# Airbus Service Bulletin A320-52-1170

Copy: SB A320-52-1170 R00 ("SB A320-52-1170 R00"), 52 pages: PDF https://openairdocs.org/files/sha256/64/bb/64bb6aa0e334f136a00e7f0d257a8650ab231c54fb2a2821ff600984ae8ce8bd; text https://openairdocs.org/service-documents/airbus/a320-52-1170/file/64bb6aa0e334.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2017-0478; AD 2017-22-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A320-52-1170
- Latest revision known: A320-52-1170, Revision 01, dated June 14, 2018 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a320-52-1170

## ADs that cite it (2) (OpenAirDocs)

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

- [AD 2018-25-08](https://openairdocs.org/ad/2018-25-08.md), effective Feb 1, 2019: Revision 01
- [AD 2017-22-07](https://openairdocs.org/ad/2017-22-07.md), effective Jan 2, 2018: No revision named

Also cited in [2 proposed ADs](https://openairdocs.org/service-documents/airbus/a320-52-1170/proposed.md).

## Text (52 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2017-0478; AD 2017-22-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

@A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
This summary is for information only and is not approved for modification of the aircraft.
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 52
TITLE: DOORS - CARGO - INTRODUCE COLD WORKING AT THE FRAME OF
FWD/AFT CARGO DOOR
**CONF ALL
MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR
 None
MINOR
 157312K18115
NOTE
: As per EASA IR 21, a minor change is one that has no appreciable effect on the
mass, balance, structural strength, reliability, operational characteristics affecting the
airworthiness of the product. All other changes are major changes.
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
During inspection of the full scale fatigue test, cracks were found on the outer skin and on the
frame forks ends of the FWD and AFT Cargo Compartment Door (CCD). Due to Widespread Fatigue
Damage (WFD) regulation requirements (FAR 26.21), a new Inspection Service Bulletin requested to do
repetitive Special Detailed Inspection (SDI) by rotating probe testing of frame fork at beam 4 with new
compliance time on the FWD and AFT CCD for the aircraft version which are equipped with pre MOD
No. 22948K2807 cargo doors.
This modification introduces oversize and cold working of riveting for all frame forks at FWD and AFT
CCD for the aircraft version which are applicable to pre MOD No. 22948K2807.
The accomplishment of this service Bulletin will ensure structural integrity and improves the fatigue
behaviour of the frame forks up to the extended service goal of 60000 Flight Cycles (FC).
The accomplishment of this Service Bulletin will introduce the compliance with the Widespread Fatigue
Damage new regulation (FAR26.21).
Accomplishment of this Service Bulletin cancels the requirements of the Inspection Service Bulletin No.
A320-52-1171.
The accomplishment of Service Bulletin No. A320-52-1171 cancels the requirement of Service Bulletin
No. A320-52-1032.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
Embodiment of MOD No. 22948K2807 through Service Bulletin No. A320-52-1042 and cold working
MOD No. 157312K18115 through this Service Bulletin cancel the Inspection.
GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE
 MANDATORY (1)
 CANCELS INSPECTION SB
 YES
POTENTIAL AD
 YES
 A/C OPERATION AFFECTED
 NO
RELIABILITY AFFECTED
 NO
 PAX COMFORT AFFECTED
 NO
COST SAVING
 NO
 ETOPS AFFECTED
 NO
STRUCTURAL LIFE EXTN
 NO
 VENDOR SB INVOLVED
 NO
NOTE
 (1)
: Service Bulletin must be accomplished.
MATERIAL PRICE INFORMATION
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 521170D01R05
 2
 480.00
 Nut, Bolt
Component COMPD01
 2
 See SB
 Placard
Standard tool TOOLD01
 1
 See SB
 Durable tooling, Expendable tooling,
Capital tooling
Standard tool TOOLD02
 1
 See SB
 Durable tooling, Expendable tooling,
Capital tooling
EFFECTIVITY
This Service Bulletin is applicable to this (these) operator(s) :
03Q 13Y 29S 31P 31V 40N 41S 47P 61W 66P 69X 73W 76W
81P 82U 83Q 85T 87Q 89Q 98W 98X AAF AAY ACA AFR AHY
AIC AIJ AMU ANA ANR ART ARU ATR AUA AWW AXM AZA AZI
B2V BGH BIE BSX BUC CES CQN CSC CSN DAL DAT DLH DNU
DTR DWI EAA ETD ETJ F2I FCB FIA FRN GBB GCA GHT GMI
GWI HDA HRM I2L IBE IND IRA IRC IRM ISS IZG JAV JBW
KAC KHO KKK KPM LFO LLP MLD MMA MRJ MSR MXA NVD OHY
OLY OZW QSM RYW SAI SDM SFW SGD SNX SOL SVR SWM SWR
TAP TAR TBZ TNA UAL UJX USA VRE WHT WRC
CONCURRENT REQUIREMENTS
None
REFERENCES / REPERCUSSIONS
TFU
 52.31.00.008
OEB
 None
AOT
 None
SIL
 None
ISI
 None
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 3

@A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
OTHER
 None
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
HARD
 NO
SOFT
 NO
OBRM
 NO
MANPOWER
Task 521170-831-848-001: Modification
TOTAL MANHOURS
 23.50
ELAPSED TIME (HOURS)
 11.75
APPENDICES
Appendix 01 - Manpower Gantt Chart
Appendix 02 - Alternative Fasteners for ASNA2657K3 Series
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 4

@A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
**CONF ALL
B
VIEW LOOKING INBOARD
FR24A
FR52A
FR25
FR53
FR25A
FR53A
FR26
FR54
FR26A
FR54A
FR27
FR55
FR27A
FR55A
FR28
FR56
BEAM4
FWD
COLD WORKING AT THE FRAME OF  
FWD AND AFT CARGO COMPARTMENT
DOOR FRAME FORKS AND OUTER SKIN
FR28
FR24A
A
BEAM4
ACCESS PANEL
FR56
FR52A
B
Z825
Z826
A
A
INSTALLATION OF PLACARD ON FRAME OF
FWD AND AFT CARGO COMPARTMENT DOOR
N_SB_521170_6_SAAA_01_01
Figure A-GSAAA - Sheet 01
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 4
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 5

