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Mandatory Mandatory Mandatory: A318/A319/A320/A321

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607 views130 pages

Mandatory Mandatory Mandatory: A318/A319/A320/A321

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dkir

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A318/A319/A320/A321

SERVICE BULLETIN

CONF ALL
AIRBUS
2, ROND POINT EMILE DEWOITINE
31700 BLAGNAC
FRANCE

The content of this document is the property of Airbus. All rights including copyrights are reserved.
It is supplied in confidence and commercial security on its contents must be maintained.
It must not be used for any purpose other than that for which it is supplied, nor may information
contained in it be disclosed to unauthorized persons.
It must not be reproduced in whole or in part without permission in writing from the owners of the
copyright. Requests for reproduction of any data in this document and the media authorized for it must
be addressed to Airbus.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - CENTER FUSELAGE - INSPECT MLG DOOR ACTUATOR

FITTING ON KEEL BEAM (NEO)
MODIFICATION No.:
None

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 1
A318/A319/A320/A321
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
ATA SYSTEM: 53

TITLE: FUSELAGE - CENTER FUSELAGE - INSPECT MLG DOOR ACTUATOR

FITTING ON KEEL BEAM (NEO)
REVISION TRANSMITTAL SHEET
This page transmits Revision No. 04 of Service Bulletin No. A320-53-1325.
A. ADDITIONAL WORK
No additional work is required by this revision.
B. REASON
Revision No. 04 issued to:

- Introduce Modification Service Bulletin (MSB) No. A320-53-1503 as terminative

solution for this Inspection Service Bulletin
- Delete NTM 53-31-60, which is included in NTM 53-31-54
- Introduce repair procedure in case of negligible damages as per SRM 51-73-00 (blend
out repair)
- Update the applicability of this Service Bulletin
- Update the industry support information
- Introduce actuator fitting replacement whatever the type of damage.

NOTE: This Service Bulletin revision No. 04 satisfies the requirements of all Repair Design
Approval Form (RDAF)s issued to cover NTM deviation:
- NTM 53-31-60 has been deleted and its content has been included in NTM 53-
31-54.
These RDAFs are valid for related Manufacturer Serial Number (MSN)s mentioned in
the document until this Service Bulletin revision No. 04 dispatched date.

NOTE: This Service Bulletin revision No. 04 satisfies the requirements of all RDAFs issued
to cover the addition of MSN Pre-MOD 165315K33958 not delivered at the previous
issues of this open-end Inspection Service Bulletin. These RDAFs are valid for
related MSNs mentioned in the document until this Service Bulletin revision No. 04
dispatched date.

C. CHANGES

SUMMARY
REASON Advantages updated.
GENERAL EVALUATION General evaluation table updated.
APPLICABILITY Operators updated.
PLANNING INFORMATION
APPLICABILITY - Open end applicability note deleted.
- Note added.
- Applicability updated.
REASON Advantages updated.
COMPLIANCE
Classification Classification changed from RECOMMENDED to
MANDATORY.
REV 00 Apr 29/16 A320-53-1325
REV 04 Nov 07/23 Page 2
A318/A319/A320/A321
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Accomplishment Timescale Tables updated to introduce terminative solution and
repair instructions for other damages.
MANPOWER
Task set A320-A-53-XX-1325- Manpower updated.
01000-93BA-A Special Detailed
Inspection of the Actuator
Fitting
REFERENCES
Task set A320-A-53-XX-1325- References updated.
01000-93BA-A Special Detailed
Inspection of the Actuator
Fitting
INDUSTRY SUPPORT INFORMATION Warranty date changed from Jun 30/22 to Nov 30/25.
MATERIAL INFORMATION
MATERIAL APPLICABILITY
Material for task set A320-A- Referenced part added.
53-XX-1325-01000-93BA-A
Special Detailed Inspection of
the Actuator Fitting
TOOLING Note deleted.
Tool kit 531325T02R00 Note added.
Tool kit 531325T03R00 Note added.
Referenced tools for task set References added.
A320-A-53-XX-1325-01000-
93BA-A Special Detailed
Inspection of the Actuator
Fitting
CONSUMABLES
Referenced consumables for Reference added.
task set A320-A-53-XX-1325-
01000-93BA-A Special Detailed
Inspection of the Actuator
Fitting
LIST OF NEW PARTS
Part kit 531325D01R02 Price and availability updated.
Components for task set A320- Note added.
A-53-XX-1325-01000-93BA-A
Special Detailed Inspection of
the Actuator Fitting
Referenced parts for task set Reference added.
A320-A-53-XX-1325-01000-
93BA-A Special Detailed
Inspection of the Actuator
Fitting
ACCOMPLISHMENT INSTRUCTIONS
Task set A320-A-53-XX-1325-01000-93BA-A Special Detailed Inspection of the Actuator
Fitting
PREPARATION

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 3
A318/A319/A320/A321
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
A320-A-53-XX-1325- - Caution sentence updated
02001-540A-A Disconnect
the MLG Door Actuator
- Workstep added.
from Actuator Fitting on LH
Side
A320-A-53-XX-1325- - Caution sentence updated
03001-540A-A Disconnect
the MLG Door Actuator
- Workstep added.
from Actuator Fitting on
RH Side
PROCEDURE Subtasks rearranged to show all LH side first followed
by RH side.
A320-A-53-XX-1325- - Title updated
01001-300A-A Do an SDI
of the Keel Beam MLG
- Standard practices wordings updated.
Door Actuator Fitting on
Aircraft, on Left Hand (LH)
side - Subtask updated to introduce terminative action and
repair instruction for other damages

- NTM Ref. 53-31-60 removed

- Standard sentence added

- Worksteps updated.
Fig.BI Sol.AA Check of Illustrations updated.
the Plain Bush Migration,
Flanged Bush Axial loose
and Wear Marks LH Side
Fig.FB Sol.AA Inspection Flowchart updated.
Flowchart
Fig.RB Sol.AA Inspection Inspection report updated.
Report Sheet
Fig.BA Sol.AA Inspection Illustrations updated.
Area LH Side
A320-A-53-XX-1325- Title updated.
01001-920A-A Depending
on the Inspection Results,
Replace the MLG Door
Actuator Fitting on Aircraft,
on LH side
A320-A-53-XX-1325- Note added.
05001-690A-A Depending
on the Inspection Results,
Repair the Other Damages
on LH side
A320-A-53-XX-1325- - Title updated
02001-300A-A Do an SDI
of the Keel Beam MLG
- Standard practices wordings updated.
Door Actuator Fitting on
Aircraft, on Right Hand
(RH) side
REV 00 Apr 29/16 A320-53-1325
REV 04 Nov 07/23 Page 4
A318/A319/A320/A321
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
- Subtask updated to introduce terminative action and
repair instruction for other damages

- NTM Ref. 53-31-60 removed

- Standard sentence added

- Worksteps updated.
Fig.BE Sol.AA Inspection Illustrations updated.
Area RH Side
Fig.BF Sol.AA Check of Illustrations updated.
the Plain Bush Migration,
Flanged Bush Axial loose
and Wear Marks RH Side
Fig.FB Sol.AA Inspection Flowchart updated.
Flowchart
Fig.RB Sol.AA Inspection Inspection report updated.
Report Sheet
A320-A-53-XX-1325- Title updated.
02001-920A-A Depending
on the Inspection Results,
Replace the MLG Door
Actuator Fitting on Aircraft,
on RH side
A320-A-53-XX-1325- Note added.
06001-690A-A Depending
on the Inspection Results,
Repair the Other Damages
on RH side
PREPARATION FOR TEST
A320-A-53-XX-1325- Subtask and associated information added.
01001-331A-A Connect the
MLG Door Actuator to the
Actuator Fitting on LH Side
A320-A-53-XX-1325- Subtask and associated information added.
02001-331A-A Connect the
MLG Door Actuator to the
Actuator Fitting on RH Side
TEST
A320-A-53-XX-1325- Workstep added.
02001-390A-A Test of the
MLG Door
APPENDIX
MANPOWER GANTT CHART
Fig.AA Sol.AA Manpower Gantt Gantt chart updated.
Chart
D. FILING INSTRUCTIONS
This Service Bulletin has been generated electronically and is reissued as a complete
document. Replace the complete document.

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 5
A318/A319/A320/A321
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Put this Revision Transmittal Sheet in front of the Service Bulletin.
E. HISTORY OF PREVIOUS REVISIONS
Revision No. 01 issued to:
Extend the effectivity
Include bush migration repair procedure.
Revision No. 02 issued to modify the inspection procedure.
This revision satisfies the requirements of the subsequent Technical Adaptation(s) (TA)
issued for the related Manufacturer Serial Number (MSN)s:
TA
MSN
80560561/013/2019
6286 6419 6642 6720 6744 6772 6799 6801 6819 6829 6833 6849 6860 6864 6868 6904
6907 6914 6920 6946 6952 6967 6975 7001 7011 7033 7047 7051 7053 7060 7074 7078
7083 7094 7102 7103 7107 7124 7126 7129 7140 7141 7147 7150 7162 7172 7175 7185
7186 7192 7195 7205 7209 7236 7249 7252 7269 7273 7277 7283 7290 7291 7309 7321
7323 7329 - 7331 7333 7334 7341 7343 7352 7354 7359 7367 7380 7386 7387 7391 7396
7399 7401 7409 7417 7428 7429 7449 7459 7466 7470 7472 7475 7477 7480 7483 7484
7486 7489 7494 7495 7499 7501 7504 7505 7507 7508 7510 7512 7514 7517 7521 7523
7526 7530 7533 7535 7538 7540 7544 7547 7548 7553 - 7555 7559 7560 7563 7565 7567
7568 7571 7576 7577 7579 7581 7587 - 7589 7591 7594 7598 7600 7602 7603 7606 7610
7612 7616 7618 7626 7629 7634 7638 7639 7642 7648 7649 7662 7663 7671 7676 7677
7682 7688 7694 7697 7698 7703 7705 7710 7719 7721 7723 7727 7731 7733 7735 7737
7744 7746 7751 7753 7755 7757 7764 7768 7770 7776 7778 7786 7788 7791 7794 7795
7799 7800 7802 - 7804 7807 7811 - 7813 7822 7824 7828 7834 7835 7837 7839 7841
7842 7844 7847 - 7851 7853 7854 7856 7858 - 7862 7864 7871 7875 7881 7887 7891
7892 7895 7897 7899 7912 7914 7917 7918 7920 7921 7925 7928 7930 7931 7936 7939
7941 7942 7944 - 7946 7949 - 7952 7959 - 7961 7965 7967 7968 7972 7979 7980 7983
7984 7986 7990 - 7992 7995 - 7997 7999 8000 8005 8008 8014 - 8017 8020 8023 8025
8030 8031 8038 8039 8043 8048 8050 - 8052 8056 8058 8059 8074 8077 8079 8084 -
8096 8098 - 8103 8105 - 8110 8112 8113 8117 8118 8120 - 8123 8126 8129 8131 8135
- 8140 8142 8144 - 8146 8148 8150 8152 8154 8156 - 8158 8164 8166 - 8168 8170 8172
8173 8175 8181 8182 8184 8186 8187 8193 - 8199 8202 - 8204 8206 8208 8209 8212
8214 8217 - 8219 8221 8224 - 8226 8228 8229 8231 8235 8237 8239 8240 8242 8243
8246 - 8249 8253 8255 8256 8259 - 8262 8264 - 8268 8270 8272 - 8275 8277 8278 8280
8282 8284 8286 8288 - 8292 8294 8297 8300 - 8304 8306 - 8310 8312 8318 8320 8323
8326 8330 8331 8333 8335 8337 8338 8340 8341 8345 8348 - 8351 8353 8356 8357 8360
8361 8364 - 8368 8371 - 8375 8377 8380 8382 and 8383
Revision No. 03 issued to:

- Transform Service Bulletin data from ATA iSpec 2200 norm to ASD S1000D norm
- Update industry support information
- Add plain bush axial migration value for Right Hand (RH) side similar to Left Hand (LH)
side
- Replace the repair instruction R53370502 by R53370501 for replacement of the
actuator fitting on RH side
- Replace the repair instruction R53370501 by R53370502 for plain bush migration on
LH side
- Add bush PN R530711620000 and R530711620200 for both LH and RH side

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 6
A318/A319/A320/A321
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
- Update the flowchart
- Add repair procedures for loose flanged bush and wear marks
- Update the applicability of the Service Bulletin.

NOTE: This revision satisfies the requirements of the subsequent Technical Adaptation(s)
(TA) issued for the related Manufacturer Serial Number (MSN)s.

