# Airbus All Operators Transmission A36L009-22

## Copies (2)

Copies the FAA filed in AD dockets on regulations.gov, newest revision first. A newer revision may exist.

- Revision 01 ("AOT-A36L009-22-01"): PDF https://openairdocs.org/files/sha256/96/fd/96fd3a2d8460d2df3f9755962117b7e4d317b21fe6da9de966227332c47b0444; text https://openairdocs.org/service-documents/airbus/aot-a36l009-22/file/96fd3a2d8460.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2023-0156, the docket of AD 2023-11-08. Not covered by OpenAirDocs’ CC0 dedication.
- AOT_A36L009-22_R2 ("AOT_A36L009-22_R2"), 29 pages: PDF https://openairdocs.org/files/sha256/5f/68/5f68817f7262777eb6c3359ddb473032bc9c54c9eb68450550e33471bb2a6557; text https://openairdocs.org/service-documents/airbus/aot-a36l009-22/file/5f68817f7262.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2024-0766, the docket of AD 2025-04-05. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Other document (All Operators Transmission)
- Number: A36L009-22
- Latest revision known: A36L009-22, Revision 01, dated October 3, 2022 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/aot-a36l009-22

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2023-11-08](https://openairdocs.org/ad/2023-11-08.md), effective Jul 18, 2023: Revision 01

## Text (29 pages)

AOT_A36L009-22_R2, the newest copy. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2024-0766, the docket of AD 2025-04-05. Not covered by OpenAirDocs’ CC0 dedication. Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A36L009-22 Rev 02 Page 1 of 29 Date: 15-MAY-2023
C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
SUBJECT: ATA 36 – A330neo - HPV clip failure and butterfly sealing rings damaged
AIRCRAFT TYPE:  A330-800, A330-900
OUR REF.: A36L009-22 Rev 02 dated 15-MAY-2023
OUR PREVIOUS REF.: A36L009-22 Rev 01 dated 03-OCT-2022
OUR PREVIOUS REF.: A36L009-22 Rev 00 dated 25-AUG-2022
EFFECTIVITY DATE: 29-AUG-2022
0. REASON FOR REVISION
This AOT is revised for the following reasons:
- Correct typo errors,
- Improve wording,
- Introduce the limit of 600 FC for preventive clip replacement in § 5.6.H,
- Include troubleshooting procedure for ECAM Warning ENG 1 BLEED NOT CLSD and ENG 2 
BLEED NOT CLSD without associated maintenance message § 5.6.D,
- Introduce a 1000FH periodic HPV seal integrity test for aircraft embodied with BMC software 4.0 PN 
LIE3EL71078AAAH in § 5.6.I,
- Introduce alleviation of inspections after take-off or go-around with engine bleed OFF, packs off or 
APU bleed on for aircraft embodied with BMC software 4.1 PN LIE3EL71078AAAJ in § 5.6.E,
- Update maintenance instructions in § 5.6.H:
●Allow enough time for the bleed system to be pressurised to a stable value before 
checking the BMPS value,
The revised paragraphs are indicated between ***BEG REV*** and ***END REV***.
1. AIRCRAFT AFFECTED
A330-800
A330-900
2. REFERENCED DOCUMENTATION
2.1 APPENDIX
Reporting sheet
2.2 REFERENCES
TFU 36.11.00118
FOT REF.:999.0062/22
EASA AD 2022-0181
EASA AD 2022-0227
FAA AD 2022-19-05
AMM TASK 36-11-00-040-831-A: Deactivation of the High Pressure Valve (HPV)
AMM TASK 36-11-00-440-825-A: Reactivation of the High Pressure Valve (HPV)
AMM TASK 36-11-51-000-806-A: Removal of the HP Bleed Valve
AMM TASK 36-11-51-400-806-A: Installation of the HP Bleed Valve

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ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A36L009-22 Rev 02 Page 2 of 29 Date: 15-MAY-2023
C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
AMM TASK 36-11-51-720-813-A: Functional Test of the HP Bleed Valve (HPV) with the Test Set P/N 
98L36103002000 and the KIT 98F3610900100
AMM TASK 36-11-51-720-813-A01: Functional Test of the HP Bleed Valve with Test Set P/N 99127B04
AMM TASK 36-11-52-000-807-A: Removal of the Bleed Valve
AMM TASK 36-11-52-400-807-A: Installation of the Bleed Valve
AMM TASK 36-11-52-720-810-A01: Functional Test of the Pressure Regulating Valve (PRV) with Test 
Set P/N 99127B04
AMM TASK 36-11-52-720-810-A Functional Test of the Pressure Regulating Valve (PRV) with the Test 
Set P/N 98L36103002000 and the Adaptor Kit P/N 98F36109001000
SB 36-3049 DISTRIBUTION - ADAPT WING BELLOWS DEFINITION ON A330 NEO PYLON FOR 
QUALIFICATION PURPOSE
AMM TASK 36-11-49-200-809-A: Detailed Inspection of the Wing Bellow
AMM TASK 36-11-49-220-802-A: Detailed Inspection of the Pylon Bellows
AMM TASK 36-11-53-720-809-A: Functional Check of Overpressure Valve with the Test Set P/N 
98L36103002000 and the KIT 98F36109001000
AMM TASK 36-11-53-720-809-A01: Functional Check of Overpressure Valve with Test Set P/N 
99127B04
3. REASON
3.1 FACTS
Airbus informs operators that several cases of High Pressure Bleed Valve (HPV) clip rupture have been 
reported. HPV clip degradation and rupture lead to damage to the HPV butterfly sealing rings.
NOTE: HPV CLIP AND HPV CLAMPING PIN ARE REFERRING TO THE SAME PART.
Figure 1: Location of HPV PN 71070A010001 or PN 71070A020001

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ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A36L009-22 Rev 02 Page 3 of 29 Date: 15-MAY-2023
C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
Figure 2: HPV butterfly clip and sealing rings 
Figure 3: HPV with clip and sealing rings still in place

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ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A36L009-22 Rev 02 Page 4 of 29 Date: 15-MAY-2023
C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
Figure 4: HPV with clip and sealing rings missing
3.2 CONSEQUENCES
In case of HPV clip failure with sealing rings damaged or missing, there is a tightness degradation when 
the valve is in closed position and an excessive residual leakage at the HPV is experienced. This 
leakage could eventually cause damage to the Pressure Regulating Valve (PRV) bearings, and thus 
prevent the PRV from properly closing when required.  
It has been observed that the above phenomenon has caused an overpressure event and pylon ducts 
deformation:
  
     
Figure 5: Pylon Duct and structure damage
This scenario could result in a potential unsafe condition if the wing ducting is damaged, leading to hot 
bleed air leak in the area, that would not be isolated if the PRV bearings are degraded with the HPV 
butterfly sealing rings damage condition.

