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© Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2021-0719, the docket of AD 2021-18-08. Not covered by OpenAirDocs’ CC0 dedication.
© Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2021-0950, the docket of AD 2021-23-05. Not covered by OpenAirDocs’ CC0 dedication.
© Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2021-0950, the docket of AD 2021-23-05. Not covered by OpenAirDocs’ CC0 dedication.
- Manufacturer
- Airbus
- Type
- All Operators Transmission
- Number
- A29N008-16
- Latest revision known
- A29N008-16, Revision 2, dated January 23, 2019
- Copies
- 3 files of 3 revisions
A newer revision may exist than any OpenAirDocs knows of: check with the manufacturer.
Text · 6
Revision 2, the newest copy. From the PDF’s text layer: layout, tables and figures are lost. The PDF is the document. © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2021-0719, the docket of AD 2021-18-08. Not covered by OpenAirDocs’ CC0 dedication.
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CUSTOMER SERVICES DIRECTORATE 2 ROND POINT EMILE DEWOITINE 31700 BLAGNAC FRANCE TELEPHONE + 33 (0)5 61 93 33 33
ALERT OPERATORS TRANSMISSION - AOT AOT ref: A29N008-16 Rev 02 Page 1 of 6 Date: 23-JAN-2019 © AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT SUBJECT: ATA 29 – A320NEO FAMILY-PYLON/ENGINE INTERFACE ROD END INSPECTION AIRCRAFT TYPE: A320,A321 OUR REF: A29N008-16 Rev 02 dated 23-JAN-2019 OUR PREVIOUS REF: A29N008-16 Rev 01 dated 05-JAN-2017 OUR PREVIOUS REF: A29N008-16 Rev 00 dated 03-JAN-2017
0. REASON FOR REVISION ***BEG REV*** -This AOT is revised to add the final fix and to clarify the aircraft affected by the rod end inspection.
-Torque Value added for the body rod nut.
-AOT A29N008-16 Rev 02 cancels and supersedes AOT A29N008-16 Rev 01.
***END REV*** The revised paragraphs are indicated between **BEG. REV** and **END REV**.
1. AIRCRAFT AFFECTED ***BEG REV*** This AOT applies to all A320NEO and A321NEO aircraft with PW engines only and pre mod 163348 or pre SB A320-29-1189.
NOTE: The AOT inspection A29N008-16 Rev 02 is not applicable to aircraft post mod 163348 or post SB 29-1189 because they are equipped with the new rods P/N D0003107000400 and D0003107000600.
***END REV***
2. REFERENCED DOCUMENTATION
2.1 APPENDIX Appendix 1: AOT Aircraft inspection report sheet
2.2 REFERENCES Ref 1: AMM Task 78-36-00-010-802-A “Opening of the Thrust Reverser Cowl-Doors” Ref 2: AMM Task 78-36-00-410-802-A “Closing of the Thrust Reverser Cowl Doors” Ref 3: IPC 29-11-86-03A LH Pylon (Items 440, 450) P/N D0003107000200 and D0003107000000.
Ref 4: IPC 29-13-86-03A RH Pylon (Items 360, 370) P/N D0003107000200 and D0003107000000.
Ref 5: AMM Task 20-11-11-911-001-A Safety by Wirelocking Ref 6: Technical Follow-up (TFU) 29.00.00.084 – A320NEO Family PW Rod Damage at Pylon/Engine Hydraulic Interface.
Ref 7: Mod 161775; SB A320 29-1169 “Define and Install EDP in Line Damper for NEO Equipped with PW Engines” Ref 8: Mod 163348; SB A320 29-1189 “Change Material of Rods Ends at Dog-Head Location”
ALERT OPERATORS TRANSMISSION - AOT AOT ref: A29N008-16 Rev 02 Page 2 of 6 Date: 23-JAN-2019 © AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
3. REASON Hydraulic and fuel pipes from the engine are connected to the pylon through a pylon / engine interface plate. This interface plate is secured to the pylon structure with a set of two rods and brackets.
