# Airbus Alert Operators Transmission A71L002-13 ## Copies (3) Copies the FAA filed in AD dockets on regulations.gov, newest revision first. A newer revision may exist. - No revision named ("U.S. DOT/FAA - AOT A71L002-13"), 6 pages: PDF https://openairdocs.org/files/sha256/10/9d/109dc3d81da0ecd847a44ea53fb900cc270cb74d6b94c39a57151b4bd0c95d48; text https://openairdocs.org/service-documents/airbus/aot-a71l002-13/file/109dc3d81da0.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2015-0079; AD 2015-02-18 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - No revision named ("U.S. DOT/FAA - AOT A71L002-13"): File https://openairdocs.org/files/sha256/d3/de/d3de6c1c9ae0bca7cb7a826de6b6f545b6f1671c07d1563d03c513388115d9e2; text https://openairdocs.org/service-documents/airbus/aot-a71l002-13/file/d3de6c1c9ae0.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2015-0079; AD 2015-02-18 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - No revision named ("U.S. DOT/FAA - AOT A71L002-13 with Appendix"), 11 pages: PDF https://openairdocs.org/files/sha256/c4/79/c4797a1f51acea0eecaeb9a0530f0fe743357f2b952e1fd8e6282648200fc2e6; text https://openairdocs.org/service-documents/airbus/aot-a71l002-13/file/c4797a1f51ac.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2015-0079; AD 2015-02-18 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md) - Type: Other document (Alert Operators Transmission) - Number: A71L002-13 - Page: https://openairdocs.org/service-documents/airbus/aot-a71l002-13 ## ADs that cite it (1) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2015-02-18](https://openairdocs.org/ad/2015-02-18.md), effective Feb 17, 2015: No revision named ## Text (6 pages) No revision named, the newest copy. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2015-0079; AD 2015-02-18 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 ALERT OPERATORS TRANSMISSION - ALERT OPERATORS TRANSMISSION SUBJECT: ATA 71 - A330 CF6-80E1 Upper aft mount bolt inspection OUR REF.: A71L002-13 dated 08 Apr 2013. 1. AIRCRAFT AFFECTED All A330 powered with GE CF6-80E1. 2. REFERENCED DOCUMENTATION 2.1 APPENDIX Appendix 1: Airbus Technical report Reference G54RP1310441 - GE CF6-80E1 - ATA 54- 51-18 Fractured Bolts on Aft Engine Mount Upper Beam. 2.2 REFERENCES A330 GE IPC 71-22-41 Item 20 BOLT-DBL HEX HD. A330 GE AMM 24-42-00-861-801-A Energize the Ground Service Network. A330 GE AMM 78-31-00-040-802 Deactivation of the Thrust Reverser System for Maintenance. A330 GE AMM Figure 05-24-50-991-03100-06-A / SHEET 1 - Access Doors/ Panels, Engine 1 Pylon. A330 GE AMM Figure 05-24-50-991-03200-06-A / SHEET 1 - Access Doors/ Panels, Engine 2 Pylon. A330 GE AMM 78-31-00-440-802-A Reactivation of the Thrust Reverser System after Maintenance. A330 GE AMM 24-42-00-862-801-A De-energize the Ground Service Network. 3. REASON 3.1 FACTS During the scheduled replacement of a CF6-80E1 engine#1 on an A330 aircraft, one bolt part- number 1672M36P01 (IPC 71-22-41 Item 20 BOLT-DBL HEX HD) on the aft engine mount upper beam was found totally broken. The bolt reportedly "fell down" upon removal of the lower beam. The bolt in question is one of the four bolts that attach the upper beam to the pylon. This was the original engine on the aircraft and had no removal since entry into service. ### Page 2 Since EIS, amongst numerous scheduled or unscheduled CF6-80E1 engine removals this is the only case reported. Extensive investigation on the fractured bolt and the upper beam revealed: - A fatigue origin area with crack propagation from the boundary of the bolt. - Visual examination of the bolt reveals spiral groove with cold work and microstructural distortion underlying that extended axially along the shank. The crack initiated at the edge of the groove. - Once initiated, the complete fracture of the bolt was reached very quickly (quick propagation). - The upper beam revealed a score mark on counter-bore edge. To be noted that the 3 other bolts were found in good condition. Preliminary root-cause understanding is that unusual contact with the counter-bore edge of the beam induced a very significant groove on the bolt during its installation, which eventually led to the bolt fracture. As the root-cause is still under investigation, including the installation sequence specific to this aircraft - engine model, the AOT is not applicable for other A330 propulsion systems. 3.2 CONSEQUENCES Failure of one pylon-upper beam bolt is a failsafe case taken into account in certification analysis. During this abnormal flight condition the structure is designed to continue to sustain residual fatigue loads and limit loads during a minimum of one inspection interval (9,500 FC) as required per ALI task 545111-02-01. Furthermore, the engine mount structure is not designed to sustain the residual fatigue and limit loads on 2 bolts or less. 3.3 AIM The aim of this AOT is to ask operators to perform a onetime ultrasonic inspection of the four aft mount-pylon bolts of each engine. That makes a total of eight aft mount pylon bolts inspected by aircraft. This will allow detection of cracks completely sheared through the bolt section. 