TA MSNs
80685120/023/2021 6286 6419 6642 6720 6744 6772 6799 6801
6819 6829 6833 6849 6860 6864 6868 6904
6907 6914 6920 6946 6952 6967 6975 7001
7011 7033 7047 7051 7053 7060 7074 7078
7083 7094 7102-7103 7107 7124 7126 7129
7140-7141 7147 7150 7162 7172 7175 7181
7185-7186 7192 7195 7205 7209 7236 7249
7252 7269 7273 7277 7283 7290-7291 7309
7321 7323 7329-7331 7333-7334 7341
7343 7352 7354 7359 7367 7380 7386-7387
7391 7396 7399 7401 7409 7417 7428-7429
7449 7459 7466 7470 7472 7475 7477 7480
7483-7484 7486 7489 7494-7495 7499 7501
7504-7505 7507-7508 7510 7512 7514 7517
7521 7523 7526 7530 7533 7535 7538 7540
7544 7547-7548 7553-7555 7559-7560 7563
7565 7567-7568 7571 7576-7577 7579 7581
7587-7589 7591 7594 7598 7600 7602-
7603 7606 7610 7612 7616 7618 7626 7629
7634 7638-7639 7642 7648-7649 7662-7663
7671 7676-7677 7682 7688 7694 7697-7698
7703 7705 7710 7719 7721 7723 7727 7731
7733 7735 7737 7744 7746 7751 7753 7755
7757 7764 7768 7770 7776 7778 7786 7788
7791 7794-7795 7799-7800 7802-7804 7807
7811-7813 7822 7824 7828 7834-7835 7837
7839 7841-7842 7844 7847-7851 7853-
7854 7856 7858-7862 7864 7871 7875 7881
7887 7891-7892 7895 7897 7899 7912 7914
7917-7918 7920-7921 7925 7928 7930-7931
7936 7939 7941-7942 7944-7946 7949-7952
7959-7961 7965 7967-7968 7972 7979-
7980 7983-7984 7986 7990-7992 7995-
7997 7999-8000 8005 8008 8014-8017 8020
8023 8025 8030-8031 8038-8039 8043 8048
8050-8052 8056 8058-8059 8074 8077 8079
8084-8096 8098-8103 8105-8110 8112-
8113 8117-8118 8120-8123 8126 8129 8131
8135-8140 8142 8144-8146 8148 8150 8152
8154-8158 8164 8166-8168 8170 8172-8173
8175 8181-8182 8184 8186-8187 8193-
8199 8202-8204 8206 8208-8209 8212 8214
8217-8219 8221 8224-8226 8228-8229 8231
8235 8237 8239-8240 8242-8243 8246-
8249 8253 8255-8257 8259-8262 8264-
8268 8270 8272-8275 8277-8278 8280 8282
8284 8286 8288-8292 8294 8297 8300-8304

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A318/A319/A320/A321
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET

TA MSNs
8306-8310 8312 8314 8318 8320 8323 8326
8330-8331 8333 8335 8337-8338 8340-8341
8345 8348-8351 8353 8356-8357 8360-8361
8364-8369 8371-8375 8377 8380 8382-
8383 8386-8387 8389 8392 8395 8397 8399
8402-8406 8408-8409 8411-8417 8419-
8421 8425-8426 8430-8433 8436 8440-8441
8443-8446 8449 8451 8453-8456 8458-8461
8464-8465 8467-8472 8474-8476 8478 8480
8482-8484 8486-8492 8494-8498 8501 8503
8505-8508 8510-8518 8520-8521 8523-8524
8526-8529 8531 8533 8535 8537 8540-8547
8551-8554 8556-8560 8562-8573 8575-
8576 8578 8580 8583-8584 8586-8589 8591
8593-8594 8596 8598 8601-8603 8607-8610
8613 8617-8624 8626-8631 8633 8635-8639
8642-8643 8645 8647-8650 8653-8656 8658
8660-8662 8665-8666 8668-8669 8674-8675
8678-8679 8681-8693 8698-8708 8710-8712
8714-8715 8717-8723 8725-8729 8731-8733
8735-8745 8747 8749-8762 8764 8766-
8777 8779-8783 8785 8787-8790 8792-8796
8799-8807 8811 8813-8821 8823 8825-
8834 8836-8837 8839-8840 8843-8844 8846
8848-8852 8855 8857 8860-8870 8872-8878
8880-8890 8893-8901 8903-8910 8912-8913
8917-8924 8926-8930 8932-8941 8944-8946
8948-8949 8952-8959 8961-8963 8965-
8973 8976-8985 8987-8993 8995-9002 9008
9011 9013-9019 9021-9024 9026 9029-9032
9034-9036 9038-9042 9044-9051 9053-9056
9059-9065 9068-9080 9082-9097
80685120/013/2019 6286 6419 6642 6720 6744 6772 6799 6801
6819 6829 6833 6849 6860 6864 6868 6904
6907 6914 6920 6946 6952 6967 6975 7001
7011 7033 7047 7051 7053 7060 7074 7078
7083 7094 7102-7103 7107 7124 7126 7129
7140-7141 7147 7150 7162 7172 7175 7181
7185-7186 7192 7195 7205 7209 7236 7249
7252 7269 7273 7277 7283 7290-7291 7309
7321 7323 7329-7331 7333-7334 7341
7343 7352 7354 7359 7367 7380 7386-7387
7391 7396 7399 7401 7409 7417 7428-7429
7449 7459 7466 7470 7472 7475 7477 7480
7483-7484 7486 7489 7494-7495 7499 7501
7504-7505 7507-7508 7510 7512 7514 7517
7521 7523 7526 7530 7533 7535 7538 7540
7544 7547-7548 7553-7555 7559-7560 7563
7565 7567-7568 7571 7576-7577 7579 7581
7587-7589 7591 7594 7598 7600 7602-
7603 7606 7610 7612 7616 7618 7626 7629
7634 7638-7639 7642 7648-7649 7662-7663
7671 7676-7677 7682 7688 7694 7697-7698
7703 7705 7710 7719 7721 7723 7727 7731
7733 7735 7737 7744 7746 7751 7753 7755

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SERVICE BULLETIN
REVISION TRANSMITTAL SHEET

REV 04 Nov 07/23 Page 11
A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY

EVALUATION TABLE
COMPLIANCE MANDATORY COST SAVING NO
A/C OPERATION NO VENDOR SB NO
AFFECTED
CANCELS INSPECTION SB NO ETOPS AFFECTED NO
PAX COMFORT AFFECTED NO POTENTIAL AD YES
RELIABILITY AFFECTED NO STRUCTURAL LIFE EXTENSION NO
LIFE LIMIT NO LINE MAINTENANCE AFFECTED NO

NOTE: Service Bulletin must be accomplished.

D. MAINTENANCE CONFIGURATION
No specific aircraft maintenance configuration required.
E. MATERIAL PRICE INFORMATION

(1) Special Detailed Inspection of the Actuator Fitting

(a) Task set A320-A-53-XX-1325-01000-93BA-A Special Detailed Inspection of the
Actuator Fitting

MATERIAL PRICE INFORMATION TABLE

QTY
MATERIAL SET PRICE PER A/C MAIN PARTS
PER A/C
Tool kit 531325T02R00 1 2490.00 USD Reamer kit
Tool kit 531325T03R00 1 4140.00 USD Reamer kit
Part kit 531325D01R02 2 111.80 USD Pin,washer
TOTAL 6741.80 USD
Components See SB See Note Bush

NOTE: Price information to be obtained from the given supplier.

F. APPLICABILITY
This Service Bulletin is applicable to this (these) operator(s):
09K 27V 34H 47H 48P 59Z 64X 82W 87Z AAL AAR ABL ABQ ABY ACI AEE AFL AHY AIC AIZ
ALK AMC AMU ANA ANZ APJ ASA AUA AUL AVA AWC AXB AXM AZU BAV BAW BEL BTK CAL
CBG CBJ CCA CCM CDC CEB CES CGZ CHB CLH CPA CQH CQN CSC CSN CSZ CTV CXA DAL
DCS DJT DKH DLH DRK EIN ESW EWG EXS EZY FAD FFT FLI FPY GAF GCR GFA GOW HAL HKE
HVN HXA HYS IAD IBE IBS IGO ITY JAT JBE JBU JJP JST JZR KAC KAL KAY KAZ KNE KZR LAN LKE
MBU MEA MFX MLM MSC MSR NDA NKS NVR NWC NWS OMS OTC PAL PGT PKZ QDA QNT
RBA RZO SAS SBI SEH SEY SFJ SJX SKU STW SVA SVR SVW SWM SWR TAI TAM TAP TAR TBA
TGW THY TSC TTW UEA UZB VIV VJC VLG VOI VRE VTI WAZ WMT WZZ
G. CONCURRENT REQUIREMENTS
None
H. NATURE OF THE WORK

(1) Special Detailed Inspection of the Actuator Fitting

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A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
(a) Task set A320-A-53-XX-1325-01000-93BA-A Special Detailed Inspection of the
Actuator Fitting

AIRCRAFT YES
EQUIPMENT NO
I. MANPOWER

(1) Special Detailed Inspection of the Actuator Fitting

(a) Task set A320-A-53-XX-1325-01000-93BA-A Special Detailed Inspection of the
Actuator Fitting

MANPOWER
TOTAL MAN-HOURS 19.50 h
ELAPSED TIME (HOURS) 10.25 h

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A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
J. GENERAL OVERVIEW
CONF ALL
FR34
A

B
FR50
C
Z190

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A318/A319/A320/A321
SERVICE BULLETIN

in-house warranty labor rate. Claims for labor allowance should be received no later than 90
days after completion of the last affected warranted aircraft.
This specific Industry Support shall not apply as an alternative to accomplishing the
corrective action, when such corrective action has been made available, and is valid until
Nov 30/25.

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A318/A319/A320/A321
SERVICE BULLETIN

2. MATERIAL INFORMATION
A. MATERIAL APPLICABILITY
Material for task set A320-A-53-XX-1325-01000-93BA-A Special Detailed
Inspection of the Actuator Fitting

MATERIAL QTY SEE NOTES

Tool kit 531325T02R00 1
Tool kit 531325T03R00 1
Referenced tools See SB
Consumables See SB
Referenced consumables See SB
Part kit 531325D01R02 2
Components See SB (1)
Referenced parts See SB
NOTE(S)
(1): Operator supplied AIRBUS parts required to accomplish this Service Bulletin are to be
purchased by a spares purchase order.
B. TOOLING
Tool kit 531325T02R00

Cost 2490.00 USD

Availability 150 d (calendar days from receipt of order)
NOTE(S)
Procurement to be negotiated directly with AIRBUS.

R5307111620000
2 BUSH (1) (2) (3)
(D4296)
R5307111620200
2 BUSH (1) (2) (3)
(D4296)
R5307111620400
2 BUSH (1) (2) (4)
(D4296)
R5307111620600
2 BUSH (1) (2) (4)
(D4296)
NOTE(S)
(1): Operator supplied AIRBUS parts required to accomplish this Service Bulletin are to be
purchased by a spares purchase order.
(2): The components listed above are not an AIRBUS Kit, the required parts must be
ordered as necessary through the given channel.
(3): The components listed above are only necessary if the Repair Instruction R53370502
is applied. The quantity of these items are to be ordered as required.
(4): The components listed above are only necessary if the Repair Instruction R53370510
is applied. The quantity of these items are to be ordered as required.
Referenced parts for task set A320-A-53-XX-1325-01000-93BA-A Special Detailed
Inspection of the Actuator Fitting
To accomplish this Service Bulletin it is necessary to use the expendable parts listed in:
Ref. AMM Task 32-31-35-400-001
E. LIST OF EXISTING PARTS
No parts

REV 00 Apr 29/16 A320-53-1325

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A318/A319/A320/A321
SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS
Task set A320-A-53-XX-1325-01000-93BA-A (A320-A-53-XX-1325-01ZZZ-93BZ-A)
Special Detailed Inspection of the Actuator Fitting

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED
BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES 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.

WARNING: OBEY THE HYDRAULIC SAFETY PROCEDURES.

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE
LANDING GEAR AND THE WHEEL CHOCKS ARE IN POSITION.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY
SERVICEABLE). WHEN YOU DO A MAINTENANCE WORK, REPAIRS OR
MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND
THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS:
- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC., AS
NECESSARY ON WIRING AND COMPONENTS.
- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND
OTHER CONTAMINATION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND
DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IF THERE IS CONTAMINATION, REFER TO Ref. ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin include procedures given in
other documents or in other sections of the Service Bulletin. When the words “refer to”
are used and the operator has a procedure accepted by the local authority he belongs to,
the accepted alternative procedure can be used. When the words “in accordance with”
are used then the given procedure must be followed.

NOTE: The access and close-up instructions, not comprising return to service tests, in this
Service Bulletin do not constitute or affect the technical intent of the Service Bulletin.
Operators can therefore, as deemed necessary, omit or add access and/or close-up steps
to add flexibility to their maintenance operations as long as the technical intent of the
Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Refer
to paragraph 1.J., References, for the definition of acronyms.

NOTE: The purpose of flowcharts is to supplement the information given in the Procedure and
Compliance paragraphs and not to serve as the primary source for tasks or compliance
times given in this Service Bulletin.

NOTE: This Service Bulletin contains the instructions for the on-aircraft maintenance necessary
to ensure the continued airworthiness of the aircraft.
For any deviations to the instructions, contact AIRBUS for further instructions and
approval.

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 52
A318/A319/A320/A321
SERVICE BULLETIN

NOTE: Discarded parts must be managed at the operator's discretion.

