 160.0

C-2 Coat Hangers Assy 2 2 0 160.0

C-7 Entry Door Rope/Pouch 1 1 0 180.0

C-8 Service Door Rope/Pouch 1 10 180.0

C-9 Guidance Switching Units (964-0414-001) 2 1 5 189.0 2,4

C-10 Airspeed Transducer (964-0421-001) 1 1 0 189.0 2,4

C-11 Accelerometer (979-0223-001) 1 1 5 189.0 2,4

C-12 OPEN

C-13 Tray (600-5705-002) 1 1 8 189.0 2,4

C-14 GPWS Computer (965-0876-001) 1 5 86 189.0 2,4

C-15 Fwd Cargo Barrier Net 1 7 00 203.0

C Station 239 to 328

C-18 Boarding Ladder 1 10 0 247.0

C-19 Container/Pallet Stop 20167E500 2 34 249.0

C-56 Flight Director Accelerometer (229-0324-010)

2 5 677.0 5,6

D Wing Compartment Left and Right

D-1 Drainable Unusable Fuel 122 9 659.0545.0696.0

2,3

4

D-2 Strut, Main Landing Gear(Cleveland 5910706-1 & 2)(DACO 5910496-511 & -512)

2 435406435

555

736.0622.0775.0

2,3

4

ITEM NO.

ITEMS CK REQ APL

WEIGHT (LBS)

ARM CODE

Rev 3 04 March 2014

7-6


D-3 Wheel, Main Landing Gear(Goodyear 9560892)(Goodyear 9560645)(Goodyear 9560859)

4 92651

12

470

736.0622.0775.0

2,3

4

D-4 Tires, Main Landing Gear(Bridgestone 40-14)(Bridgestone 41-15)

44

127127140

000

736.0622.0775.0

2,3

4

D-5 Brakes, Main Landing Gear(Goodyear 9560788-5)(Goodyear 9560743)(Goodyear 9560861-2)

4 161132161

575

736.0622.0775.0

2,3

4

D-6 Trapped Unusable Fuel 494967

585867

623.7778.0794.0

2,3

4

E Tail CompartmentStation 996 to Station 1112

E-1 Extinguishers, Fire (892857) 222

16 7 1011.0832.01087.0

2,3

4

E-2 APU, Gas Turbine(Air Research GTCP85-98D)

1 329 0 1024.0845.01100.0

2,3

4

E-3 Air Conditioning Unit, Primary(Air Research 683435-2-3) or(204950-5-3)

1 33 0 1079.0880.01138.0

2,3

4

E-4 Air Conditioning Unit, Secondary(Air Research 926290-1-1) or(2150206-117)

1 55 6 1079.0880.01138.0

2,3

4

E-5 Cone, Tail (DACO 5910456-1) 1 56 0 1225.01045.01306.0

2,3

4

E-6 Digital Flight Data Recorder(17M703-01) or(17M703-275)

1 28 5 1152.0948.01228.0

2,3

4

F Lower Forward FuselageStation 69 to Station 218

F-1 Tire, Nose Landing Gear(Goodyear Tubeless 26 x 6.6)

2 2 95 97.0

ITEM NO.

ITEMS CK REQ APL

WEIGHT (LBS)

ARM CODE

Rev 3 04 March 2014

7-7


F-2 Wheel, Nose Landing Gear(Goodyear 9550107)

2 26 8 97.0 1

Wheel, Nose Landing Gear(Goodyear 9550267)

20 8 97.0 2,3,4

F-3 Strut, Nose Landing Gear(Menasco 5910448-1)

1 176149176

252

97.097.097.0

2,3

4

F-4 Battery Charger (VAP AIR 26340061-06) 1 16 6 113.0

F-5 Batteries (General Electric 43B034LB02) 2 46 1 129.0

F-6 Transceiver, VHF #1(King 064-1005-04) or622-1181-001 or2070326-4218

1 18 7 123.0 2,3,4

F-7 Transceiver, VHF #2(King 064-1005-04)or 622-1181-001 or2070326-4218

1 18 7 130.0 2,3,4

F-8 Receiver, VHF NAV #1(King 066-1060-00)

1 17 5 136.0 2,3,4

F-9 Receiver, VHF NAV #2(King 066-1060-00)

1 17 5 143.0 2,3,4

F-10 Receiver, Marker Beacon(Collins 522-2996-001)

1 3 3 149.0 2,3,4

Receiver, Marker Beacon(Bendix 2087821-2801

3 4 149.0 2,3,4

F-11 Receiver ADF #1 (Collins 522-1836-000) 1 9 5 154.0

F-12 Amplifier, Flight Interphone(Gables G-610-11)

1 1 2 116.0

F-13 Amplifier, Flight Interphone(Gables G-610-11)

1 1 2 116.0

F-14 Computer, Flight Director #1(Collins 522-3750-005)

1 7 7 129.0 2,3,4

F-15 Amplifier, Flight Director Instrument #1(Collins 522-3120-005)

1 7 4 132.0 2,3,4

F-16 Rack, Compass #1 (Sperry 614937-10) 1 3 5 135.0 2,3,4

ITEM NO.

ITEMS CK REQ APL

WEIGHT (LBS)

ARM CODE

Rev 3 04 March 2014

7-8


F-17 Rack, Compass #2 (Sperry 614937-10) 1 3 5 138.0 2,3,4

F-18 Amplifier, Flight Director Instrument #2(Collins 522-3120-005)

1 7 4 141.0 2,3,4

F-19 Computer, Flight Director #2(Collins 522-3750-005)

1 7 7 144.0 2,3,4

F-20 Computer, Stall Warning #1(United Data Control 965-0041-029)

1 3 0 153.0

F-21 Computer, Stall Warning #2(United Data Control 965-0041-029)

1 3 0 156.0

F-22 Generator, Stall Warning Tone(593-1-000-11)

1 3 0 156.0

F-23 Computer, Speed Command(1310-10)(1312-25)(1313-50)

111

272727

222

171.0171.0171.0

2,34

F-24 Flyaway Spares Kit

-503, -505, and -507 Installation 119 5 189.0 2

VHF Comm. (064-1005-XX) 1

NAV Receiver (066-01060-000) 1

Indicator, EGT (152BL705H), or(152BL705J), or(152BL705P), or(152BL705N)

1

Charger, Battery (26340061-06) 1

Sensor, Battery Temp. (2824-1) 1

Detector, Smoke (30-231-4) 1

Amplifier, Smoke Detector (30-326-2) 1

Wrench, Main Wheel (4916706-509) 1

Amplifier, Instrument (522-3120-004) 1

Compass Rack (614937-10) 1

Amplifier, Fire Detector (892809-0400-01) 1

Switch (700-001-01-01) 1

Switch (H14-1005-1) 1

ITEM NO.

ITEMS CK REQ APL

WEIGHT (LBS)

ARM CODE

Rev 3 04 March 2014

7-9


Switch (H20-1) 1

Switch (H20-2) 1

Switch (H20-3) 1

Switch (H20-6) 1

Switch (H20-9) 1

Switch (H20-21) 1

Switch (H20-24) 1

Switch (H20-28) 1

Stick Shaker (C25502) 1

Standby Horizon Indicator (705-15V1) 1

Standby Horizon Inverter (8472V1) 1

Computer, Proximity (if equipped)(008-0004-003 or -005)

1

Sensor, Proximity (if equipped) (8-018-01) 1

NAV Comm. Control Panel (G4816) 1

Wrench, Transducer (3916731-505) 1

-509 Installation 112 2 189.0 3

VHF Comm. (064-1005-XX) 1

NAV Receiver (066-01060-000) 1


1



Detector, Smoke (30-231-4) 1

Amplifier, Smoke Detector (30-326-2) 1




ITEM NO.

ITEMS CK REQ APL

WEIGHT (LBS)

ARM CODE

Rev 3 04 March 2014

7-10


Amplifier, Fire Detector(892809-0400-01)

1

Switch (700-001-01-01) 1

Switch (H14-1005-1) 1

Switch (H20-1) 1

Switch (H20-2) 1

Switch (H20-3) 1

Switch (H20-6) 1

Switch (H20-9) 1

Switch (H20-21) 1

Switch (H20-24) 1

Switch (H20-28) 1

Stick Shaker (C25502) 1




1




-511 Installation 122 1 189.0 4

VHF Comm. (064-1005-XX) 1

NAV Receiver (066-01060-000) 1


1



Detector, Smoke (775001) 1

ITEM NO.

ITEMS CK REQ APL

WEIGHT (LBS)

ARM CODE

Rev 3 04 March 2014

7-11





Amplifier, Fire Detector(892809-0400-01)

1

Switch (700-001-01-01) 1

Switch (H14-1005-1) 1

Switch (H20-1) 1

Switch (H20-2) 1

Switch (H20-3) 1

Switch (H20-6) 1

Switch (H20-9) 1

Switch (H20-21) 1

Switch (H20-24) 1

Switch (H20-28) 1

Shaker, Stick (35A557) 1




1




F-25 Box, Anti Skid Control (Hydro-Aire 42-139) 1 4 5 209.0

F-26 Receiver, DME #2 (522-2702-054) or(066-1094-01)

1 21 7 197.0 2,3,4

F-27 Receiver, DME #1 (522-2702-054) or(522-2702-052)

1 21 7 190.0 2,3,4

F-28 Computer, Stability Augmentation (Sperry2587826-3)

1 14 6 176.0

ITEM NO.

ITEMS CK REQ APL

WEIGHT (LBS)

ARM CODE

Rev 3 04 March 2014

7-12


F-29 Computer, Roll Axis (Sperry 25886687-3)or (25886687-8)

1 24 0 169.0

F-30 Computer, Air Data (Sperry 2587400-745)or (2587400-373)

1 18 8 176.0 2,3,4

F-31 Computer, Pitch Axis (Sperry 2586686-3) 1 21 4 169.0

F-32 Computer (GPWS) Sunstrand 965-04876-088) or (965-0876-001-B03) or (965-0876-001-B04)

1 7 4 179.0

F-33 Inverter (Standby Horizon) (TSG420-102) 1 2 0 63.0 2,3

F-34 Comparator Warning Computer (522-3394-005) or (522-3949-001)

1 12 8 116.0 2,3,4

F-48 TCAS Computer 1 21 00 180.00 2,3,4

F-49 TCAS Tray 1 3 40 180.00 2,3,4

F-50 Mode-S Computer 1 12 8 200.00 2,3,4

F-51 Mode-S Tray 1 2 00 200.00 2,3,4

F-52 Air Data Display Unit (ADDU) 1 3 00 90.00 2,3,4

F-53 TAWS Control Panel 1 3 00 94.00 2,3,4

F-54 Analog Interface Unit (AIU) 1 8 32 176.00131.00

2,3,4

F-55 TAWS Computer 1 9 60 135.00 2,3,4

F-56 GPS Computer 1 3 60 134.00 2,3,4

G Forward Cargo Compartment Station 218to Station 596.5

G-1 Radio Altimeter R/T (Collins 522-3698-003) 1 10 0 450.0 2,3,4

G-3 TCAS Directional Antenna 1 2 10 265.0 2,3,4

H Main Gear Well

H-1 Auxiliary Hydraulic Pump (AS19593) 1 40 5 689.0727.0

2,34

K Aft Cargo Compartment Station 760 toStation 996

ITEM NO.

ITEMS CK REQ APL

WEIGHT (LBS)

ARM CODE

Rev 3 04 March 2014

7-13


Inventory Completed By: _______________________________________Date: _______________

K-1 Cockpit Voice Recorder 1 23 0 951 4

(Fairchild 93A100) 874.0 2,3

Cockpit Voice Recorder(L3 2100-1020-00)

1 10 0 951.0 4

874.0 2,3

K-2 Smoke Goggles 3 3 4 115.0 All Codecs

K-3 OPEN

K-4 Manuals:

Wiring Diagram Manual 11

15 80 960.01034.0

2,34

K-5 Tail Stand 1 171220

0 778.1

854.0

2,3

4

L Nacelle Compartment

L-1 Engine, Turbofan(Pratt & Whitney JT8D-7)(Pratt & Whitney JT8D-9)(Pratt & Whitney JT8D-11)(Pratt & Whitney JT8D-15)

222

320532523309

000

989.0

1060.0

2,3

4

L-2 Unusable Engine Oil 454545

777

950.0

1020.0

2,3

4

L-3 Usable Engine Oil 808080

999

950.0

1020.0

2,3

4

ITEM NO.

ITEMS CK REQ APL

WEIGHT (LBS)

ARM CODE

Rev 3 04 March 2014

7-14


Rev 3 04 March 2014

DC-9TASK CARD

TC-1

AIRLINE CARD NO.N/A

TITLEDaily Check

EAC CARD NO.05-01EAC

DATE TASKINS

RELATED CARD

TAIL NUMBER WORK AREANONE

VERSION1

THRESHOLD1 Per Day

REPEAT1 Per Day

APPLICABILITYAIRPLANE ENGINES

ALLSTATION SKILL

Pilot/MechanicBODY STATION STRINGER

ATA CHAPTER12-00

ACCESSNONE

ZONE

NONE

General Section1. Equipment and Materials - None

FLEET EFFECTIVITY PAGE 1 OF 317-APR-2012

Rev 3 04 March 2014

DC-9TASK CARD

TC-2

AIRLINE CARD NO.N/A

TITLEDaily Check


DATE TASKINS

RELATED CARD


VERSION1

THRESHOLD1 Per Day

REPEAT1 Per Day


ALLSTATION SKILL


ATA CHAPTER12-00

ACCESSNONE

ZONE

NONE

Procedure

1. Prepare aircraft for Daily Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A. Check Aircraft Log Book for open Squawks and that the Airworthy release is current.

B. Connect External power source 115V, 400 HZ or start APU as applicable to provide electrical power.

C. Ensure Landing gear pins are removed.

NOTE: Airworthy Release is not required for a Daily Check but is required for the Service Check and is completed every 3 days but may exceed 72 hours.

2. Verify the following aircraft servicing requirements have been accomplished. .

A. Engine Oil - Use oil quantity gauges in cockpit.

B. CSD oil quantity

C. Crew Oxygen

D. Fueling

3. Perform external walk around check for obvious irregularities. . . . . . . . . . . . . .

A. NLG & MLG tires and oleo struts.

B. Check for tools, loose or damaged parts, foreign objects & fluid leaks in the wheel wells.

C. Access doors & panels.

D. Wing external surfaces.

E. Foreign Object Damage (FOD).

F. Fuselage external surface.


MECHANIC

MECHANIC

MECHANIC

Rev 3 04 March 2014

DC-9TASK CARD

TC-3

AIRLINE CARD NO.N/A

TITLEDaily Check


DATE TASKINS

RELATED CARD


VERSION1

THRESHOLD1 Per Day

REPEAT1 Per Day


ALLSTATION SKILL


ATA CHAPTER12-00

ACCESSNONE

ZONE

NONE

G. Stabilizer horizontal & vertical surfaces.

H. During the external inspection of the aircraft particular attention should be paid to any component that affects altimetry system accuracy, the condition of each static port and the fuselage skin in the vicinity of each static port (RVSM).

4. Perform visual check of engines & nacelles with cowlings closed & latched. . .

A. Evidence of FOD

B. Engine inlet. Air intake & spinners.

C. Fan blades for free rotation by hand

D. Drain mast for obstructions and excessive leakage.

E. Cowlings for condition & security.

F. Reversers for condition & evidence of leakage.

G. Tail pipe area for metal deposits.

H. Pylons for condition & FOD.

5. Ensure that Cargo doors are properly closed & latched. . . . . . . . . . . . . . . . . . .

6. Ensure that parking & departure area is clear of debris & obstructions. . . . . . .

7. Remove static ground cables if required.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8. Shut down APU or remove external power if required. . . . . . . . . . . . . . . . . . . .

9. Remove wheel chocks. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


MECH

MECH

MECH

MECH

MECH

MECH

Rev 3 04 March 2014

DC-9TASK CARD

TC-4


Rev 3 04 March 2014

DC-9TASK CARD

TC-5

AIRLINE CARD NO.N/A

TITLEService Check


DATE TASKINS

RELATED CARD


VERSION1

THRESHOLD3 Day

REPEAT 3 Days


ALLSTATION SKILL

MechanicBODY STATION STRINGER

ATA CHAPTER12-00

ACCESSNONE

ZONE

NONE

General Section1. Equipment and Materials - None


Rev 3 04 March 2014

DC-9TASK CARD

TC-6

AIRLINE CARD NO.N/A

TITLEService Check


DATE TASKINS

RELATED CARD


VERSION1

THRESHOLD3 Day

REPEAT 3 Days


ALLSTATION SKILL


ATA CHAPTER12-00

ACCESSNONE

ZONE

NONE

Procedure1.Prepare aircraft for Service Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.Ensure Landing gear pins are installed

B.Connect External power source 115V, 400 HZ or start APU as applicable to provide electrical power.