@A318/A319/A320/A321
SERVICE BULLETIN
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 52
TITLE: DOORS - CARGO - INTRODUCE COLD WORKING AT THE FRAME OF
FWD/AFT CARGO DOOR
MODIFICATION No.: 157312K18115
This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the
property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with
any information contained in it. It is delivered on the express condition that said document and the
information contained in it shall be treated as confidential, shall not be used for any purpose other than
that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall
not be duplicated in any manner (except for the purposes of performing the tasks described hereunder
and provided that any recipient of such document shall comply with the conditions herein), without
AIRBUS prior written consent.
1. PLANNING INFORMATION
**CONF ALL
A. EFFECTIVITY
NOTE
: This modification is applicable by Service Bulletin only.
NOTE
: This Service Bulletin is only applicable to aircraft on which MOD No.
22948K2807 (Service Bulletin No. A320-52-1042) is not embodied.
NOTE
: Due to interchangeability, it has to be checked if pre MOD No. 22948K2807
cargo doors installed up to MSN 0758.
(1) Models
319-111 319-112 319-113 319-114 319-131 320-211 320-212 320-214
320-231 320-232 320-233 321-111 321-112 321-131 321-211 321-231
(2) Effectivity by MSN
0029 0045-0046 0049-0057 0059 0064-0073 0076-0078 0081-0087 0093-0094 0099
0104 0110-0113 0115-0119 0121-0127 0135 0137-0138 0140-0142 0148-0150
0152-0154 0157-0162 0164-0166 0168-0169 0171-0175 0178 0181-0183 0185 0192
0194-0195 0197-0198 0200-0203 0205-0211 0213 0216-0220 0224 0229-0232 0234
0237 0239 0242-0244 0248-0249 0251-0256 0259-0260 0262-0263 0265-0269
0272-0273 0275-0277 0279 0281-0282 0284-0285 0287 0289-0298 0300-0303
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 6

@A318/A319/A320/A321
SERVICE BULLETIN
0306-0309 0311-0312 0314 0316-0322 0324-0325 0328-0332 0339-0343 0345-0347
0350-0351 0354-0362 0364 0366-0368 0370-0373 0376 0378 0380-0383 0385-0388
0390 0393 0395 0398-0410 0412 0414-0418 0420-0424 0426-0432 0434-0436
0438-0439 0441-0442 0444-0445 0447-0450 0452 0454 0456-0458 0460 0462-0466
0468 0470 0472-0477 0479-0480 0482-0491 0493 0495-0514 0516-0535 0537-0546
0548-0556 0558-0587 0589 0591-0593 0595-0600 0603-0604 0607-0614 0616-0623
0625 0627 0629-0631 0633-0662 0664-0673 0675-0706 0709 0711-0752 0754-0758
(3) Effectivity by Operator
The Operator/MSN relationship is provided for information only and is correct at the time
of issue in accordance with the information available to AIRBUS. Any future changes
resulting from transfer of an aircraft from one operator to another will not be reflected in
this list unless the Service Bulletin is revised for another reason.
OPERATOR
 MSN
03Q
 0584 0620
13Y
 0371
29S
 0291 0292
31P
 0229
31V
 0164 0293 0332 0420 0436 0565 0579 0591
40N
 0065 0077
41S
 0630
47P
 0619
61W
 0112
66P
 0368
69X
 0219 0300 0328
73W
 0087
76W
 0140 0157
81P
 0308
82U
 0279 0677
83Q
 0477 0495
85T
 0234
87Q
 0052
89Q
 0427 0747
98W
 0434 0441 0516 0524
98X
 0551
AAF
 0639
AAY
 0706 0714 0716 0730 0745
ACA
 0059 0068 0073 0084 0122 0126 0127 0141 0149 0150 0154 0159
0174 0175 0183 0210 0231 0232 0242 0248 0253 0254 0255 0265
0277 0284 0290 0309 0324 0330 0341 0378 0403 0404 0546 0572
0634 0656 0670 0672 0682 0688 0691 0693 0695 0697 0711 0719
0721 0728 0732 0736 0740 0742 0752 0757
AFR
 0115 0237 0239 0285 0287 0498 0509 0521 0529 0544 0598 0600
0608 0618 0625 0637
AHY
 0331
AIC
 0045 0046 0049 0050 0051 0056 0057 0398 0416 0423 0431 0432
0486 0490 0499
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 7

@A318/A319/A320/A321
SERVICE BULLETIN
OPERATOR
 MSN
AIJ
 0169
AMU
 0631
ANA
 0383 0482 0501 0507 0531 0534 0549 0554 0658 0669 0685
ANR
 0671 0726
ART
 0244 0359 0533 0566 0662
ARU
 0573 0582
ATR
 0314 0373 0393
AUA
 0552 0570 0581
AWW
 0597
AXM
 0667 0743
AZA
 0513 0514 0526 0532 0576 0583 0586 0593 0599
AZI
 0527
B2V
 0185
BGH
 0142
BIE
 0519
BSX
 0648 0650
BUC
 0256
CES
 0665 0754
CQN
 0696 0698 0704 0705
CSC
 0540 0556
CSN
 0712 0718 0720 0722
DAL
 0118 0121 0125 0152 0153 0160 0171 0192 0197 0206 0208 0213
0262 0263 0272 0273 0281 0282 0297 0298 0306 0307 0318 0319
0329 0339 0340 0355 0358 0360 0367 0372 0380 0381 0387 0388
0399 0408 0410 0417 0418
DAT
 0466
DLH
 0069 0070 0071 0072 0078 0083 0086 0093 0094 0104 0110 0111
0116 0172 0412 0458 0468 0473 0474 0484 0493 0502 0505 0518
0560 0563 0564 0567 0595 0609 0610 0616 0623 0627 0636 0641
0651 0652 0679 0689 0692 0694 0699 0700 0717 0723 0729 0738
0744
DNU
 0113 0406
DTR
 0444 0447
DWI
 0561
EAA
 0386
ETD
 0350
ETJ
 0325 0428
F2I
 0082 0085 0099 0138 0148 0168 0203 0220 0230 0243 0249 0251
0294 0301 0317 0342 0347 0422 0449 0460 0488 0496 0497 0525
0538 0555 0653 0657 0724 0758
FCB
 0558
FIA
 0295
FRN
 0647 0660
GBB
 0053 0054 0064 0076 0081
GCA
 0415
GHT
 0438
GMI
 0684
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 8

