eo. no - avianca

A320HC54-113/12 R0EO. No:

11/07/2012Rev. Date: Pag 2 of 47

ENGINEERING ORDER

FORM QA-073/96 TS-F R0

Date: 11/07/2012

During current heavy check Nicks and Scatches were found on Engine #1 Intake Cowl Inner Barrel.

Damages were out of V2500 SRM limits due to number and distances between damages. Goodrich was

contacted for assessment as per Ref./A/ and Ref./C/. Goodrich provided assessment as per Ref./B/

and Ref./D/.

This repair has been classified as minor and permanent by means of Ref./E/.

ENG. ASSESSMENT:

REFERENCES: COMPLIANCE

/A/

/B/

/C/

/D/

/E/

PCW

FCW

PCW

FCW

FCW

NDD Report: AEM-12-03152/001

Goodrich Definition Sheet: CV12-4814 REV A

NDD Report: AEM-12-03152/002

Goodrich Definition Sheet: CV12-4814 REV B

Repair Design Approval Sheet: ROHR/S177/2012 Issue B

INTAKE COWL 745-3000-511 0868001 Currently installed on A/C A320-233,

N493TA (MSN: 2917) Engine #2.

AIRCRAFT MODEL /

COMPONENT

P/N S/NREMARKS

EFFECTIVITY:

A320HC54-113/12 R0EO. No:

11/07/2012Rev. Date: Pag 3 of 47

ENGINEERING ORDER


Date: 11/07/2012

DISTRIBUTION LIST

(Planning will distribute all copies)

Technical Records

Stockroom

Reliability

Line Maintenance

Hangar Maintenance

Flight Operations

Quality Control

Quality Assurance

Technical Publicactions

Warranty

Other

..............

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..............

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Comments:

PUBLICATIONS AFFECTED

None

LABOR ESTIMATE:

DOCUMENT NUMBER DOCUMENT TYPE TITLE

SUPPORT DOCUMENTATION

SKILLS: CREW: MAN-HRS: ELAPSED:

12-34-24

54-10-00

54-10-00

AMM

V2500 SRM REPAIR #15

V2500 SRM REPAIR #29

AIRCRAFT GROUNDING - MAINTENANCE PRACTICES

AIR INTAKE COWL ACOUSTIC STRUCTURE SURFACE DAMAGE

REPAIR

AIR INTAKE COWL ACOUSTIC LINER FACING SHEET HOLE

REPAIR

COMP

INS

1

1

30

5

30

5

TOTAL: 2 35

None

---

Chapter Publications

X

X

35

A320HC54-113/12 R0EO. No:

11/07/2012Rev. Date: Pag 4 of 47

ENGINEERING ORDER


Date: 11/07/2012

PARTS AND MATERIALS (Per Unit)

PART NUMBER DESCRIPTION QTY UNIT P.O./M.R. REMARKS

--- NA --- REFER TO EO INSTRUCTIONS

TOOLS

PART NUMBER DESCRIPTION QTY P.O. REMARKS

--- --- REFER TO EO INSTRUCTIONS

ENGINEERING ORDER E.O. No: A320HC54-113/12 R0 DATE: 11/07/2012 Rev. No: 0 PAGE: 5 of 47 SUBJECT: ENGINE #2 – INLET COWL – INTAKE BARREL WITH SCRATCH ES AND NICKS – REPAIR. FREQUENCY: NA TAIL: STATION: DATE:

MECHANIC Q.C. INSTRUCTIONS

FORM QA-073/96-TS-F R0

XXX XXX ACCOMPLISHMENT INSTRUCTIONS

IMPORTANT: PLEASE READ THIS INFORMATION CAREFULLY BEFORE

PROCEEDING WITH THE STEP-BY-STEP INSTRUCTIONS. WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE

CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES.

1. Make sure that the Aircraft is electrically grounded (refer to AMM

task12-34-24 page block 201)

2. Perform DVI IAW NTM 51-90-00 to confirm damage area location and

dimensions are IAW Ref. /A/.

3. Perform tap test on damage area to confirm damage area location and

dimensions are IAW ref. /A/.

XXX XXX A. REPAIR INSTRUCTIONS

XXX

1. Verify that Intake Cowl Engine #2 part and serial numbers are as follows:

P/N: 745-3000-511; S/N: 0868001

Any discrepancy?

If YES, contact Engineering for further assessment.

If NO, continue with the next step.

2. Inspect the damaged areas and confirm the damage is as reported in Ref. /A/ and Ref./C/.

Any deviation or propagation?; YES ( ); NO ( )

If YES contact Engineering for further assessment. If NO follow next step of this EO.

XXX 3. Clean the areas with MEK and a lint free cloth, wipe dry prior to solvents

evaporation.

