for c.a.p. special missions avionics installed per …cessna and/or garmin approved avionics service...

Yingling A, iation Document !CA 18281388-8 Rev. C

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YINGLING AVIATION

INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

FOR

C.A.P. SPECIAL MISSIONS AVIONICS

INSTALLED PER STC. No. SA01216WI

SIN /f :rt11t¢

REG. NO~ N 591 ff

These instructions for .continued airworthiness comply with the requirements of-part 23 par. 23.1529 and part 23 Appendix G of

the Federal Aviation Regulations

Prepared by• Jf/j~ R Gallop -

Date: _Aug 28, 2008

FAA APPROVED ________ Date: it -1.J.-:. ~

Federal Aviation Administration Aircraft Certification Office Wichita , KS 67209

ooc~r.1ENT ,u. ~en · 3%-8 RE',' C

YiJ1gling Aviation Documem JCA 18281388-8 Rev. C

Table of Contents

REv~SlONS .. ... .. . ... .. . ..... . .. . .. . .. .... ...... .. . ...... .. ...... ... . .. .... ... ... ..... 2

TABLE OF CONTENTS .. .. .. . ... .. . . . . . .. . .. .. .. ... . .... . .. .. .... .. ... .. .. . .. ... . ... 3

1.0- INTRODUCTION . . ... .. ........ .... .... .. .. . . ... . . . .. ..... .... ... .............. 4

2.0 - DESCRIPTION OF THE ALTERATION •. ..... ..... ... .......... ... ...... 5

3.0- CONTROL AND OPERATION INFORMATION ........................ 6

4.0 - SERVICING INFORM.ATION .............................................. 6

5.0- MAINTENANCE INSTRUCTIONS . .... ..... .... ...... ... .. ... .•..•.. ... . 7

6.0- TROUBLESHOOTING INFORMATION .. ... .... ...... ... ....... ...... 7

7.0 - REMOVAL AND REPLACEMENT INFORMATION................ 7

8.0 - DL-lGR.4..MS . .. .. .. . . .. . . .. . . . . . .. . . . .. . .. . . . .. . . . .. .. . . .. . .. . ... . . ... . .. ... . . .. . 7

- 9.0 - SPECIAL INSPECTION REQUIREMENTS .............. .............. 8

10.0 - APPLICATION OF PROTECTIVE TREATMENTS ... ............ 8

11.0-DATA RELATIVE TO STRUCTURAL FASTENERS............... 8

12.0 - SPECIAL TOOLS ...... ................... ...... ... ... . ........... ........ .... 8

13.0- COMMUTER CATEGORY AIRCRAFT ........................ :...... 8

14.0- OVERHAUL PERIOD........................ ................................ 8

15.0 - AIRWORTIIlNESS LIMITATION SECTION ..... ........ ........... 8

16.0-REVlSION AND DISTRIBUTION........................................ 9

Appendix A MDL 2701-34351 Rev. J Master Document List

Appendix B AFMSJB,281388 Rev. D Airplane Flight Manual Supplement

Appendix C WD18218388-14 Rev. D Wiring Diagram w/IPC

Appendix D WR 18281388-2 Wire Routing Diagram

DOCUMENT ICA 18281388-8 REV. C

3

Yingling Aviation Document ICA 1828 1388-8

2.0 Description of the Alteration, continued:

Rev.C

The optional ARNAV RCOM 100 SAT COM consists of optional wiring provisions for a Receiver/Transmitter located in the aft baggage area, an Antenna located on the aircraft empennage, and a PTA-12 Telephone Dialer located in the Copilot's instrument panel. The audio from the optional RCOM 100 transceiver unit is supplied to the audio panels and is controlled at the audio panels through the TEL switch on the audio panels.

The COM 3 FM/UHF switch/annunciator is located in the avionics sub-panel and labeled UCOM 3 FM/UHF". Selection of the desired radio allows control of either the TDFM-136 VHF/FM radio or an optional UHF radio at the audio panels on COM3.

The optional ARTEX EL T System is located aft of the cabin is equipped with a remote switch in the Copilot's instrument panel for testing, status, and operation.

3.0 Control and Operation Information: Cqntrqt and operation for the CAP Special Missions Avionics Package is

"described in the Approved Flight Manual Supplement AFMS18281388. ~

·- 4.0 Servicing Information:

None. In the event of a system failure, return the unit to the manufacturer or a properly qualified and certified Cessna/Garmin Approved Avionics Service Organization.

5.0 Maintenance Instructions

5.1 Inspection Intervals

The Equipment mechani~al installation and associated wiring must be checked on a yearly basis as part of an annual aircraft inspection for condition and security as required by FAR 43 Appendix D(i)(1-4). The inspection must include a visual inspection of the antennas to ensure they are properly sealed at the antenna bases.

DOCUMENT ICA 18281388-8 REV C

7

I

Rev.C

5. 3 Testing Requirements, continued:

To properly test the P A.X I Communication Mods, (refer to : FAA Approved Airplane Flight Manual Supplement for CAP Special Missions Equipment installed in a Cessna l 82T/TI 82T w/NA VIII A , ·ionics and Dual Audio, document no. AF.MS 18281388 located in Appendix B of this document).

To properly test the TDFM-136 VHF/FM, (refer to: Functional Test Procedures -TDFM-136 VHF/FM Airborne Transceiver, document no. FT2701-34201 located in Appendix G of this document).

Specialized test equipment is required to properly test the KGS RG28 Power Converter/ 28VDC Aux Power, (refer to: Functional Test Procedures - KGS RG28 Power Converter/ 28VDC Aux power, document no. FTl 82813 88-28VDC located in Appendix H of this document). The required testing should be referred to a properly qualified and certified Cessna and/or Garmin approved avionics service organization.

To properly test the COM 3 FM/UHF Audio Switch, (refer to: FAA Approved Airplane Flight Manual Supplement for CAP Special Missions

,,.,. _. Equipment installed in a Cessna l 82Tffl 82T w/NAV III Avionics and Dual Audio, docwnent no. AFMSI8281388 located in Appendix B ofthis document).

Specialized test equipment is required to properly test the optional ARTEX 406 MHZ EL T w/Navigation Interface, (refer to: Functional Test Procedures -AR TEX 110/406 Emergency Locator Transmitter, document no. FT18281388-20 located in Appendix I of this documen.t). The required testing should be referred to a properly qualified and certified Cessna and/or Garmin approved avionics service organization.

6.0 Troubleshooting Information:

For system troubleshooting, perform a functional test as outlined in Testing Requirements - Section 5.3 of this document. If an equipment malfunction is suspected as a result of any failure in the functional test outlined in Testing Requirements - Section 5.3 of this document, return the urut to the appropriate manufacturer or a properly approved and certified avionics service organization.