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ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A36L009-22 Rev 02 Page 5 of 29 Date: 15-MAY-2023
C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
4. OBJECTIVES OF THIS AOT
The aim of this AOT is to provide the below instructions to mitigate the HPV clip failure issue:
●A one-off HPV Seal Integrity test must be performed before the next flight from the AOT effective 
date. Refer to Instruction paragraph 5.6.B.
●Introduction of additional maintenance actions for Class 1 Maintenance Messages associated to 
the HPV “Not fully closed” fault or in case HPV Seal Integrity test failed (see paragraph 5.6.C).
***BEG REV***
●Introduction of additional maintenance actions for Class 1 and Class 2 Maintenance Messages and 
E/W associated to the PRV fault (see paragraph 5.6.D).
***END REV***
●Introduction of the HPV Seal Integrity test, if one of the following conditions is reported in the aircraft 
logbook (aircraft log book to be checked after each flight) (see paragraph 5.6.E):
●Take-off or Go-Around with pack(s) OFF
●Take-off or Go-Around with engine(s) bleed OFF
●Take-off or Go-Around with APU Bleed ON
●Introduction of the HPV Inspection Procedure (see paragraph 5.6.F).
●Introduction of the Visual Inspection of the EBAS after failure of the HPV (see paragraph 5.6.G).
●Introduction of the Preventive HPV clip replacement (see paragraph 5.6.H).
***BEG REV***
●Introduce a periodic HPV seal integrity test for aircraft embodied with BMC software previous to 4.1 
PN LIE3EL71078AAAJ in § 5.6.I
***END REV***
●FOT REF.: 999.0062/22 for operation instructions, and MMEL dispatch conditions.
5. MAINTENANCE PROCEDURE
***BEG REV***
NOTE: A new EASA AD is expected to be issued to encompass the changes introduced by this revision, 
in the meantime, the A36L009-22 Rev 01 remains mandated by the EASA Airworthiness Directive (AD) 
reference AD 2022-0227, which superseded EASA AD 2022-0181, and FAA AD 2022-19-05. 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 “as per”.
***END REV***
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 their local authority. These instructions are 
introduced by “refer to”.
NOTE: When this AOT gives the access, close-up or job set-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.

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ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A36L009-22 Rev 02 Page 6 of 29 Date: 15-MAY-2023
C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
NOTE: Any tool listed as alternate in the Tool and Equipment Manual is acceptable for the 
accomplishment of the AMM tasks or instructions called in this AOT.
NOTE: Operators may use any alternate tool or equipment qualified under agreement, or 
privileges  granted by their local authorities.
5.1 PLANNING – (RC)
New troubleshooting instructions and maintenance actions given in this AOT (see paragraph 5.6.C, 
5.6.D, 5.6.E) are applicable from the AOT Rev. 00 effective date.
The compliance time for the one-off HPV Seal Integrity test is before the next flight from the AOT Rev. 
00 effective date (paragraph 5.6.B).
 ***BEG REV***
The compliance time for the HPV clip (PN 6764-222) replacement (paragraph 5.6.H) is the following 
one:
●The first replacement of the HPV clip has to be performed before one of this two conditions is 
met, whichever occurs first:
oBefore the HPV clip has accumulated 4000FH or within 1500FH from the effective date 
of EASA AD 2022-0181, whichever occurs later of these two conditions
oBefore the HPV clip has accumulated 600FC or, whichever comes first, within 60 days 
or 225 FC from the issuance date of this AOT Rev.02, whichever occurs later of these 
two conditions.
●Then, the interval for the repetitive replacement of the HPV clip is 4000FH or 600FC whichever 
occurs first.
Refer to the figure 6: Clip replacement compliance time flowchart below for additional clarification.
Figure 6: Clip replacement compliance time flowchart
***END REV***
5.2 MANPOWER
Removal of the HPV:
Wichever occurs later 
Wichever occurs first 
Before HPV clip has cumulated 4000FH
Within 1500 FH from AD 2022-0181 effective date
Clip replacement compliance time
Wichever occurs later 
Before the HPV clip has cumulated 600FC
Wichever occurs first 
Within 60 days from AOT 36L009-22 rev02 issuance date
Within 225FC from AOT 36L009-22 rev02 issuance date

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ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A36L009-22 Rev 02 Page 7 of 29 Date: 15-MAY-2023
C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
●Job Set-up and access refer to AMM TASK 36-11-51-000-806-A: 0.50 MH
●Removal of the HPV on ENG1 side or ENG2 side refer to AMM TASK 36-11-51-000-806-A: 1 MH
Replacement of clip PN 6764-222:
●Removal of the HPV clip as per AOT instruction: 0.25 MH
●Installation of the HPV clip as per AOT instruction: 0.25 MH
Installation of the HPV:
●Installation of the HPV on ENG1 side or ENG2 side refer to AMM TASK 36-11-51-400-806-A: 2 MH
●Test for HPV leak check refer to AMM TASK 36-11-51-400-806-A: 1 MH
●Close-up: 1 MH
Removal of the PRV:
●Job Set-up and access refer to AMM TASK 36-11-52-000-807-A: 1 MH
●Removal of the PRV on ENG1 side or ENG2 side refer to AMM TASK 36-11-52-000-807-A: 1 MH
Installation of the PRV:
●Installation of the PRV on ENG1 side or ENG2 side refer to AMM TASK 36-11-52-400-807-A: 1 MH
●Test for PRV leak check refer to AMM TASK 36-11-52-400-807-A: 0.75MH
●Close-up refer to 36-11-52-400-807-A: 0.50 MH
●between 6 hours and 48 hours for EBAS flare seal curing time. 
Functional test of the PRV refer to AMM Task 36-11-52-720-810-A01: 1 MH for test + between 6 hours 
and 48 hours for EBAS flare seal curing time. 
HPV Seal Integrity test as per AOT instruction (paragraph 5.6.A): 0.5 MH 
Visual Inspection of the EBAS After Failure of the HPV as per AOT instruction (paragraph 5.6.G): 7 MH
5.3 ACCESS
For the removal and installation of the HPV:
●AMM task 36-11-51-000-806-A – Removal of the HPV
●Access door 811 
●Fan Cowl Doors 415AL and 416AR for ENG1 
●Fan Cowl Doors 425AL and 426AR for ENG2 
●Thrust Reverser 417AL and 418AR for ENG1
●Thrust Reverser 427AL and 428AR for ENG2
●AMM task 36-11-51-400-806-A – Installation of the HPV
●Access door 811 
●Fan Cowl Doors 415AL and 416AR for ENG1 
●Fan Cowl Doors 425AL and 426AR for ENG2 
●Thrust Reverser 417AL and 418AR for ENG1
●Thrust Reverser 427AL and 428AR for ENG2
For the PRV Functional test, and for the removal and installation of the PRV:
●AMM task 36-11-52-720-810-A / AMM task 36-11-52-720-810-A01: 
●Access door 811 
●Fan Cowl Doors 415AL and 416AR for ENG1 
●Fan Cowl Doors 425AL and 426AR for ENG2
●Thrust Reverser 417AL and 418AR for ENG1
●Thrust Reverser 427AL and 428AR for ENG2