4. SHORT TERM ACTION 4.1 PLANNING AND MANPOWER 4.1.1 ACCOMPLISHMENT TIMESCALE Airbus requires that the inspection as per procedure described in paragraph 4.2, is carried out at first opportunity and no later than 1000FH after receipt of this "Alert Operators Transmission". ### Page 3 4.1.2 MANPOWER The estimated time to get access and perform the inspection is 2.5MH per engine. The estimated time to apply the corrective actions in case of findings is 25Mh per engine. 4.2 DESCRIPTION 4.2.1 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. Energize the ground service network as per AMM TASK 24-42-00-861-801. Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do the inspection. Put a WARNING NOTICE(S) to tell persons not to start the engines. Get Access to the Avionics Compartment: - Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at access door 811 - Open access door 811. - Open the protective door of the AC/DC emergency power-center 740VU. Open, safety and tag these circuit breakers: - For FIN 4030EM1 (DEMOUNTABLE POWER PLANT, ENG1): o Panel: 722VU / Designation: FADEC B ENG 1 / FIN: 13KS1 / Location: D44 o Panel: 742VU / Designation: FADEC A ENG 1 / FIN: 12KS1 / Location: Q73 - FOR FIN 4030EM2 (DEMOUNTABLE POWER PLANT, ENG2) o Panel: 722VU / Designation: FADEC B ENG 2 / FIN: 13KS2 / Location: K49 o Panel: 742VU / Designation: FADEC A ENG 2 / FIN: 12KS2 / Location: Q74 Make the thrust reverser unserviceable as per AMM TASK 78-31-00-040-802. Put an ACCESS PLATFORM 5M (16 FT) - ADJUSTABLE in position at the pylon leading edge (zones 453, 463). Remove the access panels: - For pylon 1: 453BL and 453BR - For pylon 2: 463BL and 463BR ### Page 4 (Refer to AMM Figure 05-24-50-991-03100-06-A / SHEET 1 and - Figure 05-24-50-991- 03200-06-A / SHEET 1 for the locations of the Access Doors/ Panels, respectively on Engine 1 Pylon and Engine 2 Pylon). Perform the inspection as per paragraph 4.2.2 and contact Airbus in case of findings as per paragraph 4.2.3. Make the thrust reverser serviceable as per AMM TASK 78-31-00-440-802 Remove the safety clips and the tags and close these circuit breakers: - For FIN 4030EM1 (DEMOUNTABLE POWER PLANT, ENG1): o Panel: 722VU / Designation: FADEC B ENG 1 / FIN: 13KS1 / Location: D44 o Panel: 742VU / Designation: FADEC A ENG 1 / FIN: 12KS1 / Location: Q73 - FOR FIN 4030EM2 (DEMOUNTABLE POWER PLANT, ENG2) o Panel: 722VU / Designation: FADEC B ENG 2 / FIN: 13KS2 / Location: K49 o Panel: 742VU / Designation: FADEC A ENG 2 / FIN: 12KS2 / Location: Q74 Make sure that the work area is clean and clear of tools and other items Install the access panels: - For pylon 1: 453BL and 453BR - For pylon 2: 463BL and 463BR (Refer to AMM Figure 05-24-50-991-03100-06-A / SHEET 1 and - Figure 05-24-50-991- 03200-06-A / SHEET 1 for the locations of the Access Doors/ Panels, respectively on Engine 1 Pylon and Engine 2 Pylon). Close the protective door of the AC/DC emergency power-center 740VU. Remove the WARNING NOTICE(S) in the cockpit. Close access door 811. Remove the access platform(s). Remove the ground support and maintenance equipment, the special and standard tools and all other items. De-energize the ground service network as per AMM TASK 24-42-00-862-801 4.2.2 INSPECTION REQUIREMENTS Perform a onetime ultrasonic inspection of the four aft mount-pylon bolts of each engine. Please refer to Appendix 1 to be provided with all the inspection instructions and tooling requirements for application of this AOT. 4.2.3 FINDINGS ### Page 5 In case of a fractured bolt is identified, before next flight contact Airbus since specific instructions would be provided with regards to components removal / installation. Findings of a fracture bolt shall require the following actions: - Removal of the engine. - Removal of the aft mount hardware for shop inspection and potential repair. 5. FURTHER INFORMATION 5.1 FOLLOW-UP PLAN Further actions may be considered based upon results of the ongoing investigations. 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 Operators are requested to acknowledge receipt of this AOT within 48 hours after receipt to: Emilie GAILLANOU, SEEE E-mail: emilie.gaillanou@airbus.com Fax number +33 (0)5 61 39 36 14 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: Marie LALO Repair & System Nacelles Customer Engineering Support - SEEE6 CUSTOMER SERVICES Phone: +33 (0)5 62 11 83 03 Fax: +33 (0)5 61 93 36 14 mailto: marie.lalo@airbus.com ### Page 6 Best Regards, Jean-Luc MOUYSSET Philippe GOURDON VICE PRESIDENT ENGINEERING SUPPORT VICE PRESIDENT A330/A340 PROGRAMME CUSTOMER SERVICES CUSTOMER SERVICES --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. 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