DOCUMENT ICA18281388-8 REV C

l 111g1mg A VIUtJon

Document ICA 18281388-8 Rev. C

7 .0 Removal and Replacement Information, continued:

To remove the AR TEX 11 0/406 EL T, remove the existing access panel from the aft R/H side of the fuselage, use a # 2 Phillips screwdriver to remove the existing access panel from the aft R/H side of the fuselage. Disconnect interface connectors from the front-end of the EL T assy. Turn the 2 thumbscrews on the mounting cap assy. approx. 3 turns W1til the rnoWlting cap can be freely pulled from the mounting assy. Release the protective top cover assy. and remove the ELT 110/406 from the bottom mounting tray assy. To install the ELT 110/406, reverse the above procedure.

Refer to Master Drawing List MDL2701-34351 for diagrams, access locations and system diagrams.

8.0 Diagrams:

Refer to Master Drawing List MDL2701-34351, AppendixC (WD18218388-14 Rev. D Wiring Diagram w/lPC), and Appendix D (WR 18281388-2 Wire Routing Diagram) of this document for diagrams, access locations and system diagrams. ·

;, ..... ~ .. :. .;,,

-1:~ g·_o Special Inspection Requirements:

None

10.0 Application of Protective Treatments:

None.

11.0 Data Relative to Structural Fasteners:

Refer to Master Drawing List MDL2701-34351 for the appropriate installation drawings. The installation drawings contain all pertinent data relating to proper torque of fasteners.

12.0 Special Tools:

None

DOCUMENT ICA18281388-B REV C

11

Yingling Aviation Document ICA18281388-8 Rev. C

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Appendix A

MDL 2701-34351 Rev. J

Master Document List

Document JCA l 8.281388-8 Re\'. C Ap;,tndix A - l

Yingling Aviation Document No: MDL2Y01 -;;q.:,:::n Maren , ~ . ..::uuo Master Document List Cessna C-182T/T182T Civil Air Patrol FAA STC No. SA01216WI Rev. I

Revision Record

Rcl'ision Date Description By / ApprO\·al

By: IR June 10, Initial Release JAP

2003 Approval: wee By:

A Sept. 18, Updated document to reflect current status of documents and reports JAP 2003 Approval:

wee By:

B May 27, Updated document to reflect current status of documents and reports WC 2004 Approval:

WC C July 9, 2004 Added ID2701-25107 Copilot Instrument Panel lnstl, By:

Deleted FIR2701-3435 l, S.Sauerwein ID2701-25351 was rev A. SA2701-51351 was rev IR. Approval: Deleted revision bv level sheet

D March 8, Added MDL 2701-34351-2 "SPECIAL MJSSIONS EQUIPMENT w/ By: 2005 NA V IIl & Dual Audio" R. Gallop

Avoroval: E March 21 , WDl8218388-14 was Rev A. By:

2005 AFMSl8281388 was Rev IR R. Gallop ~ Aooroval:

F ..... April 6, 2005 Added Compli;311ce Report CRl 8281388, Rev IR By: ..... . R. Gallop

Annraval: G June 27, WD18281388-14 was rev 8, By:

2006 Added Il) I 8281388-10 (IR), R. Gallop Added CPI8281388-I8A. CRl 8281388 was Rev IR, Approval: Added GTP18281388-16 (IR), Added FT1828l388-28VDC, JCA1828l388-8 was Rev IR. EL18281388 was Rev A. and AFMS 18281388 was Rev A.

H March 17, WD18281388-12 was IR, By: 2007 WD18281388-14 was Rev C, R. Gallop

ID2701-23351 W8S Rev.A, and AFMS 18281388 was Rev B Approval:

I March 18, ID2701-343S I was Rev A, By: 2008 CP18281388-18B was CP18281388-18A. R. Gallop

CR18281388B was CR18281388A. FT2701-34224 was Rev. IR. Approval: FT2701-34201 was Rev IR, FTl 8281388-20 was Rev IR, FTI 82813 88-4 was Rev. IR. FT18281388-28VDC was Rev. IR, JCA 18281388-8 was Rev. A. EL18281388 was Rev. B, and AFMS 18281388 was Rev. C.

J Oct 6, FT2701-34224 was Rev. A. By: 2008 FT2701-34201 was Rev A, R. Gallop

FT! 8281388-4 was Rev. A. FT! 828J388-28VDC was Rev. A. Approval : lCA 18281388-8 was Rev. B, YAl20704SA was IR, and CRJ8l 81388B was IR.

2

/). -3

Master Document List Cessna C-182T/T182T CivH Air Patrol FAA STC No. SA01216WI Rev. I

Jv1DL2701-34351-1 SPECIAL l\11S SIONS EQUIPMENT w/ UPSAT AVIONICS

Drawing Number Rev Drawing Title

Wiring Diagrams WO - C-182 Special Mission Avionics Pkg WD2701-34351 * F

WR2701-34351 * B Wire Routing, C-182 CAP Special Mission Pkg

Installation Drawings Installation Mission Equipment 102701~34352,. A

102701-34351 ,. A Installation, OF Antenna 1D2701-23351 ,. A Installation, Antenna VHF-FM

AD2701-25107 • IR Assembly Copilot Instrument Panel 1D2701-24154 * IR Installation, KGS Power Converter 1D2701-23182 * IR lnst'I, SAR-OF 517 Maint Data Port 1D2701-25351 • 8 lnst'I, Observer Station Components AO2701-24400 * IR Assy, Panel OD2701-24400 * IR Panel OD2701-25150,. A Bezel 1D2701-25107 * IR Copilot Instrument Panel lnstl

Floor plan Drawings

FP2701-34351 * A Equipment Layout, C-182 Special Missions Options

REPORTS MDL2701-34351 * J Master Document List, Cessna 1 82 Civil Air Patrol

Special Missions Equipment CP2701-34351 A Certification Plan C-182 Special Missions Avionics

ELA2701-34350 * A Electrical Load Analysis C-1 82 FMS2701-34351 * IR · Flight Manual Supplement C-182 Avionics Special

Missions Avionics FTP2701-34351 B Flight Test Plan C-182 Special Missions Avionics

GTP2701-34351 A Ground Test Plan C-182 Avionics Equipment GTR2701-34351 IR Ground Test Report C-182 Avionics Equipment CR2701-34351 IR Compliance Report C-182 Special Missions

Avionics ICA2701-34351 • IR Instructions for Continued Airworthiness C-182

Special Missions Avionics

4

Yingling Aviation Document No: MDL2701-34351 March 18, 2008 Master Document List Cessna C-182T/T182T Civil Air Patrol FAA STC No. SA01216WI Rev. I ... . - . .

1\.IDL 2701-34351-2 SPECIAL 1\11S SIONS EOUIPl\ffiNT w/ NA VIII & Dua] Audio

Drawina Number Rev Drawing Title Wiring Oiaarams

WD18281388-12 * A W.D.- C-182 ARTEX ELT (optional) WD18281388-14 * D W.D.- C-182 Special Mission Avionics Pkg. WR18281388-2"' IR Wire Routing, C-182 CAP Special Mission Pkg

Installation Drawings 1D2701-34351 * B Installation, DF Antenna 1D2701-23351 * 8 Installation, Antenna VHF-FM 102701-34208 * 8 El T Antenna Installation (optional) YA18281388-1 * IR ELT NAV INTFC &XMTR INSTL (optional) YA18281388-3 * IR EL T NAV Components Rack Assy.

