# Airbus All Operators Transmission A28N010-22 Copy: Revision 1 ("AOT A28N010-22 Rev 01"), 10 pages: PDF https://openairdocs.org/files/sha256/82/73/8273af45bf827e7805ff8eccf50c87bb0c528fa69dd3555faa8402dffc102d52; text https://openairdocs.org/service-documents/airbus/aot-a28n010-22/file/8273af45bf82.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2023-1396, the docket of AD 2023-13-01. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md) - Type: Other document (All Operators Transmission) - Number: A28N010-22 - Latest revision known: A28N010-22, Revision 1, dated March 6, 2023 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/airbus/aot-a28n010-22 ## Text (10 pages) Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2023-1396, the docket of AD 2023-13-01. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 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: A28N010-22 Rev 01 Page 1 of 10 Date: 06-MAR-2023 C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT SUBJECT: ATA 28 – Fuel Pump P/N 568-1-27202-02R Cavitation Erosion AIRCRAFT TYPE: A318-100, A319-100, A319-100N, A320-200, A321-100, A321-200 OUR REF.: A28N010-22 Rev 01 dated 06-MAR-2023 OUR PREVIOUS REF.: A28N010-22 Rev 00 dated 09-FEB-2023 EFFECTIVITY DATE: 14 Feb 2023 0. REASON FOR REVISION ***BEG REV*** This AOT is revised to: Incorporate AMM reference corrections. Add a reporting sheet. Remove A320-200N from the applicability given that fuel pumps P/N 568-1-27202-02R cannot be installed on A320-200N based on the applicable IPC interchangeability criteria. Add a note to clarify the affected locations. Add the exact compliance time end dates. AOT A28N010-22 Rev 01 cancels and supersedes AOT A28N010-22 Rev 00. The revised paragraphs are indicated between ***BEG REV*** and ***END REV***. ***END REV*** 1. AIRCRAFT AFFECTED ***BEG REV*** The following A320 family aircraft models: A318-111, A318-112, A318-121, A318-122, A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132, A319-133, A319-151N, A319-153N, A319-171N, A320-211, A320-212, A320-214, A320-215, A320-216, A320-231, A320-232, A320-233, A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231 and A321-232. ***END REV*** 2. REFERENCED DOCUMENTATION 2.1 APPENDIX - List of A319 and A320 aircraft with MOD 154327 embodied ***BEG REV*** - Inspection Flowchart - AOT Reporting Sheet ***END REV*** 2.2 REFERENCES Reference 1: AMM TASK 28-21-51-000-001-A Removal of the Fuel Pumps (for wing tanks) Reference 2: AMM TASK 28-21-51-400-001-A Installation of the Fuel Pumps (for wing tanks) Reference 3: AMM TASK 28-21-51-000-002-A Removal of the Fuel Pumps (for centre tank) Reference 4: AMM TASK 28-21-51-400-002-A Installation of the Fuel Pumps (for centre tank) Reference 5: IPC sections in IPC chapter 28-21- MAIN FUEL PUMP SYSTEM ### Page 2 ALERT OPERATORS TRANSMISSION - AOT AOT ref: A28N010-22 Rev 01 Page 2 of 10 Date: 06-MAR-2023 C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 3. REASON The purpose of this AOT is to inform A318, A319, A320 and A321 operators of cavitation erosion risk on fuel pump P/N 568-1-27202-02R, which must be inspected. 3.1 FACTS Airbus informs the operators that fuel pumps Part Number 568-1-27202-02R can be subject to cavitation erosion on the wiring conduit. If the cavitation erosion is observed on the wiring conduit area of the fuel pump housing it can expose the fuel pump supply wires. It is to be noted that cavitation erosion is accelerated on fuel pumps operating at a lower flow rate. Wing tank fuel pumps on A321 aircraft and on post-MOD 154327 A319 and A320 aircraft operate at a lower flow rate. There are 6 fuel pumps on A318/A319/A320 prior to MOD 154327, 2 in each wing tank and 2 in the centre tank. There are 4 fuel pumps on A321 and A319/A320/A321 post MOD 154327, two in each wing tank. NOTE: MOD 154327 introduces jet pumps on centre tank. Figure 1: Fuel Pump Illustration Figure 2: Fuel Pump Erosion On The Wiring Conduit 3.2 CONSEQUENCES There is an in-tank ignition risk when: -The cavitation erosion is observed on the wiring conduit area of the fuel pumps. -The cavitation erosion on the wiring conduit is severe enough to expose the fuel pump supply wires (ignition source). -The fuel vapors are exposed to an ignition source. In the collector cells, the submersion in fuel of the fuel pumps reduces the ignition risk. 4. OBJECTIVES OF THIS AOT This AOT is issued