4. The damaged areas identified as condition “C1” are to be repaired using the materials and methodology contained in SRM section 54-10-00 Repair #15 “AIR INTAKE COWL ACOUSTIC STRUCTURE SURFACE DAMAGE”.

ENGINEERING ORDER E.O. No: A320HC54-113/12 R0 DATE: 11/07/2012 Rev. No: 0 PAGE: 6 of 47 SUBJECT: ENGINE #2 – INLET COWL – INTAKE BARREL WITH SCRATCH ES AND NICKS – REPAIR. FREQUENCY: NA TAIL: STATION: DATE:

MECHANIC Q.C. INSTRUCTIONS

FORM QA-073/96-TS-F R0

5. The damaged areas identified as condition “C2” are to be repaired using the materials and methodology contained in SRM section 54-10-00 Repair #29 “AIR INTAKE COWL ACOUSTIC LINER FACE SHEET HOLE REPAIR”

6. Vibro-etch the OTC number S1218B on the component serial plate and/or

record in the aircraft log book.

7. Ensure cumulative acoustic attenuation loss limit is not exceeded IAW IAE SRM 54-01-00

Any discrepancy? YES [ ] NO [ ]

If YES, contact Engineering for further instructions.

If NO, continue with the next step.

XXX XXX End of this E.O.

XXX

XXX The following step is for documentation purposes only and is not related to the actual

tasks performed on the subject aircraft.

XXX

XXX

TECHNICAL RECORDS : Insert a copy of this Engineering Order in the records of the subject aircraft and component.

Name: ______________________________

Title: _______________________________

Date: _______________________________

Signature: ___________________________

Rohr, Inc., a subsidiary of the Goodrich Corporation, operating as Goodrich Aerostructures Group FORM NO. E8210-4

Rohr, Inc., operating as Goodrich Aerostructures Group

NACELLE DAMAGE DESCRIPTION AFTERMARKET TECHNICAL SERVICES ENGINEERING 850 Lagoon Drive, Chula Vista, CA 91910-2098

REQUEST TYPE: *DATE REQUIRED: 10/30/2012

CRITICAL REPAIR (Work Stoppage) AOG (2-4 Hrs) A/C LOCATION EL SALVADOR

ROUTINE REPAIR A/C NEXT SCHEDULED FLIGHT 11/05/2012 GENERAL INFORMATION A/C TAIL REGISTRATION

NUMBERN493TA

Inaccurate or missing information can result in delay s. Please forward all other information ava ilable (photo, etc.) to help p rovide a clear and complete damage description. Pictures may be inserted under the “Damage Description” section. For AOG Request, please contact the Good rich Spares Sales Desk at (619) 691-2089 or [email protected] and a response will be provided within 2 to 4 hours after receipt of the complete damage.

Important Note: All *RED highlighted blocks must contain an entry in order to process a repair request.

CUSTOMER INFORMATION

Maintenance Facilities Name: Date: 10/29/2012 *Operator: TAI Location: El Salvador C.A.

Contact: Jose Canjura Ref No.: AEM-12-03152/001

Tel: (503) 2312-4468 Fax:

E-mail: [email protected] P.O. No.

AIRCRAFT INFORMATION

*Engine Type: V2500-A5 *Aircraft Type: A320-233 Engine S/N: *Aircraft Registration: N493TA

*Engine Position: ENG #2 (RH) *Aircraft MSN: 2917

Engine Flight Hours: *Aircraft Flight Hours: 23,183

Engine Flight Cycles: *Aircraft Flight Cycles: 9,324

PARTS INFORMATION

DESCRIPTION *PART NUMBER *NAME *SERIAL NUMBER

*A/C Component: 745-3000-511 RH Inlet Cowl 0868001

Affected Part

Affected Part

Affected Part

*SUMMARY

Nicks and scratches common to the inner barrel wire mesh.

*REPORT ANY PREVIOUS REPAIR IN THE DAMAGED AREA

See following pages for details.

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A320HC54-113/12 R00 PAGE 7 OF 47 REF. /A/: SHEET 1 OF 10



DAMAGE DESCRIPTION PAGE 2 OF 10


SUBJECT

ENGINE POSITION 2 – INLET COWL – INTAKE BARREL SEVERAL DAMAGES Goodrich team, please take into account this report that has been updated since more damages were found. Refer to the attached figures for the classification, location and dimensions. The following actions have been taken in order to assess these damages: 1. Tap test performed and no further damage exists. 2. DV inspection performed and no other damage found. IAW V2500 SRM 54-10-00 no repair is applicable for the damage situation described by this report. Aeroman proposes the following: Repair the damages that are unrepaired using the materials and methodology contained in SRM 54-10-00 Repair #15, even for those that do not meet with the minimum required distance between damage areas; after ensuring that the cumulative repair limit is not exceeded by the combination of these repairs with any previous repair. ACTION Aeroman request from Goodrich the following:

1. To take this report into account instead of previous report in order to address all damages. 2. An answer by October 30th, 2012 will be highly appreciated.