A. TASK SET ASSOCIATED INFORMATION

Task Manpower
TOTAL MAN-HOURS 19.50 h
ELAPSED TIME (HOURS) 10.25 h
B. PREPARATION
(1) Task A320-A-53-XX-1325-01001-540A-A (A320-A-53-XX-1325-01ZZZ-540Z-A)
Job Set-up
Job Set-Up Information
Manpower/Resources/Skills

Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Skills Airframe

Referenced Information

Manuals/Drawings References/Sheets
Task 12-34-24-869-002
Task 24-41-00-861-002
AMM
Task 32-12-00-010-001
Task 32-31-35-000-001
Procedure

NOTE: For the basic Aircraft configuration, refer to AMM Chapter "Introduction -
Aircraft status for maintenance" in Manual Front Matter section.

(a) Make sure that the aircraft is electrically grounded, refer to Ref. AMM Task 12-34-
24-869-002.
(b) Energize the aircraft electrical circuits, refer to Ref. AMM Task 24-41-00-861-002.
(c) Open the MLG doors, refer to Ref. AMM Task 32-12-00-010-001.

NOTE: Make sure that the appropriate MLG door safety-equipment is installed.

(d) Put an access platform in position of work area at Door 734 and Door 744.
(e) Open, safety/lock and tag the applicable circuit breaker(s), refer to Ref. AMM Task
32-31-35-000-001.
(f) Put the warning notices in position to tell persons not to operate the green
hydraulic system:
- On the Electrical Panel 40VU in the cockpit
- On the ground service panel of the green hydraulic system.
(g) Put the warning notices in position in the flight compartment to tell persons not
to operate the landing gear doors.
(2) Task A320-A-53-XX-1325-02001-540A-A (A320-A-53-XX-1325-02ZZZ-540Z-A)
Disconnect the MLG Door Actuator from Actuator Fitting on LH Side

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 53
A318/A319/A320/A321
SERVICE BULLETIN

Job Set-Up Information

Working Area

Impacted Zone Access / Work Location

147 Access Door 734
Manpower/Resources/Skills

Man-hours 0.25 h
Minimum Number of person 1
Elapsed Time 0.25 h
Skills Airframe

Referenced Information

Manuals/Drawings References/Sheets
06-20-00, Page Block 001
AMM 06-31-53, Page Block 001
Task 32-31-39-000-001
SRM 51-42-00
Procedure
(a) Standard Practices given in this procedure:
1 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
2 For the Frame (FR) identification, refer to Ref. AMM 06-31-53, Page Block
001.
3 Tag all the parts you must remove and retain to make the subsequent
installation easier.
4 Put all the retained hardware in identified plastic bags and attach the bags
to the related unit.
5 Remove and install fasteners in accordance with Ref. SRM 51-42-00.
CAUTION: HOLD OR SUPPORT THE ACTUATING-CYLINDER DURING
INSPECTION IN ORDER TO AVOID DAMAGING THE HYDRAULIC
PIPES AND HOSES FIN: 2765GM, 2766GM, 2767GM, 2768GM. THIS
CAN CAUSE INCREASED STRAIN ON THE HOSE AND POSSIBLE
HOSE DAMAGE.

(b) Disconnect the actuator from the actuator fitting without disconnecting hydraulic
pipes on LH side, refer to Ref. Fig.BC Removal of the MLG Door Actuator LH Side.
1 Remove:

1 ACTUATING-CYLINDER Item (4) Retain

attached with:

1 COTTER PIN Item (9) Discard

1 NUT Item (7) Retain

1 WASHER Item (6) Retain

1 SPACER Item (5) Retain

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REV 04 Nov 07/23 Page 54
A318/A319/A320/A321
SERVICE BULLETIN

1 BOLT Item (1) Retain

If installed, remove:

1 SHIM WASHER Item (8) Discard

NOTE: Make sure that the shim washer does not fall.

(c) Hold and secure the door actuator to prevent damage to flexible hoses.
(d) If necessary, disconnect the flexible hose assembly from the door actuator, refer
to Ref. AMM Task 32-31-39-000-001.

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 55
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

Z190

FR34

B FR50

ICN-A320-A-53XX1325-A-FAPE3-00X4X-A-003-01

Figure ICN-A320-A-53XX1325-A-FAPE3-00X4X-A-003-01 Fig.BC Sol.AA SHEET 1/2

REV 00 Apr 29/16 A320-53-1325
Removal of the MLG Door Actuator LH Side
REV 04 Nov 07/23 Page 56
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

(1)

(8)

(9)

(5)
(6) (4)

(7)

ICN-A320-A-53XX1325-A-FAPE3-00X4Y-A-006-01

Figure ICN-A320-A-53XX1325-A-FAPE3-00X4Y-A-006-01 Fig.BC Sol.AA SHEET 2/2

REV 00 Apr 29/16 A320-53-1325
Removal of the MLG Door Actuator LH Side
REV 04 Nov 07/23 Page 57
A318/A319/A320/A321
SERVICE BULLETIN

(3) Task A320-A-53-XX-1325-03001-540A-A (A320-A-53-XX-1325-03ZZZ-540Z-A)

Disconnect the MLG Door Actuator from Actuator Fitting on RH Side
Job Set-Up Information
Working Area

Impacted Zone Access / Work Location

148 Access Door 744
Manpower/Resources/Skills

Man-hours 0.25 h
Minimum Number of person 1
Elapsed Time 0.25 h
Skills Airframe

Referenced Information

Manuals/Drawings References/Sheets
06-20-00, Page Block 001
AMM 06-31-53, Page Block 001
Task 32-31-39-000-001
SRM 51-42-00
Procedure
(a) Standard Practices given in this procedure:
1 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
2 For the FR identification, refer to Ref. AMM 06-31-53, Page Block 001.
3 Tag all the parts you must remove and retain to make the subsequent
installation easier.
4 Put all the retained hardware in identified plastic bags and attach the bags
to the related unit.
5 Remove and install fasteners in accordance with Ref. SRM 51-42-00.
CAUTION: HOLD OR SUPPORT THE ACTUATING-CYLINDER DURING
INSPECTION IN ORDER TO AVOID DAMAGING THE HYDRAULIC
PIPES AND HOSES FIN: 2765GM, 2766GM, 2767GM, 2768GM. THIS
CAN CAUSE INCREASED STRAIN ON THE HOSE AND POSSIBLE
HOSE DAMAGE.

(b) Disconnect the actuator from the actuator fitting without disconnecting hydraulic
pipes on RH side, refer to Ref. Fig.BG Removal of the MLG Door Actuator RH Side.
1 Remove:

1 ACTUATING-CYLINDER Item (4) Retain

attached with:

1 COTTER PIN Item (9) Discard

1 NUT Item (7) Retain

1 WASHER Item (6) Retain

1 SPACER Item (5) Retain

REV 00 Apr 29/16 A320-53-1325
REV 04 Nov 07/23 Page 58
A318/A319/A320/A321
SERVICE BULLETIN

1 BOLT Item (1) Retain

If installed:

1 SHIM WASHER Item (8) Discard

NOTE: Make sure that the shim washer does not fall.

(c) Hold and secure the door actuator to prevent damage to flexible hoses.
(d) If necessary, disconnect the flexible hose assembly from the door actuator, refer
to Ref. AMM Task 32-31-39-000-001.

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 59
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

Z190

FR34

FR50
B

ICN-A320-A-53XX1325-A-FAPE3-02127-A-001-01

Figure ICN-A320-A-53XX1325-A-FAPE3-02127-A-001-01 Fig.BG Sol.AA SHEET 1/2

REV 00 Apr 29/16 A320-53-1325
Removal of the MLG Door Actuator RH Side
REV 04 Nov 07/23 Page 60
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

(9)
(6)
(5)

(7)
(8)

(4) (1)

ICN-A320-A-53XX1325-A-FAPE3-02128-A-004-01

Figure ICN-A320-A-53XX1325-A-FAPE3-02128-A-004-01 Fig.BG Sol.AA SHEET 2/2

REV 00 Apr 29/16 A320-53-1325
Removal of the MLG Door Actuator RH Side
REV 04 Nov 07/23 Page 61
A318/A319/A320/A321
SERVICE BULLETIN

C. PROCEDURE
(1) Task A320-A-53-XX-1325-01001-300A-A (A320-A-53-XX-1325-01ZZZ-300Z-A)
Do an SDI of the Keel Beam MLG Door Actuator Fitting on Aircraft, on Left
Hand (LH) side
Job Set-Up Information
Working Area

Impacted Zone Access / Work Location

147 Work location Door 734
Manpower/Resources/Skills

Man-hours 3.50 h
Minimum Number of person 1
Elapsed Time 3.50 h
Skills Non-Destructive Testing
Material necessary to do the job

Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
Non Aqueous Cleaner-
08BAA9
General
14SBA1 Textile-Lint free-Cotton
Referenced Information

Manuals/Drawings References/Sheets
AMM 06-20-00, Page Block 001
CML CONSUMABLE MATERIAL LIST (CML)
ISI 00.00.00179
NTM 53-31-54
SB A320-53-1503
51-73-00
SRM 51-73-11
51-75-12
R53370502 all sheets
R53370506 all sheets
R53370510 all sheets
Procedure
(a) Standard Practices given this procedure:
1 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
2 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
3 Repair the paint coating in accordance with Ref. SRM 51-75-12.
(b) At the threshold given in the PLANNING INFORMATION paragraph 1.E.(2):
Refer to Ref. Fig.FB Inspection Flowchart.

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REV 04 Nov 07/23 Page 62
A318/A319/A320/A321
SERVICE BULLETIN

1 Remove the sealant and clean the inspection area with:

Non Aqueous Cleaner- 08BAA9

General

Textile-Lint free-Cotton 14SBA1

2 Do an HFEC and ultrasonic inspection on the keel beam actuator fittings on
LH side for crack(s) in accordance with Ref. NTM 53-31-54.
Do a detailed visual inspection for fretting/wear and condition of bearing.

NOTE: It is not necessary to remove MLG door and not necessary to

disconnect hydraulic pipes from MLG door actuator to do the HFEC
and ultrasonic inspection.

Refer to Ref. Fig.BA Inspection Area LH Side.

a If crack is found:
<1> Do the replacement of the MLG door actuator fitting in
accordance with Ref. Task A320-A-53-XX-1325-01ZZZ-920Z-A.
<2> Send the completed Inspection Report sheet in accordance with
Ref. ISI 00.00.00179 and refer to Ref. Fig.RB Inspection Report
Sheet.

NOTE: To send the Inspection Report sheet is not Required for

Compliance (RC).

<3> Repeat the inspection in accordance with Ref. Task set A320-A-
53-XX-1325-01ZZZ-93BZ-A, at the repetitive interval given in
the PLANNING INFORMATION paragraph 1.E.(2).

OR
<4> Send the completed Inspection Report sheet in accordance with
Ref. ISI 00.00.00179 and refer to Ref. Fig.RB Inspection Report
Sheet.

NOTE: To send the Inspection Report sheet is not Required for

Compliance (RC).

<5> Accomplish the MSB No. Ref. SB A320-53-1503.

<6> No further action for this Service Bulletin.

OR
<7> Contact AIRBUS and follow their instructions at the threshold
given in the PLANNING INFORMATION paragraph 1.E.(2).
b If no crack is found:
<1> Accomplish the MSB No. Ref. SB A320-53-1503.
<2> No further action for this Service Bulletin.

OR
<3> Do a DET for plain bush axial migration on the actuator fitting,
refer to Ref. Fig.BI Check of the Plain Bush Migration, Flanged
Bush Axial loose and Wear Marks LH Side.

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REV 04 Nov 07/23 Page 63
A318/A319/A320/A321
SERVICE BULLETIN

<a> If the plain bush axial migration is found to be more than

0.80 mm (0.032 in.):

NOTE: Do not apply a repair before completing the

4 inspections, check if the repair is possible
following the criteria included in the 3 RIs
(R53370502; R53370506; R53370510).

Check according to RI Ref. R53370502 all sheets if the

damage can be repaired within its limits.
[1] If the damage can be repaired within its limits
according to RI Ref. R53370502 all sheets:
[a] Do the repair in accordance with Ref. Task
A320-A-53-XX-1325-03ZZZ-920Z-A.
[b] If the damage is eliminated:
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).
- Repeat the inspection in accordance with
Ref. Task set A320-A-53-XX-1325-01ZZZ-
93BZ-A, at the repetitive interval given in
the PLANNING INFORMATION paragraph
1.E.(2).
[c] If the damage is not eliminated:
- Contact AIRBUS and follow their
instructions at the threshold given in the
PLANNING INFORMATION paragraph 1.E.
(2).
OR
- Do the replacement of the MLG door
actuator fitting in accordance with Ref.
Task A320-A-53-XX-1325-01ZZZ-920Z-A.
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

NOTE: To send the Inspection Report

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 64
A318/A319/A320/A321
SERVICE BULLETIN

- Send the completed Inspection Report

sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).
- Accomplish the MSB No. Ref. SB A320-53-
1503.
- No further action for this Service Bulletin.
[2] If the damage cannot be repaired within its limit
according to RI Ref. R53370502 all sheets:
[a] Contact AIRBUS and follow their instructions
at the threshold given in the PLANNING
INFORMATION paragraph 1.E.(2).

OR
[b] Do the replacement of the MLG door actuator
fitting in accordance with Ref. Task A320-A-53-
XX-1325-01ZZZ-920Z-A.
[c] Send the completed Inspection Report sheet in
accordance with Ref. ISI 00.00.00179 and refer
to Ref. Fig.RB Inspection Report Sheet.

