CUSTOMER SERVICES DIRECTORATE

1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE TELEPHONE + 33 (0)5 61 93 33 33


# A L E R T O P E R A T O R S T R A N S M I S S I O N

- A O T

AOT ref: A71L005

- 14 Rev 01 Page 1 of 9 Date : 11

- DEC

- 2014

© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPR IETARY DOCUMENT SUBJECT: ATA 71 – TRENT 700 - AFT AND FWD ENGINE MOUNT BOLTS - TORQUE CHECK

AIRCRAFT TYPE: A330

OUR REF.: A71L005-14 Rev 01 dated 11-DEC-2014

OUR PREV. REF.: A71L005-14 Rev 00 dated 29-SEPT-2 014

0. REASON FOR REVISION

The revision 01 is issued to include MSN1509 in the AOT effectivity list, the aft engine mounts retain er part number, and the Engine Manual task references. The revised paragraphs are indicated between **BEG. REV** and **END REV**.

1. AIRCRAFT AFFECTED

Applicable to all A330 aircraft fitted with TRENT70 0 engines within below effectivity and on engine(s) that was (were) never removed since first Entry Int o Service (EIS): - From MSN0730 included, till MSN1506 included.

**BEG REV**

- MSN1509

**END REV**

2. REFERENCED DOCUMENTATION

2.1 APPENDIX

N/A

2.2 REFERENCES

AMM 20-21-11 PB 201 CONF 00 AMM Task 24-42-00-861-801 AMM Task 24-42-00-862-801 AMM Task 71-00-00-000-805-A AMM task 71-00-00-000-806-A AMM task 71-00-00-000-806-A01 AMM task 71-00-00-000-806-A02 AMM task 71-00-00-000-806-A03 AMM Task 71-00-00-400-805-A AMM Task 71-00-00-400-806-A AMM Task 71-00-00 PB401 AMM Task 71-13-00-010-805 AMM Task 71-13-00-410-805 AMM Task 78-30-00-410-803

# A L E R T O P E R A T O R S T R A N S M I S S I O N

- A O T

AOT ref: A71L005

- 14 Rev 01 Page 2 of 9 Date : 11

- DEC

- 2014

© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPR IETARY DOCUMENT AMM Task 78-30-00-010-803 AMM Task 78-31-00-040-805 AMM Task 78-31-00-440-805

Figure 71-00-00-991-17400-04-A / Sheet 1 of AMM tas k 71-00-00-000-805-A AIPC Figure 60 (Sheet 01/01) / 71-21-42 AIPC Figure 60 (Sheet 01/01) / 71-22-42

**BEG REV**

Rolls-Royce Engine IPC Chapter 71 Rolls-Royce Figure 71-21-12-01 Rolls-Royce Engine IPC Chapter 71 Rolls-Royce Figure 71-21-11-01 Rolls-Royce Engine Manual 71-21-11 Pageblock 801 Rolls-Royce Engine Manual 71-21-12 Pageblock 801 Rolls-Royce Engine Manual 71-21-11-200-804 Rolls-Royce Engine Manual 71-21-11-200-801 Rolls-Royce Engine Manual 71-21-12-200-801 Rolls-Royce Engine Manual 71-21-12-200-803

**END REV**

3. REASON

3.1 FACTS

In July 2013, while performing an engine removal on an A330 aircraft at the Airbus Long Range (LR) Final Assembly Line (FAL) in Toulouse, one forward engine mount bolt was found not torqued.

The investigation concluded that in this case durin g engine installation, the bolt was under torqued. All other aircraft that were in the FAL were inspec ted and confirmed compliant.

Since January 2014 an improved process related to e ngine installation is applied in LR FAL. However it is possible that some aircraft may have been delivered between Jun-2006 and Jan-2014 with under torqued bolts, and consequently a torque chec k of the AFT and FWD engine mount bolts is required.