RG-28 Power Converter "Relocate" YA18281388-5 * IR R/H Instrument Panel Mod.

Provisions for #2 GMA-134 7 SAR DF-517 wRelocate• TDFM-136 (FM Rec.) "Relocate" SB Avionics Panel "Renamed SB & relocate panel"

YA18281388-7 * IR Mount Assy. Audio Relay 1D18281388-1 O" IR I nst'I-Aux-Pwr-Relay

REPORTS CP18281388-188 IR Certification Plan C-182 Special Missions Package FTP18281388-16 A Flight Test Plan & Test Report - C-182 Special

Missions Avionics CR182813888 A Compliance Report CAP Special Missions Eouip. YA120704SA A Stress Analysis

GTP18281388-16 IR Ground Test Plan FT2701-34224 * B Functional Test SAR-OF 517 Direction Finder FT2701-34201 * B Functional Test TDFM-136 VHF/FM Comm Sys

FT 18281388-20 -* A Functional Test ARTEX 110-406 EL T (optional) FT 18281388-4 * B Functional Test# 2 GMA-1347 Audio Panel

FT18281388-28VDC * B Functional Test KGS RG28 Power Converter/28VDC Aux Power

ICA 18281388-8 * C Instructions for Continued Airworthiness C-182 Special Missions Equipment w/NAV Ill & Dual Audio

El 18281388 * C Electrical Load Analysis AFMS18281388 * D Airplane Flight Manual Supplement

C 182T w/NAV Ill Avionics & Dual Audio MDL2701-34351 • J Master DrawinQ List

Note: Documents marked with Asterisk (*) are required for follow-on installations.

6

Yingling Aviation Document AFMS18281388

Table of Contents

REVISIONS: . . ... .. .. . . . . .. . .. . .. ... . ... ... ... .. . ... ... . .. . ...... .. ... ..... ... .. ... ..... ... . . 2

TABLE OF CONTENTS.................................................................. 3

SECTION 1 - GENERAL............................................................... 4

SECTION 2 - LIMITATIONS............................................................ 9 2.1 Dual Garmin GMA-1347 Audio Panel Limitations.. . ............................. 9

2.1.l GMA-1347 Audio Panel User's Manual.............................. .. .... ... 9 2 .2 PAX I Communications Modifications Limitations........................... 9 2.3 Becker DF System Limitations................................................... 9

2.3. l Becker DF System User Manual............................................... 9 2.4 Technisonic TDFM-136 VHF/FM System Limitations............... . ........ 9

2.4.1 TDFM-136 User Manual.. ................... : ............................... 9 2.5 KGS Power Converter/ Aux Power Outlet Limitations.......................... 9 2.6 ARN AV RCOM 100 Limitations.............................. .... ............ .... . 9 2.7 Optional COM 3 FM/UHF Audio Switch Limitations...................... . . I 0 2.8 Optional Artex 110-406 EL T System................................ . ............ I 0

SECTION 3 - EMERGENCY PROCEDURES.................................... 11 3.1 Abnonnal Procedures............................................................... J I

3 .1. 1 General ........................................... : . .. . . . . . . . . . . . . . . .. . . . . . . . . . . . . I 1 3. l.2 Electrical Problems........ . . . . . . . . .. . .. . . . . . . . . . . . . . . .. . . . .. . . . . . . .. . . . . . . . . . . . . . J 1 3 .1.3>Artex ELT Abnormal........... . ... . . . . . . .. . . . . . . . . . . . . . . . . . . • . . .. . . . . . . .. . .. . . . 11

--:- 32 Emergency Procedures............................................................ 11 3 .2'.'l Optional AR TEX 110-406 EL T Emergency Procedures .. . .. . . . . . . . . . . . .. 11

-SECTIPN 4- NO~MAL PROCEDURES ..................................... ;.... 13 .•. 4.1 Dual GMA-1347 Audio Panel Nonna! Operation...................... ... ...... 13

4 .1..1. General. . ." ........................................ :............................... 13 4.2 PAX I Communications Modifications Normal Operation..................... 13

4.2.1 Operation ....... .-.. :................................................................ 13 4.3 Becker OF System Nonnal Operation................................ ... ........ .. 13

4.3. l General........................................................................... 13 4 .4 Technisonic TDFM-136 VHF/FM System Normal Operation.................. 13

4.4.1 General.............................................................................. 13 4.5 KGS Power Converter/ Aux.. Power Outlet.................................... 14

4.5.l Operation .......................... ~ . .-........................................... 14 4.6 ARNA V RCOM 100 Normal Operation...... . . . . . .. . . . . . . . . . .. . . . . . . . . . .. . . . . . . . 14

4.6.1 General........................................................................... 14 4.7 Optional COM 3 FM/UHF Audio Switch Nonna! Operation.................. 14

4.7.1 Operation ................................................................... ·..... 14 4.8 Optional AR TEX 110-406 EL T No11T1al Operation . . . . .. .. . . . .. . . .. . .. . . .. .. . . .. 14

4 .8.1 Operation . . . . . . . . . . . . . .. .. . . . . . . . . . . . . . .. . . . . . .. . . . . . . . . . . . . .. .. . . . . . . . . . . . . . . .. . I 4

SECTION 5 - PERFORMANCE...................................................... 15

SECTION 6 - WEIGHT ANO BALANCE............................................. 15

FAA APPROVED CJ.ATE: 4-'2..D - c7 -~--------

Rev. C

3

£.--/

Yingling Aviation Document AFMS18281388 Rev. A

SECTION 1 - GENERAL, continued

DUAL GARMIN GMA-1347 AUDIO PANEL, continued The Pilot and Copilot (or Rear Left Seat passenger [Seat 3] when enabled) positions shall be able to •independently choose which receivers to monitor, COM1, COM2, COM3 (FM or UHF when selected), NAV1, NAV2, TEL, & AUX (OF). The primary (mic selected) COM will automatically be selected along with the corresponding transmitter.

PA, DME, ADF, PLAY, & COM1/2 on both GMA #1 and GMA #2 are disabled. In this installation, pressing the PA, DME, ADF, PLAY, & COM1 /2 keys on either GMA #1 or GMA #2 will not light the corresponding annunciator light.

In dual audio panel configuration the DISPLAY BACKUP and SPKR buttons operate on the pilot side only. n,e SPKR & red Display Backup switches on GMA #2 are disabled .

• -. j· . .

~".-·J"lj.e TEL interface is full duplex and therefore has no transmit priority. Whoever is connected to the phone will transmit whenever they speak and multiple inputs will simply be transmitted simultaneously.