NOTE: To send the Inspection Report sheet is

not Required for Compliance (RC).

[d] Repeat the inspection in accordance with Ref.

Task set A320-A-53-XX-1325-01ZZZ-93BZ-A, at
the repetitive interval given in the PLANNING
INFORMATION paragraph 1.E.(2).

OR
[e] Send the completed Inspection Report sheet in
accordance with Ref. ISI 00.00.00179 and refer
to Ref. Fig.RB Inspection Report Sheet.

NOTE: To send the Inspection Report sheet is

not Required for Compliance (RC).

[f] Accomplish the MSB No. Ref. SB A320-53-1503.

[g] No further action for this Service Bulletin.
 If plain bush axial migration is not found or plain bush
axial migration is less than 0.80 mm (0.032 in.):
[1] Send the completed Inspection Report sheet in
accordance with Ref. ISI 00.00.00179 and refer to
Ref. Fig.RB Inspection Report Sheet.

NOTE: To send the Inspection Report sheet is not

Required for Compliance (RC).

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 65
A318/A319/A320/A321
SERVICE BULLETIN

[2] Repeat the inspection in accordance with Ref.

Task set A320-A-53-XX-1325-01ZZZ-93BZ-A, at
the repetitive interval given in the PLANNING
INFORMATION paragraph 1.E.(2).
<4> Do a DET for flanged bush axial loose on the actuator fitting,
refer to Ref. Fig.BI Check of the Plain Bush Migration, Flanged
Bush Axial loose and Wear Marks LH Side.
<a> If loose flanged bush is found:

NOTE: Do not apply a repair before completing the

4 inspections, check if the repair is possible
following the criteria included in the 3 RIs
(R53370502; R53370506; R53370510).

Check according to RI Ref. R53370510 all sheets if the

damage can be repaired within its limits.
[1] If the damage can be repaired within its limits
according to RI Ref. R53370510 all sheets:
[a] Do the repair in accordance with Ref. Task
A320-A-53-XX-1325-01ZZZ-690Z-A.
[b] If the damage is eliminated:
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 66
A318/A319/A320/A321
SERVICE BULLETIN

- Repeat the inspection in accordance with

Ref. Task set A320-A-53-XX-1325-01ZZZ-
93BZ-A, at the repetitive interval given in
the PLANNING INFORMATION paragraph
1.E.(2).
OR
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).
- Accomplish the MSB No. Ref. SB A320-53-
1503.
- No further action for this Service Bulletin.
[2] If the damage cannot be repaired within its limit
according to RI Ref. R53370510 all sheets:
[a] Contact AIRBUS and follow their instructions
at the threshold given in the PLANNING
INFORMATION paragraph 1.E.(2).

NOTE: To send the Inspection Report sheet is

not Required for Compliance (RC).

[d] Repeat the inspection in accordance with Ref.

Task set A320-A-53-XX-1325-01ZZZ-93BZ-A, at
the repetitive interval given in the PLANNING
INFORMATION paragraph 1.E.(2).

OR
[e] Send the completed Inspection Report sheet in
accordance with Ref. ISI 00.00.00179 and refer
to Ref. Fig.RB Inspection Report Sheet.

NOTE: To send the Inspection Report sheet is

not Required for Compliance (RC).

[f] Accomplish the MSB No. Ref. SB A320-53-1503.

[d] Repeat the inspection in accordance with Ref.

Task set A320-A-53-XX-1325-01ZZZ-93BZ-A, at
the repetitive interval given in the PLANNING
INFORMATION paragraph 1.E.(2).

OR
[e] Send the completed Inspection Report sheet in
accordance with Ref. ISI 00.00.00179 and refer
to Ref. Fig.RB Inspection Report Sheet.

NOTE: To send the Inspection Report sheet is

not Required for Compliance (RC).

[f] Accomplish the MSB No. Ref. SB A320-53-1503.

[g] No further action for this Service Bulletin.
[2] If damage can be repaired:

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 70
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SERVICE BULLETIN

[a] Do a repair for other damages found on LH

side in accordance with Ref. Task A320-A-53-
XX-1325-05ZZZ-690Z-A.
[b] If the part thickness remains within the
tolerance of the negligible damage in
accordance with Ref. SRM 51-73-11 and there
are no findings after HFEC inspection:
- Restore the surface protection in
accordance with Ref. SRM 51-75-12.
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).
- Repeat the inspection in accordance with
Ref. Task set A320-A-53-XX-1325-01ZZZ-
93BZ-A, at the repetitive interval given in
the PLANNING INFORMATION paragraph
1.E.(2).
[c] If the part thickness is outside the tolerance of
the negligible damage in accordance with Ref.
SRM 51-73-11 or there are findings after HFEC
inspection:
- Contact AIRBUS and follow their
instructions at the threshold given in the
PLANNING INFORMATION paragraph 1.E.
(2).
OR
- Do the replacement of the MLG door
actuator fitting in accordance with Ref.
Task A320-A-53-XX-1325-01ZZZ-920Z-A.
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).
- Repeat the inspection in accordance with
Ref. Task set A320-A-53-XX-1325-01ZZZ-
93BZ-A, at the repetitive interval given in
the PLANNING INFORMATION paragraph
1.E.(2).
OR
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.
REV 00 Apr 29/16 A320-53-1325
REV 04 Nov 07/23 Page 71
A318/A319/A320/A321
SERVICE BULLETIN

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).
- Accomplish the MSB No. Ref. SB A320-53-
1503.
- No further action for this Service Bulletin.
 If other damage(s) is/are not found:
[1] Send the completed Inspection Report sheet in
accordance with Ref. ISI 00.00.00179 and refer to
Ref. Fig.RB Inspection Report Sheet.

NOTE: To send the Inspection Report sheet is not

Required for Compliance (RC).

[2] Repeat the inspection in accordance with Ref.

Task set A320-A-53-XX-1325-01ZZZ-93BZ-A, at
the repetitive interval given in the PLANNING
INFORMATION paragraph 1.E.(2).
3 Renew the protective finish in accordance with Ref. SRM 51-75-12.

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SERVICE BULLETIN

CONF ALL
DO A SPECIAL DETAILED INSPECTION WITH HFEC
AND ULTRASONIC AND VISUAL INSPECTION FOR
FRETTING/WEAR AND CONDITION OF BEARING ON C
NO FURTHER ACTION FOR THE KEEL BEAM MLG DOOR ACTUATOR FITTING 01 02
THIS SERVICE BULLETIN

ACCOMPLISH THE MODIFICATION

IS THERE ANY
SERVICE BULLETIN No A320-53-1503 OR NO YES
CRACK FOUND?
01
CAN
DAMAGE BE
REPAIRED IN ACCORDANCE NO
AND WITH SRM 51-73-00?

YES

DO A DETAILED INSPECTION FOR DO A DETAILED INSPECTION FOR DO A DETAILED INSPECTION FOR WEAR DO A DETAILED INSPECTION - DO A BLEND OUT IN ACCORDANCE WITH
PLAIN BUSH AXIAL MIGRATION 01 FLANGED BUSH AXIAL LOOSE 01 MARKS UNDERNEATH BOLT HEAD 01 FOR ANY OTHER DAMAGE 01 SRM 51-73-00 AND HFEC INSPECTION IN
ACCORDANCE WITH NTM 51-10-08
- MEASURE REMAINING THICKNESS OF THE
PART IN ACCORDANCE WITH NTM 51-10-04

IS LOOSE FLANGED YES IS OTHER DAMAGE

IS PLAIN BUSH FOUND? ARE WEAR YES
YES FOUND?
BUSH MIGRATION FOUND MARKS FOUND?
YES
MORE THAN 0.8 mm IS THE PART
(0.032 in)?
THICKNESS WITHIN
THE TOLERANCE OF NEGLIGIBLE
DAMAGE IN ACCORDANCE WITH NO
SRM 51-73-11 AND NO FINDING
NO
A NO AFTER HFEC INSPECTION
NO A IN ACCORDANCE WITH
NO A NTM 51-10-08?

YES

RESTORE THE SURFACE PROTECTION

REPEAT THE SEND THE COMPLETED INSPECTION IN ACCORDANCE WITH SRM 51-75-12
INSPECTION 01 REPORT SHEET TO AIRBUS 01 B 01

NOTE: D
THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE
AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR
COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.
01 FOR THE ACCOMPLISHMENT TIMESCALE, REFER TO PARAGRAPH 1.E.(2).
02 THIS FLOWCHART IS APPLICABLE FOR THE INSPECTION TASK. ICN-A320-A-53XX1325-A-FAPE3-026Y1-A-008-01

Figure ICN-A320-A-53XX1325-A-FAPE3-026Y1-A-008-01 Fig.FB Sol.AA SHEET 1/3

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Inspection Flowchart
REV 04 Nov 07/23 Page 73
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

D C

CONTACT AIRBUS SEND THE COMPLETED INSPECTION REPLACE THE ACTUATOR

AND FOLLOW THEIR REPORT SHEET TO AIRBUS FITTING IN ACCORDANCE
INSTRUCTIONS WITH RI R53370501 01
01
01

SEND THE COMPLETED

INSPECTION REPORT
ACCOMPLISH THE MODIFICATION SHEET TO AIRBUS 01
SERVICE BULLETIN No A320-53-1503
01

REPEAT THE INSPECTION 01

NO FURTHER ACTION FOR

THIS SERVICE BULLETIN

NOTE:
THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE
AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR
COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.
01 FOR THE ACCOMPLISHMENT TIME SCALE, REFER TO PARAGRAPH 1.E.(2).
ICN-A320-A-53XX1325-A-FAPE3-026Y2-A-006-01

Figure ICN-A320-A-53XX1325-A-FAPE3-026Y2-A-006-01 Fig.FB Sol.AA SHEET 2/3

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Inspection Flowchart
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A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

ALL THE FOUR INSPECTIONS

COMPLETED 03

CHECK IF DAMAGE(S) CAN BE REPAIRED

WITHIN THE LIMITS OF APPLICABLE
REPAIR INSTRUCTION 04

IS (ARE)
DAMAGE(S)
REPAIRABLE WITHIN THE
LIMITS OF APPLICABLE REPAIR YES
INSTRUCTION
05 ?

APPLY RI R53370502 APPLY RI R53370510 APPLY RI R53370506

TO REPAIR PLAIN BUSH TO REPAIR FLANGED BUSH TO REPAIR WEAR MARKS
06 06 06
NO

IS(ARE)
OR NO DAMAGE(S)
ELIMINATED?

B YES

CONTACT AIRBUS AND REPLACE THE ACTUATOR FITTING SEND THE COMPLETED INSPECTION
FOLLOW THEIR INSTRUCTIONS 01 IN ACCORDANCE WITH RI R53370501 REPORT SHEET TO AIRBUS
NOTE: 01
01
THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE
AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR
COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.
01 FOR THE ACCOMPLISHMENT TIME SCALE, REFER TO PARAGRAPH 1.E.(2). SEND THE COMPLETED INSPECTION
REPORT SHEET TO AIRBUS ACCOMPLISH THE MODIFICATION
03 THIS FLOWCHART IS APPLICABLE FOR THE REPAIR TASK. SERVICE BULLETIN No A320-53-1503
01
04 DO NOT APPLY A REPAIR BEFORE COMPLETING THE 4 INSPECTIONS, CHECK IF THE REPAIR(S) IS(ARE) 01
POSSIBLE FOLLOWING THE CRITERIA INCLUDED IN THE 3 REPAIR INSTRUCTIONS (R53370502,
R53370506, R53370510).
05 DEPENDING ON THE INSPECTION RESULTS, IF ONE OR MORE DAMAGE(S) EXCEED(S) THE REPEAT THE INSPECTION 01
CORRESPONDING REPAIR LIMITATION, CONTACT AIRBUS. NO FURTHER ACTION FOR
THIS SERVICE BULLETIN
06 ONLY THE REPAIR INSTRUCTIONS CORRESPONDING TO THE DAMAGE
FOUND SHOULD BE PERFORMED. ICN-A320-A-53XX1325-A-FAPE3-02FTK-A-004-01

Figure ICN-A320-A-53XX1325-A-FAPE3-02FTK-A-004-01 Fig.FB Sol.AA SHEET 3/3

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Inspection Flowchart
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A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

Z190

FR34

A
B

FR50

NOTE:
01 ACTUATOR FITTING TO BE INSPECTED. ICN-A320-A-53XX1325-A-FAPE3-00X4T-A-006-01

Figure ICN-A320-A-53XX1325-A-FAPE3-00X4T-A-006-01 Fig.BA Sol.AA SHEET 1/2

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Inspection Area LH Side
REV 04 Nov 07/23 Page 76
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

FR44

FR43

FR42

FR41

STGR36RH

01
STGR44

STGR36LH

NOTE:
01 ACTUATOR FITTING TO BE INSPECTED. ICN-A320-A-53XX1325-A-FAPE3-00X4U-A-006-01

Figure ICN-A320-A-53XX1325-A-FAPE3-00X4U-A-006-01 Fig.BA Sol.AA SHEET 2/2

REV 00 Apr 29/16 A320-53-1325
Inspection Area LH Side
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A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No : A320-53-1325