Thank you for your continuing support. Best regards. Jose Canjura

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A320HC54-113/12 R00 PAGE 17 OF 47 REF. /B/: SHEET 1 OF 10

Rohr, Inc., operating as Goodrich Aerostructures DEFINITION SHEET AFTERMARKET TECHNICAL SERVICES ENGINEERING 850 Lagoon Drive, Chula Vista, CA 91910-2098

DOCUMENT NUMBER

CV12-4814 REV A ORIGINAL DATE: PAGE

15TH OCTOBER 2012 2 OF 10

HAZARDOUS MATERIALS WARNING

Before you work with any component, assembly or product referred to in this document, read, understand and obey all safety ins tructions and take all appropriate safety precautions. Th ese instructions include ins tructions fr om the manufacturer, the material s afety d ata sheet ( MSDS), th e component maintenance man ual, s ervice info rmation letters, all operators let ters, and gove rnment regulations. A MSD S gives instructions on how you must safely use, keep and d iscard chemicals. Ge t ins tructions from your emp loyer on how you must sa fely use, keep and discard chemicals. Chemicals may cause injuries to you or make you sick. Personal injury or disease may result if safety instructions are not obeyed.

THIS DOCUMENT IS SUBJECT TO THE CONTROLS AND RESTRICTIONS ON THE FIRST PAGE. FORM NO. E8207-8

REPAIR INSTRUCTIONS

1. INSPECT THE DAMAGE AREAS AND CONFIRM THE DAMAGE IS AS REPORTED. ANY DEVIATION OR PROPAGATION MUST BE REPORTED FOR FURTHER DISPOSITION.

2. CLEAN THE AREAS WITH MEK AND A LINT FREE CLOTH, WIPE DRY PRIOR TO SOLVENTS

EVAPORATION.

3. THE DAMAGE AREAS IDENTIFIED AS CONDITION “C1” ARE TO BE REPAIRED USING THE MATERIALS AND METHODOLOGY CONTAINED IN SRM SECTION 54-10-00 REPAIR #15 “AIR INTAKE COWL ACOUSTIC STRUCTURE SURFACE DAMAGE”.

4. THE DAMAGE AREAS IDENTIFIED AS CONDITION “C2” ARE TO BE REPAIRED USING THE MATERIALS

AND METHODOLOGY CONTAINED IN SRM SECTION 54-10-00 REPAIR #29 “AIR INTAKE COWL ACOUSTIC LINER FACE SHEET HOLE REPAIR”.

5. VIBRO-ETCH THE OTC NUMBER S1218A ON THE COMPONENT SERIAL PLATE AND/OR RECORD IT IN

THE AIRCRAFT LOG BOOK.

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DEFINITION SHEET AFTERMARKET TECHNICAL SERVICES ENGINEERING 850 Lagoon Drive, Chula Vista, CA 91910-2098

DOCUMENT NUMBER

CV12-4814 REV A DATE: PAGE


FORM NO. 8207-4

FIGURE 1

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REQUEST TYPE: *DATE REQUIRED: 10/30/2012

CRITICAL REPAIR (Work Stoppage) AOG (2-4 Hrs) A/C LOCATION EL SALVADOR

ROUTINE REPAIR A/C NEXT SCHEDULED FLIGHT 11/05/2012

GENERAL INFORMATION A/C TAIL REGISTRATION NUMBER

N493TA

Inaccurate or missing information can result in delays. Please forward all other information available (photo, etc.) to help provide a clear and complete damage description. Pictures may be inserted under the “Damage Description” section. For AOG Request, please contact the Goodrich Spares Sales Desk at (619) 691-2089 or [email protected] and a response will be provided within 2 to 4 hours after receipt of the complete damage.

Important Note: All *RED highlighted blocks must contain an entry in order to process a repair request.

CUSTOMER INFORMATION

Maintenance Facilities Name: Date: 10/29/2012

*Operator: TAI Location: El Salvador C.A.

Contact: Jose Canjura Ref No.: AEM-12-03152/002

Tel: (503) 2312-4468 Fax:

E-mail: [email protected] P.O. No.

AIRCRAFT INFORMATION

*Engine Type: V2500-A5 *Aircraft Type: A320-233

Engine S/N: *Aircraft Registration: N493TA

*Engine Position: ENG #2 (RH) *Aircraft MSN: 2917

Engine Flight Hours: *Aircraft Flight Hours: 23,183

Engine Flight Cycles: *Aircraft Flight Cycles: 9,324

PARTS INFORMATION

DESCRIPTION *PART NUMBER *NAME *SERIAL NUMBER

*A/C Component: 745-3000-511 RH Inlet Cowl 0868001

Affected Part

Affected Part

Affected Part

*SUMMARY

Nicks and scratches common to the inner barrel wire mesh.