3.2 CONSEQUENCES

Engine mounts are certified with a failsafe case co nsidering one pylon bolt fully broken. However, it is possible that some aircraft may have been delivered with one or several bolt under-torqued.

3.3 AIM

The aim of this AOT is to provide operators with th e instructions to perform a onetime torque check on the AFT and FWD engine mount bolts.

This AOT applies to aircraft within effectivity def ined in paragraph 1 of this AOT and whose engines have never been removed since first EIS.

4. SHORT TERM ACTION

4.1 PLANNING AND MANPOWER

# A L E R T O P E R A T O R S T R A N S M I S S I O N

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AOT ref: A71L005

- 14 Rev 01 Page 3 of 9 Date : 11

- DEC

- 2014

© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPR IETARY DOCUMENT 4.1.1 ACCOMPLISHMENT TIMESCALE

Airbus requires that the inspections as per procedu re described in paragraph 4.2, are carried out at f irst opportunity and no later than 2000FH after receipt of this “Alert Operators Transmission”.

4.1.2 MANPOWER

The estimated time to perform the inspection is 3 m an-hours (MH) per engine:

- Get and close access: 2 MH.

- Check Torque of aft and fwd Bolts: 1 MH.

The estimated time to perform the corrective action (s) in case of findings is:

- Torqueing on an under-torqued bolt (get and close access time not included): 0,5 MH

- Replacement of all fwd engine mount bolts, nuts, a nd watchers:

o All bolts at once (requiring engine removal and th en reinstallation): 10 MH

- Replacement of all aft engine mount bolts, nuts, a nd watchers:

o All bolts at once (requiring engine removal and th en reinstallation): 10 MH

4.2 DESCRIPTION

4.2.1 ACCESS

4.2.1.1 Get access

Make sure that the safety devices and the warning n otices are in position before you start a task on o r
near:

- The flight control.

- The flight control surfaces.

- The landing gear and the related doors.

- Components that move.

Movement of components can kill or injure persons.

WARNING: YOU MUST BE CAREFUL WHEN YOU DO WORK ON TH E ENGINE PARTS AFTER THE ENGINE IS SHUTDOWN. THE ENGINE PARTS CAN STAY H OT FOR ALMOST 1 HOUR.

WARNING: YOU MUST NOT TOUCH HOT PARTS WITHOUT APPLI CABLE GLOVES. HOT PARTS CAN CAUSE AN INJURY. IF YOU GET AN INJURY PUT IT IN COLD WATER FOR 10 MINUTES AND GET MEDICAL AID.

Energize the ground service network as per AMM Task 24-42-00-861-801.

Make sure the engine 1 (2) has been shut down for a minimum of 5 minutes before doing this procedure.

Put a WARNING NOTICE(S) to tell persons not to star t the engines.

Get Access to the Avionics Compartment

- Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the access door 811.

- Open the access door 811.

- Open the protective door of the AC/DC emergency po wer-center 740VU.

Open, safety and tag these circuit breakers:

# A L E R T O P E R A T O R S T R A N S M I S S I O N

- A O T

AOT ref: A71L005

- 14 Rev 01 Page 4 of 9 Date : 11

- DEC

- 2014

© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPR IETARY DOCUMENT - FOR FIN 4030EM1 (DEMOUNTABLE POWER PLANT, ENG1)

o Panel: 721VU / Designation: TR INHIB B ENG 1 / FIN : 8KS1 / Location: R16

o Panel: 722VU / Designation: FADEC B ENG 1 / FIN: 1 3KS1 / Location: D44

o Panel: 722VU / Designation: TR INHIB A ENG 1 / FIN : 7KS1 / Location: U35

o Panel: 742VU / Designation: FADEC A ENG 1 / FIN: 1 2KS1 / Location: Q73

- FOR FIN 4030EM2 (DEMOUNTABLE POWER PLANT, ENG2)

o Panel: 721VU / Designation: TR INHIB A ENG 2 / FIN : 7KS2 / Location: R1

o Panel: 722VU / Designation: FADEC B ENG 2 / FIN: 1 3KS2 / Location: K49

o Panel: 722VU / Designation: TR INHIB B ENG 2 / FIN : 8KS2 / Location: U34

o Panel: 742VU / Designation: FADEC A ENG 2 / FIN: 1 2KS2 / Location: Q74

Open the fan cowl doors as per AMM Task 71-13-00-01 0-805:

- FOR 4030EM1 (DEMOUNTABLE POWER PLANT, ENG1), 415AL , 416AR.