@A318/A319/A320/A321
SERVICE BULLETIN
OPERATOR
 MSN
GWI
 0117 0135 0137 0161 0162 0200 0201 0202 0209 0216 0217 0218
0267 0268 0269 0346 0382 0401 0646 0654
HDA
 0633 0756
HRM
 0642
I2L
 0491 0668
IBE
 0158 0173 0207 0224 0266 0356
IND
 0343
IRA
 0303 0312 0345 0575
IRC
 0354 0414 0480
IRM
 0550
ISS
 0737 0749
IZG
 0376 0395 0400 0407 0430 0476
JAV
 0029 0537
JBW
 0445
KAC
 0181 0182 0195
KHO
 0311 0409 0426 0644
KKK
 0604 0614 0675
KPM
 0357
LFO
 0659
LLP
 0739
MLD
 0622 0741
MMA
 0316
MRJ
 0530
MSR
 0165 0166 0178 0194 0198 0322 0351 0366 0680 0687 0715 0725
MXA
 0252 0259 0260 0275 0276 0296 0320 0321
NVD
 0211 0528 0709
OHY
 0364 0385 0543 0580 0640 0661 0676
OLY
 0517 0535 0666
OZW
 0429
QSM
 0607 0611 0617
RYW
 0569
SAI
 0542
SDM
 0649
SFW
 0734
SGD
 0424
SNX
 0289
SOL
 0302
SVR
 0735
SWM
 0421
SWR
 0520 0522 0541 0545 0553 0559 0562 0574 0577 0578 0585 0596
0603 0612 0621 0635 0643 0664 0673 0681 0701 0703 0713 0727
TAP
 0629 0750 0755
TAR
 0119 0123 0124 0205 0370 0390 0402 0511
TBZ
 0361 0362 0405
TNA
 0731 0746
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 4
6
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### Page 9

@A318/A319/A320/A321
SERVICE BULLETIN
OPERATOR
 MSN
UAL
 0435 0439 0442 0450 0452 0454 0456 0457 0462 0463 0464 0465
0470 0472 0475 0479 0483 0485 0487 0489 0500 0503 0504 0506
0508 0510 0512 0523 0539 0568 0571 0587 0589 0592 0613 0638
0655 0678 0683 0686 0690 0702 0748 0751
UJX
 0733
USA
 0055 0066 0448
VRE
 0067
WHT
 0548
WRC
 0645
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 5
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 10

@A318/A319/A320/A321
SERVICE BULLETIN
(4) Configuration by MSN
MSN
 CONFIGURATION
0029 0045 0046 0049 0050 0051 0052 0053 0054 0055 0056
0057 0059 0064 0065 0066 0067 0068 0069 0070 0071 0072
0073 0076 0077 0078 0081 0082 0083 0084 0085 0086 0087
0093 0094 0099 0104 0110 0111 0112 0113 0115 0116 0117
0118 0119 0121 0122 0123 0124 0125 0126 0127 0135 0137
0138 0140 0141 0142 0148 0149 0150 0152 0153 0154 0157
0158 0159 0160 0161 0162 0164 0165 0166 0168 0169 0171
0172 0173 0174 0175 0178 0181 0182 0183 0185 0192 0194
0195 0197 0198 0200 0201 0202 0203 0205 0206 0207 0208
0209 0210 0211 0213 0216 0217 0218 0219 0220 0224 0229
0230 0231 0232 0234 0237 0239 0242 0243 0244 0248 0249
0251 0252 0253 0254 0255 0256 0259 0260 0262 0263 0265
0266 0267 0268 0269 0272 0273 0275 0276 0277 0279 0281
0282 0284 0285 0287 0289 0290 0291 0292 0293 0294 0295
0296 0297 0298 0300 0301 0302 0303 0306 0307 0308 0309
0311 0312 0314 0316 0317 0318 0319 0320 0321 0322 0324
0325 0328 0329 0330 0331 0332 0339 0340 0341 0342 0343
0345 0346 0347 0350 0351 0354 0355 0356 0357 0358 0359
0360 0361 0362 0364 0366 0367 0368 0370 0371 0372 0373
0376 0378 0380 0381 0382 0383 0385 0386 0387 0388 0390
0393 0395 0398 0399 0400 0401 0402 0403 0404 0405 0406
0407 0408 0409 0410 0412 0414 0415 0416 0417 0418 0420
0421 0422 0423 0424 0426 0427 0428 0429 0430 0431 0432
0434 0435 0436 0438 0439 0441 0442 0444 0445 0447 0448
0449 0450 0452 0454 0456 0457 0458 0460 0462 0463 0464
0465 0466 0468 0470 0472 0473 0474 0475 0476 0477 0479
0480 0482 0483 0484 0485 0486 0487 0488 0489 0490 0491
0493 0495 0496 0497 0498 0499 0500 0501 0502 0503 0504
0505 0506 0507 0508 0509 0510 0511 0512 0513 0514 0516
0517 0518 0519 0520 0521 0522 0523 0524 0525 0526 0527
0528 0529 0530 0531 0532 0533 0534 0535 0537 0538 0539
0540 0541 0542 0543 0544 0545 0546 0548 0549 0550 0551
0552 0553 0554 0555 0556 0558 0559 0560 0561 0562 0563
0564 0565 0566 0567 0568 0569 0570 0571 0572 0573 0574
0575 0576 0577 0578 0579 0580 0581 0582 0583 0584 0585
0586 0587 0589 0591 0592 0593 0595 0596 0597 0598 0599
0600 0603 0604 0607 0608 0609 0610 0611 0612 0613 0614
0616 0617 0618 0619 0620 0621 0622 0623 0625 0627 0629
0630 0631 0633 0634 0635 0636 0637 0638 0639 0640 0641
0642 0643 0644 0645 0646 0647 0648 0649 0650 0651 0652
0653 0654 0655 0656 0657 0658 0659 0660 0661 0662 0664
0665 0666 0667 0668 0669 0670 0671 0672 0673 0675 0676
0677 0678 0679 0680 0681 0682 0683 0684 0685 0686 0687
0688 0689 0690 0691 0692 0693 0694 0695 0696 0697 0698
0699 0700 0701 0702 0703 0704 0705 0706 0709 0711 0712
0713 0714 0715 0716 0717 0718 0719 0720 0721 0722 0723
0724 0725 0726 0727 0728 0729 0730 0731 0732 0733 0734
0735 0736 0737 0738 0739 0740 0741 0742 0743 0744 0745
0746 0747 0748 0749 0750 0751 0752 0754 0755 0756 0757
001
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 6
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 11