### Page 8

ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A36L009-22 Rev 02 Page 8 of 29 Date: 15-MAY-2023
C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
For the EBAS ducting inspection after failure of the HPV:
●Fan Cowl Doors 415AL and 416AR for ENG1 
●Fan Cowl Doors 425AL and 426AR for ENG2
●Thrust Reversers 417AL and 418AR for ENG1 
●Thrust Reversers 427AL and 428AR for ENG2 
 
5.4 INSPECTION – RC
A HPV Seal Integrity test must be performed to ensure the correct condition of the HPV butterfly  sealing 
rings:
●at the release of the AOT Rev. 00 (paragraph 5.6.B),
●and after flight performed under the following conditions (paragraph 5.6.E):
o   Take-off or Go-Around with pack(s) OFF
o   Take-off or Go-Around with engine(s) bleed OFF
o   Take-off or Go-Around with APU Bleed ON
***BEG REV***
A check of the PFR for HPV Class 1 Maintenance Messages and PRV Class 1 and 2 Maintenance 
Messages and E/W must be performed before each flight (paragraph 5.6.C and 5.6.D).
***END REV***
A visual inspection of the HPV must be performed to check the butterfly clip and sealing rings condition 
(paragraph 5.6.F). 
5.5 FINDINGS – RC 
In case of butterfly clip failure and/or sealing rings findings, the HPV replacement procedure and EBAS 
inspection procedure must be performed as per AOT Instructions paragraph 5.6.G 
5.6 INSTRUCTIONS – RC Instructions are highlighted in grey in this paragraph
5.6.A. HPV SEAL INTEGRITY TEST (test instructions similar to AMM task 36-11-00-720-840-A)
Required at paragraphs 5.6.B, 5.6.C, 5.6.D, 5.6.E and 5.6.I
***START OF THE PROCEDURE***
5.6.A.1. General
1. Perform firstly "5.6.A.2.1. SECURE CLOSED INSTRUCTIONS" or not, to HPV1 and/or HPV2, 
as per airline convenience.
NOTE: IF STEP 5.6.A.2.2 RESULT IS BMPS1 AND BMPS2 ABOVE 5 PSIG (SUCCESSFUL) 
AND STEP 5.6.A.2.1 WAS NOT CARRIED OUT BEFORE, THE TEST IS CONSIDERED 
FINISHED AND CARRIED OUT IN THE SHORTEST WAY (NO NACELLE OPENING TO 
GET ACCESS TO THE HPV).

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ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A36L009-22 Rev 02 Page 9 of 29 Date: 15-MAY-2023
C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
NOTE: IN CASE THE AIRLINE DO NOT APPLY STEP 5.6.A.2.1 FIRST, IF 5.6.A.2.2 
RESULT IS EQUAL OR BELOW 5 PSIG (UNSUCCESSFUL), 5.6.A.2.2  TEST WILL BE 
REQUIRED AGAIN WITH 5.6.A.2.1 APPLICATION REQUIRED TO CONFIRM THE 
RESULT.
5.6.A.2. Instructions
5.6.A.2.1. SECURE CLOSED INSTRUCTIONS
Manually secure corresponding HPV in the Fully Closed position Refer to AMM TASK 36-11-00-040-
831-A. 
Perform 5.6.A.2.2 instructions.
5.6.A.2.2. BMPS CHECKING INSTRUCTIONS
1. Job Set-up Information
A. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits refer to AMM TASK 24-41-00-861-801.
(2) On ENG MASTER control panel 125VU:
(a) Make sure that the ENG/MASTER switches for engines 1 and 2 are set to the 
OFF position.
 (3) On AIR COND panel 225VU:
(a) Make sure that all the ENG BLEED pushbutton switches are released (the OFF 
legends are on).
(b) Make sure that all the PACK pushbutton switches are released (the OFF 
legends are on).
B. Check of the Transferred Pressure Transducer conditions:
(1) Check of the CLASS 3 Maintenance Messages Refer to AMM TASK 36-11-00-
710-828-A Operational Test to Read the CMC for the CLASS 3 FAULTS of the 
BMC. Before you continue, perform the required troubleshooting/maintenance 
tasks to address the following Maintenance Messages, if present: 
●36.11.34 BMC1 (1HA1)/WRG:TRANSF PRESS XDCR
●TSM task 36-11-00-810-A97-A.
●36.11.34 BMC2 (1HA2)/WRG:OPPTRANSF PRESS XDCR or 
36.11.34 BMC2 (1HA2)/WRG:LTRANSF PRESS XDCR
●TSM task 36-11-00-810-A98-A.
●36.11.34 BMC2 (1HA2)/WRG:TRANSF PRESS XDCR
●TSM task 36-11-00-810-B00-A.
●36.11.34 BMC1 (1HA1)/WRG:OPPTRANSF PRESS XDCR or 
36.11.34 BMC1 (1HA1)/WRG:RTRANSF PRESS XDCR
●TSM task 36-11-00-810-A99-A.
(2) Check of the CLASS 2 Maintenance Messages in the Post Flight Report of the 
previous flight. Before you continue, perform the required 
troubleshooting/maintenance tasks, to address the following Maintenance 
Messages, if present:
●36.11.15 DRIFT TRANSF PRESS XDCR(9HA1)/SENSE LINE
●TSM task 36-11-00-810-A69-A.
●36.11.15 DRIFT TRANSF PRESS XDCR(9HA2)/SENSE LINE
●TSM task 36-11-00-810-A70-A.
●36.11.15 TRANSF PRESS XDCR (9HA1)

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C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
●TSM task 36-11-00-810-A71-A.
●36.11.15 TRANSF PRESS XDCR (9HA2)
●TSM task 36-11-00-810-A72-A.
***BEG REV***
(3) On the MCDU, refer to AMM TASK 31-36-00-740-805-A, SUBTASK 31-36-00-
740-054-A:
(a) Add the following parameter alpha call-up: 
- Parameter: BMPS1 - Information: Engine 1 (Left side) transferred 
pressure. 
- Parameter: BMPS2 - Information: Engine 2 (Right side) transferred 
pressure.
***END REV***
2. Procedure
Ref. Fig. MCDU BMPS page
Ref Fig. Flowchart summary
***BEG REV***
A. Reading of the alpha call-up for the BMPS value
(1) Pressurize the bleed system either with the APU bleed refer to AMM TASK 36-
12-00-860-803-A, or with the Ground Air Supply Unit refer to AMM 36-12-00-
860-804-A.
(2) Make sure that, on the BLEED page of the SD, the green crossbleed-valve 
symbol is shown in the open position. If not, set the X-BLEED selector switch 
to OPEN.
(a)Pressurize the bleed system with the APU or the Ground Air Supply Unit, when 
the pressure is steady, check the BMPS1 and BMPS2 values
***END REV***
●If BMPS1 is higher than 5 PSIG and BMPS2 is higher than 5 PSIG, then the test is successful.
If 5.6.A.2.2 test was carried out with any HPV manually closed (5.6.A.2.1 instruction applied), 
REACTIVATE THE CORRESPONDING HPV REFER TO AMM TASK 36-11-00-440-825-A. 
No further action is necessary.
●In any other case:
 1 If BMPS1 is lower than or equal to 5 PSIG:
●If 5.6.A.2.2 test was carried out with HPV1 not manually closed (5.6.A.2.1 
instruction not applied), then:
●Apply 5.6.A.2.1 instructions on HPV1
●Repeat 5.6.A.2.2 instructions on EBAS1.
●If 5.6.A.2.2 test was carried out with HPV1 manually closed (5.6.A.2.1 
instruction applied), then:
●REACTIVATE THE CORRESPONDING HPV REFER TO 
AMM TASK 36-11-00-440-825-A
●Perform HPV1 INSPECTION PROCEDURE (paragraph 
5.6.F).
 2 If BMPS2 is lower than or equal to 5 PSIG:
●If 5.6.A.2.2 test was carried out with HPV2 not manually closed (5.6.A.2.1 
instruction not applied), then:
●Apply 5.6.A.2.1 instructions on HPV2
●Repeat 5.6.A.2.2 instructions on EBAS2.