- The TEL interface is designed so that in conjunction with ICS Isolation every - .. group in the airplane can either talk on the phone individually or collectively. · The easiest way to remember this is:

• If TEL interface is lit (LED on) - The Pilot will hear TEL audio • If TEL interface is not lit (LED off) - The Pilot will not hear TEL audio

(others do) • If no TEL audio is desired at all, the satellite telephone must be off

The states of these switches are: ·

TEL audio - TEL selected (TEL illuminated) TEL not selected (TEL not illuminated)

heard is by: '.Nct,s-o: :r:>1idf1scf copliobso Cre~ilSO

Pilot Yes Yes Yes Yes

Copilot Yes No No Yes

Passengers Yes No Yes No

F AP. APPROVED DATE: 3 -~ ~J • os

, ........ . . :• t . •:••

No ISO: ·:Pl16(1s6

No No

No Yes

No Yes

- ·~~-.,-,.: . ·, · : , ..... ',: : . --

· Cb611of1S0

No

Yes

No

5

-. :cr~w:1so,

No

No

Yes

j,., .· :-, . {_-


SECTION 1 - GENERAL, continued

BECKER SAR-DF517 DIRECTION FINDING SYSTEM

Rev. C

The Becker SAR-DF517 direction finding system consists of a Receiver/Antenna located on the aircraft empennage and an indicator/controller located in the Copilot's instrument panel. The System is design to point to the origin of radio signals. The audio from the unit is supplied to the audio panels and is controlled at the audio panels through the AUX switch on the audio panels.

TECHNISONIC TDFM-136 VHF/FM RADIO SYSTEM The Technisonic TDFM-136 VHF/FM radio is located in the Copilot's instrument panel and is controlled on the Audio Panels as COM 3.

KGS 28-14 POWER CONVERTER/ AUX POWER OUTLET The KGS 24-14VDC power converter/ aux power outlet system provides

. 28,VDC & 14VDC to a connector at the PAX 2 seat. The system is activated ~- th.rough a circuit breaker switch in the Avionics Circuit Breaker Panel located · in.the Copilot Instrument Panel. The 28VDC output of the system is ·· regulated to 5 amps by an in-line fuse :located below the co-pilot instrument

panel adjacent to the glove box. The 14 voe output of the system is regulated to 20 amps by a circuit breaker located just aft of the aft cabin wall in the avionics rack area.

ARNAV RCOM 100 SATCOM (optional) The optional ARNA V RCOM I 00 SATCOM consists of a Receiverffransmitter located in the aft baggage area, an Antenna located on the aircraft empennage, and a PTA-12 Telephone Dialer located in the Copilot's instrument panel. The audio from the unit is supplied to the audio panels and is controlled at the audio panels through the TEL switch on the audio panels.

COM 3 FM/UHF AUDIO SWITCH Toe COM 3 FM/UHF switch/annunciator is located in the avionics sub-panel and labeled "COM 3 FM/UHF". Selection of the desired radio allows control of either the TDF:M-136 VHF/FM radio or optional UHF radio at the audio panels on COM 3.

Optional ARTEX 110-406 EL T The ARTEX 110-406 EL T equipment installed consists of the following equipment:

• ARTEX 110-406 MHZ ELT • ARTEX NAVIGATION INTERFACE

FAA .L.PPRO\'ED DJ:.TE : 4- 2-c- c7 7

/· . · r:> --r.

Yingling Aviation Document AFMS18281388 - .. . -· . ~

SECTION 2- LIMITATfONS

2.1 DUAL GARMIN GMA .. 1347 AUDIO PANEL LIMITATIONS

2.1.1 Garmin GMA-1347 Audio Panel User Manual

Rev. B

The manual, or the information contained in the manual listed below (or later applicable revision), must be immediately available to the flight crew.

• G 1000 Cessna Nav III Pilot's Guide (Garmin PIN 190-00498-00, Rev. A, or later applicable version)

2.2 BECKER OF SYSTEM LIMITATIONS

2.2.1 Becker SAR DF517 DF System User Manual The manual, or the information contained in the manual listed below (or later applicable revision), must be immediately available to the flight crew.

• Becker DF System User Manual, Installation and Operation

2.2.2 The Becker SAR DF517 DF is not to be used for primary navigation.

2.3 PAX 1 COMMUNICATIONS MODIFICATION LIMITATIONS NONE

2.4 TECHNISONIC TDFM-136 VHF/FM RADIO LIMITATIONS

2.4. 1 TDFM-136 User Manual The manual, or the information contained in the manual listed below (or later applicable revision), must be immediately available to the flight crew.

• TDFM-136 Installation and Operation Manual 99RE255 rev D.

2.5 KGS 28-14 POWER CONVERTER / AUX POWER OUTLET LIMITATIONS

2.5. 1 The maximum allowable load that can be connected to the AUX POWER OUTLET connector at the PAX 2 seat is 28 VDC@ 5 AMPS & 14 VDC@ 20 amps:

2.6 ARNAV RCOM 100 SATCOM LIMITATIONS

2. 6. 1 ARNA V RCOM 100 User Manual

The manual, or the information contained in the manual listed below (or later applicable revision), must be immediately available to the flight crew.

• ARNAV Systems, Inc. RCOM-100 Pilot Operations Handbook Part No. 572-8050 revision B.

FAA .L-PPROVED D . .u. TE: \ c - \ e · c, [p 9

J:5- ,: :


SECTION3-EMERGENCYPROCEDURES

3.1 ABNORMAL PROCEDURES

3. 1. 1 General

Rev. C

Should any of the Special Missions circuit breakers "trip" or "open" in flight, do !!!!! reset the circuit breaker. If able, turn off the affected system/s.

3.1.2 Electrical Problems If the aircraft experiences electrical system failure, switch both the MISSION MASTER and the ACC OUTLETS circuit breaker switches to the OFF ( down) position.

3.1.3 Optional Artex 110-406 ELT Abnormal If the EL T begins to transmit while still airborne, turn off the EL T at the EL T switch located in the Copilot's instrument panel. Verify using one of the VHF communications receivers set on 121.5 MHz that the EL T is not transmitting a signal.

NOTE: If the EL T continues to transmit even after switching the unit to OFF, notify Air Traffic Personnel of the malfunction and act accordingly.

3.2 EMERGENCY PROCEDURES

3.2.1 Optional Artex 110-406 EL T Emergency

Before performing a forced landing, especially in remote and mountainous areas. activate the EL T transmitter by positioning the remote switch to the ON position. The annunciator next to the rocker switch should be illuminated.

a. Immediately after a forced landing where emergency assistance is required, the EL T should be utilized as follows:

N01E: The EL T remote switch/annunciator subsystem could be inoperative if damaged in a forced landing. If inoperative, the inertia "G" switch wilJ activate automatically. However, to tum the ELT OFF and ON again requires manual switching of the master function selector switch which is located on the EL T urut.

1. Ensure ELT Activation: 2. Position remote switchf a.'lllunciator to the ON position even if annunciator

light is already on.

• 1 .


SECTION 4- NORMAL PROCEDURES

4.1 DUAL GMA-1347 AUDIO PANEL NORMAL OPERATION

4. 1.1 General

Rev. A

The normal operating procedures for the Garmin GMA.134 7 audio system are included in the GI 000 Cessna Nav III Pilot's Guide (Gannin PIN 190-00498-00, Rev. A or later applicable version).