@A318/A319/A320/A321
SERVICE BULLETIN
MSN
 CONFIGURATION
0758
 001
(5) Configuration definition
**CONF 001
Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a
standard configuration.
(6) Material Effectivity
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit 521170D01R05
 2
Component COMPD01
 2
Consumable CMLD01
 1
Standard tool TOOLD01
 1
 (1)
Standard tool TOOLD02
 1
 (1)
NOTE
 (1)
: Only one tool kit is necessary to perform cold working, either TOOLD01
or TOOLD02 depending on supplier chosen.
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
During inspection of the full scale fatigue test, cracks were found on the outer skin and
on the frame forks ends of the FWD and AFT Cargo Compartment Door (CCD). Due
to Widespread Fatigue Damage (WFD) regulation requirements (FAR 26.21), a new
Inspection Service Bulletin requested to do repetitive Special Detailed Inspection (SDI)
by rotating probe testing of frame fork at beam 4 with new compliance time on the
FWD and AFT CCD for the aircraft version which are equipped with pre MOD No.
22948K2807 cargo doors.
(2) Objective/Action
This modification introduces oversize and cold working of riveting for all frame forks at
FWD and AFT CCD for the aircraft version which are applicable to pre MOD No.
22948K2807.
(3) Advantages
The accomplishment of this service Bulletin will ensure structural integrity and improves
the fatigue behaviour of the frame forks up to the extended service goal of 60000 Flight
Cycles (FC).
The accomplishment of this Service Bulletin will introduce the compliance with the
Widespread Fatigue Damage new regulation (FAR26.21).
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 7
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 12