A/C MSN :
FLIGHT CYCLES (FC) :
SEND THE COMPLETED INSPECTION REPORT
FLIGHT HOURS (FH) : SHEET IN ACCORDANCE WITH ISI 00.00.00179
DATE OF INSPECTION :
INSPECTION METHOD : SPECIAL DETAILED
INSPECTION
DETAILED INSPECTION
FUSELAGE - CENTER FUSELAGE - INSPECT MLG DOOR ACTUATOR FITTING ON KEEL BEAM
ACTUATOR FITTING
UPPER NOTCH, AREA 1

ACTUATOR FITTING
LUG, AREA 2

ACTUATOR FITTING
LOWER RADIUS,
AREA 3

ACTUATOR FITTING
JOINT TO CONNECTING
PLATE, AREA 4

CHECK FOR CRACKS AND

OTHER DAMAGE AND
FRETTING MARKS ON RESULTS FOLLOW-UP ACTIONS
ACTUATOR FITTING -
LOCATIONS
ACTUATOR FITTING REPLACED
CRACKS FOUND
ACCOMPLISHED MSB No A320-53-1503
REPORTED TO AIRBUS
CRACK LENGTH: ____ mm AIRBUS CONTACTED FOR FURTHER
REPAIR INSTRUCTIONS
AREA 1
DO A DETAILED INSPECTION FOR PLAIN
BUSH AXIAL MIGRATION, FLANGED
BUSH AXIAL LOOSE, WEAR MARKS
NO CRACK FOUND UNDERNEATH BOLT HEAD AND ANY
OTHER DAMAGE, SEE SHEET 4 AND 5
ACCOMPLISHED MSB No A320-53-1503

ICN-A320-A-53XX1325-A-FAPE3-01V9J-A-006-01

Figure ICN-A320-A-53XX1325-A-FAPE3-01V9J-A-006-01 Fig.RB Sol.AA SHEET 1/5

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Inspection Report Sheet
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A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No : A320-53-1325

ACTUATOR FITTING REPLACED

CRACKS FOUND
ACCOMPLISHED MSB No A320-53-1503
REPORTED TO AIRBUS
CRACK LENGTH: ____ mm AIRBUS CONTACTED FOR FURTHER
REPAIR INSTRUCTIONS
AREA 2
DO A DETAILED INSPECTION FOR PLAIN
BUSH AXIAL MIGRATION, FLANGED
BUSH AXIAL LOOSE, WEAR MARKS
NO CRACK FOUND UNDERNEATH BOLT HEAD AND ANY
OTHER DAMAGE, SEE SHEET 4 AND 5
ACCOMPLISHED MSB No A320-53-1503
ACTUATOR FITTING REPLACED
CRACKS FOUND
ACCOMPLISHED MSB No A320-53-1503
REPORTED TO AIRBUS
CRACK LENGTH: ____ mm AIRBUS CONTACTED FOR FURTHER
REPAIR INSTRUCTIONS
AREA 3
DO A DETAILED INSPECTION FOR PLAIN
BUSH AXIAL MIGRATION, FLANGED
BUSH AXIAL LOOSE, WEAR MARKS
NO CRACK FOUND UNDERNEATH BOLT HEAD AND ANY
OTHER DAMAGE, SEE SHEET 4 AND 5
ACCOMPLISHED MSB No A320-53-1503

ICN-A320-A-53XX1325-A-FAPE3-026XK-A-006-01

Figure ICN-A320-A-53XX1325-A-FAPE3-026XK-A-006-01 Fig.RB Sol.AA SHEET 2/5

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Inspection Report Sheet
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A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No : A320-53-1325

ACTUATOR FITTING REPLACED

CRACKS FOUND
ACCOMPLISHED MSB No A320-53-1503
REPORTED TO AIRBUS
CRACK LENGTH: ____ mm AIRBUS CONTACTED FOR FURTHER
REPAIR INSTRUCTIONS
AREA 4
DO A DETAILED INSPECTION FOR PLAIN
BUSH AXIAL MIGRATION, FLANGED
BUSH AXIAL LOOSE, WEAR MARKS
NO CRACK FOUND UNDERNEATH BOLT HEAD AND ANY
OTHER DAMAGE, SEE SHEET 4 AND 5
ACCOMPLISHED MSB No A320-53-1503
NOTE:
IN CASE OF CRACK FINDINGS, PLEASE SPECIFY CRACK LENGTH
WITH 1/10 mm - PRECISION MEASUREMENT.

REMARKS:

ICN-A320-A-53XX1325-A-FAPE3-02FTI-A-003-01

Figure ICN-A320-A-53XX1325-A-FAPE3-02FTI-A-003-01 Fig.RB Sol.AA SHEET 3/5

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Inspection Report Sheet
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A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No : A320-53-1325

RESULTS FOLLOW-UP ACTIONS

SAME PLAIN
PLAIN BUSH AXIAL- ACTUATOR FITTING REPLACED
BUSH
MIGRATED (APPROX.
INSTALLED
MIGRATION
AIRBUS CONTACTED FOR FURTHER
MEASURED:___ mm)
OVERSIZED REPAIR INSTRUCTIONS
CHECK FOR PLAIN BUSH
PLAIN BUSH INSTALLED
REPORTED TO AIRBUS
MIGRATION
RI NOT
APPLIED ACCOMPLISH MSB No A320-53-1503

NO PLAIN BUSH AXIAL MIGRATION

REPORTED TO AIRBUS
FOUND

REMARKS:

RESULTS FOLLOW-UP ACTIONS

SAME
FLANGED BUSH FLANGED ACTUATOR FITTING REPLACED
(APPROX. LOOSE BUSH
MEASURED:___ mm) INSTALLED AIRBUS CONTACTED FOR FURTHER
OVERSIZED REPAIR INSTRUCTIONS
CHECK FOR FLANGED
LOOSE BUSH
REPORTED TO AIRBUS
FLANGED INSTALLED
BUSH
RI NOT
APPLIED ACCOMPLISH MSB No A320-53-1503

NO LOOSE FLANGED BUSH FOUND REPORTED TO AIRBUS

REMARKS:

ICN-A320-A-53XX1325-A-FAPE3-02FTJ-A-003-01

Figure ICN-A320-A-53XX1325-A-FAPE3-02FTJ-A-003-01 Fig.RB Sol.AA SHEET 4/5

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Inspection Report Sheet
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A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No : A320-53-1325

RESULTS FOLLOW-UP ACTIONS

ACTUATOR FITTING REPLACED

(DUE TO WEAR MARKS DEEPER
REPAIR R533-70506 APPLIED THAN 0.70 mm (0.027 in))
LUG SURFACE FINAL LUG THICKNESS:_______ mm
AIRBUS CONTACTED FOR FURTHER
REPAIR DUE TO
REPAIR INSTRUCTIONS
WEAR MARKS (MUST BE HIGHER THAN
9.30 mm (0.367 in)) REPORTED TO AIRBUS

ACCOMPLISH MSB No A320-53-1503

WEAR MARKS NOT FOUND REPORTED TO AIRBUS

REMARKS:

INSPECTION RESULTS FOLLOW-UP ACTIONS

DAMAGE CAN BE
BLEND OUT PERFORMED
REPAIRED
ACTUATOR FITTING REPLACED
AIRBUS CONTACTED FOR FURTHER
CHECK FOR OTHER DAMAGE DAMAGE CAN NOT REPAIR INSTRUCTIONS
BE REPAIRED
ACCOMPLISHED MSB No A320-53-1503
REPORTED TO AIRBUS
NO OTHER DAMAGES REPORTED TO AIRBUS
REMARKS:

ICN-A320-A-53XX1325-A-FAPE3-02PIG-A-001-01

Figure ICN-A320-A-53XX1325-A-FAPE3-02PIG-A-001-01 Fig.RB Sol.AA SHEET 5/5

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Inspection Report Sheet
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A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

Z190

FR34

FR50

ICN-A320-A-53XX1325-A-FAPE3-026Y3-A-002-01

Figure ICN-A320-A-53XX1325-A-FAPE3-026Y3-A-002-01 Fig.BI Sol.AA SHEET 1/2

REV 00 Apr 29/16 Check of the Plain Bush Migration, Flanged A320-53-1325
REV 04 Nov 07/23 Bush Axial loose and Wear Marks LH Side Page 83
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

FWD
ACTUATOR
FITTING

FLANGED
02
BUSH
PLAIN
BUSH

AFT
ACTUATOR
FITTING

FWD A A

INBD C
VIEW LOOKING FWD

NOTE:
01 CHECK THE PLAIN BUSH AXIAL MIGRATION.
02 CHECK THE FLANGED BUSH AXIAL LOOSE.
03 CHECK THE WEAR MARKS UNDERNEATH BOLT HEAD.
ICN-A320-A-53XX1325-A-FAPE3-026Y4-A-004-01

Figure ICN-A320-A-53XX1325-A-FAPE3-026Y4-A-004-01 Fig.BI Sol.AA SHEET 2/2

REV 00 Apr 29/16 Check of the Plain Bush Migration, Flanged A320-53-1325
REV 04 Nov 07/23 Bush Axial loose and Wear Marks LH Side Page 84
A318/A319/A320/A321
SERVICE BULLETIN

(2) Task A320-A-53-XX-1325-01001-920A-A (A320-A-53-XX-1325-01ZZZ-920Z-A)

Depending on the Inspection Results, Replace the MLG Door Actuator Fitting
on Aircraft, on LH side
Job Set-Up Information
Working Area

Impacted Zone Access / Work Location

147 Access Door 734
Manpower/Resources/Skills

Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Skills Airframe

Referenced Information

Manuals/Drawings References/Sheets
AMM 06-20-00, Page Block 001
R53370501 all sheets
Procedure
(a) Standard Practices given this procedure:
1 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
(b) Replace the actuator fitting in accordance with RI Ref. R53370501 all sheets.

NOTE: LH and RH procedures are independent from each other. If cracks/

damages are found on one side only, the corrective actions on the other
side are not necessary.

(3) Task A320-A-53-XX-1325-03001-920A-A (A320-A-53-XX-1325-03ZZZ-920Z-A)

Depending on the Inspection Results, Repair the Plain Bush Migration on LH
side
Job Set-Up Information
Working Area

Impacted Zone Access / Work Location

147 Access Door 734
Manpower/Resources/Skills

Man-hours 1.00 h
Minimum Number of person 1
Elapsed Time 1.00 h
Skills Airframe
Material necessary to do the job

Tool kit 531325T02R00

ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
98D53308001000 1 KIT (1)

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A318/A319/A320/A321
SERVICE BULLETIN

Tool kit 531325T02R00

ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
NOTE(S)
(1): For the installation of an oversize bush it is necessary to use the tool PN
98D53308001000 listed in the repair instruction R53370502

Components
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
R5307111620000 1 BUSH (1)
R5307111620200 1 BUSH (1)
NOTE(S)
(1): The components listed above are only necessary if the Repair Instruction R53370502
is applied. The quantity of these items are to be ordered as required.
Referenced Information

Manuals/Drawings References/Sheets
AMM 06-20-00, Page Block 001
R53370502 all sheets
Procedure
(a) Standard Practices given this procedure:
1 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
(b) Replace the plain bush of the LH side actuator in accordance with RI Ref.
R53370502 all sheets.

If necessary, use:

1 BUSH R5307111620000
or

1 BUSH R5307111620200
Use:

1 KIT LUG REPAIR 98D53308001000

REAMER

NOTE: LH and RH procedures are independent from each other, findings

detected only on one side do not trigger corrective actions on the other
side.

(4) Task A320-A-53-XX-1325-01001-690A-A (A320-A-53-XX-1325-01ZZZ-690Z-A)

Depending on the Inspection Results, Repair the Flanged Bush Axial Loose
on LH side
Job Set-Up Information
Working Area

Impacted Zone Access / Work Location

147 Access Door 734
Manpower/Resources/Skills

Man-hours 1.00 h

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A318/A319/A320/A321
SERVICE BULLETIN

Minimum Number of person 1

Elapsed Time 1.00 h
Material necessary to do the job

Tool kit 531325T03R00

ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
98D53308002000 1 KIT (1)
NOTE(S)
(1): For the installation of a loose flanged bush it is necessary to use the tool PN
98D53308002000 listed in the repair instruction R53370510

Components
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
R5307111620400 1 BUSH (1)
R5307111620600 1 BUSH (1)
NOTE(S)
(1): The components listed above are only necessary if the Repair Instruction R53370510
is applied. The quantity of these items are to be ordered as required.
Referenced Information

Manuals/Drawings References/Sheets
AMM 06-20-00, Page Block 001
R53370510 all sheets
Procedure
(a) Standard Practices given this procedure:
1 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
(b) Repair the flanged bush of the LH side actuator in accordance with RI Ref.
R53370510 all sheets.

If necessary, use:

1 BUSH R5307111620400
or

1 BUSH R5307111620600
Use:

1 KIT LUG REPAIR 98D53308002000

REAMER

NOTE: LH and RH procedures are independent from each other, findings

detected only on one side do not trigger corrective actions on the other
side.