4.2 PAX 1 COMMUNICATIONS MODIFICATION NORMAL OPERATION

4.2.1 Operation With a standard aviation headset plugged into the PAX 1 Mic and Phone jacks, the PAX 1 transmits and receives only through the aircraft's intercom

• _system. When the Seat 2/3 SWAP switch is activated and the passenger in -· the PAX 1 position selects TX with the PAX 1 PTT switch, that passenger will transmit on whatever the Copilot has selected on the GMA #2 audio panel.

Note: The Copilot will have only intercom privileges

during the time the Seat 2/3 SW AP switch is activated.

4.3 BECKER SAR DF517 OF SYSTEM NORMAL OPERATION

4.3.1 General The normal operating procedures for the Becker OF system are included in the User's Guide listed in the limitations section on page 9.

4.4 TECHNISONIC TDFM-136 VHF/FM RADIO SYSTEM NORMAL OPERATION

4.4.1 General Detailed operational instructions are listed in the TDFM-136 Users Guide listed in the limitations section of this document.

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WR 18281388-2

Wire Routing Diagram

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Appendix E

FT18281388-4 Rev. B

Functional Test Procedures GMA1347

Document ICA 18281388-8 Rev. C

Rev. C

Appendix E - 1

Revision Date

IR Feb. 18, 2005

A 18 MAR 08

~ 23 .AUG 08

Revision Record

Description

Initial Release

Title pg., removed Cessna Model designation and inserted STC No. SA01216WI; Sect. 2.0, updated Reference Documents. Document re-written and re-formatted for ciarit~

By I Approval

See sheet one for approvals



' ·'

I

YINGLING AVIATION ::·!3./ ·.US 08 FUNCTIONAL TEST Rev. Q GMA1347 DUAL AUDIO PANEUMARKER BEACON STC No. SA01216WI .

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Table of Contents Revision Record ................................................................................................. 3

Revision Level by Sheet ..................................................................................... 4

Table of Contents ............................................................................................... 5

1.0PURPOSE ........................................................................................................ 6

2.0 REFERENCED DOCUMENTS ....................................................................... 6

3.0 TEST EQUIPMENT NEEDED ......................................................................... 6

.. ~-- ...... '""' ..

· 4~0 TEST REQUIREMENTS ................................................................................. 6

5.0 CHECKOUT PROCEDURES .............................. · ............................................ 7

5~· 1 Marker Beacon Test .................................................. : ...................... 7 5.2 Intercom System Test ....................................... ..... .. ......................... 8 5.3 PAX 1 Communication Modifications Test ............................................. 9 5.4 Com 3 FM/UHF Audio Switch Test .............................................. ........ 9 5.5 ARNAV RCOM 100 Satellite Telephone Test ......................................... 9

6.0 T'EST SUMMARY .... · · · ·· · · · ·• · · · · · · · · · · · · · ·· · · · · · · · · · · · · ·· · ·· · · · · · · · · · · ..•............... • 10

7.0 SIGN OFF SHEET ............................................................................ 11

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YINGLING AVIATION FUNCTIONAL TEST

2S L..L:,3 08 Rev.§

GMA1347 DUAL AUDIO PANEL/MARKER BEACON STC No. SAO 1216WI

5.0 CHECKOUT PROCEDURES

5.1 Marker Beacon Test 5.1 .1 Switch on aircraft master power. 5.1.2 Move Avionics Master switch to "ON". 5.1.3 Locate the HI SENS switch on #1 GMA1347 Faceplate.

Press switch to activate the "HI Sensitivity" mode, note that the corresponding "HI SENS" annunciator light is lit.

5.1.4 Position the 402 Nav .Tester or equivalent in close proximity of Marker Beacon Antenna.

5.1.5 Power up tester and configure to transmit the "Outer Marker" 400 Hz modulated signal.

5.1.6 The Blue light should illuminate on the Primary Flight Display. Verify that a 400 Hz tone is heard in the speaker & headphones.

5.1.7 Configure the 402 Nav Tester or equivalent to transmit the "Middle Marker" 1300 Hz modulated signal.

5.1 .8 The Amber light should illuminate on the Primary Flight Display. Verify that a 1300 Hz tone is heard in the speaker & headphones.

5.1.9 Configure the 402 Nav Tester or equivalent to transmit the "Inner Marker" 3000 Hz modulated signal.

5.1.1 O The White light should illuminate on the Primary Flight Display. Verify that a 3000 Hz tone is heard in the speaker & headphones. ·

5.1.11 Locate the HI SENS switch on #1 GMA1347 Faceplate. Press switch to activate the "Low Sensitivity" mode. Note that the corresponding "HI SENS" annunciator light is not lit.

5.1 .12 Repeat steps 5.1.4 - 5.1: 10. 5.1 .13 Repeat steps 5.1.3 - 5.1.12 for the #2 GMA1347. 5.1.14 Turn off 402 Nav Tester or equivalent.

• I,..,. "IP .... • 1 '='C'= .. ~ P..::l\,I - J. d t:: D~:., :-:-,e-i ..,-. ,.., ____ . .,.., -· ·- · ::._ .. -- ----·· --------·-····-•·· ·· · -- ·--·-·----···----·-··--·-- .p;:,e-,. ,>· .....

YINGLING AVIATION FUNCTIONAL TEST

2t .,.: .. UG 08 - -ReV. £

GMA1347 DUAL AUDIO PANEL/MARKER BEACON STC No. SA01216WI

......

5.3 PAX 1 Communication Modifications Test 5.3 .1 Locate the SEAT 2/3 switch, select SEAT 3 and verify that

radio transmissions from the Rear Left Passenger (Seat 3) can be made on Com 1, Com 2, and Corn 3 radio as selected on #2 GMA 1347.

5.3.2 Verify that the Copilot has intercom capability and cannot transmit on the radio selected on #2 GMA 1347.

5.3.3 Verify the Copilot can receive radio transmissions selected on #2 GMA1347.

5.3.4 Verify that the Pilot has Com 1 transmit priority on #1 · GMA 134 7 and will override Com 1 transmissions made on #2 GMA1347. .

5.3.5 Verify that the Copilot (Seat 3 when selected) has Corn 2 transmit priority on #2 GMA 1347 and will override Com 2 transmissions made on #1 GMA 1347.

5.3.6 Verify proper annunciation/ back-lighting with both "Bright" and "Dim" modes sele·cted.

_Cj,,5.4 COM 3 FM/UHF Audio Switch Test ,

5.4.1 Locate the FM/UHF switch, select UHF and verify that radio transmissions from Pilot on #1 GMA 1347 and Copilot (Seat 3 when selected) on #2 GMA1347 cannot be made on FM, (UHF radio not installed) .

5.4.2 Verify proper annunciation / back-lighting with both "Bright" and "Dim" modes selected.

5.5 ARNAV RCOM 100 Satellite Telephone test, (if installed) 5.5.1 Select TEL on either #1 GMA 1347 or #2 GMA 1347 and verify

the corresponding "TEL" annunciator light is illuminated on both #1 GMA1347 and #2 GMA1347.