@A318/A319/A320/A321
SERVICE BULLETIN
Accomplishment of this Service Bulletin cancels the requirements of the Inspection
Service Bulletin No. A320-52-1171.
The accomplishment of Service Bulletin No. A320-52-1171 cancels the requirement of
Service Bulletin No. A320-52-1032.
(4) Operational/Maintenance Consequences
Embodiment of MOD No. 22948K2807 through Service Bulletin No. A320-52-1042
and cold working MOD No. 157312K18115 through this Service Bulletin cancel the
Inspection.
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
Task 521170-831-848-001: Modification
(1) Identify the Part Numbers of the FWD Cargo Compartment Door
(2) Remove the Fasteners from Frame Fork Ends and the Outer Skin of FWD Cargo
Compartment Door
(3) Inspect the holes in the Frame Fork Ends of FWD Cargo Compartment Door
(4) Oversize and Cold Expand the holes in the Frame Fork Ends and the Outer Skin of
FWD Cargo Compartment Door
(5) Install the Fasteners on the Frame Fork Ends and the Outer Skin of FWD Cargo
Compartment Door
(6) Identify the Part Numbers of the AFT Cargo Compartment Door
(7) Remove the Fasteners from Frame Fork Ends and the Outer Skin of AFT Cargo
Compartment Door
(8) Inspect the holes in the Frame Fork Ends of AFT Cargo Compartment Door
(9) Oversize and Cold Expand the holes in the Frame Fork Ends and the Outer Skin of
AFT Cargo Compartment Door
(10) Install the Fasteners on the Frame Fork Ends and the Outer Skin of AFT Cargo
Compartment Door
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 8
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SERVICE BULLETIN
(2) Accomplishment Timescale
This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness
Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued
to confirm this classification. It is anticipated that the AD will confirm the modification will
be applied before the Structure Modification Point (SMP) of 56300 FC but reference
should be made to the AD for confirmation of the mandated accomplishment timescale.
F. APPROVAL
The technical content of this document is approved under the authority of Design
Organisation Approval No. EASA.21J.031.
If an aircraft listed in the effectivity has a modification or repair embodied that is not of
AIRBUS origin, and which affects the content of this Service Bulletin, the operator is
responsible for obtaining approval by its airworthiness authority for any adaptation necessary
before incorporation of the Service Bulletin.
G. MANPOWER
The manpower estimates given in this Service Bulletin are based on the direct labor cost to
do the work. These estimates assume that the work will be done by experienced personnel,
and may need to be revised upwards to suit operator’s circumstances. The estimates do not
include the time to prepare, plan or inspect the work. Manufacture and procurement of parts
and tools, drying times for paints, sealants, etc., and general administration work are also not
included.
Task 521170-831-848-001: Modification
Get Access
 3.00
On Aircraft
Identify the Part Numbers of the FWD Cargo
Compartment Door
0.25
Remove the Fasteners from Frame Fork Ends and the
Outer Skin of FWD Cargo Compartment Door
1.50
Inspect the holes in the Frame Fork Ends of FWD
Cargo Compartment Door
0.50
Oversize and Cold Expand the holes in the Frame Fork
Ends and the Outer Skin of FWD Cargo Compartment
Door
3.00
Install the Fasteners on the Frame Fork Ends and the
Outer Skin of FWD Cargo Compartment Door
2.50
Identify the Part Numbers of the AFT Cargo
Compartment Door
0.25
Remove the Fasteners from Frame Fork Ends and the
Outer Skin of AFT Cargo Compartment Door
1.50
Inspect the holes in the Frame Fork Ends of AFT
Cargo Compartment Door
0.50
Oversize and Cold Expand the holes in the Frame Fork
Ends and the Outer Skin of AFT Cargo Compartment
Door
3.00
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 9
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Task 521170-831-848-001: Modification
Install the Fasteners on the Frame Fork Ends and the
Outer Skin of AFT Cargo Compartment Door
2.50
Tests
 0.0
Close-Up
 5.00
TOTAL MANHOURS
 23.50
ELAPSED TIME (HOURS)
 11.75
NOTE
: For an explanation of the manhours and elapsed time, refer to the Gantt
Chart, Fig. A-GAAAA
 given in Appendix 01 - Manpower Gantt Chart .
H. WEIGHT AND BALANCE
Not Changed
I. ELECTRICAL LOAD DATA
Not Changed
J. REFERENCES
Aircraft Maintenance Manual (AMM)
 06-20-00 06-31-53 12-34-24
20-21-11 52-31-13 52-31-14
52-32-13 52-32-14 53-31-14
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
Non Destructive Test Manual (NTM)
 51-10-01
Service Bulletin (SB)
 A320-52-1042
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-24-00 51-40-00 51-42-00
51-42-11 51-43-00 51-44-00
51-46-00 51-46-11 51-48-00
51-75-12
K. PUBLICATION AFFECTED
Maintenance Planning Document (MPD)
 523131-01-1
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
M. SPARES
FWD Cargo Door D52371000000
FWD Cargo Door D52371000002
FWD Cargo Door D52371000004
FWD Cargo Door D52371000006
FWD Cargo Door D52371000008
FWD Cargo Door D52371000010
FWD Cargo Door D52371000012
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 10
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FWD Cargo Door D52371000014
FWD Cargo Door D52371000016
FWD Cargo Door D52371000018
FWD Cargo Door D52371000022
AFT Cargo Door D52371900000
AFT Cargo Door D52371900002
AFT Cargo Door D52371900004
AFT Cargo Door D52371900008
AFT Cargo Door D52371900010
AFT Cargo Door D52371900012
AFT Cargo Door D52371900014
AFT Cargo Door D52371900016
AFT Cargo Door D52371900018
AFT Cargo Door D52371900022
The parts listed here must not be installed anymore on aircraft which have accomplished this
Service Bulletin or which have the equivalent production modification embodied.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 11
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SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
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SERVICE BULLETIN
2. MATERIAL INFORMATION
**CONF ALL
A. MATERIAL - PRICE AND AVAILABILITY
(1) Procurement Addresses
Customers with aircraft shown in the effectivity of this Service Bulletin should send a
purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:
Kit 521170D01R05
 AIRBUS Material, Logistics and Suppliers
ATP II B,
Hein-Sass-Weg 24
21129 HAMBURG
GERMANY
For ordering by internet:
http://spares.airbus.com
For ordering by E-mail: airbus.kit@airbus.com
Telephone Hotlines:
A318/319/320/321: +49 40 743 51660
Component COMPD01
 AIRBUS Material, Logistics and Suppliers
IFD - In Flight Desk
Weg beim Jaeger 150
D-22335 HAMBURG
GERMANY
For ordering by internet:
http://spares.airbus.com
For ordering modification kits by fax: +49 40
50 76 4012
For ordering by E-mail:
ifd.spares@airbus.com
(2) Price and Availability
Kit 521170D01R05
Cost
 240.00 USD
Availability
 120 calendar days from receipt of order
The availability given above is the standard lead time from the date of your purchase
order. If items are required before this time, please include a retrofit planning schedule
with your order so that we can try to comply with your requirements.
The sales terms (costs and availability) are estimated in relation to economic conditions.
The latest valid price and lead time for ordering purposes shall be obtained through the
AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
Component COMPD01
No AIRBUS kit will be provided.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 13
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SERVICE BULLETIN
Operator supplied AIRBUS parts required to accomplish this Service Bulletin are to be
purchased by a spares purchase order.
B. INDUSTRY SUPPORT INFORMATION
AIRBUS will not provide industry support for accomplishment of this Service Bulletin.
This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.
For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit
management department.
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
France
T e l :( 3 3 )56 71 90 62 2
E-mail: monitored.retrofit@airbus.com
F a x :( 3 3 )56 19 32 74 5
C. LIST OF COMPONENTS
Kit 521170D01R05
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
8
 ASNA2537-3
 66
 NUT
9
 ASNA2657K3-3
 26
 BOLT
10
 ASNA2657K3-4
 8
 BOLT
11
 ASNA2657K3-5
 18
 BOLT
12
 ASNA2657K3-6
 4
 BOLT
13
 ASNA2657K3-7
 6
 BOLT
14
 ASNA2657K3-8
 4
 BOLT
NOTE
: If you find part numbers of hardware components in the related kit(s) which
you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,
refer to Standards Manual (SM). The SM will give you the correct part number
to part number relationship.
D. LIST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Primer Polyurethane Paint -
Corrosion Inhibiting
04EAC2
 As required
Top Coat Polyurethane External -
Structure
04JAA3
 As required
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 14
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ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Polysulfide Sealant - General
Purpose Interfay
06AAC1
 As required
Corrosion Preventive Compound -
Water Displacing
12ADB1
 As required
(2) Components
Component COMPD01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
15
 D5237125600000
 1
 Placard
(3) Equipment
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
(1) Tooling - Price and Availability
(a) Procurement Addresses
Operators interested in obtaining the FTI tool kit should contact:
Standard tool TOOLD01
 Fatigue Technology Inc.
401 Andover Park East
SEATTLE, WA 98188-7605
USA
Internet: http://www.fatiguetech.com
Phone: (206) 2462010
Fax: (206) 2449886
Operators interested in obtaining the WCI tool kit should contact:
Standard tool TOOLD02
 West Coast Industries Inc.
14900 Whitman Ave. N
Seattle, Washington 98133
Tel: (206) 365-7513
Fax: (206) 365-7483
Email: info@coldwork.com
Europe, Middle-East, Africa, India and
Russia: customer@capaero.com /+33 5 61
92 04 91 (France)
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 15
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(b) Price and Availability
Procurement to be negotiated directly with Fatigue Technology Inc. (FTI) or West
Coast Industries Inc. (WCI).
(2) Tools
Standard tool TOOLD01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA320521170-1
 Durable tooling
 1
 (1)
EKA320521170-1
 Expendable tooling
 1
 (2)
FTIA320521170-1
 Capital tooling
 1
 (3)
NOTE
: FTI has allocated the following tool kit numbers for cold expansion:
For the definition of capital, durable and expendable tools, refer to ISI
51.48.00001.
NOTE
 (1)
: Durable tooling: Ref. DK-A320-52-1170-1
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to ISI
51.48.00001.
NOTE
 (2)
: Expendable tooling: Ref. EK-A320-52-1170-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
NOTE
 (3)
: Capital tooling: Ref. FTI-A320-52-1170-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long-
term investment or can be loaned from FTI.
Standard tool TOOLD02
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA320521170-1
 Durable tooling
 1
 (1)
EKA320521170-1
 Expendable tooling
 1
 (2)
WCIA320521170-1
 Capital tooling
 1
 (3)
NOTE
: WCI has allocated the following tool kit numbers for cold expansion:
For the definition of capital, durable and expendable tools, refer to ISI
51.48.00001.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 16
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NOTE
 (1)
: Durable tooling: Ref. DK-A320-52-1170-1
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to ISI
51.48.00001.
NOTE
 (2)
: Expendable tooling: Ref. EK-A320-52-1170-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
NOTE
 (3)
: Capital tooling: Ref. WCI-A320-52-1170-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long-
term investment or can be loaned from WCI.
(3) Special Tools
None
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 17
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DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
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3. ACCOMPLISHMENT INSTRUCTIONS
Task 521170-831-848-001 - Modification
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
CAUTION
: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP
ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY
AND MECHANICALLY SERVICEABLE) . WHEN YOU DO 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 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
: This Service Bulletin is classified mandatory or expected to be classified mandatory
by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these
accomplishment instructions are Required for Compliance (RC) and must be done
to comply with the AD. Other paragraphs are recommended and may be deviated
from, done as part of other actions or done with accepted methods different from
those given in the Service Bulletin, as long as the RC paragraphs can be done and
the aircraft can be put back into a serviceable condition.
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 contained herein, contact Airbus for the
further instructions and approval.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 19
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NOTE
: Discarded parts must be managed at the operator’s discretion.
Task Associated Data
Zone
825 826
Access
Door
 825 826
Panel
 825AR 826AR
Manpower
TOTAL MANHOURS
 23.50
ELAPSED TIME (HOURS)
 11.75
A. GENERAL
(1) Subtask 521170-910-201-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-20-00, Page Block 001
06-31-53, Page Block 001
Task 20-21-11-911-001
Consumable Material List (CML)
Non Destructive Test Manual (NTM)
 51-10-01
Structural Repair Manual (SRM)
 51-40-00
51-42-11
51-43-00
51-44-00
51-46-00
51-48-00
(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to
the Consumable Material List (CML).
(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.
(c) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.
(d) Remove and install fasteners in accordance with SRM 51-42-11.
(e) To torque tighten the standard threaded fasteners, refer to AMM Task
20-21-11-911-001.
(f) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.
(g) Use the countersinking data in accordance with SRM 51-46-00.
(h) Do the cold expansion of fasteners holes in accordance with SRM 51-48-00.
(i) Do the rotating probe test, refer to NTM 51-10-01.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 20
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(j) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.
(k) If the length of any fastener specified in this Service Bulletin does not meet
installation standards given in SRM Chapter 51, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards given in SRM Chapter 51 may be used. In addition, washers may be
installed for fastener grip length in accordance with SRM Chapter 51.
(l) If alternative and substitute fasteners have to be used, you must make sure that the
associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’
column.
(2) Subtask 521170-839-201-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
B. PREPARATION
(1) Subtask 521170-941-201-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 12-34-24-869-002
Task 52-31-13-000-001
Task 52-31-14-000-801
Task 52-32-13-000-001
Task 52-32-14-000-801
NOTE
: The items given in this note shall be considered as the basic Aircraft
configuration before you start a maintenance task:
- Aircraft on the ground resting on landing gear (the ground safety
locks and the wheel chocks are in position on the landing gear)
- Engine shut down, thrust reversers closed and locked
- Aircraft in clean configuration
- Parking brake applied
- Aircraft electrical network de-energized
- Hydraulic system s depressurized
- Access to the cockpit and cabin is available
- All circuit breakers are in closed position
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 21
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- All controls in NORM, AUTO or OFF position.
(a) Make sure that the aircraft is electrically grounded, refer to AMM Task
12-34-24-869-002.
(b) Put an access platform in position below the zones 825 and 826.
(c) Remove the FWD cargo compartment door linings and insulations, refer to AMM
Task 52-31-13-000-001.
(d) Remove the AFT cargo compartment door linings and insulations, refer to AMM
Task 52-32-13-000-001.
(e) Remove the FWD cargo-compartment door access-panel 825AR, refer to AMM
Task 52-31-14-000-801.
(f) Remove the AFT cargo-compartment door access-panel 826AR, refer to AMM Task
52-32-14-000-801.
C. PROCEDURE
(1) Subtask 521170-210-201-001 - Identify the Part Numbers of the FWD Cargo
Compartment Door
Work Zones and Access Panels
Zone
 Access/Work location
825
 Access
 Door 825
Panel 825AR
Work location
 from Frame 24A to Frame 28
Manpower Resources
Manhours
 0.25
Minimum number of person
 1
Subtask elapsed time
 0.25
Skills
 NON SPECIFIC
(a) Identify the FWD cargo compartment for the below Part Number (P/N):
FWD Cargo Door D52371000000
NOTE
: If PN D52371000000 is found, contact AIRBUS before next flight
and follow their instructions.
FWD Cargo Door D52371000002
FWD Cargo Door D52371000004
FWD Cargo Door D52371000006
FWD Cargo Door D52371000008
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 22
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FWD Cargo Door D52371000010
FWD Cargo Door D52371000012
FWD Cargo Door D52371000014
FWD Cargo Door D52371000016
FWD Cargo Door D52371000018
FWD Cargo Door D52371000022
1
 If any one of the part number is found:
- Do the SUBTASK 521170-831-203 001 Remove the Fasteners from
Frame Fork Ends and the Outer Skin of FWD Cargo Compartment Door .
2
 If no part number is found:
- No further action required.
(2) Subtask 521170-831-203-001 - Remove the Fasteners from Frame Fork Ends and
the Outer Skin of FWD Cargo Compartment Door
Work Zones and Access Panels
Zone
 Access/Work location
825
 Access
 Door 825
Panel 825AR
Work location
 from Frame 24A to Frame 28
Manpower Resources
Manhours
 1.50
Minimum number of person
 1
Subtask elapsed time
 1.50
Skills
 AIRFRAME
References
Structural Repair Manual (SRM)
 51-42-00
Fig. A-GBAAA
Cold working of fasteners holes in the
frame fork ends and the outer skin
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Remove the fasteners as shown in View D, E , F and G of Fig. A-GBAAA Sheet
02
, Fig. A-GBAAA Sheet 03
 and Fig. A-GBAAA Sheet 04
 .
In accordance with SRM 51-42-00.
38 Rivet NAS1097KE5-00 Item (1) Discard
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 23
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16 Pin DAN6-5-5 Item (2) Discard
28 Nut NSA5075-5 Item (3) Discard
2 Pin DAN6-5-6 Item (4) Discard
6 Pin DAN6-5-7 Item (5) Discard
4 Pin DAN6-5-8 Item (6) Discard
(3) Subtask 521170-250-201-001 - Inspect the holes in the Frame Fork Ends of FWD
Cargo Compartment Door
Work Zones and Access Panels
Zone
 Access/Work location
825
 Access
 Door 825
Panel 825AR
Work location
 from Frame 24A to Frame 28
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 NON DESTRUCTIVE
TESTING
References
Non Destructive Test Manual (NTM)
 Task 51-10-01-250-801
Fig. A-GBAAA
Cold working of fasteners holes in the
frame fork ends and the outer skin
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Do a High Frequency Eddy Current (HFEC) rotating probe inspection of the holes
for cracks in the frame fork ends.
Refer to Fig. A-GBAAA
.
In accordance with NTM Task 51-10-01-250-801.
1
 If crack found:
a
 Contact AIRBUS before next flight and follow their instructions.
2
 If no crack found:
a
 In accordance with SUBTASK 521170-831-201 001 Oversize and Cold
Expand the holes in the Frame Fork Ends and the Outer Skin of FWD
Cargo Compartment Door .
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 24
6
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### Page 29