2.Check Aircraft Log Book for open Squawks & Deferred discrepancies. Record on M-3 as appropriate.

3.Check Hydraulic transfer Pump vent line recovery bottle fluid level.

4.Service the following items:

A.Engine oil (BP2380) between 5 and 30 minutes after shut down.

B.MLG & NLG tire for condition, wear & pressure. Refer to AMM 12-52-00

C.Ensure that a placard stating "INFLATE TIRES WITH NITROGEN ONLY" is installed either in each wheel well or on or near each landing gear strut easily readable by the per-son servicing the tires.

D.Check APU oil quantity (Refer to AMM 12-23-00).

E.Hydraulic fluid quantity (Refer to AMM 12-03-01) (AMM 12-30-00)

F.CSD oil (Refer to AMM 12-22-00)

G.Crew Oxygen (Refer to AMM 12-70-00).

H.Fueling (Refer to AMM 12-11-00).

(i)Check fueling adapter flanges for cracks before fueling.

(ii) Drain aircraft fuel tank sumps and perform water contamination check before fueling. This task is N/A if OAT is below 0 degrees C. This task is N/A if the elapsed time on the ground between flights is less than 3 hours when this service check is being performed.

(iii) Check auxiliary fuselage fuel tank cavity & shroud drain valves for accumulation of fuel (if installed)

5.Check left & right air-conditioning unit cooling turbine oil level. (Refer to AMM 12-64-00).

6.Check brakes for condition, wear and evidence of leakage (Refer to AMM 32-40-00).

NOTE:Replace brake if wear pin is flush with housing.FLEET EFFECTIVITY PAGE 2 OF 5

17-APR-2012

MECH

MECH

MECH

MECH

MECH

MECH

MECH

MECH

MECH

MECH

MECH

MECH

MECH

Rev 3 04 March 2014

DC-9TASK CARD

TC-7

AIRLINE CARD NO.N/A

TITLEService Check


DATE TASKINS

RELATED CARD


VERSION1

THRESHOLD3 Day

REPEAT 3 Days


ALLSTATION SKILL


ATA CHAPTER12-00

ACCESSNONE

ZONE

NONE

7. Perform external walk around check with emphasis on the following items:A. NLG & MLG wheel wells

i. Check landing gear shock strut for cleanliness, leaks, and proper extension. Refer to AMM 32-11-20 MLG & AMM 32-21-20 NLG. Wipe exposed shock struts and door snub-bers with a rag dampened with MIL-H-5606 oil.

(ii) Check doors for condition & security.(iii) Check Landing gear system installations for condition, security & leakage.(iv) Check hubcaps for security.(v) Check shimmy damper reservoirs for condition, security & proper servicing.

B. Enginesi. Check inlets & exhaust for foreign object damage (FOD) & metal deposits.(ii) Check all cowling access & latches for condition & security.

C. Aft accessory compartment.i. Check system installations for condition, security & leakage.(ii) Check hydraulic systems differential pressure indicators.

D. Check APU area for evidence of fuel & oil leaks.E. Check forward & aft cargo compartments, cargo door seals, latches, & hinges for

condition & security.i. Check compartment floor boards, sidewalls & ceiling panels for condition & security.

NOTE: If sidewall repair or replacements are required, use only liner material meeting requirements of FAR 25, Fire Resistance material.

(ii) Check cargo doors & cargo barrier door/nets for operation, condition & security.(iii) Ensure all floor, ceiling & sidewall seams are taped with fire resistant tape (replace any deterio-

rated tape) (Refer to AMM 25-52-10).(iv) Check cargo compartment lights & lenses for operation, condition & security.

F. Check the radome, nose, forward & aft fuselage, empennage, wings, fillets, flight con-trols, engine nacelles & cowling with emphasis on the following items, as seen from the ground.i. Access doors & panels for condition & security.(ii) Pitot tubes & static ports for obstructions & damage (RVSM).(iii) Evidence of fluid leakage.(iv) Foreign object damage.

G. Perform walk around visual check of airframe, wings & tail for condition, security & evidence of fluid leaks.

H. Check main & nose landing gear view mirror window indicating mechanism & align-ment strips for condition, security & cleanliness.


MECH

MECH

MECH

MECH

MECH

MECH

MECH

Rev 3 04 March 2014

DC-9TASK CARD

TC-8

AIRLINE CARD NO.N/A

TITLEService Check


DATE TASKINS

RELATED CARD


VERSION1

THRESHOLD3 Day

REPEAT 3 Days


ALLSTATION SKILL


ATA CHAPTER12-00

ACCESSNONE

ZONE

NONE

I. Check hydraulic filter indicators and accumulator per-charge pressure.J. Check oxygen blow out disk for security or missing. (replace if missing).K. Check static dischargers for condition & security. (replace if missing).L. Clean all surfaces of outflow valve.

8. Install engine inlet covers as required.9. Perform internal walk through check with emphasis on the following items:

A. Check crew seats, seat belts & harnesses for condition and operation.B. Check cockpit windows for condition and cleanliness.C. Check crew oxygen & smoke masks for condition and cleanliness.

NOTE: One set of the same manufacture for each crew position.

D. Check all emergency equipment for condition, inspection date, & security.E. Check battery charger for proper operation (Refer to MM 24-30-2).F. Check security of cockpit instrument panels including secondary latches on both captain's & first offi-

cer's side.G. Check all cargo door-warning lights for proper operation (LIGHT ON when door OPEN).H. Check date on FMS NAV database (if applicable).I. Check forward entry door and service door assist handles for condition and security.J. Check empennage hydraulic accumulators for condition, security and proper pre-charge pressure

(Ref MM 29-10-13).10. Perform the following Electrical Checks:

A. Check instruments for condition and clean bezels.B. Check cockpit lighting including standby and emergency lighting systems and spare bulb supply.C. Ensure that pitot, static and angle of attack vane heater switches are in "off" position.D. Perform self-test of radio altimeter.E. Perform flight recorder operational check.F. Check voice recorder operation from all three positions.G. Check external lights and lenses for proper operation.H. Check communication headsets for proper operation and condition.I. Check audio control panels for proper operation and condition.


MECH

MECH

MECH

Rev 3 04 March 2014

DC-9TASK CARD

TC-9

AIRLINE CARD NO.N/A

TITLEService Check


DATE TASKINS

RELATED CARD


VERSION1

THRESHOLD3 Day

REPEAT 3 Days


ALLSTATION SKILL


ATA CHAPTER12-00

ACCESSNONE

ZONE

NONE

11. Assure all access doors and inspection covers are secured upon completion of work.12. Ensure that aircraft Maintenance Log Book and all required forms are properly completed

and signed off, including current airworthiness release.


MECH

MECH

Rev 3 04 March 2014

DC-9TASK CARD

TC-10


Rev 3 04 March 2014

DC-9TASK CARD

TC-11

AIRLINE CARD NO.N/A

TITLEWeight and Balance

EAC CARD NO.08-02 EAC

DATE TASKINS

RELATED CARD

TAIL NUMBER WORK AREAALL

VERSION1

THRESHOLDN/A

REPEAT36 months


ALLSTATION SKILL

InspectorBODY STATION STRINGER

ATA CHAPTER08-00

ACCESSInclinometers installed in the nose gear wheel well on the right side are used for determining the attitude of the airplane. Access to the inclinometers is through the nose gear wheel well.

ZONE

NONE

General SectionEquipment and Materials - Jacks, Load cells

References:

Boeing (Douglas) DC-9 AMM

08-00 General

08-10 Leveling

08-20 Weighing

Weight & Balance Manual DM-WB9 (Chapter 1)

Weight & Balance Manual DM-WBCH2 (Chapter 2)


Rev 3 04 March 2014

DC-9TASK CARD

TC-12

AIRLINE CARD NO.N/A



DATE TASKINS

RELATED CARD


VERSION1

THRESHOLDN/A

REPEAT36 months


ALLSTATION SKILL


ATA CHAPTER08-00


ZONE

NONE

Procedure1. Accomplish Preweighing Checklist (Section 6.5)

2. Verify aircraft is in agreement with Equipment List (Section 7)

.

1. Jack aircraft IAW Boeing DC-9 AMM 07-10

2. Level the aircraft IAW Boeing DC-9 AMM 08-10.

3. Weigh aircraft IAW Boeing DC-9 AMM 08-20.


MECH INSP

Rev 3 04 March 2014

DC-9TASK CARD

TC-13

AIRLINE CARD NO.N/A



DATE TASKINS

RELATED CARD


VERSION1

THRESHOLDN/A

REPEAT36 months


ALLSTATION SKILL


ATA CHAPTER08-00


ZONE

NONE


WEIGHING POINTS SCALE READING TARE CORRECTION NET WT H-ARM (FUS STA) *MOMENTRIGHT WING JACKLEFT WING JACKSUBTOTAL (WING JACKS) 641AFT FUSELAGE JACK 995.5ACFT AS WEIGHED (Wt)

Table 1 (BEW)Table 2 (BOW)Basic Operating Weight (BOW)

(BOW)

(BOW)

*ALL MOMENTS ARE CALCULATED ABOUT FUSELAGE STATION “0” AS REFERENCE DATUMScale Type: Serial Number: Calibration Date:

Inspector’s Signature: __________________________________________ A & P # ________________________

AIRPLANE C.G. (% MAC)H-ARM 658.5–

147.4--------------------------------------- 100 658.5–

147.4-------------------------------= 100 % MAC=–

INDEX UNIT BOW H-ARM 694 –1000

---------------------------------------------------------- x 694–

1000---------------------------------------------------------------------- ===

Rev 3 04 March 2014

DC-9TASK CARD

TC-14

AIRLINE CARD NO.N/A



DATE TASKINS

RELATED CARD


VERSION1

THRESHOLDN/A

REPEAT36 months


ALLSTATION SKILL


ATA CHAPTER08-00


ZONE

NONE

AIRPLANE ACTUAL WEIGHT AND BALANCE (ALTERNATE METHOD)


AS-WEIGHTED DATA, AIRPLANE LEVELWEIGHING POINTS (JACKPOINTS)

SCALE READING TARE SCALE CORRECTION

NET WT (POUNDS)

H-ARM (FUS STA) *MOMENT (INCH-LB)

LEFT MAIN GEARRIGHT MAIN GEARSUBTOTAL (MAIN GEAR)NOSE GEAR (WN)

AIRPLANE AS WEIGHED (WT)

LESS ITEMS ON PAGEADD ITEMS ON PAGEMANUFACTURER’S EMPTY WEIGHT (MEW)

(BOW)

(BOW)

*ALL MOMENTS ARE CALCULATED ABOUT FUSELAGE STATION “0” AS REFERENCE DATUMScale Type: Serial Number: Calibration Date:

Inspector’s Signature: __________________________________________ A & P # ________________________

AIRPLANE C.G. (% MAC)H-ARM 658.5–

147.4--------------------------------------- 100 658.5–

147.4-------------------------------= 100 % MAC=–

INDEX UNIT BOW H-ARM 694 –1000

---------------------------------------------------------- x 694–

1000---------------------------------------------------------------------- ===

Rev 3 04 March 2014

DC-9TASK CARD

TC-15

AIRLINE CARD NO.N/A

TITLEVOICE RECORDER UNDERWATER LOCATOR

BEACON BATTERY


DATE TASKRST

RELATED CARD


VERSION1

THRESHOLDN/A

REPEAT6 years


ALLSTATION SKILL BODY STATION STRINGER

ATA CHAPTER23

ACCESS5708A

ZONE

57

General SectionEquipment and Materials - None

Ref - FA2100 CVR CMM

Procedure1. Open access door 5708A in the aft cargo compartment.

2. Open, safety and tag the circuit breaker that follows:

Circuit BreakerPanel LocationF6 Cockpit Voice RecorderUEPC CBP

3. Perform functional test of locator beacon.

4. Remove cockpit voice recorder ULB battery.

5. Install serviceable voice recorder ULB battery.

A. Perform a return to service test for the cockpit voice recorder ULB battery IAW FA2100 CVR CMM.

6. Close access 5708A.

7. Close circuit breaker listed in Step 2.

***END OF WORK STEPS - NO FURTHER SIGNOFFS REQUIRED***


Date Emp # Mech

Date Emp # Insp

Rev 3 04 March 2014

DC-9TASK CARD

TC-16


Rev 3 04 March 2014

DC-9TASK CARD

TC-17

AIRLINE CARD NO.N/A

TITLESurvival Kit Inventory


DATE TASKGVI

RELATED CARD25-16EAC

TAIL NUMBER WORK AREA4

VERSION1

THRESHOLDN/A

REPEAT24 MO


ALLSTATION SKILL


ATA CHAPTER25

ACCESSFLIGHT COMPARTMENT

ZONE

6


References:

1. EAC GMM Chapters 5 & 8

2. 14 CFR 121.353


Rev 3 04 March 2014

DC-9TASK CARD

TC-18

AIRLINE CARD NO.N/A

TITLESurvival Kit Inventory


DATE TASKGVI



VERSION1

THRESHOLDN/A

REPEAT24 MO


ALLSTATION SKILL


ATA CHAPTER25


ZONE

6

Procedure


MECH

1. Remove Survival Kit from aircraft.

2. Discard seal and open Survival Kit.

3. Inventory Survival Kit paying special attention to expiration Dates.

4. Replace any item that will expire before next inspection.

5. Re-inventory Survival Kit IAW EAC GMM 8.8.1.

6. Fill out Emergency Equipment Tag IAW EAC GMM 5.15

7. Have Survival Kit Yellow tagged

8. Close Survival Kit and replace seal.

9. Re-install Survival Kit.

Rev 3 04 March 2014

DC-9TASK CARD

TC-19

AIRLINE CARD NO.N/A

TITLEWidget Inspection


DATE TASKIN

RELATED CARD

TAIL NUMBER WORK AREA VERSION1

THRESHOLDN/A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER25

ACCESS ZONE

Inspection CriteriaWidget must be free from corrosion of metal. Outward discoloration (e.g. changing of color from gold to white) is common and acceptable. It is caused by normal chemical reactions and minor oxidation processes. If the surface of the hardware has been eaten into by the corrosive process, the strength of the metal has been compromised. This condition is not considered safe and airworthy.

All moving parts must be in working order.

Source: Cargo System, Inc. Inspection and repair Procedure Rev D, 12-15-10.

No corrosion damage permitted.


Task Complete: __________________________ Date: _____________


Rev 3 04 March 2014

DC-9TASK CARD

TC-20


Rev 3 04 March 2014

DC-9TASK CARD

TC-21

AIRLINE CARD NO.N/A

TITLENet Inspection


DATE TASKIN

RELATED CARD


THRESHOLDN/A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER25

ACCESS ZONE

Inspection CriteriaWebbing:

Cuts, tears or severely frayed webbing edges require removal from service.

"Fuzzing" or "light fraying" of webbing edge is common, and is not a problem so long as no cuts or tears have occurred in the webbing yarns.

Hardware:

Hardware must be free from corrosion of metal. Outward discoloration (e.g. changing of color from gold to white) is common and acceptable. It is caused by normal chemical reactions and minor oxidation processes. If the surface of the hardware has been eaten into by the corrosive process, the strength of the metal has been compromised. This condition is not considered safe and airworthy.





Rev 3 04 March 2014

DC-9TASK CARD

TC-22


Rev 3 04 March 2014

DC-9TASK CARD

TC-23

AIRLINE CARD NO.N/A

TITLECargo Strap Inspection


DATE TASKIN

RELATED CARD


THRESHOLDN/A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER25

ACCESS ZONE

Inspection CriteriaWebbing:

Cuts, tears or severely frayed webbing edges require removal from service.

"Fuzzing" or "light fraying" of webbing edge is common, and is not a problem so long as no cuts or tears have occurred in the webbing yarns.

Hardware:

Hardware must be free from corrosion of metal. Outward discoloration (e.g. changing of color from gold to white) is common and acceptable. It is caused by normal chemical reactions and minor oxidation processes. If the surface of the hardware has been eaten into by the corrosive process, the strength of the metal has been compromised. This condition is not considered safe and airworthy.