- FOR 4030EM2 (DEMOUNTABLE POWER PLANT, ENG2), 425AL , 426AR.

Deactivate the thrust reverser for maintenance as p er AMM Task 78-31-00-040-805.

WARNING: YOU MUST DEACTIVATE THE THRUST REVERSER BE FORE YOU DO WORK ON OR AROUND IT. IF YOU DO NOT, THE THRUST REVERSER CAN O PERATE ACCIDENTALLY AND CAUSE INJURY AND/OR DAMAGE.

Open the thrust reverser doors as per AMM Task 78-3 0-00-010-803:

- FOR 4030EM1 (DEMOUNTABLE POWER PLANT, ENG1), 417AL , 418AR.

- FOR 4030EM2 (DEMOUNTABLE POWER PLANT, ENG2), 427AL , 428AR.

4.2.1.2 Forward Engine mount

Put the ACCESS PLATFORM 3M (10 FT) ADJUSTABLE in po sition at the side of the engine.

CAUTION: BE CAREFULL NOT TO DISCONNECT THE HARNESSE S. IN CASE OF DISCONNECTION, ADDITIONAL TESTS WOULD BE REQUIRED A FTER AOT COMPLETION IN ORDER TO CONFIRM RE-CONNECTION WAS PROPERLY MADE.

Harnesses of the 3820VC, 3821VC and 3822VC shall be move aside.

- Start by removing the harnesses of the 3820VC, 382 1VC and 3822VC from the bracket (item 65 - AIPC Figure 60 (Sheet 01/01) / 71-21-42) of th e engine mount retaining assy.

- Then, remove the harnesses of the 3820VC, 3821VC a nd 3822VC in the clamps of the ramps (4). Refer to figure 71-00-00-991-17400-04-A / Shee t 1 of the AMM task 71-00-00-000-805-A.

Remove Forward Mount Bolt Retaining assy. (Refer to AIPC Figure 60 (Sheet 01/01) / 71-21-42)

- Remove the bolts (items 10 and 15), washers (item 30), nuts (items 45 and 50), brackets (items 60 and 65) and plates (items 70 and 80) from the fo ur bolts (item 20).

Proceed to torque check as detailed in paragraph 4. 2.2.1 and proceed to corrective actions defined in 4.2.3.1 in case of findings. Refer to paragraph 4.3 for bolts, nuts and washers part number.

Install Forward Mount Bolt Retaining assy. (Refer to AIPC Figure 60 (Sheet 01/01) / 71-21-42)

# A L E R T O P E R A T O R S T R A N S M I S S I O N

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AOT ref: A71L005

- 14 Rev 01 Page 5 of 9 Date : 11

- DEC

- 2014

© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPR IETARY DOCUMENT - Install the bolts (items 10 and 15), washers (item 30), nuts (items 45 and 50), brackets (items 60 and 65) and plates (items 70 and 80) on the four bo lts (item 20). Apply torque as per standard practices AMM 20-21-11.

Repositioning of the harness of the 3820VC, 3821VC and 3822VC.

- Clamp the harnesses along the ramp (4). Refer to f igure 71-00-00-991-17400-04-A / Sheet 1 of AMM task 71-00-00-000-805-A.

- Fasten the harnesses to the engine mount bolt reta ining assy by installing the attaching parts on the bracket (item 65 - AIPC Figure 60 (Sheet 01/01) / 71-21-42). Apply torque as per standard practices AMM 20-21-11.