There is the same installation and parts on both left (LH) & right (RH) pylons.
The purpose of this AOT is to inspect these rods on both pylons and repeat the inspection every 750FH.
In case of finding, the rod(s) is/are to be replaced prior next flight.
3.1 FACTS During Removal / Installation of a PW engine from A320 Neo aircraft, an operator discovered wear on the eye ends of both rods (ref: 3 & 4).
3.2 CONSEQUENCES A degradation of rod eye ends could with time induce a failure of the rod with possible chafing with fuel tube located underneath the rod.
3.3 AIM The aim of this AOT is to:
-Request a repetitive inspection of the rods (ref: 3 & 4) located on the pylon interface to determine that there is no axial or radial play in the rod eye ends.
-In case of finding, it is requested to the operator, to visually inspect the pylon fittings, interface plate (fittings, brackets) and to replace the rod.
4. SHORT TERM ACTION
4.1 PLANNING AND MANPOWER
4.1.1 ACCOMPLISHMENT TIMESCALE -For A/C having already accumulated 375FH, at the date of issuance of this AOT, perform the first inspection within the next 375FH. Then repeat the inspection every 750FH.
-For A/C having accumulated less than 375FH at the date of issuance of this AOT, perform this inspection prior reaching 750FH. Then repeat the inspection every 750FH.
4.1.2 MANPOWER The estimated time to inspect and replace the 2 rods is 3 hours (elapsed time) per pylon.
4.2 DESCRIPTION The following procedure consists in an inspection of the pylon interface rod end eyes for ensuring that there is no wear, no axial and radial play.
The procedure has to be performed on the LH and RH pylons.
The hereafter described procedure is for LH pylon, for RH pylon the item numbers which are different to the LH pylon are in brackets.
For details refer to (ref: 3) for LH pylon and to (ref: 4) for RH pylon.
ALERT OPERATORS TRANSMISSION - AOT AOT ref: A29N008-16 Rev 02 Page 3 of 6 Date: 23-JAN-2019 © AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
4.2.1 INSPECTION PROCEDURE
1) In the cockpit on the overhead panel and ENG START section of panel 22VU: Put a WARNING NOTICE in position to tell not to start engines.
2) Get Access:
a) Put an ACCESS PLATFORM 3m (10FT) ADJUSTABLE in position and open the thrust reverser cowl-doors (ref: 1).
b) Put on and attach a SAFETY HARNESS before you start work in the work area.
3) Inspection of the installed rods (ref: 3 & 4):
Note: to inspect the rod it is not necessary to remove it, if it is installed in stress free condition.
Manually turn the body of the rod to check if the rod is installed in stress free condition:
a) If a partial rotation movement of the rod is possible then the rod is not under stress installation.
Do a visual inspection of the rod and make sure that there is no wear, no axial and radial play between the rod eye ends and the rod body, no play is permitted, If wear or play is detected, remove the rod, go to para 4.2.1.3)c).
If no wear or no play is detected. Go to para 4.2.2
b) If a partial rotation movement of the rod is not possible then the rod is installed under stress condition. Release stress in rod installation prior its removal:
Put the rod in stress free condition before removal, cut and discard the lock wires from the rod Items 440 (360) and 450 (370), unscrew the nuts from the body rod and turn the body in order to get the rod in free stress condition (see picture here below).
c) Remove the 2 rods (Ref: 3, 4 and here below extracts) Turn the body to adjust the rod length Nuts to be unscrewed for rod adjustment
ALERT OPERATORS TRANSMISSION - AOT AOT ref: A29N008-16 Rev 02 Page 4 of 6 Date: 23-JAN-2019 © AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT Remove the nut item 15, the washer item 25, the bolt item 35 and the washer item
25.
Remove the rod item 440 (360) or 450 (370).
Remove the bush item 430 (350) from the fitting item F1, F2 and from the interface plate item 420 (340).
