# Airbus All Operators Transmission A52P013-19

Copy: No revision named ("AOT_A52P013-19_r00"), 14 pages: PDF https://openairdocs.org/files/sha256/12/a4/12a42cf9fd9b315d9290b7cf03fcc57b059b932589febc8688d0cc2c73737129; text https://openairdocs.org/service-documents/airbus/aot-a52p013-19/file/12a42cf9fd9b.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2019-0865, the docket of AD 2020-04-17. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Other document (All Operators Transmission)
- Number: A52P013-19
- Page: https://openairdocs.org/service-documents/airbus/aot-a52p013-19

## Text (14 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2019-0865, the docket of AD 2020-04-17. 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: A52P013-19 Rev 00 Page 1 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
SUBJECT: ATA  52 –  Inspection of the Passenger/Crew Door Girt Bar Fitting Assemblies
AIRCRAFT TYPE:  A350
OUR REF.: A52P013-19 Rev 00 dated 07-MAY-2019
1. AIRCRAFT AFFECTED
This AOT is applicable to all Airbus A350 model -941, -1041
2. REFERENCED DOCUMENTATION
2.1 APPENDIX
Appendix 1 – AOT Flowchart
Appendix 2 – AOT Reporting 
2.2 REFERENCES
Ref. 1: IPD 52-11/12/13-68 item 70 – Girt bar fitting assembly P/N V5217170000000
Ref. 2: IPD 52-11/12/13-68 item 200 – Girt bar fitting assembly P/N V5217170000100
Ref. 3: IPD 52-11/12/13-68 items 160/290 – Bush P/N V5217170520000
Ref. 4: IPD 52-11/12/13-68 items 150/280 – Bush P/N V5217170520200
Ref. 5: MP TASK A350-A-52-1X-XX-00001-132A-A – Opening of the Passenger/Crew Door
Ref. 6: MP TASK A350-A-52-1X-XX-03001-132A-A – Installation of the Safety-Barrier
Ref. 7: MP TASK A350-A-52-1X-XX-01001-133A-A – Removal of the Safety-Barrier
Ref. 8: MP TASK A350-A-52-1X-XX-01001-132A-A – Closing of the Passenger/Crew Door
Ref. 9: Girt Bar Fitting Assembly Drawing V52171700
Ref. 10: MP TASK A350-A-52-11-68-00001-520A-A – Removal of the Door Frame Fittings of 
Passenger/Crew Door 1, Left/Right Side
Ref. 11: MP TASK A350-A-52-12-68-00001-520A-A – Removal of the Door Frame Fittings from 
Passenger/Crew Door 2, Left/Right Side and Passenger/Crew Door 3, Left/Right Side
Ref. 12: MP TASK A350-A-52-13-68-00001-520A-A – Removal of the Door Frame Fittings of 
Passenger/Crew Door 4, Left/Right Side
Ref. 13: MP TASK A350-A-53-XX-XX-06001-520A-A – Removal of a Door Mat
Ref. 14: MP TASK A350-A-52-11-68-00001-720A-A – Installation of the Door Frame Fittings of 
Passenger/Crew Door 1, Left/Right Side
Ref. 15: MP TASK A350-A-52-12-68-00001-720A-A – Installation of the Door Frame Fittings on 
Passenger/Crew Door 2, Left/Right Side and Passenger/Crew Door 3, Left/Right Side
Ref. 16: MP TASK A350-A-52-13-68-00001-720A-A – Installation of the Door Frame Fittings of 
Passenger/Crew Door 4, Left/Right Side
Ref. 17: MP TASK A350-A-52-11-73-0A001-270A-A – Adjustment of the Girt Bar Fittings of 
Passenger/Crew Door 1, Left/Right Side
Ref. 18: MP TASK A350-A-52-12-73-06001-270A-A – Adjustment of the Girt Bar Fittings of 
Passenger/Crew Door 2, Left/Right Side and Passenger/Crew Door 3, Left/Right Side
Ref. 19: MP TASK A350-A-52-13-73-06001-270A-A – Adjustment of the Girt Bar Fittings of 
Passenger/Crew Door 4, Left/Right Side
Ref. 20: ASR A350-A-51-23-12-01ZZZ-667Z-A – Special coatings