for the concerned A320 family operators to inspect (refer to section 5.6 INSPECTION) fuel pump Part Number 568-1-27202-02R installed at specific locations (identified below) within certain timescales (defined in section 5.1 PLANNING). The inspection is performed to ### Page 3 ALERT OPERATORS TRANSMISSION - AOT AOT ref: A28N010-22 Rev 01 Page 3 of 10 Date: 06-MAR-2023 C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT check if these fuel pumps are impacted by erosion on specific areas of the fuel pump and scrap the pump, if necessary (refer to section 5.5 FINDINGS and 5.6 INSPECTION for applicable criteria). The affected fuel pump locations are defined as follow: Center tank locations 37QA and 38QA. Wing tank locations 21QA, 22QA, 25QA and 26QA on A319/A320 aircraft post-MOD 154327. Any wing tank location on A321 aircraft. ***BEG REV*** NOTE: Wing tank locations 21QA, 22QA, 25QA and 26QA on A318, A319 and A320 aircraft pre-MOD 154327 are not affected locations. ***END REV*** NOTE: The results from these inspections on all the concerned aircraft, depending on the rate and the extent of the findings, may lead to future actions (e.g. total fuel pump P/N 568-1-27202-02R withdrawal). 5. MAINTENANCE PROCEDURE NOTE: This AOT is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). If the instructions of this AOT are marked as Required for Compliance (RC), the operator must follow the instructions as indicated. These instructions are introduced by “in accordance with”. NOTE: The instructions of this AOT include procedures given in other documents or in other sections of the AOT. If the instructions of this AOT are NOT marked as Required for Compliance (RC), the operator can use an alternative procedure accepted by his/her local authority. These instructions are introduced by “refer to”. NOTE: When this AOT gives the access or close-up instructions with no return to service tests, the operator can adapt these instructions to add flexibility to the maintenance operations. The technical intent of this AOT must comply with the set parameters. 5.1 PLANNING – (RC) The compliance time begins with the effectivity date of this AOT and depends on the location in which the fuel pump is installed and on the MSN (MOD 154327 embodiment status). First the operator must determine if fuel pump P/N 568-1-27202-02R is installed on the concerned aircraft. NOTE: A review of aeroplane delivery and maintenance records is acceptable to make this determination, provided those records can be relied upon for that purpose and the P/N 568-1- 27202-02R can be positively identified from that review. ***BEG REV*** Fuel pumps P/N 568-1-27202-02R must be removed and inspected (refer to section 5.6 INSPECTION) within 30 days (i.e. 16 March 2023) after the effectivity date of this AOT: oIf the fuel pumps are installed in center tank locations 37QA and 38QA. Fuel pumps P/N 568-1-27202-02R must be removed and inspected (refer to section 5.6 INSPECTION) within 90 days (i.e. 15 May 2023) after the effectivity date of this AOT: ### Page 4 ALERT OPERATORS TRANSMISSION - AOT AOT ref: A28N010-22 Rev 01 Page 4 of 10 Date: 06-MAR-2023 C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT oIf installed in wing tank locations 21QA, 22QA, 25QA and 26QA on A319/A320 aircraft post-MOD 154327. oIf installed in wing tank locations 21QA, 22QA, 25QA and 26QA on A321 aircraft. ***END REV*** If after inspection (refer to section 5.6 INSPECTION) of the fuel pumps installed on the affected locations, there are no findings: oThe fuel pumps are acceptable for flight but must be removed and scrapped after a maximum 4000 Flight Hours if: a) The fuel pumps are re-installed in center tank locations (37QA or 38QA) Or b) The fuel pumps are re-installed in wing tank locations (21QA, 22QA, 25QA or 26QA) on A319/A320 aircraft post-MOD 154327 and on A321 aircraft oIf the fuel pumps are re-installed in wing tank locations 21QA, 22QA, 25QA or 26QA on A318, A319 or A320 aircraft pre-MOD 154327, it is acceptable for flight with no restrictions. 5.2 MANPOWER The estimated time to perform the AOT instruction is: The estimated time for fuel pump removal is 1 MH per fuel pump. The estimated time for fuel pump inspection is 0.5 MH per fuel pump. The estimated time for fuel pump installation is 3 MH per fuel pump. 5.3 ACCESS WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT. For the center tank fuel pumps installed in locations 37QA and 38QA, refer to the access section of this task: AMM task 28-21-51-000-002-A Removal of the Center Tank Fuel-Pumps. For the wing tank fuel pumps installed in locations 21QA, 22QA, 25QA and 26QA, refer to the access section of this task: AMM task 28-21-51-000-001-A Removal of the Wing Tank Fuel- Pumps. 