(5) Task A320-A-53-XX-1325-03001-690A-A (A320-A-53-XX-1325-03ZZZ-690Z-A)

Depending on the Inspection Results, Repair the Wear Marks Underneath
the Bolt Head on LH side

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A318/A319/A320/A321
SERVICE BULLETIN

Job Set-Up Information

Working Area

Impacted Zone Access / Work Location

147 Access Door 734
Manpower/Resources/Skills

Man-hours 0.25 h
Minimum Number of person 1
Elapsed Time 0.25 h

Referenced Information

Manuals/Drawings References/Sheets
AMM 06-20-00, Page Block 001
R53370506 all sheets
Procedure
(a) Standard Practices given this procedure:
1 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
(b) Repair the wear marks underneath bolt head in accordance with RI Ref.
R53370506 all sheets.

NOTE: LH and RH procedures are independent from each other, findings

detected only on one side do not trigger corrective actions on the other
side.

(6) Task A320-A-53-XX-1325-05001-690A-A (A320-A-53-XX-1325-05ZZZ-690Z-A)

Depending on the Inspection Results, Repair the Other Damages on LH side
Job Set-Up Information
Working Area

Impacted Zone Access / Work Location

147 Access Door 734
Manpower/Resources/Skills

Man-hours 1.00 h
Minimum Number of person 1
Elapsed Time 1.00 h
Skills Airframe

Referenced Information

Manuals/Drawings References/Sheets
AMM 06-20-00, Page Block 001
51-10-04
NTM
51-10-08
SRM 51-73-00
Procedure

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REV 04 Nov 07/23 Page 88
A318/A319/A320/A321
SERVICE BULLETIN

(a) Standard Practices given in this procedure:

1 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
(b) Do a blend out in accordance with Ref. SRM 51-73-00.
(c) Do an HFEC inspection in accordance with Ref. NTM 51-10-08.
(d) Measure the remaining thickness in accordance with Ref. NTM 51-10-04.

NOTE: LH and RH procedures are independent from each other, findings

detected only on one side do not trigger corrective actions on the other
side.

(7) Task A320-A-53-XX-1325-02001-300A-A (A320-A-53-XX-1325-02ZZZ-300Z-A)

Do an SDI of the Keel Beam MLG Door Actuator Fitting on Aircraft, on Right
Hand (RH) side
Job Set-Up Information
Working Area

Impacted Zone Access / Work Location

148 Access Door 744
Manpower/Resources/Skills

Man-hours 3.50 h
Minimum Number of person 1
Elapsed Time 3.50 h
Skills Non-Destructive Testing
Material necessary to do the job

Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
Non Aqueous Cleaner-
08BAA9
General
14SBA1 Textile-Lint free-Cotton
Referenced Information

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REV 04 Nov 07/23 Page 89
A318/A319/A320/A321
SERVICE BULLETIN

(a) Standard Practices given this procedure:

1 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
2 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
3 Repair the paint coating in accordance with Ref. SRM 51-75-12.
(b) At the threshold given in the PLANNING INFORMATION paragraph 1.E.(2):
Refer to Ref. Fig.FB Inspection Flowchart.
1 Remove the sealant and clean the inspection area with:

Non Aqueous Cleaner- 08BAA9

General

Textile-Lint free-Cotton 14SBA1

2 Do an HFEC and ultrasonic inspection on the keel beam actuator fittings on
RH side for crack(s), in accordance with Ref. NTM 53-31-54.

NOTE: It is not necessary to remove MLG door and not necessary to

disconnect hydraulic pipes from MLG door actuator to do the HFEC
and ultrasonic inspection.

Refer to Ref. Fig.BE Inspection Area RH Side.

a If crack is found:
<1> Do the replacement of the MLG door actuator fitting in
accordance with Ref. Task A320-A-53-XX-1325-02ZZZ-920Z-A.
<2> Send the completed Inspection Report sheet in accordance with
Ref. ISI 00.00.00179 and refer to Ref. Fig.RB Inspection Report
Sheet.

NOTE: To send the Inspection Report sheet is not Required for

Compliance (RC).

<3> Repeat the inspection in accordance with Ref. Task set A320-A-
53-XX-1325-01ZZZ-93BZ-A, at the repetitive interval given in
the PLANNING INFORMATION paragraph 1.E.(2).

OR
<4> Send the completed Inspection Report sheet in accordance with
Ref. ISI 00.00.00179 and refer to Ref. Fig.RB Inspection Report
Sheet.

NOTE: To send the Inspection Report sheet is not Required for

Compliance (RC).

<5> Accomplish the MSB No. Ref. SB A320-53-1503.

<6> No further action for this Service Bulletin.

OR
<7> Contact AIRBUS and follow their instructions at the threshold
given in the PLANNING INFORMATION paragraph 1.E.(2).
b If no crack is found:
<1> Accomplish the MSB No. Ref. SB A320-53-1503.

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REV 04 Nov 07/23 Page 90
A318/A319/A320/A321
SERVICE BULLETIN

<2> No further action for this Service Bulletin.

OR
<3> Do a DET for plain bush axial migration on the actuator fitting,
refer to Ref. Fig.BF Check of the Plain Bush Migration, Flanged
Bush Axial loose and Wear Marks RH Side.
<a> If the plain bush axial migration is found to be more than
0.80 mm (0.032 in.):

NOTE: Do not apply a repair before completing the

4 inspections, check if the repair is possible
following the criteria included in the 3 RIs
(R53370502; R53370506; R53370510).

Check according to RI Ref. R53370502 all sheets if the

damage can be repaired within its limits.
[1] If the damage can be repaired within its limits
according to RI Ref. R53370502 all sheets:
[a] Do the repair in accordance with Ref. Task
A320-A-53-XX-1325-04ZZZ-920Z-A.
[b] If the damage is eliminated:
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).
- Repeat the inspection in accordance with
Ref. Task set A320-A-53-XX-1325-01ZZZ-
93BZ-A, at the repetitive interval given in
the PLANNING INFORMATION paragraph
1.E.(2).
[c] If the damage is not eliminated:
- Contact AIRBUS and follow their
instructions at the threshold given in the
PLANNING INFORMATION paragraph 1.E.
(2).
OR
- Do the replacement of the MLG door
actuator fitting in accordance with Ref.
Task A320-A-53-XX-1325-02ZZZ-920Z-A.
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 91
A318/A319/A320/A321
SERVICE BULLETIN

- Repeat the inspection in accordance with

NOTE: To send the Inspection Report

OR
[b] Do the replacement of the MLG door actuator
fitting in accordance with Ref. Task A320-A-53-
XX-1325-02ZZZ-920Z-A.
[c] Send the completed Inspection Report sheet in
accordance with Ref. ISI 00.00.00179 and refer
to Ref. Fig.RB Inspection Report Sheet.

NOTE: To send the Inspection Report sheet is

not Required for Compliance (RC).

[d] Repeat the inspection in accordance with Ref.

Task set A320-A-53-XX-1325-01ZZZ-93BZ-A, at
the repetitive interval given in the PLANNING
INFORMATION paragraph 1.E.(2).

OR
[e] Send the completed Inspection Report sheet in
accordance with Ref. ISI 00.00.00179 and refer
to Ref. Fig.RB Inspection Report Sheet.

NOTE: To send the Inspection Report sheet is

not Required for Compliance (RC).

[f] Accomplish the MSB No. Ref. SB A320-53-1503.

[g] No further action for this Service Bulletin.
 If plain bush axial migration is not found or plain bush
axial migration is less than 0.80 mm (0.032 in.):

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 92
A318/A319/A320/A321
SERVICE BULLETIN

[1] Send the completed Inspection Report sheet in

accordance with Ref. ISI 00.00.00179 and refer to
Ref. Fig.RB Inspection Report Sheet.

NOTE: To send the Inspection Report sheet is not

Required for Compliance (RC).

[2] Repeat the inspection in accordance with Ref.

Task set A320-A-53-XX-1325-01ZZZ-93BZ-A, at
the repetitive interval given in the PLANNING
INFORMATION paragraph 1.E.(2).
<4> Do a DET for flanged bush axial loose on the actuator fitting,
refer to Ref. Fig.BF Check of the Plain Bush Migration, Flanged
Bush Axial loose and Wear Marks RH Side.
<a> If loose flanged bush is found:

NOTE: Do not apply a repair before completing the

4 inspections, check if the repair is possible
following the criteria included in the 3 RIs
(R53370502; R53370506; R53370510).

Check according to RI Ref. R53370510 all sheets if the

damage can be repaired within its limits.
[1] If the damage can be repaired within its limits
according to RI Ref. R53370510 all sheets:
[a] Do the repair in accordance with Ref. Task
A320-A-53-XX-1325-02ZZZ-690Z-A.
[b] If the damage is eliminated:
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).
- Repeat the inspection in accordance with
Ref. Task set A320-A-53-XX-1325-01ZZZ-
93BZ-A, at the repetitive interval given in
the PLANNING INFORMATION paragraph
1.E.(2).
[c] If the damage is not eliminated:
- Contact AIRBUS and follow their
instructions at the threshold given in the
PLANNING INFORMATION paragraph 1.E.
(2).
OR
- Do the replacement of the MLG door
actuator fitting in accordance with Ref.
Task A320-A-53-XX-1325-02ZZZ-920Z-A.
- Send the completed Inspection Report
sheet in accordance with Ref. ISI

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 93
A318/A319/A320/A321
SERVICE BULLETIN

00.00.00179 and refer to Ref. Fig.RB

Inspection Report Sheet.

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).
- Repeat the inspection in accordance with
Ref. Task set A320-A-53-XX-1325-01ZZZ-
93BZ-A, at the repetitive interval given in
the PLANNING INFORMATION paragraph
1.E.(2).
OR
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).
- Accomplish the MSB No. Ref. SB A320-53-
1503.
- No further action for this Service Bulletin.
[2] If the damage cannot be repaired within its limit
according to RI Ref. R53370510 all sheets:
[a] Contact AIRBUS and follow their instructions
at the threshold given in the PLANNING
INFORMATION paragraph 1.E.(2).

NOTE: To send the Inspection Report sheet is

not Required for Compliance (RC).

[d] Repeat the inspection in accordance with Ref.

[f] Accomplish the MSB No. Ref. SB A320-53-1503.

NOTE: To send the Inspection Report sheet is not

Required for Compliance (RC).

[2] Repeat the inspection in accordance with Ref.

[b] Do the replacement of the MLG door actuator

fitting in accordance with Ref. Task A320-A-53-
XX-1325-02ZZZ-920Z-A.
[c] Send the completed Inspection Report sheet in
accordance with Ref. ISI 00.00.00179 and refer
to Ref. Fig.RB Inspection Report Sheet.

NOTE: To send the Inspection Report sheet is

not Required for Compliance (RC).

[d] Repeat the inspection in accordance with Ref.

Task set A320-A-53-XX-1325-01ZZZ-93BZ-A, at
the repetitive interval given in the PLANNING
INFORMATION paragraph 1.E.(2).

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 97
A318/A319/A320/A321
SERVICE BULLETIN

[e] Send the completed Inspection Report sheet in

accordance with Ref. ISI 00.00.00179 and refer
to Ref. Fig.RB Inspection Report Sheet.

NOTE: To send the Inspection Report sheet is

not Required for Compliance (RC).

[f] Accomplish the MSB No. Ref. SB A320-53-1503.

[g] No further action for this Service Bulletin.
[2] If damage can be repaired:
[a] Do a repair for other damages found on RH
side in accordance with Ref. Task A320-A-53-
XX-1325-06ZZZ-690Z-A.
[b] If the part thickness remains within the
tolerance of the negligible damage in
accordance with Ref. SRM 51-73-11 and there
are no findings after HFEC inspection:
- Restore the surface protection in
accordance with Ref. SRM 51-75-12.
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).
- Repeat the inspection in accordance with
Ref. Task set A320-A-53-XX-1325-01ZZZ-
93BZ-A, at the repetitive interval given in
the PLANNING INFORMATION paragraph
1.E.(2).
[c] If the part thickness is outside the tolerance of
the negligible damage in accordance with Ref.
SRM 51-73-11 or there are findings after HFEC
inspection:
- Contact AIRBUS and follow their
instructions at the threshold given in the
PLANNING INFORMATION paragraph 1.E.
(2).
OR
- Do the replacement of the MLG door
actuator fitting in accordance with Ref.
Task A320-A-53-XX-1325-02ZZZ-920Z-A.
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 98
A318/A319/A320/A321
SERVICE BULLETIN

NOTE: To send the Inspection Report

sheet is not Required for Compliance
(RC).
- Repeat the inspection in accordance with
Ref. Task set A320-A-53-XX-1325-01ZZZ-
93BZ-A, at the repetitive interval given in
the PLANNING INFORMATION paragraph
1.E.(2).
OR
- Send the completed Inspection Report
sheet in accordance with Ref. ISI
00.00.00179 and refer to Ref. Fig.RB
Inspection Report Sheet.

NOTE: To send the Inspection Report

NOTE: To send the Inspection Report sheet is not

Required for Compliance (RC).

[2] Repeat the inspection in accordance with Ref.

Task set A320-A-53-XX-1325-01ZZZ-93BZ-A, at
the repetitive interval given in the PLANNING
INFORMATION paragraph 1.E.(2).
3 Renew the protective finish in accordance with Ref. SRM 51-75-12.