### Page 2

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: A52P013-19 Rev 00 Page 2 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
Ref. 21: MP TASK A350-A-53-XX-XX-06001-720A-A – Installation of a Door Mat
Ref. 22: MMEL item 52-10-01A
Ref. 23: TFU 52.10.00.046
Ref. 24: ASR TASK A350-A-51-73-XX-0B001-660A-A - Removal of Damage by Blending or Rework
3. REASON
3.1 FACTS
The safety hook of a passenger door 1 girt bar fitting assembly Ref. 1 and 2 was reported stuck in the 
upward position by one operator (see Figure 1 for location).
Two cases were also experienced on flight-test aircraft at passenger doors 1 and 2.
Figure 1. Pax door girt bar fitting assembly and safety hook
3.2 CONSEQUENCES
The safety hooks of the girt bar fitting assemblies ensure that the girt bar is properly engaged and 
secured into the fittings during emergency slide deployment.
In case one (or both) safety hook(s) is (are) stuck in the upward position, there is a risk of girt bar 
disengagement from the girt bar fitting(s), potentially leading to slide deployment failure.
3.3 AIM
The aim of this AOT is to request operators to:
- Perform a Detailed Inspection (DI) of every passenger/crew door girt bar fitting assembly to 
ensure the safety hooks are not stuck or stiff to rotate.
- Rework or replace the damaged parts as necessary.
- Apply grease to girt bar fitting assembly bushes Ref. 3 and 4.
3.4 INVESTIGATION

### Page 3

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: A52P013-19 Rev 00 Page 3 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
Preliminary investigation showed that safety hook jamming is linked to surface treatment 
incompatibility, leading to galling effect on bushes Ref. 3 and 4.
4. SHORT TERM ACTION
4.1 PLANNING AND MANPOWER
4.1.1 ACCOMPLISHMENT TIMESCALE
The accomplishment of the DI described in Para. 4.2.2 must be performed no later than 4 months after 
AOT issuance date or within 4 months from A/C Entry into Service (EIS) if delivered after AOT issuance 
whichever occurs later.
After first AOT inspection, repetitive DI of every passenger/crew door girt bar fittings associated with 
bush greasing are required every 12 months.
4.1.2 MANPOWER
- The inspection and greasing described in Para. 4.2.2 is estimated to take 0.5 Man-Hour (M/H) 
per door.
- The bush(es) rework described in Para. 4.2.3 is estimated to take 0.3 M/H per door.
- The bush (item 6) replacement described in Para. 4.2.3 is estimated to take 0.1 M/H per door.
- The girt bar fitting assembly replacement described in Para. 4.2.3 is estimated to take 1 M/H 
per door (door rigging not included).
4.2 DESCRIPTION
4.2.1 ACCESS
- Open the Passenger/Crew Doors as per MP Task Ref. 5 to gain access to the girt bar fitting 
assemblies.
- In case no adjustable access platform is put in front of and below the applicable 
passenger/crew door, install a Safety-Barrier as per MP Task Ref. 6.
- After accomplishment of the DI and greasing described in Para. 4.2.2 and corrective actions 
described in Para. 4.2.3, remove the Safety-Barrier as necessary as per MP Task Ref. 7 and 
close the Passenger/Crew Doors as per MP Task Ref. 8.
 
4.2.2 INSPECTION REQUIREMENTS
For each passenger/crew door, perform the following steps:
(1) Perform preliminary General Visual Inspection (GVI) on both forward and aft girt bar fittings to 
check safety hooks downward position.
(2) Move each safety hook from downward to upward position to check for stiff point (Figure 2). 
Moving the hook upward should require low force with one finger; the hook should quickly 
come back downward when released.

### Page 4

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: A52P013-19 Rev 00 Page 4 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
Figure 2. Safety hook in downward position
(3) Remove items 100, 102, 104, 106, 108, then 2 (or 3) and 10 as shown in drawing Ref. 9 and 
highlighted in yellow in Figure 3.
Figure 3. Girt Bar Fitting Assembly 
(4) Remove long bush item 6 of Figure 3 and perform DI on its outer surface.
(5) Perform DI on inner surface of bushes item 8 of Figures 3 and 4. 
Bushes items 6 and 8 are highlighted in green in Figure 4 and typical galling wear marks are 
shown in Figure 5.