5.5.2 Enter test telephone number on the Telephone keypad and verify normal telephone communications can be made.

5.5.3 Move "Avionics Master" switch to off and remove external power from aircraft .

. ,~I __ , --~~g C: ~ -

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YI NGLING AVIATION :2:: .L.. UG 08 FUNCTIONAL TEST Rev. § GMA1347 DUAL AUDIO PANEUMARKER BEACON STC No. SA01216WI ~~zr::r.-c::, ... ~......--..~c::::r:3::tT""f3i':t--~~~~ .. .,~~ .. 't'""~•~~r"'"!,~-~m-ac,-;~';ft~i,C_z.J/,. ... .r;;:, -.... -J~.•;-•--~ ... -~, .~-):"'1':,:;,,.~-..~. -:If-~ ··~v -•-.... _r.f" .. .,4-r ......... rcflt~~"'~:

SIGN-OFF SHEET

TEST ADMINISTRATOR

I CERTIFY THAT I HAVE PERFORMED THE ABOVE TESTS

NAME: DATE: ----------- -----------DISCREPANCIES NOTED:

WITNESS

I CERTIFY THAT I WITNESSED THE EXECUTION OF THE FUNCTIONAL TEST PROCEDURES.

NAME: _______________ _

DATE: ______ _

NOTE: A COPY OF THIS MUST BE FILED WITH THE DRAWINGS AND 337 FORM, IF APPLICABLE.

Docc:rne: '.l: ICA i82£" '.5 SE,-e Re v _: ·- ·---- --- ---··-·------ --- --------.l-·~Pend1.>- E - 11

YINGLING .. AVIATION

FUNCTIONAL TEST PROCEDURES SAR-OF 517

4-BAND PRECISION DIRECTION FINDER STC No. SA01216WI

THIS DOCUMENT CONTAINS INFORMATION OF A PROPRIETARY NATURE ANO SHALL NOT BE TRANSMITTED, REVEALED, OR DISCLOSED TO ANYONE WITHOUT

THE EXPRESS WRITTEN PERMISSION OF YINGLING AVIATION. ADD/TIO NALLY. USE OF THE INFORMA T/ON IS PROHIBITED EXCEPT WHEN EXPRESSLY

AUTHORIZED IN WRITING BY YING/_ING AVIATION.

Document No: FT-2701-34224

Revision: B Date: 23 AUG 08 --- ____ __.;...;.____,.. ____ _..;a~

Prepared in Support of a FAA STC No. _SA01216WI

Prepared By: RB Gallop

Approved By: ________________ _

J Wiginton

Date: ----

Date: ----

-

YINGLING AVIATION Document No FT2701-34224 ;,;E -",~t~C: 2 FUNCTIONAL TEST PROCEDURES SAR-OF 517 4-BAND PRECISION DIRECTION FINDER STC No. SA01216WI Rev. B .... -. .,...,., ~-~:::zn7!33!t::;~~'¥';:?(~~. ~-'l'..-U.•(--.~"~1';"'~~~ 4 ~-.-~•~~,c:-..,w".1.-r:3~,,.?'::"T-""'~•r .~-..::- r1 ,~•:::-~--~~ .-:<"l· v •.- _.;;f"'"~?(?.''"':9°.' • ,:C. , • ~- · • ·•

Revision Level by Sheet

Revision Revision Page Revision Page

Level Page Level Level Cover B

Rev. Rec. B Rev. Lev. B TO.C. B

5 B 6 B 7 8 8 8 9 B

· ' (• -. < ' • 81 " P ~-r, · ,:·u·~1:>:l' l l :' .. ,._,.,:, ,-,, .. , 4

I I I I I I I I I

YINGLING AVIATION Document No FT2701-34224 :&...:.'::u,3DE-FUNCTIONAL TEST PROCEDURES SAR-OF 517_4-BANO PRECISION DIRECTION FINDER STC No. SA01216WI Rev. 6

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1.0 Purpose

This document provides operational checkout instructions for the Becker SAR-OF 517 4-Band Precision Direction Finder.

2.0 Referenced Documents MDL2701-34351 Master Document List STC No. SA01216WI

Becker DF System User Manual, Installation and Operation Installation and Operation Manual

SAR-OF 517

3.0 Test Equipment Needed:

None

4.0 Setup and Checkout

4.1 Power on procedure

Note: When switching on the unit (and only then) the operating mode can be selected by the means of the PAGE rotary switch. There is the choice between the emergency mode with fixed pre-selected emergency frequencies and the training mode. The training mode is characterized by freely selectable training frequencies instead of pre-adjusted emergency frequencies.

(, ' '

YINGLING AVIATION Document No: FT2701-34224 23 .'..,UGOS FUNCTIONAL TEST PROCEDURES SAR-OF 517 4-BAND PRECISION DIRECTION FINDER STC No . SA01216WI Rev. B

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TEST SUMMARY

After all testing is complete , turn off all systems. List any abnormal readings or operations observed during the test.


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Appendix G

FT2701•34201 Rev. B

Functional Test Procedures - TDFM-136

Aprend;x C: - I

Revision Record

Revision Date Description By / Approval

By: RG IR August 21 , Initial Release

2003 Approval: RBG

A 18 MAR 08 Title pg, removed Cessna Model designation and By: RBG inserted STC No. SA01216WI, Sect. 2.0, updated Reference Documents.

Aooroval: JW B 23AUG 08 Document re-written and re-formatted for clarity. See sheet one

for approvals

YINGLING AVIATION Document No: FT2701-34201 FUNCTIONAL TEST PROCEDURES TOFM-136 VHF/FM AIRBORNE TRANSCIEVER STC No. SA01216WI Rev. 8

23 AUG 08

Table of Contents REVISION RECORD ............................................................................................ 3

REVISION LEVEL BY SHEET ............................................................................. 4

TABLE OF CONTENT'S ...................................................................................... · 5

1.0 PURPOSE ................................................................................................. 6

2.0 REFERENCED DOCUMENTS .................................................................. 6

3.0 TEST EQUIPMENT NEEDED: .................................................................. 6

4.0 SETUP AND CHECKOUT ......................................................................... 6

TEST SUMMARY ................................................................................................. 9

SIGN-OFF SHEET .............................................................................................. 10

.....

Dc,~:n,en: iC 1., ; 8:f ,:: ~8 -8 R.~, . C

YINGLING AVIATION Document No: FT2701-34201 23 AUG 08 FUNCTIONAL TEST PROCEDURES TDFM-136 VHF/FM AIRBORNE TRANSCIEVER STC No. SA01216WI Rev. B "'"'~~~'""'-.1~~---n::::x::::el:'<s.""'!'-i:....-.-:r.~-e,~,~-:i-t:,.r ... ~,--.r;-~~ ..... ~.:.-t4"""'1r.M'... ....... ~<•-. .. ~·,,~n:--·2 ~<11(,:Y,-, .... - -:~·,:,.-..~:rr.~<T"P'~"'~..w.o:r~~"i

4.4 Adjust MAIN knob on the TDFM-136 Control Panel to mid-range for volume control.

4.5 Select 1/CHAN on the TDFM-136 Control Panel. Flashing X should be present in the first character of channel display located in the upper left hand corner of TDFM-136 display. Select MAIN channel should be displayed in second row of text displayed on the TDFM-136 control.