Rev 3 04 March 2014

DC-9TASK CARD

TC-24


Rev 3 04 March 2014

DC-9TASK CARD

TC-25

AIRLINE CARD NO.N/A

TITLESeat Track Cleaning


DATE TASKSVC

RELATED CARD


THRESHOLDN/A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER25

ACCESS ZONE


MECH

1. Remove protective “Diamond Plate Floor” per Task Card No. 25-15EAC.

2. Clean seat tracks (DO NOT use metallic scrapers to clean seat tracks. Use "plastic" or "phe-nolic" scrapers when required.)

3. Perform a general visual inspection for corrosion or other damages (Using criteria outlined in CPCP document Appendix B and DC-9 SRM).

4. Install protective "Diamond Plate Floor" per Task Card No. 25-15EAC.

Rev 3 04 March 2014

DC-9TASK CARD

TC-26


Rev 3 04 March 2014

DC-9TASK CARD

TC-27

AIRLINE CARD NO.N/A

TITLEPROTECTIVE FLOOR

INSTALLATION/REMOVAL


DATE TASKSVC



THRESHOLDN/A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER25

ACCESS ZONE

Four persons are required to remove/install the floor. DO NOT drag panels. Instead, lift them or use Broom Handles. Dragging the panels may cause damage to the fire retardant paint or cause the "T nuts" to fall.


FLOOR REMOVAL: MECH

1. Remove all Fittings P/N DC-9-101 and DC-9-102 and their studs (Stud P/N 657N3304).

2. Remove the screws at the FORWARD EDGE only of each panel/compartment.)

3. Remove the floor panels.

FLOOR INSTALLATION:NOTE: Inspect floor panels, attach fittings and studs for any damages before installation. Replace

any damaged component. Any plywood base panels (panel 1 to 5) must be protected with fire retardant paint meeting or exceeding the requirements of ASTM E84 and/or NFPA 255.

MECH1. Place panel #1A in position as shown on drawing 1.14P1.

2. Install four (4) DC-9-101 fittings as shown on drawing 1.14 P2. DO NOT tighten the nuts at this time.

3. Install five (5) DC-9-102 fittings as shown on drawing 1.14 P3. DO NOT tighten the nuts at this time.

4. Place panel #2B in position, front flange on top of panel #1A. Use 5/32" punches in outboard holes to align connecting row of holes as you lower the panel. Keep the aft end of the panel ele-vated approximately 2 inches off the floor and start screws (P/N MS24693S272) in holes next to punches on both sides. Lower the aft end of the panel and install remaining screws and tighten.NOTE: Maintain equal gap between floor panel and seat track on both sides.

5. Install four (4) DC-9-101 fitting as before. (step 2)

6. Install the rest of the panels in the same manner as mentioned in step 4.

7. Install five (5) DC-9-102 fittings on the aft end of panel #9J in the same manner as on the front end of panel #1A. (Step 3)

8. Tighten all nuts on all studs and torque to 160-190 in-lbs

NOTE: Use Washer P/N AN960-616 and Nut P/N MS21044N6 as required.

Rev 3 04 March 2014

DC-9TASK CARD

TC-28

AIRLINE CARD NO.N/A




DATE TASKSVC



THRESHOLDN/A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER25

ACCESS ZONE


Rev 3 04 March 2014

DC-9TASK CARD

TC-29

AIRLINE CARD NO.N/A




DATE TASKSVC



THRESHOLDN/A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER25

ACCESS ZONE


Rev 3 04 March 2014

DC-9TASK CARD

TC-30

AIRLINE CARD NO.N/A




DATE TASKSVC



THRESHOLDN/A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER25

ACCESS ZONE


Rev 3 04 March 2014

DC-9TASK CARD

TC-31

AIRLINE CARD NO.N/A

TITLESurvival ELT OPS Check


DATE TASKOP



VERSION1

THRESHOLDN/A

REPEAT12 MO


ALLSTATION SKILL


ATA CHAPTER25


ZONE

6

General SectionEquipment and Materials - NONE

References

1. EAC GMM Chapter 12

2. 14 CFR 91.207


Rev 3 04 March 2014

DC-9TASK CARD

TC-32

AIRLINE CARD NO.N/A

TITLESurvival ELT OPS Check


DATE TASKOP



VERSION1

THRESHOLDN/A

REPEAT12 MO


ALLSTATION SKILL


ATA CHAPTER25


ZONE

6

Procedure


MECH

1. Gain access to Survival ELT located in survival kit.

2. Inspect Survival ELT IAW 14 CFR 91.207 (c)

3. Inspect Survival ELT for proper installation.

4. Inspect Survival ELT for battery corrosion.

5. Inspect Survival ELT for operation of controls and crash sensor.

6. Inspect Survival ELT for sufficient signal radiated from antenna.

7. If any defects are noted replace affected part.

8. Re-install Survival ELT.

Rev 3 04 March 2014

DC-9TASK CARD

TC-33

AIRLINE CARD NO.N/A

TITLEFirst Aid Kit Inventory


DATE TASKGVI

RELATED CARD


VERSION1

THRESHOLDN/A

REPEAT12 MO


ALLSTATION SKILL


ATA CHAPTER25


ZONE

6


References:

1. EAC GMM Chapter 5 & 8

2. 14 CFR Part 91.513


Rev 3 04 March 2014

DC-9TASK CARD

TC-34

AIRLINE CARD NO.N/A

TITLEFirst Aid Kit Inventory


DATE TASKGVI

RELATED CARD


VERSION1

THRESHOLDN/A

REPEAT12 MO


ALLSTATION SKILL


ATA CHAPTER25


ZONE

6

Procedure


MECH

1. Remove First Aid Kit from aircraft.

2. Discard seal and open First Aid Kit.

3. Inventory First Aid Kit paying special attention to expiration Dates.

4. Replace any item that will expire before next inspection.

5. Re-inventory First Aid Kit IAW EAC GMM 8.6.1.

6. Fill out Emergency Equipment Tag IAW EAC GMM 5.15

7. Close First Aid Kit and replace seal.

8. Re-install First Aid Kit.

Rev 3 04 March 2014

DC-9TASK CARD

TC-35

AIRLINE CARD NO.N/A

TITLEDFDR


DATE TASKOPC

RELATED CARD


THRESHOLD1C

REPEAT1C


ALLSTATION SKILL


ATA CHAPTER31

ACCESSAFT PRESSURE BULKHEAD (ACCESS DOOR 5817D)

ZONE

44, 45


Ref - DC-9 AMM, STC# ST89CH

Procedure1. Open aft pressure bulkhead (access door 5817D).

2. Remove Flight Data Recorder

WARNING: TAG AND USE SAFETY CLIPS TO SAFETY THE CIRCUIT BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFE TIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

A. Open and tag the following circuit breaker:

Circuit BreakerPanel LocationPanel Area

Flight Recorder (2)Upper EPCLeft Radio Bus.

B. Unscrew knurled hold down nuts at front end of mounting rack and swing hold down assemblies down.

C. Turn driver/extractor handle counterclockwise until flight data recorder electrical connector is disen-gaged from mounting rack support.

D. Remove flight data recorder.


Date Emp # Mech

Date Emp # Insp

Date Emp # Mech

Date Emp # Insp

Rev 3 04 March 2014

DC-9TASK CARD

TC-36

AIRLINE CARD NO.N/A

TITLEDFDR


DATE TASKOPC

RELATED CARD


THRESHOLD1C

REPEAT1C


ALLSTATION SKILL


ATA CHAPTER31


ZONE

44, 45

3. Send the DFDR to the shop for a function check for correct recording of the required aircraft parameters.

4. Install flight data recorder.

A. Visually check flight data recorder and rack connectors for loose, dirty, or broken pins and wires.

B. Slide flight data recorder into rack; ensure that guide pin bushings and connectors are properly aligned.

C. With front panel bottom edge of flight data recorder seated in extractor slot, turn driver/extractor han-dle clockwise until recorder is firmly engaged in rack.

D. Engage and tighten hold down assemblies.

E. Remove tags and close circuit breakers opened in step 2.A.

5. Do an operation check of the DFDR IAW DC-9 AMM.

A. Check that FLT RECORDER OFF light on annunciator panel comes ON>

B. Place flight recorder switch in GND TEST position. Check that FLT RECORDER OFF light goes OFF.

C. Place flight recorder switch in NORM position. Check that FLT RECORDER OFF light comes ON>


Date Emp # Mech

Date Emp # Insp

Date Emp # Mech

Date Emp # Insp

Date Emp # Mech

Date Emp # Insp

Rev 3 04 March 2014

DC-9TASK CARD

TC-37

AIRLINE CARD NO.N/A

TITLEDFDR


DATE TASKOPC

RELATED CARD


THRESHOLD1C

REPEAT1C


ALLSTATION SKILL


ATA CHAPTER31


ZONE

44, 45

General Section6. Close aft pressure bulkhead (access door 5817D).

***END OF WORK STEPS / NO FURTHER SIGNOFFS REQUIRED***


Date Emp # Mech

Date Emp # Insp

Rev 3 04 March 2014

DC-9TASK CARD

TC-38


Rev 3 04 March 2014

DC-9TASK CARD

TC-39

AIRLINE CARD NO.N/A

TITLEFlight Data Recorder ULB Battery


DATE TASKDIS

RELATED CARD


VERSION1

THRESHOLDN/A

REPEAT6 year


ALLSTATION SKILL BODY STATION STRINGER

ATA CHAPTER31

ACCESS ZONE

57


Ref - DC-9 AMM, F1000 DFDR CMM

Procedure1. Open aft pressure bulkhead (access door 5817D).

2. Open, safety and tag the circuit breakers that follow

Circuit BreakerPanel Location

F21 Cockpit Flight RecorderUEPC CBP

F22 Cockpit Flight RecorderUEPC CBP

3. Perform functional test on locator beacon.

4. Remove the underwater locator battery/beacon battery.

5. Install serviceable ULB battery.

A. Perform a return to service test for the flight data recorder ULB IAW DC-9 AMM.

6. Close access door 5817D.

7. Close circuit breaker listed in Step 2.



Date Emp # Mech

Date Emp # Insp

Rev 3 04 March 2014

DC-9TASK CARD

TC-40


Rev 3 04 March 2014

DC-9TASK CARD

TC-41

AIRLINE CARD NO.N/A

TITLETest of Main Landing Gear Backup Position

Indicating System


DATE TASK RELATED CARD


THRESHOLDN/A

REPEAT1500 Flight

Cycles


STATION SKILLMechanic

BODY STATION STRINGER

ATA CHAPTER32

ACCESS ZONE

04/003 05/005 05/006

Test Landing Gear Position and Warning Indication System

1. Test Position and Warning System

A. Raise airplane 22 inches minimum above ground level on wing and fuselage jacks by measuring amount of jack extension (per AMM Chapter 7).

NOTE: This will provide about 5 inches between tire and ground, with struts fully extended, for main gear inboard door operational clearances.

B. Pressurize right hydraulic power system per AMM Chapter 29.

C. Remove landing gear down lock pins and main gear inboard doorkeepers.

D. Advance throttle levers 1-1/4 inch forward of idle stop position.

E. Do the following:

i. Verify all landing gears are down and locked.

(ii) Verify landing gear control lever is in down detent position.

(iii) Verify three green landing gear safe (LDG GEAR) lights above the instrument panels are on.

(iv) Turn on MAIN GEAR DOWN LOCK switch on first officer's instrument panel. Verify both MAIN GEAR DOWN LOCK lights (above switch) come on.

F. Verify flaps are at full up position.

WARNING: CLEAR AREA AROUND GEARS BEFORE MOVING GEARS TO AVOID INJURING WORKERS AND DAMAGING EQUIPMENT OR AIRCRAFT.


Rev 3 04 March 2014

DC-9TASK CARD

TC-42

AIRLINE CARD NO.N/A


Indicating System




THRESHOLDN/A

REPEAT1500 Flight

Cycles




ATA CHAPTER32

ACCESS ZONE

04/003 05/005 05/006

G. Do the following:

i. Place landing gear control lever in full up position.

(ii) As landing gear control lever leaves down detent position, verify green landing gear safe (LDG GEAR) lights go out and three red landing gear unsafe (GEAR UNSAFE) lights (also above the instrument panels) come on. (Warning horn should not sound.)

(iii) Verify both MAIN GEAR DOWN LOCK lights go out as landing gear control lever leaves down detent position.

H. When each gear reaches up and latched position, verify its related red landing gear unsafe (GEAR UNSAFE) light goes out. Verify also both MAIN GEAR DOWN LOCK lights stay out. Verify green landing gear safe (LDG GEAR) lights do not come back on when all gears are at up and latched posi-tions. Verify warning horn stays silent.

I. Do the following:

i. Place landing gear control lever in gear down position.

(ii) Verify red landing gear unsafe (GEAR UNSAFE) lights come on as gears move down from up and latched position. Verify red landing gear unsafe (GEAR UNSAFE) lights stay on until all three landing gears are down and locked. When all three landing gears are down and locked, verify red landing gear unsafe (GEAR UNSAFE) lights go out and green landing gear safe (LDG FEAR) lights come on. (Warning horn should not sound.)

(iii) Verify MAIN GEAR DOWN LOCK lights come on when all three landing gears are down and locked.


Rev 3 04 March 2014

DC-9TASK CARD

TC-43

AIRLINE CARD NO.N/A


Indicating System




THRESHOLDN/A

REPEAT1500 Flight

Cycles




ATA CHAPTER32

ACCESS ZONE

04/003 05/005 05/006

(iv) Turn off MAIN GEAR DOWN LOCK switch.

WARNING: CLEAR AREA AROUND DOORS BEFORE MOVING DOORS TO AVOID INJURING WORKERS AND DAMAGING EQUIPMENT OR AIRCRAFT.

Mechanic _______________________ Date __________

Inspector _______________________ Date __________


Rev 3 04 March 2014

DC-9TASK CARD

TC-44


Rev 3 04 March 2014

DC-9TASK CARD

TC-45

AIRLINE CARD NO.N/A

TITLERVSM ICA


DATE TASKINS

RELATED CARD34-08EAC, 34-02EAC, 34-03EAC


VERSION1

THRESHOLDN/A

REPEAT24 MO


ALLSTATION SKILL

See belowBODY STATION STRINGER

ATA CHAPTER34

ACCESSNONE

ZONE

NONE


Skills required: Mechanic, Avionics, Inspector, RII

References:

1. STC# ST01136LA. Page 6, 1.4.2 24 month maintenance requirements for continued airworthiness.

2. STC# ST01136LA Page 14, 2.1.3.1 Option 1. (Primary method)

3. STC# ST01136LA Page 17, Option 2. (Secondary method, used when option 1 fails inspection)

4. Note: If the aircraft fails this RVSM inspection it may be dispatched as Non-RVSM compliant IAW the DC-9 MEL procedures.


Rev 3 04 March 2014

DC-9TASK CARD

TC-46

AIRLINE CARD NO.N/A

TITLERVSM ICA


DATE TASKINS



VERSION1

THRESHOLDN/A

REPEAT24 MO


ALLSTATION SKILL

See belowBODY STATION STRINGER

ATA CHAPTER34

ACCESSNONE

ZONE

NONE

Procedure


NOTE: All related task cards may be accomplished concurrently. MECH INSP

1. Verify that all of the avionics components listed in table 1 (section 1.3 of STC# ST01136LA) are installed and operational.

2. Conduct an air data system, altitude alert, and transponder ground check using cal-ibrated ground test equipment. Verify the air data system errors are within specified RVSM tolerance. Confirm appropriate accuracy of the altitude alerter and transpon-ders. (Section 2.1.1 of STC# ST01136LA)

3. Mark the RVSM Critical Region and conduct a visual inspection of the skin surface and static plates. (Section 2.1.2 of STC# ST01136LA)

4. An Inspection of the static plate and surrounding skin contour (SP/SC) is required. This inspection may be conducted per the instructions provided in the l SRM and AMM IAW (Option 1)with the special provisions or an alternate method (Option 2) for checking the (SP/SC) per AeroMech documents AMI-TPDC9-002 (DC-9-30 series airframe) latest revision is also acceptable for RVSM compliance (Section 2.1.3 of STC# ST01136LA)

5. Verify the corner markings identifying the RVSM Critical Region are discernible and in good condition. If necessary rework and/or replace those markings.

6. Sign off M-13 as required.

Rev 3 04 March 2014

DC-9TASK CARD

TC-47

AIRLINE CARD NO.N/A

TITLERVSM ICA In-Flight


DATE TASKINS



VERSION1

THRESHOLDN/A

REPEAT24 MO


ALLSTATION SKILL


ATA CHAPTER34

ACCESSNONE

ZONE

NONE


References:

1. STC# ST01136LA. Page 6, 1.4.2, 24 month maintenance requirements for continued airworthiness.

2. Note: If the aircraft fails this RVSM inspection, it may be dispatched as "Non-RVSM" compliant IAW the DC-9 MEL procedures.