### Page 5

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: A52P013-19 Rev 00 Page 5 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
Figure 4. Bush items 6 and 8
Figure 5. Typical galling wear marks
(6) In case of wear marks on bushes item 6 and/or 8, go to Para. 4.2.3.
(7) In case of Nil finding, apply AEROSHELL Grease 33 on the outer surface of bush item 6 and 
on the inner surface of bushes item 8.
(8) Re-install all removed items from steps (3) and (4), refer to drawing Ref. 9, except the 
removed cotter pin item 108 and nut item 106 that have to be discarded and replaced by new 
ones (P/N are given in Para. 4.3).
(9) Re-check safety hook correct function as per step (2) to check for stiff point.
(10)Repeat inspection and grease application every 12 months.
4.2.3 FINDINGS

### Page 6

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: A52P013-19 Rev 00 Page 6 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
In case of finding, do either below procedure (1) (preferred) or (2) (optional temporary mitigation):
(1) In case of safety hook stuck or stiff to rotate and/or wear marks on bushes item (6) and (8), do 
the following steps:
(1.1) Perform rework within manufacturing tolerances, removing the material in excess on 
affected bush(es) using non-ferrous reamer or sandpaper (at least 200-grit) as per 
ASR task Ref. 24.
(1.2) Measure outer diameter of bush item 6 and/or inner diameter of bush(es) item 8 at 
each bush extremity, making sure they are within the tolerances shown in Figure 5.
Figure 5. Bushes tolerances after rework
(1.3) If both reworked diameters of bush items 6 and 8 are within manufacturing 
tolerances, perform steps (7) to (9) of Para. 4.2.2 and then go to step 1.13.
(1.4) If only outer diameter of bush item 6 is out of tolerance, replace it before next flight, 
then perform steps (7) to (9) of Para. 4.2.2 and go to step 1.13.
(1.5) If inner diameter of bush(es) item 8 is out of tolerance, the complete affected girt bar 
fitting assembly must be replaced before next flight. Perform steps 1.6 to 1.13.
(1.6) Remove girt bar fitting, refer to MP Task Ref.10 to 12 depending on affected door and 
replace it with a new one. 
(1.7)On the new girt bar fitting, perform steps (7) to (9) of Para. 4.2.2.
(1.8) Remove the Door Mat, refer to MP Task Ref.13 for access.
(1.9) Through the manhole, clean the bottom side of the girt bar fittings using textile (CML 
code 14SBA1) soaked with non-aqueous cleaner (CML code 08BAA9) as shown in 
Figure 6 and install the new fitting, refer to MP Task Ref. 14 to 16 depending on 
affected door.

### Page 7

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: A52P013-19 Rev 00 Page 7 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
Figure 6. Girt bar fitting bottom area
(1.10) Perform girt bar fitting rigging, refer to with Ref. 17 to 19 depending on affected door.
(1.11) Through manhole, apply CPC (Corrosion Preventive Compound - refer to CML code 
12AEB1 or similar product as designated by the operator’s Corrosion Prevention and 
Control Program) on fasteners using a brush as per MP Task Ref. 20 and shown in 
Figure 7.
Figure 7. CPC application area
(1.12) Re-install the door mat, refer to MP Task Ref. 21.
(1.13) Repeat inspection and grease application every 12 months.
(2) In case of finding (safety hook stuck or stiff to rotate and/or wear marks on bush items 6 and 8) 
on part(s) which is (are) not fully reworked (still within manufacturing tolerances) or cannot be 
replaced (including complete girt bar fitting assy replacement and rigging); before next flight, do 
the following steps:
(2.1) Perform steps (7) to (9) of Para. 4.2.2.
(2.2) If stiff point no longer present, re-apply grease and rework or replace worn bushes 
within 4 months.

### Page 8

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: A52P013-19 Rev 00 Page 8 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
(2.3) If stiff point still present after grease application, affected bush(es) has (have) to be 
reworked or replaced (including complete girt bar fitting assembly replacement and 
rigging) before next flight or affected door has to be set inoperative, refer to MMEL 
Ref. 22. Note that only one passenger/crew door can be set inoperative per aircraft.
4.3 SPARES AND TOOLING
Shall AEROSHELL 33 not be available, AEROSHELL 64 or AMS3058 could be used as alternative. Dry 
lubricant – graphite as per CML 03QBD1 could also be used but is not the preferred solution due to 
smaller resistance to water.
Before performing AOT inspection, Airbus recommends for each operator to order Free of Charge (FoC) 
following items and quantities for its fleet (with replenishment after consumption evidence – first order 
to be done within 4 months after AOT issuance date):
- 1 EA girt bar fitting Ref. 1 (to be ordered in AOG basis).
- 1 EA girt bar fitting Ref. 2 (to be ordered in AOG basis).
- 1 EA bush Ref. 3.
- Girt bar fitting nut P/N NSA5060E4 (EA depending of fleet size).
- Girt bar fitting cotters pins P/N MS24665-151 (EA depending of fleet size).
Note that 16EA of girt bar fitting nuts and cotters pins are required per A/C.
The FoC policy will continue up to 30 JUNE 2021.
The purchase order shall be placed to SATAIR following address:
5. FURTHER INFORMATION
5.1 FOLLOW-UP PLAN
It is expected that this AOT will be mandated through an EASA AD.
Airbus is currently working on serial and retrofit solutions to cancel this repetitive inspection.
This issue will be followed through TFU Ref. 23 and further AOT update as required.
5.2 IMPACTED DOCUMENTATION
N/A
6. AOT APPROVAL