5.4 INSTRUCTIONS – (RC) WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES ### Page 5 ALERT OPERATORS TRANSMISSION - AOT AOT ref: A28N010-22 Rev 01 Page 5 of 10 Date: 06-MAR-2023 C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT. ***BEG REV*** (1) Determine if fuel pump P/N 568-1-27202-02R is installed on any of the affected locations. ***END REV*** NOTE: A review of aeroplane delivery and maintenance records is acceptable to make this determination, provided those records can be relied upon for that purpose and the P/N 568-1- 27202-02R can be positively identified from that review. (2.1) For fuel pumps installed in center pump locations 37QA and 38QA: a) Remove the fuel pump refer to AMM task 28-21-51-000-002-A Removal of the Center Tank Fuel-Pumps. b) Inspect the fuel pump (refer to section 5.6 INSPECTION) within the timescale defined in section 5.1 PLANNING. c) If after inspection (refer to 5.6 INSPECTION) there is any finding (refer to 5.5 FINDINGS), replace immediately with another fuel pump standard refer to AMM task 28-21-51-400-002-A Installation of the Fuel Pumps (for centre tank) and scrap the fuel pump. d) If after inspection (refer to 5.6 INSPECTION), there are no findings (refer to 5.5 FINDINGS): The fuel pump is acceptable for flight but must be removed and scrapped after a maximum of 4000 Flight Hours, if it is re-installed in the following positions: oCenter tank locations 37QA or 38QA (pre-MOD 154327). or oWing tank locations 21QA, 22QA, 25QA or 26QA on A319/A320 aircraft post-MOD 154327 and A321 aircraft. NOTE: For installation procedure, refer to AMM task 28-21-51-400- 002-A Installation of the Fuel Pumps (for centre tank) and/or AMM task 28-21-51-400-001-A Installation of the Fuel Pumps (for wing tanks). ***BEG REV*** If re-installed in wing tank locations 21QA, 22QA, 25QA or 26QA on A318, A319 or A320 aircraft pre-MOD 15432, the fuel pump is acceptable for flight without restrictions. To re-install it refer to AMM task 28-21-51-400-001-A Installation of the Fuel Pumps (for wing tanks). ***END REV*** ### Page 6 ALERT OPERATORS TRANSMISSION - AOT AOT ref: A28N010-22 Rev 01 Page 6 of 10 Date: 06-MAR-2023 C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT (2.2) For fuel pumps installed in wing tank locations (21QA, 22QA, 25QA and 26QA) on A319/A320 aircraft post-MOD 154327 and on A321 aircraft: a) Remove the fuel pump refer to AMM TASK AMM TASK 28-21-51-000-001-A Removal of the Wing Tank Fuel-Pumps. b) Inspect the fuel pump (refer to section 5.6 INSPECTION) within the timescale defined in section 5.1 PLANNING. ***BEG REV*** c) If after inspection (refer to 5.6 INSPECTION) there is any finding (refer to 5.5 FINDINGS), replace immediately with another fuel pump standard refer to AMM task 28-21-51-400-001-A Installation of the Fuel Pumps (for wing tanks) and scrap the fuel pump. ***END REV*** d) If after inspection (refer to 5.6 INSPECTION), there are no findings (refer to 5.5 FINDINGS): The fuel pump is acceptable for flight but must be removed and scrapped after a maximum of 4000 Flight Hours, if it is re-installed in the following positions: oCenter tank locations 37QA or 38QA. or oWing tank locations 21QA, 22QA, 25QA or 26QA on A319/A320 aircraft post-MOD 154327 and A321 aircraft. NOTE: For installation procedure, refer to AMM task 28-21-51-400- 002-A Installation of the Fuel Pumps (for centre tank) and/or AMM task 28-21-51-400-001-A Installation of the Fuel Pumps (for wing tanks). ***BEG REV*** If re-installed in wing tank locations 21QA, 22QA, 25QA or 26QA on A318, A319 or A320 aircraft pre-MOD 154327, the fuel pump is acceptable for flight without restrictions. To re-install it refer to AMM task 28-21-51-400-001-A Installation of the Fuel Pumps (for wing tanks). ***END REV*** ### Page 7 ALERT OPERATORS TRANSMISSION - AOT AOT ref: A28N010-22 Rev 01 Page 7 of 10 Date: 06-MAR-2023 C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 5.5 FINDINGS Refer below for examples of fuel pump erosion finding on the wiring conduit: Figure 3: Cavitation Erosion Example on Fuel Pump Wiring Conduit (the erosion mark above is not acceptable) Figure 4: Cavitation Erosion Example on Fuel Pump Wiring Conduit (the two erosion marks above are not acceptable) Wiring Conduit Erosion ### Page 8 ALERT OPERATORS TRANSMISSION - AOT AOT ref: A28N010-22 Rev 01 Page 8 of 10 Date: 06-MAR-2023 C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT Refer below for example of inlet guide vane erosion limit: Figure 5: Inlet Guide Vane Erosion (the erosion mark above is acceptable) In case of any finding, the fuel pump must be scrapped refer to section 5.4 INSTRUCTIONS. 