@A318/A319/A320/A321
SERVICE BULLETIN
(4) Subtask 521170-831-201-001 - Oversize and Cold Expand the holes in the Frame
Fork Ends and the Outer Skin of F WD Cargo Compartment Door
Work Zones and Access Panels
Zone
 Access/Work location
825
 Access
 Door 825
Panel 825AR
Work location
 from Frame 24A to Frame 28
Manpower Resources
Manhours
 3.00
Minimum number of person
 1
Subtask elapsed time
 3.00
Skills
 AIRFRAME
Material necessary to do the job
Standard tool TOOLD01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA320521170-1
 Durable tooling
 1
 (1)
EKA320521170-1
 Expendable tooling
 1
 (2)
FTIA320521170-1
 Capital tooling
 1
 (3)
NOTE
: FTI has allocated the following tool kit numbers for cold expansion:
For the definition of capital, durable and expendable tools, refer to ISI
51.48.00001.
NOTE
 (1)
: Durable tooling: Ref. DK-A320-52-1170-1
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to ISI
51.48.00001.
NOTE
 (2)
: Expendable tooling: Ref. EK-A320-52-1170-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
NOTE
 (3)
: Capital tooling: Ref. FTI-A320-52-1170-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long-
term investment or can be loaned from FTI.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 25
6
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### Page 30