3. 24 month Autopilot (altitude hold) Performance Test IAW STC# ST01136LA Page 20 section 2.1.4


Rev 3 04 March 2014

DC-9TASK CARD

TC-48

AIRLINE CARD NO.N/A



DATE TASKINS



VERSION1

THRESHOLDN/A

REPEAT24 MO


ALLSTATION SKILL


ATA CHAPTER34

ACCESSNONE

ZONE

NONE

ProcedureNOTE: All related task cards may be accomplished concurrently.


24 month Autopilot (altitude hold) Performance Test Procedure

(Steps 1-3 may be accomplished by Flight Crew)

MECH / FLIGHT CREW

1. During normal cruise flight at an altitude between FL 270 and FL 350 (Baro 29.92 in Hg or 1013.21mb)

2. Activate altitude hold on the auto pilot panel. Allow the aircraft to stabilize on the selected altitude. The air must be stable (no turbulence) during this check. Maintain flight level and cruise Mach number.

3. With the aircraft in the normal (cruise) mode and altitude hold engaged, record the data from the primary displays (using form attached) every minute for a minimum flight segment of 20 minutes. The maximum altitude deviation shown on the display should not exceed +/-70 feet.

4. Return this completed form to the Maintenance Supervisor for completion of the M-13 form.

Rev 3 04 March 2014

DC-9TASK CARD

TC-49

AIRLINE CARD NO.N/A



DATE TASKINS



VERSION1

THRESHOLDN/A

REPEAT24 MO


ALLSTATION SKILL


ATA CHAPTER34

ACCESSNONE

ZONE

NONE

REMOVE THIS SHEET AND FILE WITH AIRCRAFT RECORDS

RVSM AUTOPILOT PEFORMANCE CHECK TABLE CRUISE CONDITIONS

AIRCRAFT________________________ DATE__________________

DESTINATION_____________________ PILOT__________________FLEET EFFECTIVITY PAGE 3 OF 3

17-APR-2012

TIME PILOT’S COPILOT’S PILOT’S COPILOT’S PILOT’S COPILOT’SMINUTES ALTIMETER ALTIMETER MACH MACH KIAS KIAS

123456789

1011121314151617181920

Rev 3 04 March 2014

DC-9TASK CARD

TC-50


Rev 3 04 March 2014

DC-9TASK CARD

TC-51

AIRLINE CARD NO.N/A

TITLEAltimeter Bienial


DATE TASKIN



VERSION1

THRESHOLDN/A

REPEAT24 MO


ALLSTATION SKILL


ATA CHAPTER34


ZONE

NONE

General SectionEquipment and Materials - Pitot Static Test Set

References:

1. STC No: ST01136LA

2. 14 CFR 91.411

3. 14 CRF 43 Appendix E

4. DC-9 MM 34-10


Rev 3 04 March 2014

DC-9TASK CARD

TC-52

AIRLINE CARD NO.N/A

TITLEAltimeter Bienial


DATE TASKIN



VERSION1

THRESHOLDN/A

REPEAT24 MO


ALLSTATION SKILL


ATA CHAPTER34


ZONE

NONE

Procedure


NOTE: 24 month Autopilot (altitude hold) Performance Test Procedure MECH

1. Verify that all of the avionics components listed in table 1 (STC# ST01136LA section 1.3) are installed and operational.

2. Verify that the circuit breakers for Pitot Static Heat have been Pulled IAW DC-9MM 34-10.

3. Perform Altimeter Test with calibrated test equipment IAW 14 CFR 91.411 and Appendix E of Part 43.

4. In addition to requirements listed in step three (3). The Altimeter must meet the accuracy tolerances shown in Table 2 of (RVSM) STC# ST01136LA

5. Record all findings in Table 2 of STC# ST01136LA to be attached to completed M-13.

6. Restore aircraft to normal

Rev 3 04 March 2014

DC-9TASK CARD

TC-53

AIRLINE CARD NO.N/A

TITLERVSM HEIGHT KEEPING PERFORMANCE

MONITORING


DATE TASKINS



VERSION1

THRESHOLDN/A

REPEAT24 MO (READ INFO BELOW)


STATION SKILLSee Below


ATA CHAPTER34

ACCESSNONE

ZONE

NONE

GeneralEverts Air Cargo will conduct Height Keeping Performance Monitoring within 6 months of issuance of U.S. RVSM Authorization. In addition, Everts Air Cargo will conduct monitoring every 2 years or within intervals of 1000 flight hours per aircraft, whichever period is longer, in accordance with the aircraft categories as pre-sented in the current version of the (North American) RVSM Minimum Monitoring Requirements Chart.

The RVSM Minimum Monitoring Requirements Chart is coordinated with the North American Approvals Reg-istry and Monitoring Organization (NAARMO) and updated periodically to reflect changes in aircraft data. The RVSM Minimum Monitoring Requirements Chart is posted to the FAA RVSM webpage in the documentation section "Monitoring Requirements/Procedures." If Everts Air Cargo adds new RVSM compliant airframes of a type for which is already has RVSM operational approval, and has completed monitoring requirements for the type in accordance with the statements above, the new airframes will not require initial (6 month) monitoring, but will be monitored periodically as outlined above.

NOTE: EAC IS REQUIRED TO MONITOR 60% OF THE DC-9 FLEET.

Compliance Methods/Height Keeping Performance Monitoring Options:

1. Portable GPS-based Monitoring Unit (GMU)

2. Ground based Height Monitoring Unit (HMU)

3. Domestic U.S. RVSM ground-based monitoring system the AGHME (Aircraft Geometric Height Mea-surement Element)

The Director of Maintenance of the Director of Operations will select 1 of the 3 options for monitoring.

References:

RVSM Documentation:

http://www.faa.gov/about/office_org/headquarters_offices/ato/service_unis/enroute/rvsm/documentation/#req

FLEET EFFECTIVITY PAGE 1 OF 101-FEB-2012

Rev 3 04 March 2014

DC-9TASK CARD

TC-54


Rev 3 04 March 2014

DC-9TASK CARD

TC-55

AIRLINE CARD NO.N/A

TITLEMode-S Transponder Antenna Removal and Testing




THRESHOLDN/A

REPEAT1675 Flight

Cycles


STATION SKILL BODY STATION STRINGER

ATA CHAPTER34

ACCESS ZONE

Procedure1. Remove Mode-S Transponder Antenna

A. Deenergize and collar transponder ATC-1, AC and DC circuit breakers.

B. Gain access to main entry area aft of cockpit entry door (sta.190). Remove ceiling panel, disconnect and stow Mode-S antenna coaxial lead.

C. Gain access to Mode-S antenna using approved methods (manlift/stands) at top of fuselage station 190, remove antenna fasteners and gently lift up on antenna using standard practices. Tag and store antenna for later reinstallation. Clean sealant residue prior to inspection.

NOTE: Nondestructive testing of the Mode-S antenna can be accomplished through high frequency eddy cur-rent or x-ray testing.

2. High Frequency Eddy Current Testing (Preferred Method)

NOTE: High frequency eddy current equipment Nortec 24, 5/32 bolt hole probe, A07175-1 standard is required to perform this task. Equivalent substitutes for all listed equipment may be used.

CAUTION: ENSURE AIRCRAFT IS ELECTRICALLY GROUNDED.

A. Perform eddy current (bolt hole) inspection of mode-s antenna mount holes as follows:

i. Calibrate the instrument per specifications using the A07175-1 standard. Null instrument in stan-dard where EDM notch does not exist. Scan standard again at EDN notch and note proper indica-tion (CRT trace spike).

(ii) Clean antenna mount holes of dirt and debris prior to inspection.


Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-56

AIRLINE CARD NO.N/A





THRESHOLDN/A

REPEAT1675 Flight

Cycles



ATA CHAPTER34

ACCESS ZONE

(iii) Carefully scan the antenna mount holes while closely monitoring the CRT display for crack indica-tions. Ensure all doubler layers are individually scanned for defects. Each hole will have (3) three layers to inspect, skin, finger doubler, and tripler. If no defects are noted, N/A steps E & F and pro-ceed with step B..

(iv) Perform a post inspection test of calibration to validate inspection regardless of results.

(v) If cracks are found in the skin, generate a non-routine for repair accomplishment.

B. Ensure all sign offs are completed. Proceed to Step 4.

3. X-Ray Testing (Alternate Method)

NOTE: The following equipment is required for this task; SPX 160 x-ray system. Two each double load x-ray film (14X17 AGFA D-7/D-4 equal to 100-80 ASA), a lead number/ID set, and masking tape. Equivalent items may be substituted for any of the listed requirements.

A. Prepare x-ray identification tags for the Mode-S transponder antenna at F.S. 190 S-1 with the follow-ing information:

i. Aircraft registration number.

(ii) Antenna cutout type (Mode-S)


Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-57

AIRLINE CARD NO.N/A





THRESHOLDN/A

REPEAT1675 Flight

Cycles



ATA CHAPTER34

ACCESS ZONE

(iii) Date of inspection.

B. Attach x-ray ID tag to film edge.

WARNING: THE USE OF RADIATION IN NDT TESTING PRESENTS POTENTIAL HAZARDS TO ALL PERSONNEL IN THE AREA. OBSERVE ALL RADIATION SAFETY REQUIREMENTS WHEN OPERATING X-RAY EQUIPMENT.

WARNING: USE OF APPROPRIATE RIGGING, PLATFORMS AND/OR MANLIFT IN ORDER TO POSITION THE FILM AND HOLD THE PORTABLE TUBE HEAD IN PLACE.

WARNING: TO AVOID INJURY TO PERSONNEL OR DAMAGE TO EQUIPMENT, MAKE CERTAIN ADEQUATE PRECAUTIONS ARE TAKEN WHILE PERFORMING ANY WORK IF ELEC-TRICAL POWER IS APPLIED TO THE AIRCRAFT.

CAUTION: ENSURE AIRCRAFT IS ELECTRICALLY GROUNDED.

C. Perform x-ray of Mode-S transponder antenna cutout as follows:

i. Gain access to outside of aircraft, position film packet centered over the antenna cutout perpen-dicular to the sighting of the x-ray source.

(ii) Place the x-ray source inside the aircraft at a distance of 72 inches perpendicular to the x-ray film package.

(iii) Expose the film using the following technique:

KV - 130MA - 5.0Distance - 72"Time - 0.9 minutes

(iv) Process and read film. Pay close attention for crack propagation around fasteners attaching the finger doubler and tripler to the skin. Also, pay close attention for crack propagation around the antenna connector hole. If no cracks are noted, N/A steps E & F and proceed to step 04.


Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-58

AIRLINE CARD NO.N/A





THRESHOLDN/A

REPEAT1675 Flight

Cycles



ATA CHAPTER34

ACCESS ZONE

(v) If cracks are found in the finger doubler or tripler, generate a non routine to replace the doubler in question.

(vi) If cracks are found in skin, generate a non-routine to accomplish the repair.

D. Ensure all job card sign offs are completed.

4. Reinstall Mode-S Antenna

A. Reinstall mode-S antenna at conclusion of NDT with PR1422 sealant and required hardware. Be sure to keep sealant from coaxial connector surface. Cover mating surfaces evenly using moderation. Once installed clean excess from work area.

B. At station 190 inside aircraft reinstall mode-S coaxial cable, and access panel removed in step 01 B.

C. Reset transponder circuit breakers pulled in step 1 and perform a self test of transponder system Mode-S, per MM 34-53-00-5.

D. Ensure all job card sign offs are completed.


Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-59

AIRLINE CARD NO.N/A





THRESHOLDN/A

REPEAT1675 Flight

Cycles



ATA CHAPTER34

ACCESS ZONE



Rev 3 04 March 2014

DC-9TASK CARD

TC-60


Rev 3 04 March 2014

DC-9TASK CARD

TC-61

AIRLINE CARD NO.N/A

TITLETransponder STC 01136LA 24 month


DATE TASKIN

RELATED CARD34-054-01-01


VERSION1

THRESHOLDN/A

REPEAT24 MO


ALLSTATION SKILL


ATA CHAPTER34


ZONE

General SectionEquipment and Materials - Pitot Static Test Set

References:

1. STC No: ST01136LA

2. 14 CFR 91.413

3. 14 CFR 43 Appendix F

4. DC-9 MM 34-42


Rev 3 04 March 2014

DC-9TASK CARD

TC-62

AIRLINE CARD NO.N/A

TITLETransponder STC 01136LA 24 month


DATE TASKIN

RELATED CARD34-054-01-01


VERSION1

THRESHOLDN/A

REPEAT24 MO


ALLSTATION SKILL


ATA CHAPTER34


ZONE

Procedure


NOTE: All related task cards may be accomplished concurrently. MECH

1. Verify that all of the avionics components listed in table 1 (STC# ST01136LA section 1.3) are installed and operational.

2. Verify that the circuit breakers for Pitot Static Heat have been Pulled IAW DC-9MM 34-10.

3. Perform Transponder Test with calibrated test equipment IAW 14 CFR 91.413 and Appendix F of Part 43.

4. In addition to requirements listed in step three (3). The transponder should report an altitude within plus or minus 100 Feet (+/- 100 ft) of Transponder Test Equipment IAW (RVSM) STC# ST01136LA section 2.1.1.

5. Record all findings in Table 2 of STC# ST01136LA to be attached to completed M-13.

6. Restore aircraft to normal

Rev 3 04 March 2014

DC-9TASK CARD

TC-63

AIRLINE CARD NO.N/A

TITLECrew and Courier Oxygen Cylinder Hydrostatic Test


DATE TASKIN

RELATED CARD


THRESHOLD1A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER35


ZONE

General SectionEquipment and Materials - Crew Oxygen Cylinder Hydrostatic Test

References:

1. DC-9 Aircraft Maintenance Manual 12-70-0


NOTE: DOT 3HT requires a hydrostatic test every 3 years and has a limited service life of 24 years from date of manufacture. DOT 3AA cylinders require a hydrostatic test every 10 years. 3AA has an unlimited service life as set forth in 49 CFR Part 180.209.


Rev 3 04 March 2014

DC-9TASK CARD

TC-64

AIRLINE CARD NO.N/A

TITLECrew and Courier Oxygen Cylinder Hydrostatic Test


DATE TASKIN

RELATED CARD


THRESHOLD1A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER35


ZONE

Procedure

NOTE: If parts are not available, notify maintenance supervisor to schedule replacement prior to expiration date.

NOTE: The date of the test is considered to be, the last day of the month stamped on the cylinder.

Example of Requalification Markings

Where:

"9" is the month of requalification

"A123" is the RIN (approval number)

"06" is the year of requalification, and

"X" represents the symbols described in CFR Title 49 § 180.213 paragraphs (f)(2) through (f)(8). A five-

point star (j) for 10-year volumetric expansion test for cylinders.


MECH

1. Check last test date of the Crew oxygen cylinder. Replace the oxygen bottle AMM 35-10-0 if due within 20 days.

2. Check last test date of the Courier oxygen cylinder. Replace bottle if due within 120 days.

A1

9 06 X

32

Rev 3 04 March 2014

DC-9TASK CARD

TC-65

AIRLINE CARD NO.N/A

TITLEPortable Oxygen Cylinder Hydrostatic Test


DATE TASKIN

RELATED CARD


THRESHOLD1A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER35


ZONE

General SectionEquipment and Materials - Crew Oxygen Cylinder Hydrostatic Test

References:



NOTE: DOT 3HT requires a hydrostatic test every 3 years and has a limited service life of 24 years from date of manufacture. DOT 3AA cylinders require a hydrostatic test every 10 years. 3AA has an unlimited service life as set forth in 49 CFR Part 180.209.


Rev 3 04 March 2014

DC-9TASK CARD

TC-66

AIRLINE CARD NO.N/A

TITLEPortable Oxygen Cylinder Hydrostatic Test


DATE TASKIN

RELATED CARD


THRESHOLD1A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER35


ZONE

Procedure

NOTE: If parts are not available, notify maintenance supervisor to schedule replacement prior to expiration date.

NOTE: The date of the test is considered to be the last day of the month stamped on the cylinder.

Example of Requalification Markings

Where:

"9" is the month of requalification

"A123" is the RIN (approval number)

"06" is the year of requalification, and

"X" represents the symbols described in CFR Title 49 § 180.213 paragraphs (f)(2) through (f)(8). A five-

point star (j) for 10-year volumetric expansion test for cylinders.