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●If 5.6.A.2.2 test was carried out with HPV2 manually closed (5.6.A.2.1 
instruction applied), then:
●REACTIVATE THE CORRESPONDING HPV REFER TO 
AMM TASK 36-11-00-440-825-A
●Perform HPV2 INSPECTION PROCEDURE (paragraph 
5.6.F).
NOTE: PRESSURE READINGS COULD BE DIFFERENT BETWEEN BMPS1 AND BMPS2.
Figure 7: MCDU BMPS page

### Page 12 (OCR)

AIRBUS
ALERT OPERATORS TRANSMISSION - AOT
START
Choose if both HPVs will be secured closed
nOL  as pe  step 5.6.A.2.1.  before
tarting step 5.6.A.2.2. BMPS CHECKING
INSTRUCTIONS.
-Do step 5.6.A.2.2. BMPS CHECKING
INSTRUCTIONS.
•Secure close the HPV1(2) where the
BMPS1(2) is ≤ 5 psig, as per step
6.A.2.1. SECURE CLOSED
STRUCTIONS.
Are BMPS1 and
BMPS2 > 5 psig?
Was step
5.6.A.2.1.
SECURE CLOSED  NO
INSTRUCTIONS applied
on the HPV1(2) where
the BMPS1(2)
is ≤ 5 psig?
YES
-Inspect as per paragraph 5.6.F, the HPV1(2)
where the BMPS1(2) was below or equal to 5
psig.
END
Figure 8: Flowchart summary of procedure
3. Close-up
(1)  Shutdown the APU air bleed supply refer to AMM TASK 36-12-00-860-803-A,
or disconnect and remove the Ground Air Supply Unit refer to AMM TASK
36-12-00-860-804-A.
(2)  Close Access
(a) De-energize the aircraft electrical circuits Refer to AMM TASK 24-41-00-862-
801.
***END OF THE PROCEDURE***
5.6.B. ONE-OFF HPV SEAL INTEGRITY TEST
Perform a one-off check of the HPV Seal Integrity as per paragraph 5.6.A. To be performed before the
next flight after the AOT Rev.00 effective date.
5.6.C. HPV 4000HA1(2) CLASS 1 MAINTENANCE MESSAGE
From the AOT Rev. 00 effective date, in case of the below Class 1 Maintenance Messages associated
to the HPV fault, it is requested to perform the following actions before the next flight:
AOT ref: A36L009-22 Rev 02  Page 12 of 29  Date: 15-MAY-2023
C80_AOT_FM1104649_v8.0  © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT

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AOT ref: A36L009-22 Rev 02 Page 13 of 29 Date: 15-MAY-2023
C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
●ECAM Warning AIR ENG 1 BLEED FAULT with Fault Message HP BLEEDV 
(4000HA1)/SENSE LINE: apply the HPV Troubleshooting Flowchart from START to 
END. 
Additionally if SB 36-3049 is not embodied, do a detailed inspection of the wing bellow 
on engine 1 Refer to AMM TASK 36-11-49-200-809-A. If there is a damage or 
deformation, replace the wing bellow Refer to AMM TASK 36-11-49-000-855-A and 
AMM TASK 36-11-49-400-855-A.
●ECAM Warning AIR ENG 2 BLEED FAULT with Fault Message HP BLEED-V 
(4000HA2)/SENSE LINE: apply the HPV Troubleshooting Flowchart from START to 
END.
Additionally if SB 36-3049 is not embodied, do a detailed inspection of the wing bellow 
on engine 2 Refer to AMM TASK 36-11-49-200-809-A. If there is a damage or 
deformation, replace the wing bellow Refer to AMM TASK 36-11-49-000-855-A and 
AMM TASK 36-11-49-400-855-A.
●ECAM Warning AIR ENG 1 BLEED FAULT with Fault Message HP BLEED-V 
(4000HA1)/DUCT: apply the HPV Troubleshooting Flowchart from START to END.
Additionally perform:
a. Inspection of the ENG 1 wing bellow refer to AMM TASK 36-11-49-
200-809-A. In case of finding, contact Airbus and await for instructions 
before the next flight.
b. Inspection of the ENG 1 pylon bellows refer to AMM TASK 36-11-49-
220-802-A. In case of finding, contact Airbus and await for instructions 
before the next flight.
c. Functional check of the ENG 1 overpressure valve refer to AMM TASK 
36-11-53-720-809-A or AMM TASK 36-11-53-720-809-A01. In case of 
finding, contact Airbus and await for instructions before the next flight.
●ECAM Warning AIR ENG 2 BLEED FAULT with Fault Message HP BLEED-V 
(4000HA2)/DUCT: apply the HPV Troubleshooting Flowchart from START to END.
Additionally perform:
●Inspection of the ENG 2 wing bellow refer to AMM TASK 36-11-49-
200-809-A.  In case of finding, contact Airbus and await for instructions 
before the next flight.
●Inspection of the ENG 2 pylon bellows refer to AMM TASK 36-11-49-
220-802-A.  In case of finding, contact Airbus and await for instructions 
before the next flight.
●Functional check of the ENG 2 overpressure valve refer to AMM TASK 
36-11-53-720-809-A or AMM TASK 36-11-53-720-809-A01. In case of 
finding, contact Airbus and await for instructions before the next flight.