CAUTION: BE CAREFUL NOT TO DISCONNECT THE HARNESSES . IN CASE OF DISCONNECTION, ADDITIONAL TESTS WOULD BE REQUIRED A FTER AOT COMPLETION IN ORDER TO CONFIRM RE-CONNECTION WAS PROPERLY MADE.

Remove the ACCESS PLATFORM 1M (3 FT).

4.2.1.3 Aft Engine mount

Install an ACCESS PLATFORM 1M(3 FT).

Remove Aft Mount Bolt Retaining assy. (Refer to AIPC Figure 60 (Sheet 01/01) / 71-22-42)

- Remove the bolt (item 10), washer (item 20), retai ners (items 30) from the four bolts (item 40).

Proceed to torque check as detailed in paragraph 4. 2.2.2 and proceed to corrective actions defined in 4.2.3.2 in case of findings. Refer to paragraph 4.3 for bolts, nuts and washers part number.

Install Aft Mount Bolt Retaining assy. (Refer to AIPC Figure 60 (Sheet 01/01) / 71-22-42)

- Install the bolt (item 10), washer (item 20), and retainers (items 30) from the four bolts (item 40).

- Torque the bolts (item 10) as per standard practic es specified into AMM task 20-21-11.

Remove the ACCESS PLATFORM 1M (3 FT).

4.2.1.4 Close Access

Put the ACCESS PLATFORM 3M (10 FT) ADJUSTABLE in ap propriate position.

Make sure that the work area is clean and clear of tools and other items.

Close the thrust reverser cowl doors as per AMM Tas k 78-30-00-410-803:

- FOR 4030EM1 (DEMOUNTABLE POWER PLANT, ENG1), 417AL , 418AR.

- FOR 4030EM2 (DEMOUNTABLE POWER PLANT, ENG2), 427AL , 428AR.

Make the thrust reverser serviceable as per AMM Tas k 78-31-00-440-805.

Close the fan cowl doors as per AMM Task 71-13-00-4 10-805:

- FOR 4030EM1 (DEMOUNTABLE POWER PLANT, ENG1), 415AL , 416AR.

- FOR 4030EM2 (DEMOUNTABLE POWER PLANT, ENG2), 425AL , 426AR.

Remove the access platform(s).

# A L E R T O P E R A T O R S T R A N S M I S S I O N

- A O T

AOT ref: A71L005

- 14 Rev 01 Page 6 of 9 Date : 11

- DEC

- 2014

© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPR IETARY DOCUMENT Remove the safety clips and the tags and close thes e circuit breakers:

- FOR FIN 4030EM1 (DEMOUNTABLE POWER PLANT, ENG1)

o Panel: 721VU / Designation: TR INHIB B ENG 1 / FIN : 8KS1 / Location: R16

o Panel: 722VU / Designation: FADEC B ENG 1 / FIN: 1 3KS1 / Location: D44

o Panel: 722VU / Designation: TR INHIB A ENG 1 / FIN : 7KS1 / Location: U35

o Panel: 742VU / Designation: FADEC A ENG 1 / FIN: 1 2KS1 / Location: Q73

- FOR FIN 4030EM2 (DEMOUNTABLE POWER PLANT, ENG2)

o Panel: 721VU / Designation: TR INHIB A ENG 2 / FIN : 7KS2 / Location: R15

o Panel: 722VU / Designation: FADEC B ENG 2 / FIN: 1 3KS2 / Location: K49

o Panel: 722VU / Designation: TR INHIB B ENG 2 / FIN : 8KS2 / Location: U34

o Panel: 742VU / Designation: FADEC A ENG 2 / FIN: 1 2KS2 / Location: Q74

Close the protective door of the AC/DC emergency po wer center 740VU.

Close the access door 811.

De-energize the ground service network as per AMM T ask 24-42-00-862-801.