REV 00 Apr 29/16 A320-53-1325

REV 04 Nov 07/23 Page 99
A318/A319/A320/A321
SERVICE BULLETIN

ACCOMPLISH THE MODIFICATION

IS THERE ANY
SERVICE BULLETIN No A320-53-1503 OR NO YES
CRACK FOUND?
01
CAN
DAMAGE BE
REPAIRED IN ACCORDANCE NO
AND WITH SRM 51-73-00?

YES

IS LOOSE FLANGED YES IS OTHER DAMAGE

YES

RESTORE THE SURFACE PROTECTION

REPEAT THE SEND THE COMPLETED INSPECTION IN ACCORDANCE WITH SRM 51-75-12
INSPECTION 01 REPORT SHEET TO AIRBUS 01 B 01

Figure ICN-A320-A-53XX1325-A-FAPE3-026Y1-A-008-01 Fig.FB Sol.AA SHEET 1/3

REV 00 Apr 29/16 A320-53-1325
Inspection Flowchart
REV 04 Nov 07/23 Page 100
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

D C

CONTACT AIRBUS SEND THE COMPLETED INSPECTION REPLACE THE ACTUATOR

AND FOLLOW THEIR REPORT SHEET TO AIRBUS FITTING IN ACCORDANCE
INSTRUCTIONS WITH RI R53370501 01
01
01

SEND THE COMPLETED

INSPECTION REPORT
ACCOMPLISH THE MODIFICATION SHEET TO AIRBUS 01
SERVICE BULLETIN No A320-53-1503
01

REPEAT THE INSPECTION 01

NO FURTHER ACTION FOR

THIS SERVICE BULLETIN

Figure ICN-A320-A-53XX1325-A-FAPE3-026Y2-A-006-01 Fig.FB Sol.AA SHEET 2/3

REV 00 Apr 29/16 A320-53-1325
Inspection Flowchart
REV 04 Nov 07/23 Page 101
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

ALL THE FOUR INSPECTIONS

COMPLETED 03

CHECK IF DAMAGE(S) CAN BE REPAIRED

ICN-A320-A-53XX1325-A-FAPE3-01V9J-A-006-01

Figure ICN-A320-A-53XX1325-A-FAPE3-01V9J-A-006-01 Fig.RB Sol.AA SHEET 1/5

REV 00 Apr 29/16 A320-53-1325
Inspection Report Sheet
REV 04 Nov 07/23 Page 105
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No : A320-53-1325

ACTUATOR FITTING REPLACED

ICN-A320-A-53XX1325-A-FAPE3-026XK-A-006-01

Figure ICN-A320-A-53XX1325-A-FAPE3-026XK-A-006-01 Fig.RB Sol.AA SHEET 2/5

REV 00 Apr 29/16 A320-53-1325
Inspection Report Sheet
REV 04 Nov 07/23 Page 106
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No : A320-53-1325

ACTUATOR FITTING REPLACED

REMARKS:

ICN-A320-A-53XX1325-A-FAPE3-02FTI-A-003-01

Figure ICN-A320-A-53XX1325-A-FAPE3-02FTI-A-003-01 Fig.RB Sol.AA SHEET 3/5

REV 00 Apr 29/16 A320-53-1325
Inspection Report Sheet
REV 04 Nov 07/23 Page 107
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No : A320-53-1325

RESULTS FOLLOW-UP ACTIONS

NO PLAIN BUSH AXIAL MIGRATION

REPORTED TO AIRBUS
FOUND

REMARKS:

RESULTS FOLLOW-UP ACTIONS

NO LOOSE FLANGED BUSH FOUND REPORTED TO AIRBUS

REMARKS:

ICN-A320-A-53XX1325-A-FAPE3-02FTJ-A-003-01

Figure ICN-A320-A-53XX1325-A-FAPE3-02FTJ-A-003-01 Fig.RB Sol.AA SHEET 4/5

REV 00 Apr 29/16 A320-53-1325
Inspection Report Sheet
REV 04 Nov 07/23 Page 108
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No : A320-53-1325

RESULTS FOLLOW-UP ACTIONS

ACTUATOR FITTING REPLACED

ACCOMPLISH MSB No A320-53-1503

WEAR MARKS NOT FOUND REPORTED TO AIRBUS

REMARKS:

INSPECTION RESULTS FOLLOW-UP ACTIONS

ICN-A320-A-53XX1325-A-FAPE3-02PIG-A-001-01

Figure ICN-A320-A-53XX1325-A-FAPE3-02PIG-A-001-01 Fig.RB Sol.AA SHEET 5/5

REV 00 Apr 29/16 A320-53-1325
Inspection Report Sheet
REV 04 Nov 07/23 Page 109
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

Z190

FR34

FR50

A B

ICN-A320-A-53XX1325-A-FAPE3-02129-A-005-01

Figure ICN-A320-A-53XX1325-A-FAPE3-02129-A-005-01 Fig.BF Sol.AA SHEET 1/2

REV 00 Apr 29/16 Check of the Plain Bush Migration, Flanged A320-53-1325
REV 04 Nov 07/23 Bush Axial loose and Wear Marks RH Side Page 110
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

AFT
ACTUATOR
FITTING

FLANGED
02
BUSH
PLAIN
BUSH

FWD
ACTUATOR
FITTING

FWD A A

INBD C
VIEW LOOKING FWD

NOTE:
01 CHECK THE PLAIN BUSH AXIAL MIGRATION.
02 CHECK THE FLANGED BUSH AXIAL LOOSE.
03 CHECK THE WEAR MARKS UNDERNEATH BOLT HEAD.
ICN-A320-A-53XX1325-A-FAPE3-026XM-A-004-01

Figure ICN-A320-A-53XX1325-A-FAPE3-026XM-A-004-01 Fig.BF Sol.AA SHEET 2/2

REV 00 Apr 29/16 Check of the Plain Bush Migration, Flanged A320-53-1325
REV 04 Nov 07/23 Bush Axial loose and Wear Marks RH Side Page 111
A318/A319/A320/A321
SERVICE BULLETIN

(8) Task A320-A-53-XX-1325-02001-920A-A (A320-A-53-XX-1325-02ZZZ-920Z-A)

Depending on the Inspection Results, Replace the MLG Door Actuator Fitting
on Aircraft, on RH side
Job Set-Up Information
Working Area

Impacted Zone Access / Work Location

148 Access Door 744
Manpower/Resources/Skills

Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Skills Airframe

Referenced Information

NOTE: LH and RH procedures are independent from each other. If cracks/

damages are found on one side only, the corrective actions on the other
side are not necessary.

(9) Task A320-A-53-XX-1325-04001-920A-A (A320-A-53-XX-1325-04ZZZ-920Z-A)

Depending on the Inspection Results, Repair the Plain Bush Migration on RH
side
Job Set-Up Information
Working Area

Impacted Zone Access / Work Location

148 Access Door 744
Manpower/Resources/Skills

Man-hours 1.00 h
Minimum Number of person 1
Elapsed Time 1.00 h
Skills Airframe
Material necessary to do the job

Tool kit 531325T02R00

ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
98D53308001000 1 KIT (1)

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A318/A319/A320/A321
SERVICE BULLETIN

Tool kit 531325T02R00

ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
NOTE(S)
(1): For the installation of an oversize bush it is necessary to use the tool PN
98D53308001000 listed in the repair instruction R53370502

Manuals/Drawings References/Sheets
AMM 06-20-00, Page Block 001
R53370502 all sheets
Procedure
(a) Standard Practices given this procedure:
1 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
(b) Replace the plain bush of the RH side actuator in accordance with RI Ref.
R53370502 all sheets.

If necessary, use:

1 BUSH R5307111620000
or

1 BUSH R5307111620200
Use:

1 KIT LUG REPAIR 98D53308001000

REAMER

NOTE: LH and RH procedures are independent from each other, findings

detected only on one side do not trigger corrective actions on the other
side.

(10) Task A320-A-53-XX-1325-02001-690A-A (A320-A-53-XX-1325-02ZZZ-690Z-A)

Depending on the Inspection Results, Repair the Flanged Bush Axial Loose
on RH side
Job Set-Up Information
Working Area

Impacted Zone Access / Work Location

148 Access Door 744
Manpower/Resources/Skills

Man-hours 1.00 h

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SERVICE BULLETIN

Minimum Number of person 1

Elapsed Time 1.00 h
Material necessary to do the job

Tool kit 531325T03R00

Manuals/Drawings References/Sheets
AMM 06-20-00, Page Block 001
R53370510 all sheets
Procedure
(a) Standard Practices given this procedure:
1 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
(b) Repair the flanged bush of the RH side actuator in accordance with RI Ref.
R53370510 all sheets.

If necessary, use:

1 BUSH R5307111620400
or

1 BUSH R5307111620600
Use,

1 KIT LUG REPAIR 98D53308002000

REAMER

NOTE: LH and RH procedures are independent from each other, findings

detected only on one side do not trigger corrective actions on the other
side.

(11) Task A320-A-53-XX-1325-04001-690A-A (A320-A-53-XX-1325-04ZZZ-690Z-A)

Depending on the Inspection Results, Repair the Wear Marks Underneath
the Bolt Head on RH side

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A318/A319/A320/A321
SERVICE BULLETIN

Job Set-Up Information

Working Area

Impacted Zone Access / Work Location

148 Access Door 744
Manpower/Resources/Skills

Man-hours 0.25 h
Minimum Number of person 1
Elapsed Time 0.25 h

Referenced Information

NOTE: LH and RH procedures are independent from each other, findings

detected only on one side do not trigger corrective actions on the other
side.

(12) Task A320-A-53-XX-1325-06001-690A-A (A320-A-53-XX-1325-06ZZZ-690Z-A)

Depending on the Inspection Results, Repair the Other Damages on RH side
Job Set-Up Information
Working Area

Impacted Zone Access / Work Location

148 Access Door 744
Manpower/Resources/Skills

Man-hours 1.00 h
Minimum Number of person 1
Elapsed Time 1.00 h
Skills Airframe

Referenced Information

Manuals/Drawings References/Sheets
AMM 06-20-00, Page Block 001
51-10-04
NTM
51-10-08
SRM 51-73-00
Procedure

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REV 04 Nov 07/23 Page 115
A318/A319/A320/A321
SERVICE BULLETIN

(a) Standard Practices given in this procedure:

NOTE: LH and RH procedures are independent from each other, findings

detected only on one side do not trigger corrective actions on the other
side.

D. PREPARATION FOR TEST

(1) Task A320-A-53-XX-1325-01001-331A-A (A320-A-53-XX-1325-01ZZZ-331Z-A)
Connect the MLG Door Actuator to the Actuator Fitting on LH Side
Job Set-Up Information
Working Area

Impacted Zone Access / Work Location

147 Access Door 734
Manpower/Resources/Skills

Man-hours 0.75 h
Minimum Number of person 1
Elapsed Time 0.75 h
Skills Airframe
Material necessary to do the job

Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
Polysulfide Sealant
06AAB1
Purpose-Fillet
Non Aqueous Cleaner-
08BBH1
Acetone

Part kit 531325D01R02

ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
8 NAS1149C1016R 1 WASHER
9 MS24665-300 1 PIN
Referenced Information

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A318/A319/A320/A321
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Procedure
(a) Standard Practices given this procedure:
1 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
2 For the FR identification, refer to Ref. AMM 06-31-53, Page Block 001.
3 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
4 Remove and install fasteners in accordance with Ref. SRM 51-42-00.
(b) Connect the MLG door actuator on actuator fittings, on the LH side, refer to Ref.
Fig.BD Installation of the MLG Door Actuator LH Side and in accordance with Ref.
SRM 51-24-00 and Ref. AMM Task 32-31-35-400-001.
1 Clean the component with:

Non Aqueous Cleaner- 08BBH1

Acetone
2 Do an inspection of the component interface and/or the adjacent area.
3 Make sure that the parts retained from the removed component are clean
and in the correct condition.
4 Install the upper actuator attachment to the actuator fitting item (4) on LH
side, refer to Ref. Fig.BD Installation of the MLG Door Actuator LH Side

1 BOLT Item (1) Retained

1 NUT Item (7) Retained

1 WASHER Item (6) Retained

1 SPACER Item (5) Retained

NOTE: The head of the bolt (1) must be installed on the same side as
the flanged bush, refer to Ref. Fig.BD Installation of the MLG Door
Actuator LH Side.

Refer to Ref. Fig.BD Installation of the MLG Door Actuator LH Side SHEET
02.
5 Torque the nuts, item (7) to between 2.75 and 5.50 m.daN (20.28 and
40.56 lbft.ft).
6 If the gap A is less than 0.1 mm (0.004 in.), install the actuator with:

1 WASHER NAS1149C1016R Item 8

NOTE: After installing the washer item 8, if the gap is still less than 0.1
mm (0.004 in.), please contact AIRBUS for further support.

7 Install

1 PIN-COTTER MS24665-300 Item 9

8 Lubricate the bearings at each end of the actuating-cylinder, Item (4)
through the lubrication fittings, Item (2), refer to Ref. AMM Task 12-22-32-
640-001.
9 Apply to the head of the bolt, Item (1) and the nut, Item (7).
In accordance with Ref. SRM 51-24-00.