### Page 14 (OCR)

AIRBUS
ALERT OPERATORS TRANSMISSION - AOT
START
-Do the HPV SEAL INTEGRITY TEST as per
paragraph 5.6.A.
YES
Are BMPS1 and BMPS2
higher than 5 PSIG?
NO
-Perform the Air Duct Leak Check Refer to
AMM TASK 71-00-00-790-808-A.
Make sure to check that there are no leaks on
the HPV sense line itself and its two
connections (to ducting and to HPV), by
pressurising from the engine.
END
-If after the subsequent flight, the maintenance
message HP BLEED-V (4000HA1(2))/SENSE
LINE or HP BLEED-V (4000HA1(2))/DUCT is
shown on the same engine side, contact Airbus
and await for instructions before the next flight.
Figure 9: HPV Troubleshooting Flowchart
***BEG REV***
5.6.D. CLASS 1 AND 2 MAINTENANCE MESSAGES AND E/W ASSOCIATED TO THE PRV
From the AOT Rev. 00 effective date, in case of following Class 1 & Class 2 Maintenance Messages
and E/W associated to the PRV bleed valve fault, it is requested to perform the following actions before
the next flight:
ECAM Warning ENG 1 BLEED NOT CLSD with or without Fault Message PRESS
REG-V (4001HA1)/SENSE LINE: refer to TSM TASK 36-11-00-810-A08-A.
Additionally, perform the HPV Seal Integrity test as per paragraph 5.6.A.
• ECAM Warning ENG 2 BLEED NOT CLSD with or without Fault Message PRESS
REG-V (4001HA2)/SENSE LINE: refer to TSM TASK 36-11-00-810-A09-A.
Additionally, perform the HPV Seal Integrity test as per paragraph 5.6.A.
• ECAM Warning AIR ENG 1 BLEED FAULT with Fault Message PRESS REG-V
(4001HA1): refer to TSM TASK 36-11-00-810-A06-A. Additionally, perform the HPV
Seal Integrity test as per paragraph 5.6.A.
• ECAM Warning AIR ENG 2 BLEED FAULT with Fault Message PRESS REG-V
(4001HA2): refer to TSM TASK 36-11-00-810-A07-A. Additionally, perform the HPV
Seal Integrity test as per paragraph 5.6.A.
• ECAM Warning AIR ENG 1 BLEED FAULT with Fault Message PRESS REG-V
(4001HA1)/SENSE LINE: refer to TSM TASK 36-11-00-810-A04-A. Additionally,
perform the HPV Seal Integrity test as per paragraph 5.6.A.
AOT ref: A36L009-22 Rev 02  Page 14 of 29  Date: 15-MAY-2023
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ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A36L009-22 Rev 02 Page 15 of 29 Date: 15-MAY-2023
C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
●ECAM Warning AIR ENG 2 BLEED FAULT with Fault Message PRESS REG-V 
(4001HA2)/SENSE LINE: refer to TSM TASK 36-11-00-810-A05-A. Additionally, 
perform the HPV Seal Integrity test as per paragraph 5.6.A.
●Class II Maintenance Message PRESS REG-V (4001HA1)/SENSE LINE: refer to TSM 
TASK 36-11-00-810-A67-A. Additionally, perform the HPV Seal Integrity test as per 
paragraph 5.6.A.
●Class II Maintenance Message PRESS REG-V (4001HA2)/SENSE LINE: refer to TSM 
TASK 36-11-00-810-A68-A. Additionally, perform the HPV Seal Integrity test as per 
paragraph 5.6.A.
***END REV***
5.6.E. HPV SEAL INTEGRITY TEST DUE TO TAKE-OFF AND GO-AROUND CONFIGURATION  
***BEG REV***
●For aircraft equipped with BMC software 4.0 (PN LIE3EL71078AAAH)  installed (pre MOD 
209292 or SB 36-3050 not embodied):
After each flight, the aircraft logbook must be checked. 
Check if one of the below conditions was performed: 
●Take-off or Go-Around with pack(s) OFF
●Take-off or Go-Around with engine(s) bleed OFF
●Take-off or Go-Around with APU Bleed ON
If one of the above conditions was performed, do the HPV Seal Integrity test as per the procedure 
provided in paragraph 5.6.A. before the next flight.
●For aircraft equipped with BMC software 4.1 (PN LIE3EL71078AAAJ) installed (MOD 209292 
or SB 36-3050 embodied):
After each flight, the aircraft logbook must be checked. 
Check if one of the below conditions was performed: 
●Take-off or Go-Around with pack(s) OFF
●Take-off or Go-Around with engine(s) bleed OFF
●Take-off or Go-Around with APU Bleed ON
If one of the above conditions was performed, do the HPV Seal Integrity test as per the procedure 
provided in paragraph 5.6.A. within the next 10 flight cycles.
***END REV***
5.6.F. HPV INSPECTION PROCEDURE
Perform this procedure when required in paragraph 5.6.A.
***START OF THE PROCEDURE***
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER ENGINE 
SHUTDOWN. THE ENGINE PARTS CAN STAY HOT FOR ALMOST ONE HOUR. 
DO NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN 
CAUSE INJURIES TO PERSONNEL.
WARNING:

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ALERT OPERATORS TRANSMISSION - AOT 
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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.
WARNING:
MAKE SURE THAT THE PNEUMATIC SYSTEM IS DEPRESSURIZED BEFORE 
YOU START WORK.
PRESSURIZED AIR CAN CAUSE INJURY TO PERSONNEL.
WARNING:
BEFORE YOU REMOVE/INSTALL THE COMPONENT, MAKE SURE THAT YOU 
CAN HOLD IT. THE COMPONENT IS HEAVY. IF IT FALLS, IT CAN CAUSE INJURY 
TO PERSONS AND DAMAGE TO EQUIPMENT.
(1) Remove the  HPV (4000HA1(2)) refer to AMM TASK 36-11-51-000-806-A.
NOTE: AMM TASK 36-11-51-000-806-A CALLS AMM TASK 36-11-00-210-
801, WHICH IS NOT REQUIRED, SINCE THE APPLICABLE 
INSTRUCTIONS ARE PROVIDED WITHIN THIS AOT IN THE VISUAL 
INSPECTION OF THE EBAS AFTER FAILURE OF THE HPV 
(PARAGRAPH 5.6.G). 
(2) Open the valve: use the position indicator nut with a wrench OR move the 
butterfly with the hands.
(3) Do a visual inspection of the HPV (4000HA1(2)) and make sure that the clip 
in the HPV butterfly is not missing or damaged (see Figure 3 and 4).
(4) In case of clip missing and/or sealing rings missing/damaged:
a. Make pictures of the HPV (4000HA1(2)) with the following details: P/N and 
S/N, general view, clip status, butterfly status (from both ends of the valve: inlet 
and outlet). Send these pictures to Airbus via TechRequest selecting 
Engineering Domain Engineering Support Section and ATA 36-11/ Topic HPV 
Clip Failure.
b. The damaged HPV is considered unserviceable.
c. Perform an inspection of the EBAS as per paragraph 5.6.G.
***BEG REV***
d. Install a serviceable HPV, with a clip with less than 4000FH,  and less than 
600FC, refer to AMM task 36-11-51-400-806-A.
***END REV***
(5) In case of clip and the sealing rings are in good condition
a. Close the valve: use the position indicator nut with a wrench OR move the 
butterfly manually.
b. Reinstall the HPV Refer to AMM task 36-11-51-400-806-A.
NOTE: WHEN PERFORMING THE AIR DUCT LEAK CHECK REFER 
TO AMM TASK 71-00-00-790-808-A  (AS REQUIRED BY AMM TASK 
36-11-51-400-806-A), MAKE SURE TO CHECK THERE ARE NO 
LEAKS ON THE HPV SENSE LINE ITSELF AND ITS TWO 
CONNECTIONS (TO DUCTING AND TO HPV), BY PRESSURISING 
FROM THE ENGINE.