MECH

1. Check last test date of the oxygen cylinder. Replace the oxygen bottle AMM 35-30-0 if due within 120 days.

A1

9 06 X

32

Rev 3 04 March 2014

DC-9TASK CARD

TC-67

AIRLINE CARD NO.N/A

TITLERestore PBE


DATE TASKIN

RELATED CARD


VERSION1

THRESHOLDN/A

REPEAT10 year

or


ALLSTATION SKILL

MechanicManufacturer Recommendations BODY STATION STRINGER

ATA CHAPTER35


ZONE

6


References:

1. EAC GMM Chapter 8 & 12

2. PBE Manufacturer’s Manuals


Rev 3 04 March 2014

DC-9TASK CARD

TC-68

AIRLINE CARD NO.N/A

TITLERestore PBE


DATE TASKIN

RELATED CARD


VERSION1

THRESHOLDN/A

REPEAT10 year

or


ALLSTATION SKILL

MechanicManufacturer Recommendations BODY STATION STRINGER

ATA CHAPTER35


ZONE

6

Procedure


MECH

1. Remove PBE.

2. Send PBE to manufacture for inspection or overhaul.

3. Install Yellow Tagged (M-29Y) PBE with completed White Tag IAW GMM 5.15

Rev 3 04 March 2014

DC-9TASK CARD

TC-69

AIRLINE CARD NON/A

TITLE

Aircraft Wet Wash and Interior Cleaning



TAIL NUMBER WORK AREA VERSION TRESHOLD1 N/A

REPEAT APPLICABILITYAIRPLANE ENGINES


ATA CHAPTER51

ACCESS ZONE

Procedure:1. Prepare aircraft for wash.

NOTE: N/A areas not being washed.A. Remove aircraft library and give to the records department.B. Lower flaps and slats (as required).C. Open MLG inboard doors (as required).D. Open NLG doors (as required).E. Deploy thrust reversers (as required).F. Ensure all heated probes, ports, and surfaces are off and switches tagged. Even if electrical power is

not on the aircraft, switch position must be verified by a mechanic.G. Ensure all pitot tubes and static port covers are masked or taped or fitted with protective covers as

required in accordance with the AMM. Logbook entry is required.

Date Emp # Mech

Position maintenance stands and equipment to access wash areas.

Date Emp # Mech

WARNING: DO NOT WORK ON TOP OF FUSELAGE WITHOUT A SAFETY HARNESS. EXERCISE EXTREME CARE WHEN STANDING ON ANY AIRCRAFT SURFACE. AVOID FIBERGLASS PANELS AND ALL “NO STEP” AREAS. SEE SUPERVISOR IF YOU HAVE ANY QUESTIONS.

CAUTION: Observe all safety precautions when using special tools and ground equipment such as man lifts, ladders, etc. The proper use of personal safety equipment, safety harnesses, safety shoes, etc. is required.

CAUTION: Do not apply cleaning compound to control cables, or direct high pressure streams of water at control cables, electrical wires, connectors, transmitters, switches, or other sensitive equipment or appliances.

NOTE: Do not saturate insulation (if installed) with cleaning solution or water.

NOTE: Agitate cleaning compound using soft bristle brush.

FLEET EFFECTIVITY PAGE 1 OF 404-OCT-2010

Rev 3 04 March 2014

DC-9TASK CARD

TC-70

2. Using approved aircraft cleaner, thoroughly clean wheel wells, doors, MLG, and NLG. Rinse with large vol-umes of water. Remove all traces of cleaning compound by wiping with clean rags if necessary.

3. Using approved aircraft cleaner, thoroughly clean underside (belly) of aircraft and fuselage. Rinse with large volumes of water. Remove all traces of cleaning compound by wiping with clean rags if necessary.

4. Using approved aircraft cleaner, thoroughly clean tail including vertical and horizontal stabilizers. Rinse with large volumes of water. Remove all traces of cleaning compound by wiping with clean rags if necessary.

5. Using approved aircraft cleaner, thoroughly clean left and right wings including aft spars and hydraulic com-ponents. Rinse with large volumes of water. Remove all traces of cleaning compound by wiping with clean rags if necessary.

6. Using approved aircraft cleaner, thoroughly clean left and right engine cowlings and pylons. Rinse with large volumes of water. Remove all traces of cleaning compound by wiping with clean rags if necessary.

CAUTION: Do not spray water directly into engine intake or exhaust.

Date Emp # Mech

7. Perform a general visual inspection of the nose/ left and right MLG and wheel wells for quality of wash and for any new damage or discrepancies.

8. Perform a general visual inspection of the left and right wings for quality of wash and for any new damage or discrepancies.

9. Perform a general visual inspection of the aircraft fuselage for quality of wash and for any new damage or discrepancies.

10. Perform a general visual inspection of the engine cowlings and pylons for quality of wash and for any new damage or discrepancies.

11. Perform a general visual inspection of the tail section including vertical and horizontal stabilizers for quality of wash and for any new damage or discrepancies.

Date Emp # Mech

12. Remove all Pitot tube and static port covers or tape which were masked or fitted with protective covers or tape. Clear log book item stating that all Pitot tube and probe covers and masking have been removed.

Date Emp # Mech


AIRLINE CARD NON/A

TITLE







ATA CHAPTER51

ACCESS ZONE

Rev 3 04 March 2014

DC-9TASK CARD

TC-71

13. Ensure all heated probes, ports, and surfaces which were turned off and switches tagged are returned to the required configuration and all tags removed.

Date Emp # Mech

14. Return aircraft to normal configuration:A. Close MLG inboard doors (as required).B. Close NLG doors (as required).C. Raise flaps and slats (as required).

Date Emp # Mech

15. Clean the aircraft interior.A. Clean the cockpit.

(1) Remove all trash from floor area.(2) Empty trash bags.(3) Vacuum or sweep floor area.(4) Feather-dust all instrument areas, using caution not to move any switches.(5) Vacuum or sweep all seats and wipe down with damp rag (use Ivory soap on soiled spots on pilot

and co-pilot seats only).(6) Wipe down seat belts and shoulder harnesses with a damp rag (use Ivory soap on all soiled spots in

all positions).(7) Damp mop or wipe floor.

Date Emp # Mech

B. Clean the main entry way.(1) Vacuum or sweep floor area.(2) Wipe down all walls with damp rag and cleaner.(3) Damp mop or wipe floor.

Date Emp # Mech


AIRLINE CARD NON/A

TITLE







ATA CHAPTER51

ACCESS ZONE

Rev 3 04 March 2014

DC-9TASK CARD

TC-72

C. Clean main cargo area.(1) Vacuum or sweep area including tracks and shackle boxes.(2) Spot clean walls with a damp rag and cleaner, checking for scuff marks.(3) Reapply gill liner tape in areas of missing or loose tape.(4) Damp mop or wipe floor areas in fwd and aft doorway diamond plate

Date Emp # Mech

D. Clean lower cargo area.(1) Remove all trash and debris.(2) Vacuum or sweep floors including tracks.(3) Reapply gill liner tape in areas of missing or loose tape (if applicable).

Date Emp # Mech

E. Install Aircraft library

Date Emp # Mech

______________________________________________________________________________________



AIRLINE CARD NON/A

TITLE







ATA CHAPTER51

ACCESS ZONE

Rev 3 04 March 2014

DC-9TASK CARD

TC-73

AIRLINE CARD NO.N/A

TITLEVent Door Inspection and Lube


DATE TASKINS/LUBE

RELATED CARD


VERSION1

THRESHOLDN/A

REPEATA1


ALL



ATA CHAPTER52

ACCESS ZONE

References:

Tech Air Corporation McDonnell Douglas DC-9 Vent Door Maintenance Manual

Procedure:

01. Check condition of vent door seal, operating and locking mechanism.

02. Remove control cables at upper and lower rod end attachment, push and pull each cable by hand to check for bind-ing.

03. Lubricate

A. Any exposed surface or surfaces to be lubricated must be thoroughly cleaned to be sure previously applied lubricants, and accumulated foreign matter are removed before clean lubricants are applied.


Rev 3 04 March 2014

DC-9TASK CARD

TC-74

AIRLINE CARD NO.N/A



DATE TASKINS/LUBE

RELATED CARD


VERSION1

THRESHOLDN/A

REPEATA1


ALL



ATA CHAPTER52

ACCESS ZONE

Cleaning solvents should not be used on control cables. There is a possibility of washing away or diluting the lubricant in these sealed cables. Steam cleaning is not recommended for the same reason. It is recommended that lubrication be performed after other work on the aircraft has been accomplished. This practice will help control dirt, water, and cleaning solvents.

B. Work moving parts to assure thorough lubrication.

C. After lubrication, clean excess lubricant from all but working surfaces.

D. Lubricate rod ends, all bushings and bolts at pivot points, control cables, and hinge points with Oil General Purpose (OGP) MIL-L-7870.


Rev 3 04 March 2014

DC-9TASK CARD

TC-75

AIRLINE CARD NO.N/A



DATE TASKINS/LUBE

RELATED CARD


VERSION1

THRESHOLDN/A

REPEATA1


ALL



ATA CHAPTER52

ACCESS ZONE

04. Perform functional test.

A. With cargo door locked, close vent door and check.

(1) Full engagement of vent door latches.

(2) Full down and locked position of torque tube lock.

WARNING: DO NOT ROTATE “T” HANDLE WHILE PERFORMING THIS TEST. DAMAGE MAY OCCUR.

(3) Lock Pin Walking Beam / Torque Tube Lock (Key Block) NAVD-9-05-10, will not allow walking beam to move. Pull up (DO NOT ROTATE) on cargo door control “T” handle, lock pins should not unlock. If lock pin walking beam unlocks or moves more than 1/8 inch, stop on walking beam must be adjusted.

Date Emp# Mech



Rev 3 04 March 2014

DC-9TASK CARD

TC-76


Rev 3 04 March 2014

DC-9TASK CARD

TC-77

AIRLINE CARD NO.N/A

TITLEMain Cargo Door Lubrication


DATE TASKLUBE

RELATED CARD


THRESHOLDN/A

REPEATA1


ALL



ATA CHAPTER52

ACCESS ZONE

References:

DC-9 Aircraft Maintenance Manual 12-65-0

EAC DC-9 AMM 53-32-00-4

Procedure:

01. Lubricate

A. Any exposed surface or surfaces to be lubricated must be thoroughly cleaned to be sure previously applied lubricants and accumulated foreign matter are removed before clean lubricants are applied. Cleaning solvents should not be used on control cables. There is a possibility of washing away or dilut-ing the lubricant in these sealed cables. Steam cleaning is not recommended for the same reason. It is recommended that lubrication be performed after other work on the aircraft has been accomplished. This practice will help control dirt, water, and cleaning solvents.


Rev 3 04 March 2014

DC-9TASK CARD

TC-78

AIRLINE CARD NO.N/A



DATE TASKLUBE

RELATED CARD


THRESHOLDN/A

REPEATA1


ALL



ATA CHAPTER52

ACCESS ZONE




Rev 3 04 March 2014

DC-9TASK CARD

TC-79

AIRLINE CARD NO.N/A



DATE TASKLUBE

RELATED CARD


THRESHOLDN/A

REPEATA1


ALL



ATA CHAPTER52

ACCESS ZONE

ITEM NO.

ITEM DESCRIPTION LUBE TYPE

APPLICATION NUMBER OF FITTINGS OR AREAS

1 Hook-Latch Assembly Mechanism

GMD Gun 7

2 Link-Latch Assembly Mechanism (Flush Type)

GMD Gun 14

3 Spool-Fitting Assembly Latch Mechanism Attach (Flush Type)

GMD Gun 7

4 Hook Assembly–Cargo Door Mechanism Assembly

GMD Gun 2

5 Eyebolt Assembly GMD Gun 1

6 Roller Assembly-Unlock Mechanism

GMD Gun 2


Rev 3 04 March 2014

DC-9TASK CARD

TC-80

AIRLINE CARD NO.N/A



DATE TASKLUBE

RELATED CARD


THRESHOLDN/A

REPEATA1


ALL



ATA CHAPTER52

ACCESS ZONE

7 Fitting Assembly—Actuator Mechanism Attach (Flush Type)

GMD Gun 1

8 Link Assembly—Cargo Door—Outboard

GMD Gun 4

9 Support Upper Actuator Link GMD Gun 2

*10 Torque Tube Actuator Assembly (Flush Type)

GMD Gun 3

11 Hinge-Forward Upper Cargo Door OGP Oil Can -

12 Hold Open Latch Mechanism OGP Oil Can -

GMD – Grease – Mobil 28

OGP – Oil General Purpose Corrosion Preventative – EAL 146

Frequency Interval Recommended – On Condition

* Cargo Door Latch Cylinder Idler Assembly Not Installed on A/C N904CE.


Rev 3 04 March 2014

DC-9TASK CARD

TC-81

AIRLINE CARD NO.N/A



DATE TASKLUBE

RELATED CARD


THRESHOLDN/A

REPEATA1


ALL



ATA CHAPTER52

ACCESS ZONE


Rev 3 04 March 2014

DC-9TASK CARD

TC-82

AIRLINE CARD NO.N/A



DATE TASKLUBE

RELATED CARD


THRESHOLDN/A

REPEATA1


ALL



ATA CHAPTER52

ACCESS ZONE


Rev 3 04 March 2014

DC-9TASK CARD

TC-83

AIRLINE CARD NO.N/A



DATE TASKLUBE

RELATED CARD


THRESHOLDN/A

REPEATA1


ALL



ATA CHAPTER52

ACCESS ZONE


Rev 3 04 March 2014

DC-9TASK CARD

TC-84

AIRLINE CARD NO.N/A



DATE TASKLUBE

RELATED CARD


THRESHOLDN/A

REPEATA1


ALL



ATA CHAPTER52

ACCESS ZONE

Date Emp# Mech



Rev 3 04 March 2014

DC-9TASK CARD

TC-85

AIRLINE CARD NO.N/A

TITLEVent Door Inspection


DATE TASKINS

RELATED CARD


THRESHOLDN/A

REPEATC1


ALL



ATA CHAPTER52

ACCESS ZONE

References:

Tech Air Corporation McDonnell Douglas DC-9 Vent Door Maintenance Manual

Procedure:

01. Inspect outside of door assembly and area around door assembly for cracks, loose fasteners, and buckling.

02. Inspect hinge for security.

03. Inspect inside of door assembly for loose fasteners and sign of buckling.

04. Inspect vent door mechanism operating arms for loose fasteners, condition, and proper lubrication.


Rev 3 04 March 2014

DC-9TASK CARD

TC-86

AIRLINE CARD NO.N/A



DATE TASKINS

RELATED CARD


THRESHOLDN/A

REPEATC1


ALL



ATA CHAPTER52

ACCESS ZONE

05. Inspect vent door opening mechanism for loose fasteners and condition.

06. Inspect vent door mechanism for security and condition.


Rev 3 04 March 2014

DC-9TASK CARD

TC-87

AIRLINE CARD NO.N/A



DATE TASKINS

RELATED CARD


THRESHOLDN/A

REPEATC1


ALL



ATA CHAPTER52

ACCESS ZONE

07. Inspect latch lock engagement for minimum latch engagement. See below.


Rev 3 04 March 2014

DC-9TASK CARD

TC-88

AIRLINE CARD NO.N/A



DATE TASKINS

RELATED CARD


THRESHOLDN/A

REPEATC1


ALL



ATA CHAPTER52

ACCESS ZONE


Rev 3 04 March 2014

DC-9TASK CARD

TC-89

AIRLINE CARD NO.N/A



DATE TASKINS

RELATED CARD


THRESHOLDN/A

REPEATC1


ALL



ATA CHAPTER52

ACCESS ZONE

08. Open vent door. Inspect to verify fully retracted position of latches and torque tube lock assembly. Operate cargo door latching mechanism and inspect for chaffing on torque tube lock. Close vent door and inspect each latch for secu-rity in the locked position, also inspect torque tube lock for security in locked position.

09. Inspect door seal for condition and signs of leakage.

10. Inspect latch mounting brackets for tightness and signs of corrosion between brackets and vent door.

11. Disconnect control cables at upper and lower rod end attachments. Push and pull each cable by hand to check for binding or broken wires.

12. Inspect control cable upper and lower mount brackets for condition and corrosion between brackets and mounting surface.

13. Inspect switch actuator and mount brackets for cracks and security.


Rev 3 04 March 2014

DC-9TASK CARD

TC-90

AIRLINE CARD NO.N/A



DATE TASKINS

RELATED CARD


THRESHOLDN/A

REPEATC1


ALL



ATA CHAPTER52

ACCESS ZONE

14. Inspect wiring for security and chaffing.

15. Inspect logic control box for security.

16. Operate vent door and check position and warning light indicators.

17. Lubricate.

A. Any exposed surface or surfaces to be lubricated must be thoroughly cleaned to be sure previously applied lubricants and accumulated foreign matter are removed before clean lubricates are applied. Cleaning solvents should not be used on control cables, there is a possibility of washing away or diluting the lubricant in these sealed cables. Steam cleaning is not recommended for the same reason. It is recommended that lubrication be per-formed after other work on the aircraft has been accomplished. This practice will help control dirt, water, and cleaning solvents.