@A318/A319/A320/A321
SERVICE BULLETIN
Standard tool TOOLD02
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA320521170-1
 Durable tooling
 1
 (1)
EKA320521170-1
 Expendable tooling
 1
 (2)
WCIA320521170-1
 Capital tooling
 1
 (3)
NOTE
: WCI has allocated the following tool kit numbers for cold expansion:
For the definition of capital, durable and expendable tools, refer to ISI
51.48.00001.
NOTE
 (1)
: Durable tooling: Ref. DK-A320-52-1170-1
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to ISI
51.48.00001.
NOTE
 (2)
: Expendable tooling: Ref. EK-A320-52-1170-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
NOTE
 (3)
: Capital tooling: Ref. WCI-A320-52-1170-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long-
term investment or can be loaned from WCI.
References
Structural Repair Manual (SRM)
 51-44-00
51-46-00
51-46-11
51-48-00
Fig. A-GBAAA
Cold working of fasteners holes in the
frame fork ends and the outer skin
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Cold expand the holes in the frame fork ends and the outer skin of FWD Cargo
Compartment Door.
Refer to Fig. A-GBAAA
.
In accordance with SRM 51-44-00, SRM 51-46-00 and SRM 51-48-00.
NOTE
: In case the existing hole diameter is more than or equal to the
minimum starting hole diameter, please contact AIRBUS for further
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 26
6
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### Page 31

@A318/A319/A320/A321
SERVICE BULLETIN
instructions before next flight.
1
 Oversize the holes to the starting hole diameter given in Fig. A-GBAAA Sheet
02
, Fig. A-GBAAA Sheet 03
 and Fig. A-GBAAA Sheet 04
 .
Refer to FTI tool list No.
DKA320521170-1 Durable tooling 1
or
Refer to WCI tool list No.
DKA320521170-1 Durable tooling 1
2
 Clean the drilled areas.
3
 Install the sleeves in accordance with the orientation given in the Fig. A-
GBAAA Sheet 02
, Fig. A-GBAAA Sheet 03
 and Fig. A-GBAAA Sheet 04
Refer to FTI tool list No.
EKA320521170-1 Expendable tooling 1
or
Refer to WCI tool list No.
EKA320521170-1 Expendable tooling 1
4
 Do the cold expansion of the holes.
Refer to FTI tool list No.
FTIA320521170-1 Capital tooling 1
or
Refer to WCI tool list No.
WCIA320521170-1 Capital tooling 1
5
 Remove the sleeves.
6
 Reams the holes to the final diameter given in the Fig. A-GBAAA Sheet 02
 ,
Fig. A-GBAAA Sheet 03
 and Fig. A-GBAAA Sheet 04
Refer to FTI tool list No.
DKA320521170-1 Durable tooling 1
or
Refer to WCI tool list No.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 27
6
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### Page 32

@A318/A319/A320/A321
SERVICE BULLETIN
DKA320521170-1 Durable tooling 1
7
 Clean the drilled areas.
8
 If necessary rework the countersinks to the related fastener head size in
accordance with SRM 51-46-11.
(5) Subtask 521170-831-202-001 - Install the Fasteners on the Frame Fork Ends and
the Outer Skin of FWD Cargo Compartment Door
Work Zones and Access Panels
Zone
 Access/Work location
825
 Access
 Door 825
Panel 825AR
Work location
 from Frame 24A to Frame 28
Manpower Resources
Manhours
 2.50
Minimum number of person
 1
Subtask elapsed time
 2.50
Skills
 AIRFRAME
Material necessary to do the job
Kit 521170D01R05
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
8
 ASNA2537-3
 66
 NUT
9
 ASNA2657K3-3
 26
 BOLT
10
 ASNA2657K3-4
 8
 BOLT
11
 ASNA2657K3-5
 18
 BOLT
12
 ASNA2657K3-6
 4
 BOLT
13
 ASNA2657K3-7
 6
 BOLT
14
 ASNA2657K3-8
 4
 BOLT
Component COMPD01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
15
 D5237125600000
 1
 Placard
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Primer Polyurethane Paint -
Corrosion Inhibiting
04EAC2
 As required
Top Coat Polyurethane
External - Structure
04JAA3
 As required
Polysulfide Sealant -
General Purpose Interfay
06AAC1
 As required
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 28
6
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### Page 33

@A318/A319/A320/A321
SERVICE BULLETIN
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Corrosion Preventive
Compound - Water
Displacing
12ADB1
 As required
References
Aircraft Maintenance Manual (AMM)
 Task 20-21-11-911-801
Structural Repair Manual (SRM)
 51-24-00
51-42-00
51-75-12
Fig. A-GBAAA
Cold working of fasteners holes in the
frame fork ends and the outer skin
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Install the fasteners on the frame fork Ends between Frame 24A and Frame 28 at
FWD Cargo Compartment Door and between as shown in View D, E , F and G of
Fig. A-GBAAA Sheet 02
 , Fig. A-GBAAA Sheet 03
 and Fig. A-GBAAA Sheet 04
 .
Refer to AMM Task 20-21-11-911-801 and in accordance with SRM 51-24-00 and
SRM 51-42-00.
66 Nut ASNA2537-3 Item 8
26 Bolt ASNA2657K3-3 Item 9
8 Bolt ASNA2657K3-4 Item 10
18 Bolt ASNA2657K3-5 Item 11
4 Bolt ASNA2657K3-6 Item 12
6 Bolt ASNA2657K3-7 Item 13
4 Bolt ASNA2657K3-8 Item 14
Do the installation of the fasteners (wet assembly) with:
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
(b) Renew the protective finish with:
In accordance with SRM 51-75-12.
Primer
Polyurethane Paint
- Corrosion
Inhibiting
04EAC2 As required
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 29
6
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### Page 34