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***END OF THE PROCEDURE***
5.6.G. VISUAL INSPECTION OF THE EBAS AFTER FAILURE OF THE HPV
Perform this procedure when the HPV is found with a clip failed and/or with butterfly sealing rings 
damaged or missing.
***START OF THE PROCEDURE***
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER ENGINE 
SHUTDOWN. THE ENGINE PARTS CAN STAY HOT FOR ALMOST ONE HOUR. 
DO NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN 
CAUSE INJURIES TO PERSONNEL.
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.
WARNING:
MAKE SURE THAT THE PNEUMATIC SYSTEM IS DEPRESSURIZED BEFORE 
YOU START WORK.
PRESSURIZED AIR CAN CAUSE INJURY TO PERSONNEL.
WARNING:
BEFORE YOU REMOVE/INSTALL THE COMPONENT, MAKE SURE THAT YOU 
CAN HOLD IT. THE COMPONENT IS HEAVY. IF IT FALLS, IT CAN CAUSE INJURY 
TO PERSONS AND DAMAGE TO EQUIPMENT.
1. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION
No specific AR ACCESS PLATFORM 2M (6 FT)
No specific AR ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE
No specific 1 BORESCOPE SET
No specific AR SAFETY CLIP - CIRCUIT BREAKER
No specific AR WARNING NOTICE(S)
98D27803000000 1 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION
B. Work Zones and Access Panels
ZONE/ACCESS ZONE DESCRIPTION

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C80_AOT_FM1104649_v8.0 © AIRBUS S.A.S. 2023. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
410
420
193CB, 811
FOR 4030EM1 (POWERPLANT DEMOUNTABLE, ENG 1)
415AL, 416AR, 417AL, 418AR
FOR 4030EM2 (POWERPLANT DEMOUNTABLE, ENG 2)
425AL, 426AR, 427AL, 428AR
C. Referenced Information
REFERENCE DESIGNATION
24-41-00-861-801 Energize the Aircraft Electrical Circuits from the External
Power A
24-41-00-862-801 De-energize the Aircraft Electrical Circuits from the External
Power A
36-11-00-740-807 BITE Test of the Engine Bleed Air System (EBAS) (System
Test)
36-11-41-000-806 Removal of the Intermediate Pressure (IP) Bleed Non-Return
Valve
36-11-41-400-806 Installation of the Intermediate Pressure (IP) Bleed Non-
Return Valve
36-11-52-000-807 Removal of the Bleed Valve
36-11-52-400-807 Installation of the Bleed Valve
52-41-00-010-801 Opening of Avionics-Compartment Access Door 811
52-41-00-410-801 Closing of Avionics-Compartment Access Door 811
71-00-00-790-808 Air Duct Leak Check
71-13-00-010-816 Opening of the Fan Cowl Doors
71-13-00-410-816 Closing of the Fan Cowl Doors
78-30-00-040-826 Deactivation of the Thrust Reverser for Maintenance
78-30-00-440-826 Reactivation of the Thrust Reverser after Maintenance
78-36-00-010-805 Opening of the Thrust Reverser Cowl Doors for Maintenance
(44-degree angle)
78-36-00-410-805 Closing of the Thrust Reverser Cowl Doors after Maintenance
(44-degree angle)
Ref. Fig. EBAS - Location and Detail
2. Job Set-up
A. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits refer to AMM TASK 24-41-00-861-801.
B. Safety Precautions
(1) Make sure that the engine shutdown occurred five minutes or more before you 
do this procedure.
(2) On the overhead panel, on the AIR section of control panel 225VU, make sure 
that these pushbutton switches are released:
- The APU BLEED pushbutton switch (the ON legend is off)
- All the ENG BLEED pushbutton switches (the OFF legends are on)
- The PACK 1 and PACK 2 pushbutton switches (the OFF legends are on).

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(3) Put the WARNING NOTICE(S) in position to tell persons not to operate the 
pneumatic system.
(4) On APU control panel 215VU, put the WARNING NOTICE(S) in position to tell 
persons not to start the APU.
(5) On the center pedestal, on ENG START control panel 145VU, put the 
WARNING NOTICE(S) in position to tell persons not to start the engines.
WARNING: MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND 
THE WARNING NOTICES ARE IN POSITION.
MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS.
(6) On the center pedestal, on FLAPS control panel 114VU:
(a) Install the LOCKING TOOL-FLAP SLAT LEVER, INT. POSITION 
(98D27803000000) on the flap/slat control lever.
(b) Put the WARNING NOTICE(S) in position on the flap/slat control lever 
to tell persons not to operate the flap/slat controls.
(7) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at access 
door 193CB.
(8) Open access door 193CB to get access to the HP ground connectors.
(9) Put the WARNING NOTICE(S) in position on the HP ground connectors to tell 
persons not to pressurize the pneumatic system.
C. Get access to the avionics compartment
(1) Put the ACCESS PLATFORM 3M (10 FT) - ADJUSTABLE in position below 
access door 811.
(2) Open access door 811, refer to AMM TASK 52-41-00-010-801.
(3) Unlock and open the protective door of AC/DC emergency power-center 
740VU.
D. Open, safety and tag these circuit breakers
PANEL DESIGNATION FIN LOCATION
FOR FIN 4030EM1 (POWERPLANT-DEMOUNTABLE, ENG 1)
721VU C/B-ANALOG CARD, BMC1 21HA1 R06
722VU EEC1 CHAN-B 13KS1 D44
742VU C/B--CONTROL CARD, BMC1 17HA1 A80
742VU EEC1 CHAN-A 12KS1 Q73
FOR FIN 4030EM2 (POWERPLANT-DEMOUNTABLE, ENG 2)
722VU EEC2 CHAN-B 13KS2 K49
722VU C/B--CONTROL CARD, BMC2 17HA2 V34
742VU C/B-ANALOG CARD, BMC2 21HA2 F73
742VU EEC2 CHAN-A 12KS2 Q74
E. Get Access
(1) Open the fan cowl doors refer to AMM TASK 71-13-00-010-816:
(a) FOR 4030EM1 (POWERPLANT-DEMOUNTABLE, ENG 1) 415AL 
and 416AR