Rev 3 04 March 2014

DC-9TASK CARD

TC-91

AIRLINE CARD NO.N/A



DATE TASKLUBE

RELATED CARD


THRESHOLDN/A

REPEATC1


ALL



ATA CHAPTER52

ACCESS ZONE


D. Lubricate rod ends, all brushings and bolts at pivot points, control cables, and hinge points with Oil General Purpose (OPG) MIL-L-7870.

Date Emp# Mech



Rev 3 04 March 2014

DC-9TASK CARD

TC-92


Rev 3 04 March 2014

DC-9TASK CARD

TC-93

AIRLINE CARD NO. TITLEEngine Change


DATE TASK RELATED CARDSee Below / Compliance Required


THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

References

Related Task Cards: 24-001-02-01, 24-001-03-01, 76-021-01-01, 71-010-06-01/02, 71-020-01-01/02.

NOTE: Pay particular attention to the following: proper clamping methods and required clamping of wire bundles, proper safetying and required safetying of connectors, security of wires in connectors, proper routing of wires/bundles, and wire splice condition and security.

Reason for engine removal _________________________________________________________

NOTE: If an engine is being removed and is not being transferred to another aircraft, the engine shall be pre-served on-wing prior to removal.

1. Preserve engine oil system prior to engine removal as follows. (Ref: P&W MM 72-00-00 SERVICING). N/A this step if engine is to be transferred to another aircraft or reinstalled on the same aircraft.A. Drain oilB. Replace engine oil filter element.C. Fill engine oil system.D. Motor engine with starter until oil pressure is indicated.E. Start and operate engine at 75% max continuous power for five minutes then shut down engine.F. Attach a tag to engine oil tank cap stating, "ENGINE OIL SYSTEM PRESERVED"

G. Make a copy of this page and forward with the engine.


MM 071 00 MM 071 02 MM 071 10 3

MM 071 20 2 MM 071 20 3 MM 077 11 0

MM 077 20 0 SB 041 27 REV9 P&W SB 071 21 REV8

SB 076 21 REV3 SI 025 53 01

Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-94





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

2. An off wing c-check must be performed for the engine being transferred from another aircraft.

If installing a serviceable engine from stock or removing and reinstalling the same engine the technician and inspector will "N/A" this step.

3. Prepare for engine change:

NOTE: Removal and installation procedures for left and right engines are identical unless otherwise noted.A. Open the following circuit breakers and attach red "CAUTION, ENGINE CHANGE IN WORK. CONTACT

SUPERVISOR OR LEAD BEFORE RESETTING CIRCUIT BREAKERS OR MOVING ENGINE CON-TROLS" placard.i. All C/Bs in "ENGINE" and "FUEL" areas of "AC BUS" section of upper main C/B panel.(ii) All C/Bs except "LIGHTS" in are of "DC BUS" section of lower main C/B panel.(iii) "ENGINE OIL PRESSURE" C/B in "28 VAC RADIO BUS" section of upper main C/B panel.(iv) C/Bs in "DC TRANSFER BUS" section of lower main C/B panel listed:• Oil pressure low caution.

• Generator control

• Engine start pump

• Engine ignition

• Fire Detectors

• Fire extinguisher control

B. Position engine controls in positions indicated and attach red "DANGER DO NOT USE" tags.i. Throttle ................................................. Idle(ii) Thrust Reverser Lever........Forward Thrust


Date Emp # Mech

Date Emp # Insp

Rev 3 04 March 2014

DC-9TASK CARD

TC-95





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

(iii) Fuel Shut-off Lever.................................Off

(iv) Fire Control Handle...........................Pulled

C. Open access door 5901(A) for left engine or 5902(A) for right engine change. Place thrust reverser control valve arm in "DUMP" position and install safety pin.

4. Remove upper and lower cowlings:

A. Open upper cowling tension latches and stow fully open with all hooks visible.

B. Support lower cowling, release ground safety latch and allow cowling to hang vertically.

CAUTION: SNUBBER REEL STRAP IS SPRING-LOADED. RESTRAIN STRAP BEFORE REMOV-ING PIN IN THE FOLLOWING STEPS "C" AND "D". DO NOT ALLOW STRAP TO SNAP BACK INTO REEL OR POSSIBLE DAMAGE WILL OCCUR.

C. Disconnect fwd snubber reel strap from nose cowl bracket (if installed).

D. Disconnect aft snubber reel strap from engine bracker (if installed).

E. Open pylon apron forward and aft lower pin latches.

NOTE: With pin latches opened, cowling will remain engaged on apron frame bosses.

WARNING: LOWER COWLING WEIGHS APPROXIMATELY 106 POUNDS.

F. Lift cowling up and inboard to disengage latch eyes from apron. Place cowling on suitable rack to pre-vent damage.

G. Position all upper cowling tension latch handles and triggers flush with cowling surface.

H. Remove screws from cowling sling attach points. Install sling (if using sling).


Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-96





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

I. Open all apron upper pin latches, ensure each latch is fully open.

WARNING: UPPER COWLING WEIGHS APPROXIMATELY 105 POUNDS.

J. With upper cowling closed, carefully raise cowling. Place cowling on suitable rack. Replace sling attach point screws if removed.

5. Open listed pylon access panels for engine being changed:

NOTE: Technician is to "N/A" panels for engine not changed.

LEFT PYLON:

Panel Initial Panel Initial Panel Initial Panel Initial

8101 (A) ________ 8103 (A) ________ 8105 (A) _______ 8111 (A) _______

RIGHT PYLON:

Panel Initial Panel Initial Panel Initial Panel Initial

8202 (A) ________ 8204 (A) ________ 8206 (A) _______ 8212 (A) ________

6. Disconnect listed electrical connectors:

NOTE: Electrical connectors for left and right engines are identical.

A. Generator Power - engine plug #P1-802

i. Remove adel clamps that secure generator wire to apron.

B. Generator Control - engine plug #P1-803FLEET EFFECTIVITY PAGE 4 OF 35

17-APR-2012

Date Emp # Mech

Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-97





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

C. Exhaust Gas Temp - engine plug #P1-804

D. Fire Detector Loop B - engine plug #P1-823

E. Fire Detector Loop A - engine plug #P1-822

F. Misc. Electrical #2 - engine plug #P1-801

G. Misc. Electrical #1 - engine plug #P1-800

7. Disconnect listed hyd. flex lines from engine hyd. bridle support bracket:

NOTE: Clean up hydraulic fluid immediately. Use bucket to reduce spillage.

A. Hydraulic supply

B. Hydraulic pressure

C. Hydraulic case drain

8. Disconnect Pt7 flex line from fitting at side of engine hyd. bridle support bracket. Disconnect Pt2 flex line from fitting on engine bracket.

9. Disconnect fuel vapor removal flex line from engine fitting.


Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-98





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

10. Remove fuel bridle drain plug, located at bottom center of bridle, and drain fuel into suitable container. Install plug using new gasket (P/N MS29512-04) and safety with lockwire.

NOTE: Fuel bridle and line contains approximately 6.12 pts.

11. Disconnect fuel supply line from engine fuel bridle and remove gasket.

12. Remove manifold duct clamps:

A. Support or remove short section of bleed manifold ducts.

B. Remove clamps from 8th and 13th stage bleed manifold ducts.

13. Disconnect thrust reverser flex hydraulic stow and deploy lines from rev. firewall fitting. Use empty bucket to catch excess fluid.

14. Disconnect power control cable clamp from bracket on engine flange. Disconnect fuel shutoff and power control cable fittings from engine crossshaft cranks and remove fuel shutoff and power control cable bkt. from side of engine.

WARNING:ALL ENGINE INSTALLATION AND SUPPORT EQUIPMENT (SLING AND ASSOCIATED HARDWARE) MUST BE TESTED AND APPROVED TO SUPPORT WEIGHT IN EXCESS OF 4250 POUNDS (APPOXIMATE WEIGHT OF COMPLETE ENGINE). FAILURE TO USE APPROVED EQUIPMENT COULD RESULT IN FAILURE OF EQUIPMENT AND PERSONNEL INJURY.


Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-99





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

15. Install engine removal/installation support equipment as follows:

A. Preferred method - using an overhead hoist or similar suitable overhead lifting device (other than fork-lift):

WARNING: ENSURE HOIST AND ATTACHING HARDWARE IS RATED TO AT LEAST TWICE THE WEIGHT OF THE ENGINE. UNDERRATED EQUIPMENT COULD FAIL RESULT-ING IN PERSONNEL INJURY.

i. Install dynamometer onto hoist and sling onto dynamometer. Move hoist and sling into position over engine. Carefully lower sling into position to attach to engine.

(ii) Attach sling to engine.

(iii) Align beam with center point depending on engine type.

B. Alternate method - using forklift:

WARNING: ENSURE FORKLIFT AND HARDWARE HAVE LIFT RATINGS OF AT LEAST TWICE THE WEIGHT OF THE ENGINE. IF EQUIPMENT IS NOT SUFFICIENTLY RATED, EQUIPMENT DAMAGE OR PERSONNEL INJURY COULD OCCUR.

NOTE: A single-point arrangement is the approved method when using a forklift.

i. If using a 10000 or 15000 pound forklift, position single point support beam 36 inches from front face of forks. Attach the dynamometer between the single point on the forklift and the sling.If using a 20000 pound forklift with 138 inch forks, position single point support beam 120 inches from front face of forks. Attach the dynamometer between the single-point on the forklift and the sling.

(ii) Install sling onto the dynamometer on the forklift and move forklift and sling into position over the engine.

(iii) Attach sling to engine.

(iv) Align beam with center point depending on engine type:


Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-100





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

16. Prior to removing the engine weight from isolator mounts inspect the condition of the mounts for snubbing (contact), axial migration, position, damage to support elements, cushion holes and cut or broken wire bundles. (Ref: MM 71-20-2)

WARNING:ENSURE PERSONNEL ARE CLEAR OF DANGER DURING INSTALLATION. EQUIPMENT FAILURE COULD RESULT IN PERSONNEL INJURY.

WARNING:ENSURE PROPER WEIGHT IS BEING SUPPORTED ON DYNAMOMETER PRIOR TO DIS-CONNECTING ENGINE FROM PYLON. FAILURE TO SUPPORT THE CORRECT WEIGHT COULD RESULT IN SUDDEN ENGINE MOVEMENTS AND PERSONNEL INJURY.

CAUTION:When lifting engine to remove sag from vibration isolators, do not lift more than 200-300 pounds beyond engine weight to prevent pylon damage.

NOTE: A complete JT8D weighs approximately 3900-4300 pounds. The engine sling and associated hard-ware weighs approximately 400-800 pounds. Refer to MM 70-00-00-4 for weights of engine compo-nents such as thrust reverser and nose cowl if previously removed.

17. Remove engine from aircraft by raising support beam with overhead hoist or forklift and attach to engine. Take up weight of engine until sag is removed from vibration isolators.

A. Loosen forward and aft cone bolt nuts a sufficient amount to relax preload of pylon apron bulb seal.

B. Remove forward bolts connecting pylon apron to nose cowl.

C. Remove bolts connecting lower apron structure to engine brackets.

D. Remove bolts connecting upper apron structure to engine brackets.

NOTE: On installations using double shouldered bolts, bushings should be removed and retained with bolts to ensure proper installation.


Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-101





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

E. Install thread protectors on forward and aft cone bolts. Use slotted socket (P/N F22AM) if needed.

WARNING: ENGINE REMOVAL/INSTALLATION SUPPORT EQUIPMENT IS ADJUSTED TO PRO-VIDE EVEN FORE AND AFT SUPPORT TO ENGINE. UNEVEN SUPPORT CAN CAUSE THE ENGINE TO SHIFT, RESULTING IN PERSONNEL INJURY.

F. Carefully move engine away from pylon to disengage cone bolts from vibration isolators. Guide elec-trical harness during engine removal.

CAUTION: Ensure all lines, ducts, electrical connectors and control cables are clear prior to low-ering engine. Ensure fire detector is not damaged during removal.

G. Ensure cone bolts are fully disengaged from vibration isolators and lower engine. Remove lower for-ward cone bolt/hardware and attach to engine flange.

H. Install engine in approved transportation dolly with inlet facing tow bar. If engine is leaving plane side, accomplish step 22.

I. Remove engine removal/installation support equipment.

J. Remove cone bolt thread protectors. Install washers and nuts.

NOTE: If split aluminum thread protectors have been used, aluminum shavings shall be removed from cone bolt threads using only a stainless steel brush.

NOTE: If engine is to be re-installed on the same A/C in the same position, and the engine is to remain plane side, the cone bolts and attaching hardware must still be replaced. Remove all cone bolts and obtain serviceable cone bolts and attaching hardware. Cone bolts are re-installed in steps 23-25 of this card.


Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-102





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

18. Prepare removed engine for shipment. If the same engine is being reinstalled, and engine is to remain plane side, "N/A" this step.

A. Before removing hoist from engine, install, torque and safety engine dolly mounting bolts.

B. Remove lifting adapters from engine.

C. Enclose all open electrical connectors with plastic bags.

D. Install caps on all open hydraulic lines.

E. Cover all exposed bleed air ducting.

F. Install inlet and exhaust cover.

G. Complete repairable parts tag and attach to engine.

19. Check condition and security of pylon structure including forward engine mount yoke, fireshield, firewall and aft engine mount support. Check vibration isolators and absorbers for condition, security, and correct installation (ref: mm 71-20-2 and 71-20-3). Check condition and security of electrical harness, cannon plugs and fire detection elements.

A. Check for any sharp edges or forging imperfections on the yoke assy such as pits, crevices, die marks, etc. shall be rounded and smoothed by the chemical milling process. Rounded smooth imper-fections shall not be cause for rejection, provided they do not exceed original dimension req'mts. (Ref: DPS 9.482)


Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-103





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

20. Prepare engine for installation:

A. Remove humidity indicators and inlet/exhaust covers from engine. N/A this step if covers / desiccant bags were not installed or if covers / bags were used on removed engine.

B. The install engine nose cowl must be installed with modified bearing plates and attaching bolts. (Ref: AD 95-02-14 AMEND. 39-9133 and MM 71-10-01).

C. Record P/N and S/N of installed engine nose cowl.P/N: ________________S/N:_______________

D. Ensure circuit breakers listed in step "08(A)" are open and tagged.

E. Ensure the following engine controls are in positions indicated and red tagged:

i. Throttle ......................................................Idle

(ii) Thrust Reverser Lever ........... Forward Thrust

(iii) Fuel Shut-Off Lever....................................Off

(iv) Fire Control Handle ...............................Pulled

F. Ensure appropriate thrust reverser control valve arm is in "DUMP" position with safety pin installed.

WARNING:ALL ENGINE INSTALLATION AND SUPPORT EQUIPMENT (SLING AND ASSOCIATED HARDWARE) MUST BE TESTED AND APPROVED TO SUPPORT WEIGHT IN EXCESS OF 4250 POUNDS (APPROXIMATE WEIGHT OF COMPLETE ENGINE). FAILURE TO USE APPROVED EQUIPMENT COULD RESULT IN FAILURE OF EQUIPMENT AND PERSONNEL INJURY.

21. Install engine removal/installation support equipment as follows:


Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-104





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

A. Preferred method - using an overhead hoist or similar suitable overhead lifting device (other than fork-lift):

WARNING: ENSURE HOIST AND ATTACHING HARDWARE IS RATED TO AT LEAST TWICE THE WEIGHT OF THE ENGINE. UNDERRATED EQUIPMENT COULD FAIL RESULT-ING IN PERSONNEL INJURY.

i. Install dynamometer onto hoist and sling onto dynamometer. Move hoist and sling into position over engine. Carefully lower sling into position to attach engine.

(ii) Attach sling to engine.

(iii) Align beam with center point depending on engine type.

B. Alternate method - using forklift:

WARNING: ENSURE FORKLIFT AND HARDWARE HAVE LIFT RATINGS OF AT LEAST TWICE THE WEIGHT OF THE ENGINE. IF EQUIPMENT IS NOT SUFFICIENTLY RATED, EQUIPMENT DAMAGE OR PERSONNEL INJURY COULD OCCUR.