*REPORT ANY PREVIOUS REPAIR IN THE DAMAGED AREA

See following pages for details.

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A320HC54-113/12 R00 PAGE 27 OF 47 REF. /C/: SHEET 1 OF 10





SUBJECT

ENGINE POSITION 2 – INLET COWL – INTAKE BARREL SEVERAL DAMAGES Goodrich team, please take into account this report that has been updated since more damages were found. Refer to the attached figures for the classification, location and dimensions. The following actions have been taken in order to assess these damages: 1. Tap test performed and no further damage exists. 2. DV inspection performed and no other damage found. IAW V2500 SRM 54-10-00 no repair is applicable for the damage situation described by this report. Aeroman proposes the following: Repair the damages that are unrepaired using the materials and methodology contained in SRM 54-10-00 Repair #15, even for those that do not meet with the minimum required distance between damage areas; after ensuring that the cumulative repair limit is not exceeded by the combination of these repairs with any previous repair. ACTION Aeroman request from Goodrich the following:

1. To take this report into account instead of previous report in order to address all damages. 2. An answer by October 30th, 2012 will be highly appreciated.

Thank you for your continuing support. Best regards. Jose Canjura

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A320HC54-113/12 R00 PAGE 37 OF 47 REF. /D/: SHEET 1 OF 10

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RDAS Ref: RDAS Issue: B Page 1 of 1A/C Type: MSN: ATA: FC:P/N: S/N: FH:Title:

Damage Description:

Repair Description:

Regulations involved in addition to Certification Basis:

Part 21A.449 Instructions for Continued Airworthiness:Inspection areas : see details in Box 12

Threshold (or Inspection Starting Point) * :Interval :Method of Inspection :

ALS Part 2 inspection tasks adversely affected YES

Part 21A.443 Limitations:Repair Life Limitation ** :Repair Structural Modification Point (SMP) :Other Limitation :

ALS Part 1 & Part 4 limitations adversely affected YES** If no repair category is indicated in Box 17, life limitation may be further extended after detailed analysis

Part 21A.435 Classification: 17. Repair Category:

MAJOR A X Permanent repair with no additional requirements

X MINOR B Permanent repair with inspection required

C Temporary or life limited repair

Designated Airworthiness Engineer ApprovalName: Signature: Date:

CV12-4814 REV B (OTC S1218B)Ref:

For all damages that go through only the wire mesh, repair per SRM 54-10-00 Repair 15; removing damaged wire mesh, filling damaged area underneath with adhesive and applying a repair ply. For all damages that go through the wire mesh and the Brochier face sheet, repair per SRM 54-10-00 Repair 29; drill through damaged area until sectum layer, and fill hole with EA934NA epoxy paste adhesive.Note: The operator must, however, check to ensure that the cumulative acoustic attenuation loss limit is not exceeded by the combination of this repair with any previous repair.

54-100868001745-3000-511

INLET COWL - NICKS AND SCRATCHES ON WIRE MESH

A320-233

Repair Design Approval Sheet

* If not otherwise specified, threshold is from time of repair embodiment

If not otherwise specified, limitation is from time of repair embodiment

2318393242917

ROHR/S177/2012

M.S.Lai

Customer has found altogether Qty. 9 nicks and Qty. 3 scratches on acoustic panels "P", "N" and "Q" on the inlet cowl of Engine #2. The maximum nick dimensions are 0.478" long x 0.145" wide through wire mesh and the Brochier facing sheet with a distance of 1.5" to an existing repair. The maximum scratch dimensions are 1.0" long x 0.080" wide on the wire mesh only. The operator has requested an OTC to repair the reported damages as the damages have less seperation than the limits quoted in SRM 54-10-00 Repair. Issue B is raised to amend reported damage.

Nov. 6, 2012

The technical information described above is approved under the authority of EASA approved Design Organisation Number EASA 21J031 and per EASA rules Part 21 Subpart M. This approved data is based on the information provided by the requester to Airbus. Airbus disclaims any and all responsibilities for incorrect, inaccurate or incomplete information provided by the requester (including modification and Supplemental Type Certificate status). If this structural repair affects the compliance to a mandatory requirement, it is the operators' responsibility to obtain the necessary approval from its National Aviation Authority.

APPROVED UNDER EASA DESIGN ORGANIZATION APPROVAL

EASA.21J.031

FM1002568_v1 © Airbus SAS 2011. All rights reserved. Confidential and proprietary document

M.S.Lai 2012.11.06 14:36:41 -08'00'

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A320HC54-113/12 R00 PAGE 47 OF 47 REF. /E/: SHEET 1 OF 1

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