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(b) FOR 4030EM2 (POWERPLANT-DEMOUNTABLE, ENG 2) 425AL 
and 426AR.
F. Deactivation of the Thrust Reverser System
WARNING: YOU MUST DEACTIVATE THE THRUST REVERSER BEFORE YOU DO 
WORK ON OR AROUND IT. IF YOU DO NOT OBEY THIS INSTRUCTION,
THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE
INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
(1) Do the deactivation of the thrust reverser for maintenance refer to AMM TASK 
78-30-00-040-826. SUBTASK 36-11-00-010-375-A
G. Get Access
(1) Put the ACCESS PLATFORM 2M (6 FT) in position at the thrust-reverser cowl 
doors.
(2) Open the thrust-reverser cowl doors refer to AMM TASK 78-36-00-010-805:
(a) FOR 4030EM1 (POWERPLANT-DEMOUNTABLE, ENG 1) 417AL 
and 418AR.
(b) FOR 4030EM2 (POWERPLANT-DEMOUNTABLE, ENG 2) 427AL 
and 428AR.
3. Procedure
Ref. Fig. EBAS - Location and Detail
A. Visual Inspection of the EBAS
(1) Airbus recommends that you use the BORESCOPE SET for the borescope 
inspection.
NOTE: IF THE BORESCOPE LENGTH IS SUFFICIENT TO EXAMINE THE 
REMAINING POSITION FROM THE REMOVED VALVE HOLES:
●It is not necessary to disassemble the valve parts as you use the 
borescope from the other valve holes for inspection.
NOTE: THE VISUAL QUALITY OF THE BORESCOPE IS IMPORTANT TO 
HAVE SUFFICIENT VISUAL PRECISION DURING THE BORESCOPE 
INSPECTION.
(2) For the Environmental Control System (ECS) HP ducts (MID Y-duct):
(a) Do the borescope inspection through the HPV location for signs of 
FOD.
(b) If you find metallic debris, remove it.
***BEG REV***
(3) For the Pressure Regulating Valve (PRV), the Cabin Air Non Return Valve 
(CNRV), the header of the High Pressure (HP)/Intermediate Pressure (IP) duct, 
the Y-duct and the pylon ducts (Precooler Interface Duct):
(a) Remove PRV 4001HA1 (4001HA2) refer to AMM TASK 36-11-52-000-
807 and do these steps:
1 Visually examine the PRV for one of these signs of FOD:
- Metallic debris in the butterfly valve
- Dents and missing segments.

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2 If you find one of the above signs of FOD:
a. The PRV is considered as unserviceable.
3 Do the borescope inspection of the air ducts through the PRV 
location for signs of FOD:
NOTE: THIS PROCEDURE IS APPLICABLE FOR THE AIR DUCTS 
FROM THE PRV TO THE CNRV, THE HPV AND THE 
PRECOOLER EXCHANGER (PCE).
a. If you find any debris, remove it.
4 Do the borescope inspection of CNRV 4595KS for one of these signs 
of FOD:
- Metallic debris in the butterfly valve
- Dents or damages on the flaps
5 If you find one of the above signs of FOD:
a Replace CNRV 4595KS refer to AMM TASK 36-11-41-000-
806 and AMM TASK 36-11-41-400-806.
(b) Install serviceable PRV 4001HA1 (4001HA2) refer to AMM TASK 36-
11-52-400-807.
***END REV***
4. Close-up
A. Remove the safety clips and tags and close these circuit breakers in this sequence:
PANEL DESIGNATION FIN LOCATION
FOR FIN 4030EM1 (POWERPLANT-DEMOUNTABLE, ENG 1)
721VU C/B-ANALOG CARD, BMC1 21HA1 R06
722VU EEC1 CHAN-B 13KS1 D44
742VU C/B--CONTROL CARD, BMC1 17HA1 A80
742VU EEC1 CHAN-A 12KS1 Q73
FOR FIN 4030EM2 (POWERPLANT-DEMOUNTABLE, ENG 2)
722VU EEC2 CHAN-B 13KS2 K49
722VU C/B--CONTROL CARD, BMC2 17HA2 V34
742VU C/B-ANALOG CARD, BMC2 21HA2 F73
742VU EEC2 CHAN-A 12KS2 Q74
B. Test
(1) Do the leak test of the EBAS refer to AMM TASK 71-00-00-790-808.
(2) Make sure that there are no leaks. 
C. Test
(1) Do the BITE test of the EBAS refer to AMM TASK 36-11-00-740-807.
D. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust-reverser cowl doors refer to AMM TASK 78-36-00-410-805:
(a) FOR 4030EM1 (POWERPLANT-DEMOUNTABLE, ENG 1)
417AL and 418AR
(b) FOR 4030EM2 (POWERPLANT-DEMOUNTABLE, ENG 2)
427AL and 428AR.
E. Reactivation of the Thrust Reverser System

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(1) Do the reactivation of the thrust reverser system after maintenance refer to 
AMM TASK 78-30-00-440-826. 
F. Close Access
(1) Close the fan cowl doors refer to AMM TASK 71-13-00-410-816:
(a) FOR 4030EM1 (POWERPLANT-DEMOUNTABLE, ENG 1)
415AL and 416AR
(b) FOR 4030EM2 (POWERPLANT-DEMOUNTABLE, ENG 2)
425AL and 426AR.
(2) Remove the warning notice(s).
(3) On the center pedestal, on FLAPS control panel 114VU, remove the 
LOCKING TOOLFLAP SLAT LEVER,INT. POSITION(98D27803000000) 
from the flap/slat control lever.
(4) Close access door 193CB.
(5) Close and lock the protective door of AC/DC emergency power-center 
740VU.
(6) Close access door 811 refer to AMM TASK 52-41-00-410-801.
(7) Remove the access platform(s).
(8) Remove all the fixtures, tools, test and support equipment used during this 
procedure.
G. Aircraft Maintenance Configuration
(1) De-energize the aircraft electrical circuits refer to AMM TASK 24-41-00-862-
801.

### Page 23 (OCR)

AIRBUS
ALERT OPERATORS TRANSMISSION - AOT
24 00
Z400
01 > 417AL
02) 427AL
01> 415AL
02> 425AL
418AR 0
428AR 02
416AR 01
426AR 02
NOTE:
01> APPLICABLE FOR ENGINE 1.
[02> APPLICABLE FOR ENGINE 2.
Figure 10: EBAS - Location and Detail (1/2)
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Figure 11: EBAS - Location and Detail (2/2)
***END OF THE PROCEDURE***