4.6 Select channel using the keypad on the TDFM-136 Control Panel. Channel selections are from 001 -200. After selection has been made, press the #/ENTER key on the TDFM-136 Control Panel.

4.7 Select 7/FREQ key on the TDFM-136 Control Panel to edit frequency. Display should show Edit MAIN Frequency with a flashing S or T or R on the second row of the display.

Note: Sx = Simplex, Rx= Receive Only, Tx = Transmit Only. If simplex is chosen then the selected frequency will be applied to both Rx and Tx operation.

4.8 Push the 3/mode key on the TDFM-136 Control Panel to select •·, between Rx/Sx/Tx. Select Sx on the TDFM-136 Control Panel and

press enter.

4.9 The flashing cursor should be positioned in the second character of the frequency window located in the upper right hand display of the TDFM-136. Using the keypad on the TDFM-136 Control Panel, enter a frequency of 141.0000 and press ENTER.

Note: When entering the desired frequency; when an entry is made and the cursor fails to move to the next position to the right, the selection is invalid and another selection must be made.

4.1 o Repeat steps 4.1.6 through 4.1.9 to enter additional channels and frequency on the TDFM-136 Control Panel.

. I ,.- r. 1 - ( · ' ~- r," L-· 1) ·1••• ~•·•n• ](. _f., c,_ .. • : c.< ·,, Is. I

, ....... 11 ... ,.

YINGLING AVIATION Document No: FT2701-34201 23 AUG 08 FUNCTIONAL TEST PROCEDURES TDFM-136 VHF/FM AIRBORNE TRANSCIEVER . STC No. SA01216WI Rev. B

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TEST SUMMARY

After all testing is complete, turn off all systems. List any abnormal readings or operations observed during the test.


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Appendix H

FT18281388-28VDC Rev. B

Functional Test Procedures - KGS RG28

Docwnen: l CA J 82t, I 388-8 Re-Y. C

YINGLING AVIATION FUNCTIONAL TEST PROCEDURES KGS RG28 POWER CONVERTER/28VDC AUX POWER STC No. SA01216WI Rev. B

Revisioh

IR

A

B

Revision Record

.

Date Description

September 25, 2003 Initial Release

18 MAR 08 Title pg., removed Cessna Model designation and inserted FAA STC No. SA01216WI; Sect. 2.0, updated Reference Documents.

23 AUG 08 Document re-written and re-formatted for clarity

D:>:u....,er,'. IC 1 • , 828; 388-8 Rev C

23 AUG 08

·ey, : .. -Apprpval_

By: RG Approval: RBG

By: RG Approval: JW


YINGLING AVIATION 23 AUG 08 FUNCTIONAL TEST PROCEDURES KGS RG28 POWER CONVERTER/28VDC AUX POWER STC No. SA01216WI Rev. B

1.0 PURPOSE

This document pro\ ides operational checkout instructions for the KGS RG28 Power Converter / 28VDC Aux Power system & Mission Breaker Panel Lighting. The system consists of a KGS RG28 Power converter, associated circuit Breakers, and an AUX power receptacle located adjacent to the aft LH seat.

2.0 REFERENCED DOCUMENTS

3.0

MDL2701-34351 Master Document List STC No. SA01216WI

TEST EQUIPMENT NEEDED

A. A locally fabricated load bank capable of providing a minimum of 4 amps continuous load at 28VDC & 10 amps continuous load at 14VDC and capable of connecting to the AUX outlet P2732. For the purposes of this test the device will be referred to as the "LB001 ".

B. Calibrated Multimeter.

NOTE: Prior to the aircraft test verify that LB001 has a minimum of 4 amp current draw at the 28VDC input pins and a minimum of 10 amp current draw at the 14VDC input pins using a power s_upply and a calibrated multimeter.

4.0 TEST REQUIREMENTS

Connect the aircraft to external power to prevent excessive discharge of the battery. For the purposes of this test, the aircraft engine does not need to be running.

NOTE: Prior to the start of the test ensure that the ACC OUTLET CB Switch is selected off (down) and that the 20 amp 12VDC OUTLETS CB is pushed in.

D:,~Jrr11:'.l· ICA "8281388-e Re"· c fa ppend:, ;..: - 5

YINGLING AVIATION FUNCTIONAL TEST PROCEDURES KGS RG28 POWER CONVERTER/28VDC AUX POVVER STC No. SAO 1216\IVI Rev. B

TEST SUMMARY


23 AUG 08

Appendix H - 7


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Appendix I

FT18281388-20

Functional Test Procedures -ARTEX 110/406

Appenci;,..- J - l

Revision

IR

A

·-=-= . ... w,. ~ ... · •-:$~ ,.; .- .;, ....... -

Date

Feb. 18, 2005

18 MAR 08

Revision Record

Description By/ Approval

By: RBG Initial Release

Approval: JW

Removed Cessna Model designation and B:f RBG inserted STC No. SA01216WI.

A,:i :-1 roval :

YINGLING AVIATION Document No: FT18281388-20 FUNCTIONAL TEST PROCEDURES ARTEX 110/406

18 MAR 08

EMERGENCYLOCATOR TRANSMITTER Rev. A STC No. SA01216WI n

Table of Contents Re,,ision Record .................................................................................................................. 3

Re,,ision Le,,.el by Sheet ..................................................................................................... 4

Table of Contents ••..•.••••...........•.................•.....•.•...•.............•.......•..•.....••..•..•.••.••.•.•...•....•• 5

1.0 .:e RPQ~E ........ _ ............................................................................. , ......•......•.........•...•. 6

2.0 RE.FERENCED DOCUMENTS ................................................................................. 6

3.0 TEST EQUIPMENT NEEDED ••••..••••••.•..•.•••••.•••••.•.•••.••.••••.••••••.•••••.•..••••.•.•••••••••.•.•• 6

4.0 REQUIREMENTS-...••....•..........•........•..•..•........•.......•..•...•......•.........••..•.•.•.....•...•...•• 7

5.0 CHECKOUT PROCEDURES .•......•...•.....•.........•.•.•.•.•.•..•.......••........•.....•....•.•••..•••••• 7

TEST SUMMAR.¥ ..•..•....•••..•...•••....•.......•.••..•..•.•••......•......•.••...•....••...•..• ····••fl..a••············· 13 • '"'C

SIGN-OFF SHEET ............................................................................................ ..,,...,.~•ii'° ~d 14 . A . ..,. A 15 ppeDulX •••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• •••••••••••••••••••••••••••••••••••••••••• .. ••••~••-• ... •••

-f: .

f)o::umen· JCA 182f: l ~ 8f!-8 RC', C" Appcndi>; J •

YINGLING AVIATION Document No: FT18281388-20 18 MAR 08 FUNCTIONAL TEST PROCEDURES ARTEX 110/406 EMERGENCYLOCATOR TRANSMITTER Rev. A STC No. SA012"16WI

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4.0 REQUIREMENTS

Aircraft should be stationed inside a metal hangar if possible to minimize the possibility of accidentally alerting the satellite system during testing.