NOTE: A single-point arrangement is the approved method when using forklift.

i. If using a 10000 or 15000 pound forklift, position single point support beam 36 inches from front face of forks. Attach the dynamometer between the single-point on the forklift and the sling.If using a 20000 pound forklift with 138 inch forks, position single support beam 120 inches from front face of forks. Attach the dynamometer between the single-point on the forklift and the sling.

(ii) Install sling onto the dynamometer on the forklift and move forklift and sling into position over the engine.

(iii) Attach sling to engine.


Rev 3 04 March 2014

DC-9TASK CARD

TC-105





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

(iv) Align beam with center point depending on engine type.

WARNING:ENSURE PERSONNEL ARE CLEAR OF DANGER DURING INSTALLATION. EQUIPMENT FAILURE COULD RESULT IN PERONNEL INJURY.

WARNING:ENGINE REMOVAL/INSTALLATION SUPPORT EQUIPMENT IS ADJUSTED TO PROVIDE EVEN FORE AND AFT SUPPORT TO ENGINE. UNEVEN SUPPORT CAN CAUSE THE ENGINE TO SHIFT, RESULTING IN PERSONNEL INJURY.

NOTE: A complete JT8D weighs approximately 3900-4300 pounds. The engine sling and associated hard-ware weighs approximately 400-800 pounds. Refer to MM 71-00-00-4 for weights of engine compo-nents such as thrust reverser and nose cowl.

22. Carefully remove engine from transportation dolly.

23. Record serial number of forward upper cone bolt:

A. Record serial number of forward upper cone bolt: ______________________

NOTE: If cone bolt is not installed on engine, proceed with sub-step B(1). If cone bolt is installed, proceed with sub-step B(5).

WARNING: DO NOT INSTALL CONE BOLTS (BARRY CONTROLS P/N R18210-2) SERIAL NUM-BERS 15B8021 THROUGH 15B8329, 15B8332 THROUGH 15B8282, OR 15B8396 THROUGH 15B8399 IN FWD UPPER POSITION (REF: AD 89-14-10 AMEND 39-6253).

B. Inst. Fwd. upper cone bolt: (REF: DC9 MM 71-20-1)

i. Install retainer washer on attach bolt.

CAUTION: Attach bolt nut running torque must not be less than in-poundsFLEET EFFECTIVITY PAGE 13 OF 35

17-APR-2012

Date Emp # Mech

Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-106





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

CAUTION: If there is any doubt as to integrity of nut's self-locking feature, replace them to pro-vide highest margin of safety.

(ii) Install washer and nut on attach bolt. Tighten nut until cone bolt is free standing but readily mov-able by hand. Torque on nut shall not exceed 425 inch-pounds.

(iii) Determine running torque value of cone bolt nut with clean and dry threads. Running torque of cone bolt nut must be greater than 50 inch-pounds and is additive to clamp-up torque. After run-ning torque is determined, apply coating of anti-seize compound (MIL-1-25681) on cone bolt threads.

Record running torque: _________ inch-pounds

(iv) Install thread protector on cone bolt using slotted socket (P/N F22AM) if needed. Screw protectors on cone bolt as far as possible.

24. Record serial number of forward lower cone bolt and install:

A. Record serial number of forward lower cone bolt being installed:

Serial Number ______________________

WARNING: DO NOT INSTALL CONE BOLTS (BARRY CONTROLS P/N R18210-2) SERIAL NUM-BERS 15B8021 THROUGH 15B8329, 15B8332 THROUGH 15B8282, OR 15B8396 THROUGH 15B8399 IN FWD LOWER POSITION (REF: AD 89-14-10 AMEND 39-6253

B. Inst. fwd. lower cone bolt: (Ref: DC9 MM 71-20-1)

i. Install retainer washer on attach bolt.


Date Emp # RII

Date Emp # Mech

Rev 3 04 March 2014

DC-9TASK CARD

TC-107





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

CAUTION: Do not apply anti-seize compound to attach bolt threads. Bolt threads must be clean and dry prior to installing nut.

(ii) Apply coating of anti-seize compound (MIL-1-25681) on attach bolt shank and engine mount flange bushings.

(iii) Position support and cone bolt between flange bushings. Insert attach bolt through flange bushing and cone bolt.

NOTE: Right engine attach bolt is installed with bolt head FORWARD. Left engine attaché bolt is installed with bolt head AFT.

CAUTION: Attach bolt nut running torque must not be less than 50 in-pounds.

CAUTION: If there is any doubt as to integrity of nut's self-locking feature, replace them to provide highest margin of safety.

(iv) Install washer and nut on attach bolt. Tighten nut until cone bolt is free standing but readily mov-able by hand. Torque on nut shall not exceed 425 inch-pounds.

(v) Determine running torque value of cone bolt nut with clean and dry threads. Running torque of cone bolt nut must be greater than 50 inch-pounds and is additive to clamp-up torque. After run-ning torque is determined, apply coating of anti-seize compound (MIL-1-25681) on cone bolt threads.Record Running Torque: _________ inch-pounds

(vi) Install thread protector on cone bolt using slotted socket (P/N F22AM) if needed. Screw protectors on cone bolt as far as possible.


Date Emp # Mech

Date Emp # RII

Rev 3 04 March 2014

DC-9TASK CARD

TC-108





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

25. Record serial number of aft cone bolt:

A. Record serial number of aft cone bolt: ___________________________

NOTE: If cone bolt not installed on engine, proceed with sub-step B(1). If cone bolt is installed, proceed with sub-step B(8).

WARNING: DO NOT INSTALL CONE BOLTS (BARRY CONTROLS P/N R18211-2) SERIAL NUM-BERS 15B5242 THROUGH 15B5320 IN AFT POSITION (REF: AD 89-14-10 AMEND 39-6253).

B. Install aft cone bolt: (Ref: DC9MM 71-20-1)

i. Install countersunk washer on attach bolt with countersink facing bolt head.

CAUTION: Do not apply anti-seize compound to attach bolt threads. Bolt threads must be clean and dry prior to installing nut.

(ii) Apply anti-seize compound (MIL-L-25681) to attach bolt shank and engine mount flange bushings.

(iii) Position support and cone bolt between flange bushings. Insert attach bolt through flange bush-ings and cone bolt.

NOTE: Attach bolt is installed with bolt head aft.

(iv) Install countersunk washer and nut on attach bolt and tighten nut fingertight.

(v) Push nut and washer against flange bushing.

(vi) Ensure countersunk washer under bolt head is against bolt head and measure gap between washer and engine flange.


Rev 3 04 March 2014

DC-9TASK CARD

TC-109





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

NOTE: Gap should be 0.005 to 0.010 inch.

(vii)Install cotter pin.

(viii)Determine running torque value of cone bolt nut with clean and dry threads. Running torque of cone bolt nut must be greater than 50 in-pounds and is additive to camp up torque. After running torque is determined, apply coating of anti-seize compound (MIL-L-25681) on cone bolt threads.Record running torque: ________ inch-pounds

(ix) Install thread protector on cone bolt using slotted socket (P/N F22AM) if needed. Screw thread protector on cone bolts as far as possible.

26. Record the following data for installed engine, thrust reverser, and nose cowl. If the same engine is being reinstalled, "N/A" this step.

A. Record engine model number and serial numberModel number _____________ S/N _____________

B. Record thrust reverser part number and serial number:P/N _________________ S/N ___________________

C. Record nose cowl part number and serial number:P/N _________________ S/N ___________________

D. Record installation information on the nose cowl and thrust reverser and place in the ENGINE CHANGE WORKPACK.


Date Emp # Mech

Date Emp # RII

Date Emp # Insp

Rev 3 04 March 2014

DC-9TASK CARD

TC-110





THRESHOLDN/A


JT8DSTATION SKILL


ATA CHAPTER71

ACCESS ZONE

07/000 08/000 08/001 08/002

27. Install Engine:

CAUTION: When maintaining lift on engine during connection of vibration isolators, do not lift more than 200-300 pounds beyond engine weight. Failure to observe this caution could cause pylon damage.

CAUTION: When installing engine, ensure all lines, ducts, electrical connectors and control cables are guided into position. Be especially careful to not damage fire det. Ele-ments.

A. Carefully move engine toward pylon to engage cone bolts and isolators.

B. Align forward and aft cone bolts with vibration isolators.

C. Ensure forward and aft cone bolts are properly engaged, remove thread protectors.

NOTE: If split aluminum thread protectors have been used, use only a stainless steel brush to remove aluminum shavings from cone bolt threads.

D. Ensure adequate lubrication remains on threads, and install washers and nuts. Do not torque cone bolt nuts at this time.

28. Install apron structure bolts:

CAUTION: When installing double shouldered bolt on aprons, ensure bolt bushing has been installed prior to tightening or distortion of bolt may occur.

A. Install bolts that connect apron upper structure to engine brackets.

B. Torque bolts to 100-140 inch-pounds.


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29. Install bolts which connect apron lower structure to engine brackets.

30. Install forward bolts connecting pylon apron to nose cowl. Torque to 50-70 inch-pounds.

31. Tighten forward and aft cone bolt nuts:

A. Torque nut of each forward cone bolt to 200-220 foot-pounds, adding cone bolt nut running torque.

CAUTION: When using an adapter with torque wrench to tighten aft cone bolt nut, value correc-tions must be computed I/A/W formula (Ref: MM 70-30-6).

B. Torque nut of aft cone bolt to 200-220 foot-pounds, adding running torque of cone bolt nut.

32. Remove engine installation support equipment.

33. Ensure all hardware is returned with shipping sand and support equipment is returned to storage areas. If the same engine is being installed that was removed, technician to N/A this step.

34. Install fuel shutoff and power control cable bracket on side of engine.


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35. Clamp power control cable and fuel shutoff cable together. Clamp power control cable to bracket on engine flange.

NOTE: N/A is SB 76-21 (Rev3) has been complied with. Approximately 1.3 inches should exist between centerline of clamp connecting power control cable to engine flange and centerline of clamp connecting fuel shutoff cable and power control cable together.

NOTE: Pre-SB76-21 (Rev3): braided metal Teleflex covers; round, spiral internal Teleflex.Post-SB76-21 (Rev3): larger, smooth-covered, usually black Teleflex housing. Flat metal inter-nal Teleflex (resembles oil dipstick).

36. Connect power control cable:

A. Clamp flight compartment throttle handle in IDLE position (against pedestal stop) and ensure thrust reverser lever is in FORWARD THRUST position.

B. Ensure engine cross shaft is in idle position and install rig pin in linkage on right side of engine.

C. Adjust control cable rod end fitting until bolt will slide in freely. Check inspection safety hole to ensure sufficient cable engagement.

D. Install bolt, washer, nut, and cotter pin. Safety push-pull control with lockwire. Remove rig pin from linkage.

E. Remove red "DANGER DO NOT USE" tag from flight compartment throttle handle that was installed in step 08(B).

37. Connect fuel shutoff cable:

A. Place flight compartment fuel shutoff lever in full FUEL OFF position.


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B. Install rig pin in engine fuel shutoff control arm on rt side of engine.

C. Adjust control cable rod end fitting until bolt will slide freely in place. Check inspection safety hole to ensure sufficient cable engagement. Safety sable rod end fitting.

D. Install bolt, washer, nut and cotter pin.

E. Remove rig pin from linkage.

F. Remove red "DANGER DO NOT USE" tag from fuel shutoff lever that was installed during engine change preparation.

38. Check throttle alignment.

A. Verify that both engines' power trim stops are in standard day position.

NOTE: Part power trim stops are in standard day position when the letter "S" on the trim stops are facing outward.

B. Move throttles forward until a gap of 0.20-0.30 inch exists between power control arm index plate and part power trim stop.

NOTE: Gap is necessary in order to prevent preloading of system.

C. Check that throttle handles are aligned within ¼ diameter of knob.

39. Connect thrust reverser flex hydraulic stow and deploy lines to reverser firewall fitting.

40. Install bleed air manifold duct clamps:

A. Install any bleed air manifold duct that may have been removed.FLEET EFFECTIVITY PAGE 21 OF 35

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B. Install clamps on 8th and 13th stage bleed air manifold ducts. Position clamps located at 10 & 2 o'clock with threads on inboard side of manifold and parallel to engine.

C. Torque clamps (specified on clamp) and install safety pin on clamp tang.

41. Install new gasket (P/N 011157-015-24) and connect fuel supply flex line to engine fuel bridle.

NOTE: On right engine provide clearance between fuel supply flex line and starter valve sense line.

42. Connect fuel vapor removal flex line to engine fitting.

43. Connect Pt2 flex line to fitting on engine bracket. Connect Pt7 flex line to fitting at side of engine hydraulic bridle support bracket. Perform leak check of system utilizing the primary method (Ref: MM 77-11-0).

NOTE: The alternate method can be performed to adjust/test the Pt7 portion of the system (Ref MM 77-11-00-2-0101 par 4A).

44. Connect the following flex lines to engine hydraulic bridle support bracket:

A. Hydraulic supply

B. Hydraulic pressure

C. Hydraulic case drain

NOTE: Clean up hydraulic fluid immediately. Use bucket to minimize spillage.


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45. Connect electrical connectors listed below and safety with lockwire.

NOTE: Elect. Connectors for left and right eng. Installations are identical.

A. Generator power - engine plug #P1-802.

i. Install adel clamps that secure generator wires to apron.

B. Generator control - engine plug #P1-803.

C. Exhaust gas temp - engine plug #P1-804.

D. Fire detector loop B - engine plug #P1-823.

E. Fire detector loop A - engine plug #P1-822.

F. Misc. electrical #2 - engine plug #P1-801.

G. Misc. electrical #1 - engine plug #P1-800

46. Check the following engine/component oil levels. If necessary, service with 2380 turbo oil. Use referenced MM Ch. For capacity and procedures.

A. Engine oil (Ref: MM 12-20-0)

B. Starter oil (Ref: MM 12-21-1)

C. CSD oil and CSD cavity (Ref: MM 12-22-0)

47. Visually inspect (RII) the following for security:

A. Electrical connections.


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B. Hydraulic connections.

C. All engine control cables, push/pull rods and linkages from pylon connections to fuel control unit.

D. Fuel vapor line.

E. Pneumatic connections.

F. Pt2/Pt7 connections.

48. Close circuit breakers opened in step 08(A). Remove red CAUTION tag (M-76)

49. Complete serviceable tag for the installed engine. Verify tag information with store, return tag to WORK PACKAGE and log tag in. If same engine was reinstalled, "N/A" this step.

50. Check oil quantity system by energizing electrical busses and checking for proper oil quantity indication. Ensure indicator reading and visible oil quantity in tank agree within 1.5 qts of each other.

51. Install upper and lower cowlings:

A. Ensure all pylon apron upper pin latches are fully open.

B. Remove screws from upper cowling sling attach points and install sling (if using sling).

C. Raise cowling into approximate position and install, ensuring all cowling latch eyes engage apron pin latches properly.

CAUTION: Do not force pin latches when closing. If pins will not engage properly, check cowling alignment.


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D. Close all pylon apron upper pin latches.

E. Ensure all pin latch triggers are flush with pylon apron surface.

F. Remove sling and install screws in upper cowling sling attach points flush with cowling surface (if screws removed).

G. Open upper cowling, install both hold-open rods and ensure pins are properly engaged.

H. Ensure pylon apron forward and aft lower pin latches are fully open.

I. Position lower cowling, ensure latch eyes are engaged on apron and allow cowling to hang vertically.

CAUTION: Do not force pin latches when closing. If pins will not engage properly, check cowling alignment.

J. Close pylon apron forward and aft lower pin latches.

CAUTION: Snubber reel strap, if installed, is spring-loaded. Restrain strap during installation of pin. Do not allow strap to snap back into reel or possible structural damage will occur.

K. Ensure pin latch triggers are flush with apron surface.

L. Connect aft snubber reel strap to engine bracket. (If installed).

M. Connect forward snubber reel strap to nose cowl bracket. (If installed).

N. Open lower cowling, install both hold-open rods and ensure pins are properly engaged.

52. Place fire control handle in the normal position and remove red "DANGER DO NOT USE" tag installed in step "08(B)."


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53. Check throttle and fuel shutoff lever operation:

A. Cycle throttle several times from idle to FULL THRUST position and back to IDLE. Ensure freedom of movement through entire range.

B. Cycle fuel shutoff lever several times from "FUEL OFF" to "FUEL ON" position and back to "FUEL OFF". Ensure freedom of movement through entire range.

54. Check engine anti-ice valves and indicators:

A. Energize electrical busses (Ref: MM 24).

B. Place ANTI-ICE VALVE switch to "ON" position. Ensure valves operate properly, AMBER light comes on momentarily, BLUE light comes on and mechanical indicators on valves indicate OPEN.

