CUSTOMER SERVICES DIRECTORATE

1 ROND POINT MAURICE BELLONTE 

31707 BLAGNAC CEDEX FRANCE 

TELEPHONE + 33 (0)5 61 93 33 33 

ALERT OPERATORS TRANSMISSION - AOT

AOT ref: A71L005-14 Rev 01 Page 1 of 9 Date:11-DEC-2014

© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY 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-2014 

0. REASON FOR REVISION 

The revision 01 is issued to include MSN1509 in the AOT effectivity list, the aft engine mounts retainer 

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 TRENT700 engines within below effectivity and on engine(s)

that was (were) never removed since first Entry Into 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 
 

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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 task 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 during engine installation, the bolt was under torqued. 

All other aircraft that were in the FAL were inspected and confirmed compliant. 

Since January 2014 an improved process related to engine 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 check of the AFT and FWD engine mount bolts is 

required. 

3.2 CONSEQUENCES 

Engine mounts are certified with a failsafe case considering 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 the instructions to perform a onetime torque check on

the AFT and FWD engine mount bolts. 

This AOT applies to aircraft within effectivity defined 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 
 

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© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT

4.1.1 ACCOMPLISHMENT TIMESCALE 

Airbus requires that the inspections as per procedure described in paragraph 4.2, are carried out at first 

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 man-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, and watchers: 

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

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

o All bolts at once (requiring engine removal and then 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 notices are in position before you start a task on or 

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 THE ENGINE PARTS AFTER 

THE ENGINE IS SHUTDOWN. THE ENGINE PARTS CAN STAY HOT FOR ALMOST 1 HOUR. 

WARNING: YOU MUST NOT TOUCH HOT PARTS WITHOUT APPLICABLE 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 start 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 power-center 740VU. 

Open, safety and tag these circuit breakers: 
 

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© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY 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: 13KS1 / Location: D44 

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

o Panel: 742VU / Designation: FADEC A ENG 1 / FIN: 12KS1 / 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: 13KS2 / Location: K49 

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

o Panel: 742VU / Designation: FADEC A ENG 2 / FIN: 12KS2 / Location: Q74 

Open the fan cowl doors as per AMM Task 71-13-00-010-805: 

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

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

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

WARNING: YOU MUST DEACTIVATE THE THRUST REVERSER BEFORE YOU DO WORK ON OR 

AROUND IT. IF YOU DO NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND 

CAUSE INJURY AND/OR DAMAGE. 

Open the thrust reverser doors as per AMM Task 78-30-00-010-803: 

- 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 position at the side of the engine. 

CAUTION: BE CAREFULL NOT TO DISCONNECT THE HARNESSES. IN CASE OF 

DISCONNECTION, ADDITIONAL TESTS WOULD BE REQUIRED AFTER 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, 3821VC and 3822VC from the bracket (item 

65 - AIPC Figure 60 (Sheet 01/01) / 71-21-42) of the engine mount retaining assy. 

- Then, remove the harnesses of the 3820VC, 3821VC and 3822VC in the clamps of the ramps 

(4). Refer to figure 71-00-00-991-17400-04-A / Sheet 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 four 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) 
 

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© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY 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 bolts (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 figure 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 retaining 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 AFTER 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), retainers (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 practices 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 appropriate 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 Task 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 Task 78-31-00-440-805. 

Close the fan cowl doors as per AMM Task 71-13-00-410-805: 

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

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

Remove the access platform(s). 
 

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© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT

Remove the safety clips and the tags and close these 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: 13KS1 / Location: D44 

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

o Panel: 742VU / Designation: FADEC A ENG 1 / FIN: 12KS1 / 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: 13KS2 / Location: K49 

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

o Panel: 742VU / Designation: FADEC A ENG 2 / FIN: 12KS2 / Location: Q74 

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

Close the access door 811. 

De-energize the ground service network as per AMM Task 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 clockwise direction (tightening direction) to all four engine 

forward mount pylon bolts, to check for a loose condition. 

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 clockwise direction (tightening direction) to all four engine 

aft mount pylon bolts, to check for a loose condition. 

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 confirm 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 67.52m.daN (420 and 

498 lbf.ft). 

o At next engine removal, 

o Discard and replace the 4 bolts and nuts and washers by new ones, and 

proceed to inspection check. Refer to paragraph 4.2.3.1.2 for procedure 

details. 
 

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- If several bolts rotate: 

o Contact Airbus for further actions before next flight 

- If one pylon bolt fully broken: 

o Discard and replace the 4 bolts and nuts and washers 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 have to be sent to Airbus Customer Services 

Engineering. 

4.2.3.1.2 Procedure details 

Bolt replacement off-wing and inspection to carry out: 

- 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 dimensional check on impacted forward engine 

mount platform when engine is removed 

o If nil finding, replace the forward platform at next 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 dimensional check on the forward platform, if required, have to 

be performed on items 432, and 500 of the Rolls-Royce Engine Illustrated Parts Catalogue under 71 

Power Plant chapter (See figure 71-21-11-01 FRONT MOUNT). 

NOTE2: 

The fluorescent penetrant inspection and dimensional check have to be performed as described on 

Engine Manual ATA 71 chapter (Subject 71-21-11, Pageblock 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 confirm 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 81.08m.daN (502 and 

598 lbf.ft). 
 

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o At next engine removal, 

o Discard and replace the 4 bolts and nuts and washers and retainers by new 

ones, and proceed to inspection check. Refer to paragraph 4.2.3.2.2 for 

procedure details. 

 

- If several bolts rotate: 

o Contact Airbus for further actions before next flight 

- If one pylon bolt fully broken: 

o Discard and replace the 4 bolts and nuts and washers 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 has to be sent to Airbus Customer Services 

Engineering. 

4.2.3.2.2 Procedure details 

Bolt replacement off-wing and inspection to carry out: 

- 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 dimensional check on impacted engine mount 

rear beam when engine is removed 

o If nil finding, replace the rear beam at next engine 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 dimensional 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 dimensional 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 
 

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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 completion. 

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 with 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