### Page 9

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: A52P013-19 Rev 00 Page 9 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
The technical content of this document is approved under the authority of DOA nr. EASA.21J.031.
7. REPORTING
7.1 Questions about this AOT are to be addressed to Airbus Customer Services through TechRequest 
on Airbus World, selecting Maintenance & Engineering Domain, Engineering Support Section and 
ATA 52-10.
7.2 As per latest reporting policy (Ref to OIT 999.0018/16), inspection results (with or without findings) 
have to be addressed to Airbus Customer Services through the generic e-mail address:  
inspection.results@airbus.com with the Template table available in Appendix 2.
Best Regards,
Christian FREMONT
VICE PRESIDENT ENGINEERING SUPPORT
CUSTOMER SERVICES
Stephane GOSSELIN
VICE PRESIDENT A350 PROGRAMME
CUSTOMER SERVICES

### Page 10

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: A52P013-19 Rev 00 Page 10 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
APPENDIX 1 – Inspection Flow Chart
Note: for differences between text in section 4 above and this flow chart, the text in section 4 contains 
the controlling requirements.
Within accomplishment timescale defined in 4.1.1, do a 
Detailed Inspection (DI) of each Passenger/Crew Door Girt 
Bar Fitting Assembly as per Para. 4.2.2.
Wear marks on 
bushes?
Yes 
Perform rework on affected bushes or replace 
part as necessary as per Para. 4.2.3.
Apply grease on 
bushes
No 
Report to Airbus 
using AOT reporting 
sheet
Repeat inspection 
every 12 months
Ensure hook correct 
function

### Page 11

ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A52P013-19 Rev 00 Page 11 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
APPENDIX 2 – AOT Reporting Sheet
Date of INSPECTION
A/C MSN AIRLINE FLIGHT CYCLES ___________________
A/C TYPE A/C REGISTRATION FLIGHT HOURS ___________________
If wear marks If wear marks
Yes No Yes No Yes No Yes No
If wear marks If wear marks
Yes No Yes No Yes No Yes No
If wear marks If wear marks
Yes No Yes No Yes No Yes No
If wear marks If wear marks
Yes No Yes No Yes No Yes No
Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date
BUSH(ES) ITEM 8 Wear Mark? BUSH(ES) ITEM 8 Wear Mark?
Yes No Yes No
or Bush rework / 
replacement target date Part Reworked ? Part Replaced ? or Bush rework / replacement target date
No
BUSH ITEM 6 Wear Mark? BUSH ITEM 6 Wear Mark?
Yes No Yes No
AFT FITTING FWD FITTING
Pax Door R1
AFT Safety Hook stuck or stiff? FWD Safety Hook stuck or stiff?
Yes No Yes
Part Reworked ? Part Replaced ?
Pax Door L1
________________
________________
________________
___________________
___________________
BUSH(ES) ITEM 8 Wear Mark?
Yes No
Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date
Yes No
Part Reworked ? Part Replaced ? or Bush rework / replacement target date
FWD FITTING
FWD Safety Hook stuck or stiff?
Yes No
AFT FITTING
BUSH ITEM 6 Wear Mark?
AFT Safety Hook stuck or stiff?
or Bush rework / 
replacement target date
Yes
NoYes
Part Reworked ? Part Replaced ?
No
BUSH ITEM 6 Wear Mark?
BUSH(ES) ITEM 8 Wear Mark?
Yes No
Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date

### Page 12

ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A52P013-19 Rev 00 Page 12 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
Date of INSPECTION
A/C MSN AIRLINE FLIGHT CYCLES ___________________
A/C TYPE A/C REGISTRATION FLIGHT HOURS ___________________
If wear marks If wear marks
Yes No Yes No Yes No Yes No
If wear marks If wear marks
Yes No Yes No Yes No Yes No
If wear marks If wear marks
Yes No Yes No Yes No Yes No
If wear marks If wear marks
Yes No Yes No Yes No Yes No
Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date
BUSH(ES) ITEM 8 Wear Mark? BUSH(ES) ITEM 8 Wear Mark?
Yes No Yes No
AFT FITTING FWD FITTING
Pax Door R2
AFT Safety Hook stuck or stiff? FWD Safety Hook stuck or stiff?
Yes No Yes
Part Reworked ? Part Replaced ? or Bush rework / replacement target date Part Reworked ? Part Replaced ? or Bush rework / replacement target date
No
BUSH ITEM 6 Wear Mark? BUSH ITEM 6 Wear Mark?
Yes No Yes No
Pax Door L2
AFT Safety Hook stuck or stiff? FWD Safety Hook stuck or stiff?
Yes No Yes No
BUSH ITEM 6 Wear Mark? BUSH ITEM 6 Wear Mark?
Yes No Yes No
Part Reworked ? Part Replaced ? or Bush rework / replacement target date Part Reworked ? Part Replaced ?
Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date
AFT FITTING FWD FITTING
or Bush rework / 
replacement target date
BUSH(ES) ITEM 8 Wear Mark? BUSH(ES) ITEM 8 Wear Mark?
Yes No Yes No
________________
________________ ___________________
________________ ___________________