5.0 CHECKOUT PROCEDURES

Note: All functional checks of the EMERGENCY LOCATOR TRANSMITTER

SYSTEM shall be executed during the first five (5) minutes of any hour. Before conducting any EL T test, contact the local FAA Control Tower & inform the appropriate authorities of a pending test; thus avoiding any unnecessary alerts or alarms.

Each EL T 110-406/EL T 110-406ED is individually programmed with specific aircraft information that is processed by Search and Rescue Satellites. . DO NOT INTERCHANGE EL T's BETWEEN . .

AIRCRAFT

5.1 Disconnect both coaxes at the EL T transmitter and connect the portable beacon tester directly to the 406.025 transmitter output per figure 1. (The 121.5 MHz coax is to be left disconnected during the 406 test to minimize local alerts)

ELT 30db min.

SARSAT

TPS (Bottom) Beacon

Connector Attenuator Test Set

FIGURE 1

1-, ' l~,. ,. "f.-~Rc-, C J)()~·.!me:~: (_ !, ' ,.:, , _,o' c, . .

YINGLING AVIATION FUNCTIONAL TEST Document No: FT 182 81388-20 18 MAR 08 ARTEX 110/406 PROCEDURES

SETMERGENCYLOCATOR TRANSMITTER Rev. A C No. SA01216WI

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b. ff an "S' TEST BAD" or "DATA ERROR" message appears, there is a problem with the EL T (i.e. a programming problem or a problem with the transmitter module) or the battery pack.

c . If there is not a 406.025 Mhz transmitter burst present, check the 3.0 amp fuse on the circuit board in the battery pack for an open condition. If the fuse is good, there is most likely a problem with the 406.025 MHz module or its interconnections.

5.4 Refer to Appendix A for the Beacon Test Set display contents of each specific page as described in the following steps.

5 .5 Page 1 is the main menu screen. Press "V" for view to see

5.6

5.7

5.8

Note:

received message or scroll using "up" and "down" arrow keys to v iew other messages. Use "left" and "right" arrow keys to scroll between pages.

Page 2 contains the Date and Time that the message was received. Also included is an indication of whether the message was received properly. Verify that the third or bottom line reads us• TEST OK. "

Page 3 is a frequency and country code page. The frequency must read between 406.030 and 406.020 MHz to pass. The programmed country code must be the same country as the aircrafts home base. Verify that the second line of the display reads "PASS". Verify that the country code is the same as the aircraft 's home base.

Page 4 contains the com~lete me~sage_ in Hexadecimal notation. The third line is an ID string that 1s unique to the beacon being tested. Verify that ID string on the third fine matches the ID printed on the product label of the 406 EL T.

For EL T's installed with an EL T/NAV Interface where the interface is used to encode the 24 bit aircraft address, the EL T will be automatically re-programmed by the interface and will need to be re-labeled with the new 15 digit hex ID string.

I ll. A ,' f"f; J ':.~~-F. Re, . C n ... J •ncn ' - - Appe11d i~. I - <,

YINGLING AVIATION Document "10 : FT18281388-20 18 MAR OB FUNCTIONAL TEST PROCEDURES AR TEX 110/406 EMERGENCYLOCATOR TRANSMITTER Rev. A STC No. SA01216WI

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5.21 Monitor the received audio from the communications receiver. Verify reception of the characteristic repeating downward tone sweep of an EL Tin operation.

5.22 Move the transmitter located control switch from the "ON" position to the "OFF"(ARMED) position.

5.23 Verify that the red LED on the Remote Control Switch Panel goes out and the EL T tone is removed from the Comm audio.

5.24 Move the switch on the Remote Control Switch Panel from "ARM" to "ON" until three sweeps of the EL T tone are heard. Immediately move the switch to "ARM".

5.25 Verify that the LED on the Remote Control Switch Panel flashes during the test and remains on continuously for approximately one second after the switch is returned to "ARM" position then

.- , extinguishes. T

5.26 Turn off aircraft power . . ,

5.27 Switch the cockpit mounted control switch to "ON" for approximately 2 - ·3 seconds then return to "ARM". Verify that the LED on the Remote Control Switch Panel flashes and remains on continuously for approximately one second after the switch is returned to "ARM" position. This verifies the LED is powered from the aircraft hot buss.

Ap;,end i, ., - ; ;

YINGLING AVIATION Document No: FT18261388-20 18 lvlAK uo FUNCTIONAL TEST PROCEDURES ARTEX 11 0/406 EMERGENCYLOCATOR TRANSMITTER Rev. A STC No. SA01216WI n::s:s:-1"=r:31r'35!::sr:re::r:.,_,,.,:::s:-7~r;r-e.~~~~~~;,u,..,~•=N·..r-';~.:se:::r:::~ ·• :e:r :..-~·0 ..... ': rricr •:-m~.as=-·•,, ...... 11!:"..l.."".3•rm::.,.. - 'lJr,..~ f1al\.~-r:ms:r.n"""'fr,T

TEST SUMMARY


Appcr,d i~ I - 13

' ""'-='L"'"'-.:, AVIA I IUN Document No: F I 18:Ctl1jtstJ-LU FUNCTIONAL TEST PROCEDURES ARTEX 110/406 EMERGENCYLOCATOR TRANSMITTER Rev. A STC No. SA01216WI

Appendix A

BEACON TEST SET DISPLAYS

Dci:u men: IC A '. S:f! J: Sl -8 Re, . C

YINGLING AVIATION Document No: FT18281388-20 18 MAR OB FUNCTIONAL TEST PROCEDURES ART EX 110/406 EMERGENCYLOCATOR TRANSMITTER Rev. A STC No. SAO 1216WI ~?_,.,...,,.,. •. ....,,,.~"'?Tt--,,...""•_...i,._..,::r ~~m:,;~• n:.e$ w:,MPW\,~~-••5-eetlj,~~,rf~;m;l"3::::r::v . ..--:zr::~-~"'":' . .-,-.,•...,.~.,..-r:a:::r:n~.P •• . ~ •

PAGE 6 (VIEW MODE)

t .J, ~ • FL Q EP Mesg #1 STD LOG Homing: 121.5 MHz BCH: 19AID7 VALID

PAGE 7 (VIEW MODE)

t -J, +- • F L Q EP Mesg #1 Other info:

Long Mesg.

PAGE 8 (VIEW MODE)

t .J, ~ • F L Q . EP Mesg #1 Other info: Lat : 45N23.4 Long: 122Wl5.l

PAGE 9 (MENU OPTIONS)

SARSAT BEACON TESTER Recv Erase

View Setup

Quit Output

VERIFY HOMING FREQUENCY

VERIFY LONG MESSAGE

VERIFY LATITUDE AND LONGITUDE OF 45DEGREES 23.4 MINUTES NORTH, 122 DEGREES 15.1 MINUTES WEST

PRESS "Q" TO RETURN TO MAIN SCREEN PAGE

/.ppetdi'- I - I 7