5.6 INSPECTION – (RC) ***Start of procedure*** ***BEG REV*** Determine if fuel pump P/N 568-1-27202-02R is installed in any of the affected locations. ***END REV*** NOTE: A review of aeroplane delivery and maintenance records is acceptable to make this determination, provided those records can be relied upon for that purpose and the P/N 568-1- 27202-02R can be positively identified from that review. Visual Inspection of the Fuel Pumps for Cavitation Erosion (1) Hold the pump horizontally with the electrical connector in the 12 o'clock position. NOTE: This will put the pump in a good position to do the inspection. (2) Do a visual inspection for cavitation erosion of the electrical connector conduit. The pump can be moved to fully inspect the wiring conduit. Any erosion noticed on the wiring conduit is not acceptable. Refer to section 5.5 FINDINGS for erosion examples on the wiring conduit. (3) Do a general visual inspection of the fuel pump housing for erosion. Refer to section 5.5 FINDINGS for example of inlet guide vane erosion limit. Minor erosion in the inlet guide vanes is acceptable. Holes in the inlet guide vanes are not acceptable. The distance from the outer edge to the start of the erosion must be more than 12 mm (0.47 in). If this distance is less than 12mm (0.47 in), the condition is not acceptable. ### Page 9 ALERT OPERATORS TRANSMISSION - AOT AOT ref: A28N010-22 Rev 01 Page 9 of 10 Date: 06-MAR-2023 C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 5.7 SPARES AND TOOLING For references 1, 2, 3 and 4 (refer to section 2.2 REFERENCES), the following tooling will be needed: Extractor - Fuel Pump: part number 558-1-05903-002 For references 2 and 4 (refer to section 2.2 REFERENCES) the following parts may be needed depending on the outcome of the inspection (refer to section 5.6 INSPECTION): 568-1-27202-007 568-1-27202-006 568-1-27202-05R P99C38-601 P99C38-605 6. ADDITIONAL INFORMATION 6.1 FOLLOW-UP PLAN oDepending on the findings following this AOT, additional actions may be defined on fuel pumps P/N 568-1-27202-02R for in-service aircraft. 6.2 IMPACTED DOCUMENTATION Applicable IPC sections in IPC chapter 28-21- MAIN FUEL PUMP SYSTEM for fuel pumps FIN 37QA, 38QA, 21QA, 22QA, 25QA and 26QA will be updated to change the interchangeability criteria so that fuel pumps with P/N 568-1-27202-02R will only be 1-way interchangeable with other fuel pump standards (any other fuel pump standard cannot be replaced by fuel pump 568-1-27202- 02R) on the affected locations. 7. AOT APPROVAL The technical content of this document is approved under the authority of the DOA ref.EASA.21J.031. ### Page 10 ALERT OPERATORS TRANSMISSION - AOT AOT ref: A28N010-22 Rev 01 Page 10 of 10 Date: 06-MAR-2023 C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 8. REPORTING ***BEG REV*** Provide your inspection results (with or without findings) with the S/N, MSN, position (FIN) and pictures of the findings (if there are any) on fuel pumps P/N 568-1-27202-02R to Airbus Customer Services through the generic e-mail address: inspection.results@airbus.com The attached AOT reporting sheet can be filled to submit the inspection results. Refer to the latest reporting policy (Ref in the OIT 999.0018/16). Give the AOT reference in the mail title, as follows: {AOT A28N010-22-00} Inspection Result ***END REV*** You can address your questions about this AOT to Airbus Customer Services through TechRequest on Airbus World, selecting Engineering Domain, Engineering Support Section and ATA 28-21, Topic AOT A28N010-22-00. Best Regards, Ahmed CHABBOUH SENIOR DIRECTOR IN SERVICE ENGINEERING CUSTOMER CARE CENTER Jean-Pierre Gomez VICE PRESIDENT A320 PROGRAMME 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. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.