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A318/A319/A320/A321
SERVICE BULLETIN

Polysulfide Sealant 06AAB1

Purpose-Fillet
(c) If disconnected, reconnect the flexible hose assembly, refer to Ref. AMM Task 32-
31-39-400-001.
(d) Remove the safety clip(s) and/or tag(s) and close/unlock the applicable circuit
breaker(s) as specified after the installation of the MLG door actuating-cylinder,
refer to Ref. AMM Task 32-31-35-400-001.
(e) Remove the access platform(s) from the work area Door 734 LH MLG.

REV 00 Apr 29/16 A320-53-1325

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A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

Z190

FR34

B FR50

A C

ICN-A320-A-53XX1325-A-FAPE3-01VKY-A-002-01

Figure ICN-A320-A-53XX1325-A-FAPE3-01VKY-A-002-01 Fig.BD Sol.AA SHEET 1/2

REV 00 Apr 29/16 A320-53-1325
Installation of the MLG Door Actuator LH Side
REV 04 Nov 07/23 Page 119
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

(1) 01

(2)

C (5)
(6) (4)
(7)
FWD
ACTUATOR
(A) FITTING
02

FLANGED
WASHER BUSH

AFT
ACTUATOR
BUSH FITTING

SPACER
ADDITIONAL
WASHER
DOOR ACTUATOR
FWD A A
NOTE:
01 THE BOLT, ITEM (1), MUST BE INSTALLED FROM AFT ACTUATOR FITTING WITH FLANGED BUSH.
02 GAP (A) TO BE MEASURED BETWEEN WASHER AND ACTUATOR FITTING.
ICN-A320-A-53XX1325-A-FAPE3-01VKZ-A-004-01

Figure ICN-A320-A-53XX1325-A-FAPE3-01VKZ-A-004-01 Fig.BD Sol.AA SHEET 2/2

REV 00 Apr 29/16 A320-53-1325
Installation of the MLG Door Actuator LH Side
REV 04 Nov 07/23 Page 120
A318/A319/A320/A321
SERVICE BULLETIN

(2) Task A320-A-53-XX-1325-02001-331A-A (A320-A-53-XX-1325-02ZZZ-331Z-A)

Connect the MLG Door Actuator to the Actuator Fitting on RH Side
Job Set-Up Information
Working Area

Impacted Zone Access / Work Location

148 Access Door 744
Manpower/Resources/Skills

Man-hours 0.75 h
Minimum Number of person 1
Elapsed Time 0.75 h
Skills Airframe
Material necessary to do the job

Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
Polysulfide Sealant
06AAB1
Purpose-Fillet
Non Aqueous Cleaner-
08BBH1
Acetone

Part kit 531325D01R02

ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
8 NAS1149C1016R 1 WASHER
9 MS24665-300 1 PIN
Referenced Information

Manuals/Drawings References/Sheets
06-20-00, Page Block 001
06-31-53, Page Block 001
AMM Task 12-22-32-640-001
Task 32-31-35-400-001
Task 32-31-39-400-001
CML CONSUMABLE MATERIAL LIST (CML)
51-24-00
SRM
51-42-00
Procedure
(a) Standard Practices given this procedure:
1 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
2 For the FR identification, refer to Ref. AMM 06-31-53, Page Block 001.
3 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
4 Remove and install fasteners in accordance with Ref. SRM 51-42-00.
(b) Connect the MLG door actuator on actuator fittings, on the RH side, refer to Ref.
Fig.BH Installation of the MLG Door Actuator RH Side and in accordance with Ref.
SRM 51-24-00 and Ref. AMM Task 32-31-35-400-001.

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SERVICE BULLETIN

1 Clean the component with:

Non Aqueous Cleaner- 08BBH1

Acetone
2 Do an inspection of the component interface and/or the adjacent area.
3 Make sure that the parts retained from the removed component are clean
and in the correct condition.
4 Install the upper actuator attachment to the actuator fitting Item (4) on RH
side, refer to Ref. Fig.BH Installation of the MLG Door Actuator RH Side.

1 BOLT Item (1) Retained

1 NUT Item (7) Retained

1 WASHER Item (6) Retained

1 SPACER Item (5) Retained

NOTE: The head of the bolt (1) must be installed on the same side as
the flanged bush, refer to Ref. Fig.BH Installation of the MLG Door
Actuator RH Side.

Refer to Ref. Fig.BH Installation of the MLG Door Actuator RH Side Sheet 02.
5 Torque the nuts, item (7) to between 2.75 and 5.50 m.daN (20.28 and
40.56 lbft.ft).
6 If the gap A is less than 0.1 mm (0.004 in.), install the actuator with:

1 WASHER NAS1149C1016R Item 8

NOTE: After installing the washer item 8, if the gap is still less than 0.1
mm (0.004 in.), please contact AIRBUS for further support.

7 Install

1 PIN-COTTER MS24665-300 Item 9

Polysulfide Sealant 06AAB1

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A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

Z190
FR34

FR50
B

C A

A
A

B
ICN-A320-A-53XX1325-A-FAPE3-02126-A-001-01

Figure ICN-A320-A-53XX1325-A-FAPE3-02126-A-001-01 Fig.BH Sol.AA SHEET 1/2

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Installation of the MLG Door Actuator RH Side
REV 04 Nov 07/23 Page 123
A318/A319/A320/A321
SERVICE BULLETIN

CONF ALL

(9)
(6)
(5)

(7)
(8)
(2)

(4) 01 (1) AFT

(A) ACTUATOR
02 FITTING

C
FLANGED
WASHER
BUSH

BUSH

FWD
SPACER ACTUATOR
ADDITIONAL FITTING
WASHER DOOR ACTUATOR

FWD A A
NOTE:
01 THE BOLT, ITEM (1), MUST BE INSTALLED FROM FWD ACTUATOR FITTING WITH FLANGED BUSH.
02 GAP (A) TO BE MEASURED BETWEEN WASHER AND ACTUATOR FITTING.
ICN-A320-A-53XX1325-A-FAPE3-0212J-A-003-01

Figure ICN-A320-A-53XX1325-A-FAPE3-0212J-A-003-01 Fig.BH Sol.AA SHEET 2/2

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Installation of the MLG Door Actuator RH Side
REV 04 Nov 07/23 Page 124
A318/A319/A320/A321
SERVICE BULLETIN

E. TEST
(1) Task A320-A-53-XX-1325-02001-390A-A (A320-A-53-XX-1325-02ZZZ-390Z-A)
Test of the MLG Door
Job Set-Up Information
Manpower/Resources/Skills

Man-hours 2.00 h
Minimum Number of person 2
Elapsed Time 1.00 h
Skills Airframe

Referenced Information

Manuals/Drawings References/Sheets
Task 32-12-00-010-001
Task 32-12-00-410-001
AMM
Task 32-31-00-710-002
Task 32-31-39-400-001
R53370501 all sheets
Procedure
(a) If the hydraulic line is disconnected and/or if the RI Ref. R53370501 all sheets is
applied, do the operational test of the MLG doors, refer to Ref. AMM Task 32-31-
00-710-002.
(b) If the hydraulic line is not disconnected and/or if the RI Ref. R53370501 all
sheets is not applied, do the opening and closing procedure of the MLG doors,
refer to Ref. AMM Task 32-12-00-010-001 and Ref. AMM Task 32-12-00-410-001.
(c) If flexible hoses have been disconnected, do the test as specified after the
reconnection of the flexible hose assembly, refer to Ref. AMM Task 32-31-39-400-
001.
F. CLOSE-UP
(1) Task A320-A-53-XX-1325-03001-740A-A (A320-A-53-XX-1325-03ZZZ-740Z-A)
Close-up
Job Set-Up Information
Manpower/Resources/Skills

Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h

Referenced Information

Manuals/Drawings References/Sheets
Task 24-42-00-862-001
AMM
Task 32-12-00-410-001
Procedure
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.

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A318/A319/A320/A321
SERVICE BULLETIN

(b) Make sure that the MLG doors are closed, refer to Ref. AMM Task 32-12-00-410-
001.
(c) Remove the warning notice(s).
(d) Remove the access platform(s).
(e) De-energize the ground service network, refer to Ref. AMM Task 24-42-00-862-
001.
(f) Put the aircraft back to its initial configuration.
G. ADMINISTRATIVE
(1) Task A320-A-53-XX-1325-01001-90AA-A (A320-A-53-XX-1325-01ZZZ-90AZ-A)
Administrative

Procedure
Confirm in the applicable aircraft records that you have completed all the work defined
in this Service Bulletin task set as required.

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A318/A319/A320/A321
SERVICE BULLETIN
APPENDIX
APPENDIX
A. MANPOWER GANTT CHART
Manpower Gantt Chart
For an explanation of the man-hours and elapsed time, refer to the next page.

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A318/A319/A320/A321
SERVICE BULLETIN
APPENDIX
CONF ALL
01
ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320-53-1325
02

STEPS MH PER ET/S

GET ACCESS 0.50 1 0.50

DISCONNECT THE MLG DOOR ACTUATOR FROM 0.25 1 0.25

ACTUATOR FITTING ON LH SIDE

DISCONNECT THE MLG DOOR ACTUATOR FROM 0.25 1 0.25

ACTUATOR FITTING ON RH SIDE

DO A SPECIAL DETAILED INSPECTION OF THE KEEL 3.50 1 3.50

BEAM MLG DOOR ACTUATOR FITTING ON A\C WITH
TWIN WHEEL UNDERCARRIAGE ON LH SIDE
DO A SPECIAL DETAILED INSPECTION OF THE KEEL 3.50 1 3.50
BEAM MLG DOOR ACTUATOR FITTING ON A\C WITH
TWIN WHEEL UNDERCARRIAGE ON RH SIDE
CONNECT THE MLG DOOR ACTUATOR TO THE 0.75 1 0.75
ACTUATOR FITTING ON LH SIDE

CONNECT THE MLG DOOR ACTUATOR TO THE 0.75 1 0.75

ACTUATOR FITTING ON RH SIDE

TEST OF THE MLG DOOR 2.00 2 1.00

CLOSE-UP 0.50 1 0.50

0 1 2 3 4 5 6 7

TOTAL MANHOURS 12.00 SB ELAPSED TIME

SB ELAPSED TIME 6.50 (HOURS)

NOTE:
01 THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT
MH : MANHOURS ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM.
PER : NUMBER OF PERSONS 02 IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS
ET/S: ELAPSED TIME PER STEP ARE NOT REFLECTED IN THIS GANTT CHART. ICN-A320-A-53XX1325-A-FAPE3-00X47-A-010-01

Figure ICN-A320-A-53XX1325-A-FAPE3-00X47-A-010-01 Fig.AA Sol.AA SHEET 1/1

REV 00 Apr 29/16 A320-53-1325
Manpower Gantt Chart
REV 04 Nov 07/23 Page 128
A318/A319/A320/A321
SERVICE BULLETIN
APPENDIX
B. REPORTING SHEET

TITLE: FUSELAGE - CENTER FUSELAGE - INSPECT MLG DOOR ACTUATOR

FITTING ON KEEL BEAM (NEO)

MODIFICATION No.: None

(1) SB Reporting status
This Service Bulletin will only be incorporated into affected customized Maintenance
and Flight Operations Products if it is duly reported to Airbus.
(2) GENERAL information
The SB Reporting policy is published in ISI 00.00.00135. This document provides
information regarding: the SB Reporting means and benefits, the update of
customized Maintenance Products and customized Flight Operations Products.
If this Service Bulletin has an operational impact, refer to paragraph "Flight Operations
Products" for further information on the update of affected Flight Operations Products.
(3) SB Reporting procedure
Standard practice to report SB is to use the online reporting application on
AirbusWorld.
Refer to ISI 00.00.00179:

- For complete information on reporting means to Airbus, Question 2 "What are

the standard practices for SB Reporting?"
- If this SB requires previous or simultaneous accomplishment of other SBs,
Question 3 "What about the reporting of prerequisite Service Bulletins?"

NOTE: ISI 00.00.00179 covers all the frequently asked questions about SB Reporting.
It is revised on a regular basis.

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A318/A319/A320/A321
SERVICE BULLETIN
APPENDIX
C. QUALITY PERCEPTION FORM
Use this form to tell us what is your perception of the quality of this Service Bulletin.
The reported data that you provide us will be used to analyse areas of difficulties and to
take corrective action to further improve the quality of our Service Bulletin.
We thank you for the time you have taken in completing this form.

Quality rating of this SB 4 3 2 1

Quality rating of the Accomplishment Instructions 4 3 2 1
Quality rating of the Illustrations 4 3 2 1
Is this SB easy to understand ? Y/N

NOTE: Please rate on a scale of 1 to 4, with 4 being the highest score

If you have difficulties in the accomplishment of this SB please quote below the area(s) and
give a short description of the issue.

Planning Material Instructions

X Applicability X Tooling X Preparation
X Reason X List of Materials X Mod/Inspection
Operator Supplied
X Manpower X Kit content X Test
X References X Re-identification X Close-up
X Publication X Illustrations
X Industry Support

Comments :

Operator : Date :
Name/Title
Please return this form to :
AIRBUS
2, ROND POINT EMILE DEWOITINE
31700 BLAGNAC
FRANCE
Or via your Resident Customer Support Office.

REV 00 Apr 29/16 A320-53-1325

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