### Page 13

ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A52P013-19 Rev 00 Page 13 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
Date of INSPECTION
A/C MSN AIRLINE FLIGHT CYCLES ___________________
A/C TYPE A/C REGISTRATION FLIGHT HOURS ___________________
If wear marks If wear marks
Yes No Yes No Yes No Yes No
If wear marks If wear marks
Yes No Yes No Yes No Yes No
If wear marks If wear marks
Yes No Yes No Yes No Yes No
If wear marks If wear marks
Yes No Yes No Yes No Yes No
or Bush rework / 
replacement target date
BUSH(ES) ITEM 8 Wear Mark?
or Bush(es) rework / fitting 
replacement target date Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date
AFT FITTING FWD FITTING
Pax Door L3
AFT Safety Hook stuck or stiff? FWD Safety Hook stuck or stiff?
Yes No Yes No
BUSH ITEM 6 Wear Mark? BUSH ITEM 6 Wear Mark?
Yes No Yes No
Part Reworked ? Part Replaced ? or Bush rework / replacement target date Part Reworked ? Part Replaced ?
AFT FITTING FWD FITTING
Pax Door R3
AFT Safety Hook stuck or stiff? FWD Safety Hook stuck or stiff?
Yes No Yes No
BUSH ITEM 6 Wear Mark? BUSH ITEM 6 Wear Mark?
Yes No Yes No
Part Reworked ? Part Replaced ? or Bush rework / replacement target date Part Reworked ? Part Replaced ? or Bush rework / replacement target date
BUSH(ES) ITEM 8 Wear Mark? BUSH(ES) ITEM 8 Wear Mark?
Yes No Yes No
Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date
________________
________________ ___________________
________________
___________________
BUSH(ES) ITEM 8 Wear Mark?
Yes No Yes No
Part Reworked ? Part Replaced ?

### Page 14

ALERT OPERATORS TRANSMISSION - AOT 
AOT ref: A52P013-19 Rev 00 Page 14 of 14 Date: 07-MAY-2019
© AIRBUS S.A.S. 2019. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT
Date of INSPECTION
A/C MSN AIRLINE FLIGHT CYCLES ___________________
A/C TYPE A/C REGISTRATION FLIGHT HOURS ___________________
If wear marks If wear marks
Yes No Yes No Yes No Yes No
If wear marks If wear marks
Yes No Yes No Yes No Yes No
If wear marks If wear marks
Yes No Yes No Yes No Yes No
If wear marks If wear marks
Yes No Yes No Yes No Yes No
AFT FITTING FWD FITTING
Pax Door L4
AFT Safety Hook stuck or stiff? FWD Safety Hook stuck or stiff?
Yes No Yes No
BUSH ITEM 6 Wear Mark? BUSH ITEM 6 Wear Mark?
Yes No Yes No
Part Reworked ? Part Replaced ? or Bush rework / replacement target date Part Reworked ? Part Replaced ? or Bush rework / replacement target date
BUSH(ES) ITEM 8 Wear Mark? BUSH(ES) ITEM 8 Wear Mark?
Yes No Yes No
Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date
AFT FITTING FWD FITTING
Pax Door R4
AFT Safety Hook stuck or stiff? FWD Safety Hook stuck or stiff?
Yes No Yes No
BUSH ITEM 6 Wear Mark? BUSH ITEM 6 Wear Mark?
Yes No Yes No
Part Reworked ? Part Replaced ? or Bush rework / replacement target date Part Reworked ? Part Replaced ? or Bush rework / replacement target date
BUSH(ES) ITEM 8 Wear Mark? BUSH(ES) ITEM 8 Wear Mark?
Yes No Yes No
Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date Part Reworked ? Part Replaced ? or Bush(es) rework / fitting replacement target date
________________
________________ ___________________
________________ ___________________

---
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.