4.2.2 INSPECTION REQUIREMENTS

4.2.2.1 Forward engine mount bolts

Mark all four pylon bolts head and adjacent area to provide a reference point to indicate if the bolt

moves.

Apply a torque of 3540.4lbf.in (40m.daN) in a clock wise direction (tightening direction) to all four e ngine forward mount pylon bolts, to check for a loose con dition.

4.2.2.2 Aft engine mount bolts

Mark all four pylon bolts head and adjacent area to provide a reference point to indicate if the bolt

moves.

Apply a torque of 4248.5lbf.in (48m.daN) in a clock wise direction (tightening direction) to all four e ngine aft mount pylon bolts, to check for a loose conditi on.

4.2.3 FINDINGS

4.2.3.1 Forward engine mount bolts

4.2.3.1.1 Instructions

Check the marking applied in para 4.2.2.1 to confir m if the bolt has moved.

- If one bolt rotates:

o Before next flight

o Re-torque twice the affected bolt as per AMM Task 71-00-00-400-806-A (subtask 71-00-00-420-068-A) between 56.94 and 67.5 2m.daN (420 and 498 lbf.ft).

o At next engine removal,

o Discard and replace the 4 bolts and nuts and washe rs by new ones, and proceed to inspection check. Refer to paragraph 4.2 .3.1.2 for procedure details.

# A L E R T O P E R A T O R S T R A N S M I S S I O N

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AOT ref: A71L005

- 14 Rev 01 Page 7 of 9 Date : 11

- DEC

- 2014

© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPR IETARY DOCUMENT - If several bolts rotate:

o Contact Airbus for further actions before next fli ght

- If one pylon bolt fully broken:

o Discard and replace the 4 bolts and nuts and washe rs with new ones before next flight and proceed to inspection check. Refer to paragraph 4.2.3.1.2 for procedure details.

NOTE: Inspection results with or without findings h ave to be sent to Airbus Customer Services Engineering.

4.2.3.1.2 Procedure details

Bolt replacement off-wing and inspection to carry o ut:

- Proceed to engine removal as per AMM Task 71-00-00 PB401.

- Remove retaining hardware from all bolts.

- Remove and replace the 4 bolts and associated nuts and washers by new ones.

- Perform Fluorescent Penetrant Inspection and dimen sional check on impacted forward engine mount platform when engine is removed

o If nil finding, replace the forward platform at ne xt engine removal

o If local deformation is exhibited during the check , replace the forward platform before next flight

- Install the retaining hardware on all bolts.

- Install the engine as per AMM Task 71-00-00 PB401.

**BEG REV**

NOTE1: The fluorescent penetrant inspection and dimensiona l check on the forward platform, if required, have to be performed on items 432, and 500 of the Rolls-Roy ce Engine Illustrated Parts Catalogue under 71 Power Plant chapter (See figure 71-21-11-01 FRONT M OUNT).

NOTE2: The fluorescent penetrant inspection and dimensiona l check have to be performed as described on Engine Manual ATA 71 chapter (Subject 71-21-11, Pag eblock 801: Engine Front Mount inspection/check). The item 432 has to be checked as per EM task 71-21 -11-200-804 “Examine the Outer Support Assembly of the Engine Front Mount Assembly (71-21- 11,01-400)”. The item 500 has to be checked as per EM task 71-21 -11-200-801 “Examine the Vertical Load Support of the Front Mount Assembly (71-21-11,01-500)”.

**END REV**

4.2.3.2 Aft engine mount bolts

4.2.3.2.1 Instructions

Check the marking applied in para 4.2.2.2 to confir m if the bolt has moved.

- If one bolt rotates:

o Before next flight

o Re-torque twice the affected bolt as per AMM Task 71-00-00-400-806-A (subtask 71-00-00-420-068-A) between 68.06 and 81.0 8m.daN (502 and 598 lbf.ft).