.
4) Inspection of the removed rod (Ref: 3 & 4):
a) Do a visual inspection of the rod (see picture) and make sure that there is no wear, no axial and radial play between the rod end eye and the rod body, no play is permitted,
b) If any wear or play is detected, replace the rod A B A B F3 F2 F1 F4 F1 F4 F3 F2 Wear/Fretting marks
Wear marks
ALERT OPERATORS TRANSMISSION - AOT AOT ref: A29N008-16 Rev 02 Page 5 of 6 Date: 23-JAN-2019 © AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT NOTE:
The rod eye ends features as per design two machined lights to easy insertion of the rod ball.
5) Visual inspection of the structural parts:
Do a visual inspection of the 2 pylon rod fittings items F1 and F2, make sure that there is no wear and no hole damage.
Do a visual inspection of the interface plate rod fittings item 420 (340), make sure that there is no wear and no hole damage.
Do a visual inspection of the front bracket item F4 and the upper bracket item F3, make sure that there is no visible crack or abnormal deformation.
NOTE: In case of finding of structural parts, please contact Airbus Customer Services through TechRequest.
**BEG. REV**
6) Installation of the rod Put the bush item 430 (350) in position on the fitting.
Put the rod item 440 (360) or 450 (370) in position, adjust the rod length in order to install the 2 bolts item 35 and to get the rod in stress free condition.
Tighten the nuts to the rod body to between 2.4 and 3.6 Nm.
Remove the bolts item 35 and remove the rod item 440 (360) or 450 (370).
Make sure that the bush 430 (350) are still in position on the fitting item F1, F2 and on the interface plate item 420 (340).
Note: The rod has to be removed as wire locking of the nuts is not possible when the rod is connected.
Safety the nut from the body rod with lock wires corrosion-resistant steel diam 0.8 mm
(0.032 in.) (Ref 5) Install the rod item 440 (360) or 450 (370) in position, install the washer item 25 the bolt item 35, the washer item 25 and the nuts item 15.
Torque the nuts item 15 to between 3.7 and 4.8 Nm.
Check again that the rod item 440 (360) or 450 (370) is installed in stress free condition.
**END. REV** Machined lights to insert rod ball
ALERT OPERATORS TRANSMISSION - AOT AOT ref: A29N008-16 Rev 02 Page 6 of 6 Date: 23-JAN-2019 © AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
7) Close Access:
a) Remove the warning notice(s).
b) Make sure that the work area is clean and clear of tools and other items.
c) Close the thrust reverser system cowl doors (Ref: 2).
4.2.2 REPORTING / FINDINGS After completion of step 4.2.1 para 5), please fill in the AOT reporting (appendix 1)
4.3 SPARES AND TOOLING No specific tooling is required for accomplishment of this AOT.
Please anticipate spare rods availability before the inspection, contact Airbus spare to this mail address:
ifd.spares@airbus.com
5. FURTHER INFORMATION
5.1 FOLLOW-UP PLAN ***BEG REV*** This AOT is a repetitive inspection for aircraft pre Mod 163348 or pre SB A320 29-1189.
The final fix is available. No follow-up plan is foreseen.
***END REV***
5.2 IMPACTED DOCUMENTATION None
6. AOT APPROVAL The technical content of this document is approved under the authority of DOA nr. EASA.21J.031.
7. REPORTING Questions about the technical content of this AOT are to be addressed to Airbus Customer Services through TechRequest on Airbus World, selecting Engineering Domain, and ATA29.
As per latest reporting policy (Ref to OIT 999.0018/16), inspection results (with or without findings) are to be addressed to Airbus Customer Services through the generic e-mail address:
inspection.results@airbus.com.
Best Regards, Jean-Luc MOUYSSET
VICE PRESIDENT ENGINEERING SUPPORT
CUSTOMER SERVICES Jean-Pierre GOMEZ VICE PRESIDENT A320 FAMILY