C. Place ENGINE ANTI-ICE VALVE switch in "OFF" position.

55. Check fuel system

A. Place BOOST or START PUMP switch in "ON" position. Ensure no fuel leakage exists at fuel bridle or flex line.

B. Loosen vapor removal line connection at fuel bridle. Bleed until air is depleted from fuel line and tighten connection.

C. Place FUEL PUMP switch in "OFF" position.

56. Check/Reset CSD Disconnect:


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A. Pull disconnect handle on bottom of CSD lightly, until handle bottoms. Hold handle lightly in this extended position.

B. Actuate and release flight compartment CSD disconnect switch. CSD disconnect handle on bottom of CSD should pull in by spring action. Allow handle to move in. Pull disconnect handle out until audible click is heard, indicating disconnect is latched out.

NOTE: A reduction in pull force required on CSD disconnect handle is also evidence that disconnect is latched out.

C. Safety disconnect handle with copper break-away wire (P/N MS20099CU020).

57. Check fire warning system operation:

A. Place all loop selector switches on fire detector syst. Panel to "BOTH."

B. Depress and hold both LOOP TEST switches. Fire warning bell should ring and the following lights should come on:

i. FIRE CONTROL HANDLE lights.

(ii) MASTER WARNING lights on glareshield.

(iii) APU FIRE light in annunciator panel.

(iv) FIRE DETECTOR LOOP light in annunciator panel.

(v) ALL LOOP lights on fire detector system panel.

C. Release both loop TEST switches and depress MASTER WARNING light. All listed lights listed above in step "B" should go off.

D. Press both LOW AGENT indicating lights. Both lights should come on.

E. Release both LOW AGENT indicating light. Lights should go off.


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58. Check engine ignition system:

A. Before checking ignition system operation, ensure engine is clear of fuel (Ref: MM 71-00), open all fuel BOOST PUMP circuit breakers located on upper main circuit breaker panel, no pneumatic pres-sure is supplied to engine and engine compressor is not turning.

CAUTION: Limit firing time of igniter plugs to 2 minutes during check.

B. Energize 115-VAC bus. Pull 7.5A ENGINE START PUMP circuit breaker and rotate IGNITION selec-tor switch to system "A". Move #1 engine fuel shutoff lever toward the fuel "ON" position and ensure igniter plug in #1 engine fires (emits a distinct cracking sound). Return fuel shutoff lever to "OFF" posi-tion.

C. Move #2 engine fuel shutoff lever toward fuel "ON" position and ensure igniter plug in #2 engine fires (emits a distinct cracking sound). Return fuel shutoff lever to "OFF" position.

D. Rotate IGNITION selector switch to system "B." Repeat steps "A" - "C."

E. Place #1 engine IGNITION selector switch to either "A" or "B" position. Advance #1 fuel shutoff lever toward "ON" position. With fuel lever advanced, place #1 engine starter switch to "ON" position. Ensure both "A" and "B" ignition systems operate. Release starter switch and return #1 fuel shutoff lever to "OFF" position.

F. Repeat step "E" and check #2 engine ignition.

G. Reset 7.5A engine start pump circuit breaker. De-energize electrical busses. Close all fuel boost pump circuit breakers on upper main circuit breaker panel opened in step "B."


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59. Check EGT Resistance and record findings. If the same engine is reinstalled, technician to "N/A" this step.

A. Remove EGT indicator(s), as required (Ref: MM 77-20-01-02).

B. Check engine EGT circuit resistance of engine being changed and any indicator change dur to incor-rect part number, using leads and Northrup type 5305 Wheatstone Bridge, Barfield Digital Turbine Temp. Test set (P/N 10100901) or equivalent. Excluding the indicator, circuit resistance must be 15 (±0.020) ohms (Ref: MM 77-20-00 ADJ?TEST AND CHART BELOW).

NOTE: System resistance is a linear and direct function of ambient temperature. A change in ambi-ent temperature of 1°C (1.8°F) changes resistance approximately 0.003 ohms.


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NOTE: Check is only applicable to engine being changed or if indicator was changed due to incorrect part number, technician to "N/A" this task on engine position not checked.

C. Record all initial readings. If adjustment is required, record adjusted readings:

i. Left engine readings: Initial __________ Adjusted ________


Temp °C Ohms Temp °F Temp °C Ohms Temp °F0 14.937 32.0 20 14.997 68.01 14.940 33.8 21 15.000 68.92 14.943 35.6 22 15.003 71.63 14.946 37.4 23 15.006 73.44 14.949 39.2 24 15.009 75.25 14.952 41.0 25 15.012 77.06 14.955 42.8 26 15.015 78.87 14.958 44.6 27 15.018 80.68 14.961 46.4 28 15.021 82.49 14.964 48.2 29 15.024 84.2

10 14.967 50.0 30 15.027 86.011 14.970 51.8 31 15.030 87.812 14.973 53.6 32 15.033 89.613 14.976 55.4 33 15.036 91.414 14.979 57.2 34 15.039 93.215 14.982 59.0 35 15.042 95.016 14.985 60.8 36 15.045 96.817 14.988 62.6 37 15.048 98.618 14.991 64.4 38 15.051 100.419 14.994 66.2

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(ii) Right engine readings: Initial _________ Adjusted ________

D. Ensure proper P/N egt indicators are installed in Flyaway Spared kit (Ref: IPC 25-53-01).

NOTE: Two different P/N indicators may be required if engines are intermixed.

60. OK to close listed pylon access panels. Check area for foreign objects and/or removed units prior to clos-ing. (Inspection).

NOTE: N/A panels for engine not changed.

Left Pylon:

Panel Init Date Panel Init Date Panel Init Date Panel Init Date

8101 (A) ___ ____ 8103 (A) ___ _____ 8105 (A) ___ ____ 8111 (A) ___ _____

Right Pylon:


8202 (A) ___ ____ 8204 (A) ___ _____ 8206 (A) ___ ____ 8212 (A) ___ _____


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61. Close listed pylon access panels:

NOTE: N/A panels for engine not changed.

Left Pylon:


8101 (A) ___ ____ 8103 (A) ___ _____ 8105 (A) ___ ____ 8111 (A) ___ _____

Right Pylon:


8202 (A) ___ ____ 8204 (A) ___ _____ 8206 (A) ___ ____ 8212 (A) ___ _____

62. Close upper and lower cowlings and check for proper fit, adjust if necessary (Ref: MM 71-10-3).

NOTE: The engine fire loop clamps have close clearance to the lower cowling frame aft of the engine breather. Reposition clamps if necessary. (Ref: IPC 26-10-0: Fig 6)

63. On engine being installed, inspect the thrust reverser buckets, support assemblies and linkage hardware

NOTE: Flat end bolts must extend at least 1/32 inch through the self-locking nut. Chamfered end bolts must extend at least the chamfer through the self locking nut.

64. Activate thrust reversers:

A. Ensure throttle is in IDLE position and thrust reverser lever is in FORWARD THRUST position.FLEET EFFECTIVITY PAGE 32 OF 35

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B. Remove and stow thrust reverser control valve safety pin.

C. Close fuselage access door 5901(A) or 5902(A).

D. Manually position pneumatic cross-feed valve to OPEN (Ref: MM 76)

E. Remove red "DANGER DO NOT USE" tag installed in step 08(B) from thrust reverser lever.

WARNING: MAKE CERTAIN ALL PERSONNEL ARE CLEAR OF THRUST REVERSER DOORS BEFORE DEPLOYING OR STOWING BUCKETS. ANY TIME THRUST REVERSER CONTROL VALVE IS NOT IN "DUMP" POSITION, 3000 PSI IS AVAILABLE AND WILL MOVE REVERSER DOORS IN RESPONSE TO THRUST LEVER MOVEMENT REGARDLESS OF WHETHER ELECTRICAL POWER IS SUPPLIED TO AIRCRAFT.

F. Ensure area around thrust reversers is clear of personnel and equipment. Pressurize hydraulic sys-tem. Actuate cockpit thrust reverser lever to deploy, stow, and deploy the reverser. Check operation for fluid leaks. Stow reverser and depressurize hydraulic system.

65. Perform engine operation test per AMM 71-00.

66. Perform POST ENGINE RUN-UP/TRIM CHECK per AMM 71-00 and ensure all discrepancies are cleared on engine before cowling is closed.

67. Close upper and lower cowlings (if opened for ENGINE RUN).

68. If electrical power is no longer required, de-energize external power and remove external power plug from aircraft.


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69. Ensure all sign offs are completed.

NOTE: See GOM chapter 6 for test flight requirements.


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Part/Tooling Requirements


Quantity

Thread Protector4916744-503

95 0 1030 3

Bolt, Forward ConeR18210-2

71 20 65 2

Bolt, Aft ConeR18211-2

71 20 66 1

RigRP1

95 0 2860 1

Seal, Main Tank Vent Sys011157-015-24

28 10 170 1

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TITLEAIRCRAFT ENGINE RUNUP AND TRIM


DATE TASK RELATED CARD71-01EAC


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References: DC-9 AMM 71-00-00-5

DC-9 AMM 73-20-03-2

A. GENERAL INFORMATION

DATE:___/___/___ AIRCRAFT: N____________ STA:___________ TARGETS

TAMB:____________ PAMB:________________ WIND:____________ IDLE %N2 RPM_____

PART PWR PT-7 _____

LFT C S RT C S PART PWR EPR _____

PART POWER STOP:_______________/_________________ TAKE OFF EPR _____

LFT RT

Engine Model and Serial Number:________/________ ________/________

Reason for Run-up Trim:________________________________________________________

B. ENGINE START AND TRIM CHECK:

The Engine Run Up/Taxi Checklist will be utilized in conjunction with the following procedures.


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1. START AND IDLE DATA: ENG#1 ENG#2

a. Max Starting EGT (LIMIT:______________________)

b. Verify N1, N2, EGT, Fuel Flow, Oil Pressure, Hydraulic Pressure and Generator is operating normal.

c. Stabilized Idle % N2 Observed (TARGET:_______________+1/-0)

d. Stabilized Idle % N2 set to

2. PART POWER:

a. PP PT-7 (TARGET:_______________+0.5/-0)

(N/A if engine instrumentation is used, see note on page 4 for requirements)

b. PP EPR (TARGET:_______________+0.2/-0)

c. N1 RPM

d. EGT

e. N2 RPM

f. Fuel Flow

g. Oil Pressure

h. Oil Temperature

i. Oil Breather Pressure (C/W when FIRST/SECOND stage compressor disk and blade assembly is replaced, repaired or reinstalled, or at require of Director of Main-tenance.


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3. TAKE-OFF POWER: ENG#1 ENG#2

a. EPR (TARGET:____________________)

b. PWR Lever Alignment 1.65 EPR (1/2 knob or less)

c. N1 RPM

d. EGT

e. N2 RPM

f. Fuel Flow

g. Oil Pressure (40-50 PSI)

h. Oil Temperature

i. Oil Breather Pressure

4. DRAIN MOISTURE TRAP PROCEDURE:

a. Drain burner can pressure sense line moisture trap, located on forward side of fuel control unit, if either of the follow-ing conditions prevail.

1. Engines have been operated in atmospheric conditions (rain, snow, or high humidity), conducive to formation of moisture.

2. Temperatures below 32 DEG Fare expected during period of engine shutdown.

NOTE: The moisture trap should be drained before the engines have cooled to ambient temperature.


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5. STOW AND SAFETY PART POWER TRIM STOP:

a. Part Power Trim Stop.

CAUTION: IF TRIM PROCEDURE WAS PERFORMED WITH PART POWER TRIM STOP IN COLD DAY POSI-TION, MAKE CERTAIN STOP IS INVERTED SO THAT LETTER “S” IS FACING OUTWARD BEFORE STOW-ING.

Mechanic: ________________ RII: _________________

*Note: Trim Engine Using Aircraft Instrumentation—

Aircraft instrumentation can be used on a single or double engine change provided engine(s) are fresh out of test cell or engine(s) have been run-up I.A.W. DC-9 Engine. Run-up and Trim Record form before engine(s) removal.

This procedure is not approved for engine trimming during icing conditions.

This procedure is not approved if any of the following cockpit instruments (N1 RPM, N2 RPM, or EPR) have also been changed at the same time that engine trimming is to be accomplished.

Calibrated instruments must be used.

Engine Run-Up/Trim Check accomplished by:

Name:________________________________

Date:_________________________________

Signature:_____________________________

Station:_______________________________


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General SectionEquipment and Materials - Water Wash Nozzle PWA102995, Cleaning Fluid SPS 87

References:

1. P & W Maintenance Manual 72-00-00 cleaning-00

2. P & W Standard Practice Manual 70-22-00

3. DC-9 MM Chapter 6 & 71


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TITLECompressor Water Wash


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Procedure

*NOTE: WHILE STARTING ENGINES BEFORE OPENING FUEL SHUTOFF LEVER, MAKE SURE THAT THERE IS ROTATION OF THE FRONT COMPRESSOR WHILE ENGINE IS BEING MOTORED BY THE STARTER.

**NOTE: Engine Gaspath Wash should be accomplished after TC72-04EAC Fuel Nozzle Cleaning.


MECH

1. Perform Engine Gaspath Wash with detergent IAW P&W MM 72-00-00 Cleaning-00 Page 709-715.**

2. *After completion of Gaspath Wash start and run engines, in idle, for five (5) minutes. *

3. While engines are running operate the anti-icing air shutoff, fuel heat and air conditioning valves, operate air conditioning system in full-cold mode to push un-drained water through water separator.

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TITLEFuel Nozzle Cleaning


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General SectionEquipment and Materials - Fuel Nozzle Cleaning Tool, Cleaning Fluid, Isopropyl Alcohol (P11-014)

References:

1. P & W Maintenance Manual 72-00-00 cleaning-00

2. DC-9 MM Chapter 6 & 71


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TITLEFuel Nozzle Cleaning


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Procedure

*NOTE: Upon completion of the cleaning procedure, or if the cleaning procedure is interrupted, residual clean-ing fluid should not be allowed to remain in internal fuel system passages for a period greater than 24 hours as this could result in surface corrosion of passages. To prevent corrosion, either:

A. Start engines and check for leaks at the PD valve as is normal procedure after any fuel system plumb-ing removal, OR

B. Flow at least two (2) gallons of Jet A Fuel or Kerosene into primary and secondary fuel tubes.

**NOTE: If T/C 72-04EAC and T/C 72-05EAC are to be completed concurrently then T/C 72-04EAC should be completed first. T/C 72-05EAC Compressor Water Wash may be substituted for step 2 (removing of cleaning agent) in T/C 72-04EAC Fuel Nozzle Cleaning, If TC 72-05EAC is completed after TC72-04EAC, it cannot be substituted for step 2 of TC 72-04EAC.


MECH

1. Fuel Nozzle Cleaning will be performed using Method one (1) of Pratt & Whitney JT8D Engine

2. Manual 72-00-00 cleaning-02 Page 601-604.*

3. Removal of cleaning fluid from gas path will be accomplished by Option two (2)(Ref P & W EM 72-00-00 cleaning-02 Page 604-605).**

4. Disconnect cleaning equipment and return engine to operational condition.

5. Perform Leak Check IAW P&W Engine Manual 72-00-00-76-030.

Rev 3 04 March 2014

DC-9TASK CARD

TC-137

AIRLINE CARD NO.N/A

TITLEOil SOAP


DATE TASKINS

RELATED CARD


VERSION1

THRESHOLDN/A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER79

ACCESSDOOR 7703/7804

ZONE

7/8

General SectionEquipment and Materials - Oil SOAP Kit (PN: PW-MOP-NO)

References:

1. JT8D Oil Monitoring Guide(P&W Portal, for planning purposes only)

2. DC-9 AMM

3. Oil SOAP kit (Intructions)


Rev 3 04 March 2014

DC-9TASK CARD

TC-138

AIRLINE CARD NO.N/A

TITLEOil SOAP


DATE TASKINS

RELATED CARD


VERSION1

THRESHOLDN/A

REPEAT1A


ALLSTATION SKILL


ATA CHAPTER79

ACCESSDOOR 7703/7804

ZONE

7/8

Procedure

*NOTE: Sample should be taken 20 minutes after engine shutdown.


MECH

1. Access oil tank filler cap (Ref. DC-9 AMM 12-20-00).

2. Draw out required oil sample from middle of oil tank.*

3. Place oil sample in SOAP kit Container and complete SOAP kit instructions.

4. Refill oil tank IAW DC-9 AMM 12-20-00.

5. Verify oil cap is in place and secure.

Rev 3 04 March 2014