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5.6.H. PREVENTIVE REPLACEMENT OF THE HPV CLIP PN 6764-222
a. Perform the below procedure for the HPV clip replacement when:
***BEG REV***
●The first replacement of the HPV clip has to be performed before one of this two conditions is 
met, whichever occurs first:
oBefore the HPV clip has accumulated 4000FH or within 1500FH from the effective date 
of EASA AD 2022-0181, whichever occurs later of these two conditions
oBefore the HPV clip has accumulated 600FC or, whichever comes first, within 60 days 
or 225 FC from the issuance date of this AOT Rev.02, whichever occurs later of these 
two conditions.
●Then, the interval for the repetitive replacement of the HPV clip is 4000FH or 600FC whichever 
occurs first.
Refer to the figure 6: Clip replacement compliance time flowchart in § 5.1 for additional clarification.
***END REV***
NOTE: FOR ANY AIRLINE SUPPORT, IN ADDITION TO THE FOLLOWING 
PROCEDURE, A VIDEO FROM THE SUPPLIER LIEBHERR SHOWING THE 
PROCEDURE FOR THE CLIP REPLACEMENT IS AVAILABLE WITHIN THE TFU 
36.11.00118.
***START OF THE PROCEDURE***
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER ENGINE 
SHUTDOWN. THE ENGINE PARTS CAN STAY HOT FOR ALMOST ONE HOUR. 
DO NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN 
CAUSE INJURIES TO PERSONNEL.
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.
WARNING:
MAKE SURE THAT THE PNEUMATIC SYSTEM IS DEPRESSURIZED BEFORE 
YOU START WORK.
PRESSURIZED AIR CAN CAUSE INJURY TO PERSONNEL.
WARNING:
BEFORE YOU REMOVE/INSTALL THE COMPONENT, MAKE SURE THAT YOU 
CAN HOLD IT. THE COMPONENT IS HEAVY. IF IT FALLS, IT CAN CAUSE INJURY 
TO PERSONS AND DAMAGE TO EQUIPMENT.
NOTE: TWO PERSONS ARE NECESSARY TO DO THIS TASK
A. Removal of the HPV refer to AMM Task 36-11-51-000-806-A

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Do not plug the closing chamber sense line port. This can prevent the manual 
opening/closing of the butterfly valve
NOTE: AMM TASK 36-11-51-000-806-A CALLS AMM TASK 36-11-00-210-801, 
WHICH IS NOT REQUIRED, SINCE THE APPLICABLE INSTRUCTIONS ARE 
PROVIDED WITHIN THIS AOT IN THE VISUAL INSPECTION OF THE EBAS 
AFTER FAILURE OF THE HPV (PARAGRAPH 5.6.G).
 
B. Do a visual inspection of the HPV
Ref. Fig. HPV Clip replacement - Location and Detail
(1) Make sure that the HPV clip and sealing rings in the butterfly are not 
missing/damaged as per Instructions paragraph 5.6.F. 
(2) If the HPV clip/sealing rings are broken or missing:
(a) Continue with the next steps of the procedure provided in Instruction 
paragraph 5.6.F. 
(3) If the HPV clip is not missing or broken on the butterfly valve, put the HPV on 
a workshop bench and continue the procedure.
C. Replacement of the clip
(1) Disassembly of the existing clip PN 6764-222
(a) Manually open the valve.
(b) Keep the butterfly valve in the open position.
(c) Straighten the clip legs using the bending tool PN M65727534-12.
NOTE: USING THE BENDING TOOL, GENTLY STRAIGHTEN THE LEGS WITHOUT 
EXCEEDING A 90° ANGLE BETWEEN THE LEGS AND THE BUTTERFLY 
DOWNSTREAM FACE
 (d) Manually close the butterfly.
(e) Pull clip PN 6764-222 out of the butterfly and visually inspect the holes.
THE BUTTERFLY MUST NOT BE OPENED UNTIL THE NEW CLIP IS INSTALLED.
(f) Discard the removed clip PN 6764-222.
(2) Assembly of the new clip with the tool M65727534-12
NOTE: THE CORRECT POSITION OF THE CLIP IS WITH THE U-SHAPE PART ON 
THE BUTTERFLY UPSTREAM SIDE AND THE CLIP LEGS ON THE BUTTERFLY 
DOWNSTREAM SIDE.
(a) Install the new clip PN 6764-222, with the clip curve matching the butterfly 
machining mark (see Figure 12)
(b) Manually open the butterfly.
(c) Cut the longest clip leg. The final leg length must be between 4.5 and 5.5 mm 
(0.177 and 0.216 in). Then discard the cut part.
(d) Bend the two clip legs in the specified open angle with bending tool 
M65727534-12.
(e) Manually close the valve.
(f) Make sure that the HPV is clean from material and tooling.
D. Installation of the HPV refer to AMM Task 36-11-51-400-806-A
E. Perform paragraph 5.6.A HPV SEAL INTEGRITY TEST

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Figure 12: HPV Clip replacement - Location and Detail

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Figure 13: HPV Clip replacement - Clip curve orientation
***END OF THE PROCEDURE***
***BEG REV***
5.6.I Periodic HPV seal integrity test for A/C fitted with BMC SW Pre 4.1 (Pre MOD209292 or SB 
36-3050 not embodied)
For Aircraft equipped with BMC software 4.0 (PN LIE3EL71078AAAH) (Pre MOD209292 or SB 36-3050 
not embodied), a HPV seal integrity test must be done every 1000FH, starting from this AOT 36L009-
22 rec02 issuance date or the HPV the last HPV seal integrity test performed, whichever comes later.
***END REV***
5.7 SPARES AND TOOLING
The replacement of the HPV clip requires specific tooling and material. 
Find below information about the spares, tool and materials that are necessary:
●Clip PN 6764-222
●Bending tool PN M65727534-12
The functional test of the PRV requires one of the following test sets:
●P/N 98L36103002000 or 98L36103002001 and the Adaptor Kit P/N 98F36109001000 (Airbus 
test set)
●P/N 99127B04 (LTS test set)
Commercial policy:  refer to the last revision of RIL ref. G36M22001988 
5.8 ANNEX
Reporting sheet “AOT A36L009-22 reporting sheet”
6. ADDITIONAL INFORMATION
6.1 FOLLOW-UP PLAN

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***BEG REV***
A new EASA AD is expected to be issued to encompass the changes introduced by this revision, in the 
meantime, the A36L009-22 Rev 01 remains mandated by the EASA Airworthiness Directive (AD) 
reference AD 2022-0227, which superseded EASA AD 2022-0181, and FAA AD 2022-19-05. 
***END REV***
This AOT will be cancelled as soon as a technical solution is available to address the HPV clip failure. 
6.2 IMPACTED DOCUMENTATION
FOT REF.:999.0062/22
TFU 36.11.00118
6.3 AOT APPROVAL
The technical content of this document is approved under the authority of the DOA ref.EASA.21J.031.
7. REPORTING
Address your inspection results (with or without findings) using the attached reporting sheet (“AOT 
A36L009-22 reporting sheet”) to Airbus Customer Services through the generic email address: 
inspection.results@airbus.com. Refer to the latest reporting policy (Refer to OIT 999.0018/16). 
Give the AOT reference in the email title, as follows: A36L009-22 Inspection Result
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 36-11/ Topic 
HPV Clip Failure.
Best Regards,
Wolfgang WOHLERS
HEAD OF ENGINEERING AND 
MAINTENANCE
CUSTOMER SERVICES
Pilar ALVAREZ
HEAD OF WIDE BODY PROGRAM SUPPORT

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