# A L E R T O P E R A T O R S T R A N S M I S S I O N

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AOT ref: A71L005

- 14 Rev 01 Page 8 of 9 Date : 11

- DEC

- 2014

© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPR IETARY DOCUMENT o At next engine removal,

o Discard and replace the 4 bolts and nuts and washe rs and retainers by new ones, and proceed to inspection check. Refer to par agraph 4.2.3.2.2 for procedure details.

- If several bolts rotate:

o Contact Airbus for further actions before next fli ght

- If one pylon bolt fully broken:

o Discard and replace the 4 bolts and nuts and washe rs and retainers by new ones, and proceed to inspection check. Refer to paragraph 4.2 .3.2.2 for procedure details.

NOTE: Inspection results with or without findings h as to be sent to Airbus Customer Services Engineering.

4.2.3.2.2 Procedure details

Bolt replacement off-wing and inspection to carry o ut:

- Proceed to engine removal as per AMM Task 71-00-00 PB401.

- Remove retaining hardware from all bolts.

- Remove and replace the 4 bolts and associated nuts , washers and retainers by new ones.

- Perform Fluorescent Penetrant Inspection and dimen sional check on impacted engine mount rear beam when engine is removed

o If nil finding, replace the rear beam at next engi ne removal

o If local deformation is exhibited during the check , replace the rear beam before next flight.

- Install the retaining hardware on all bolts.

- Install the engine as per AMM Task 71-00-00 PB401.

**BEG REV**

NOTE1: The fluorescent penetrant inspection and a dimensio nal check, if required, have to be performed on items 600, 686 and 712 (bushes PN FK12706) on Rolls -Royce Engine Illustrated Parts Catalogue (Figure 71-21-12-01 REAR MOUNT).

NOTE2: The fluorescent penetrant inspection and the dimens ional check have to be performed as described on the Engine Manual under the 71 Power Plant chapter (Subject 71-21-12 Pageblock 801: Engine Rear Mount inspection/check). The items 600 and 712 have to be checked as per EM task 71-21-12-200-801 “Examine the Engine Rear Mount Bracket Assembly (71-21-12,01-600)”. The item 686 has to be checked as per EM task 71-21 -12-200-803 “Examine the Engine Rear Mount Remaining Parts”.

**END REV**

4.3 SPARES AND TOOLING

4.3.1 Forward mount hardware

- Bolt part-number: BLT5468 / BLT5706

- Nut part-number: U755355

- Washer part-number: UP11304

# A L E R T O P E R A T O R S T R A N S M I S S I O N

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AOT ref: A71L005

- 14 Rev 01 Page 9 of 9 Date : 11

- DEC

- 2014

© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPR IETARY DOCUMENT 4.3.2 Aft mount hardware

- Bolt part-number: BLT5533 / BLT5705

- Nut part-number: U755357

- Washer part-number: UP11493

**BEG REV**

- Retainer part-number: U755358

**END REV**

5. FURTHER INFORMATION

5.1 FOLLOW-UP PLAN

No further action is expected following AOT complet ion.

5.2 IMPACTED DOCUMENTATION

N/A

6. AOT APPROVAL

The technical content of this document is approved under the authority of DOA nr. EASA.21J.031.

7. REPORTING

Questions about this AOT and inspection results wit h or without findings are to be sent to Airbus Customer Services engineering as soon as possible, after the AOT application, to the attention of:

Virginie HIRTZ Nacelle Systems and Structure Engineer Engineering Support - SEEE6 CUSTOMER SERVICES Phone +33 (0)5 82 05 61 81 Fax +33 (0)5 61 93 36 14 Mailto: virginie.hirtz@airbus.com

Best Regards,

Jean-Luc MOUYSSET VICE PRESIDENT ENGINEERING SUPPORT CUSTOMER SERVICES Philippe GOURDON VICE PRESIDENT SUPPORT LR PROGRAMME CUSTOMER SERVICES