@A318/A319/A320/A321
SERVICE BULLETIN
Top Coat
Polyurethane
External - Structure
04JAA3 As required
(c) Apply on work area:
Corrosion
Preventive
Compound - Water
Displacing
12ADB1 As required
(d) Install as shown on Fig. A-GBAAA Sheet 01
 and View C of Fig. A-GBAAA Sheet
02
:
1 Placard D5237125600000 Item 15
(6) Subtask 521170-210-202-001 - Identify the Part Numbers of the AFT Cargo
Compartment Door
Work Zones and Access Panels
Zone
 Access/Work location
826
 Access
 Door 826
Panel 826AR
Work location
 from Frame 52A to Frame 56
Manpower Resources
Manhours
 0.25
Minimum number of person
 1
Subtask elapsed time
 0.25
Skills
 NON SPECIFIC
(a) Identify the AFT cargo compartment door for the below part number:
AFT Cargo Door D52371900000
NOTE
: If PN D52371900000 is found, contact AIRBUS before next flight
and follow their instructions.
AFT Cargo Door D52371900002
AFT Cargo Door D52371900004
AFT Cargo Door D52371900008
AFT Cargo Door D52371900010
AFT Cargo Door D52371900012
AFT Cargo Door D52371900014
AFT Cargo Door D52371900016
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 30
6
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### Page 35

@A318/A319/A320/A321
SERVICE BULLETIN
AFT Cargo Door D52371900018
AFT Cargo Door D52371900022
1
 If any one of the part number is found:
- Do the SUBTASK 521170-831-206 001 Remove the Fasteners from
Frame Fork Ends and the Outer Skin of AFT Cargo Compartment Door .
2
 If no part number is found:
- No further action required.
(7) Subtask 521170-831-206-001 - Remove the Fasteners from Frame Fork Ends and
the Outer Skin of AFT Cargo Compartment Door
Work Zones and Access Panels
Zone
 Access/Work location
826
 Access
 Door 826
Panel 826AR
Work location
 from Frame 52A to Frame 56
Manpower Resources
Manhours
 1.50
Minimum number of person
 1
Subtask elapsed time
 1.50
Skills
 AIRFRAME
References
Structural Repair Manual (SRM)
 51-42-00
Fig. A-GBAAA
Cold working of fasteners holes in the
frame fork ends and the outer skin
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Remove the fasteners as shown in View D, E , F and G of Fig. A-GBAAA Sheet
02
, Fig. A-GBAAA Sheet 03
 and Fig. A-GBAAA Sheet 04
 .
In accordance with SRM 51-42-00.
38 Rivet NAS1097KE5-00 Item (1) Discard
16 Pin DAN6-5-5 Item (2) Discard
28 Nut NSA5075-5 Item (3) Discard
2 Pin DAN6-5-6 Item (4) Discard
6 Pin DAN6-5-7 Item (5) Discard
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 31
6
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### Page 36

@A318/A319/A320/A321
SERVICE BULLETIN
4 Pin DAN6-5-8 Item (6) Discard
(8) Subtask 521170-250-202-001 - Inspect the holes in the Frame Fork Ends of AFT
Cargo Compartment Door
Work Zones and Access Panels
Zone
 Access/Work location
826
 Access
 Door 826
Panel 826AR
Work location
 from Frame 52A to Frame 56
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 NON DESTRUCTIVE
TESTING
References
Non Destructive Test Manual (NTM)
 Task 51-10-01-250-801
Fig. A-GBAAA
Cold working of fasteners holes in the
frame fork ends and the outer skin
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Do a High Frequency Eddy Current (HFEC) rotating probe inspection of the holes
for cracks in the frame fork ends.
Refer to Fig. A-GBAAA
.
In accordance with NTM Task 51-10-01-250-801.
1
 If crack found:
a
 Contact AIRBUS before next flight and follow their instructions.
2
 If no crack found:
a
 In accordance with SUBTASK 521170-831-204 001 Oversize and Cold
Expand the holes in the Frame Fork Ends and the Outer Skin of AFT
Cargo Compartment Door .
(9) Subtask 521170-831-204-001 - Oversize and Cold Expand the holes in the Frame
Fork Ends and the Outer Skin of AFT Cargo Compartment Door
Work Zones and Access Panels
Zone
 Access/Work location
826
 Access
 Door 826
Panel 826AR
Work location
 from Frame 52A to Frame 56
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 32
6
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### Page 37

@A318/A319/A320/A321
SERVICE BULLETIN
Manpower Resources
Manhours
 3.00
Minimum number of person
 1
Subtask elapsed time
 3.00
Skills
 AIRFRAME
Material necessary to do the job
Standard tool TOOLD01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA320521170-1
 Durable tooling
 1
 (1)
EKA320521170-1
 Expendable tooling
 1
 (2)
FTIA320521170-1
 Capital tooling
 1
 (3)
NOTE
: FTI has allocated the following tool kit numbers for cold expansion:
For the definition of capital, durable and expendable tools, refer to ISI
51.48.00001.
NOTE
 (1)
: Durable tooling: Ref. DK-A320-52-1170-1
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to ISI
51.48.00001.
NOTE
 (2)
: Expendable tooling: Ref. EK-A320-52-1170-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
NOTE
 (3)
: Capital tooling: Ref. FTI-A320-52-1170-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long-
term investment or can be loaned from FTI.
Standard tool TOOLD02
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
DKA320521170-1
 Durable tooling
 1
 (1)
EKA320521170-1
 Expendable tooling
 1
 (2)
WCIA320521170-1
 Capital tooling
 1
 (3)
NOTE
: WCI has allocated the following tool kit numbers for cold expansion:
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 33
6
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### Page 38

@A318/A319/A320/A321
SERVICE BULLETIN
For the definition of capital, durable and expendable tools, refer to ISI
51.48.00001.
NOTE
 (1)
: Durable tooling: Ref. DK-A320-52-1170-1
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to ISI
51.48.00001.
NOTE
 (2)
: Expendable tooling: Ref. EK-A320-52-1170-1
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
NOTE
 (3)
: Capital tooling: Ref. WCI-A320-52-1170-1
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long-
term investment or can be loaned from WCI.
References
Structural Repair Manual (SRM)
 51-44-00
51-46-00
51-46-11
51-48-00
Fig. A-GBAAA
Cold working of fasteners holes in the
frame fork ends and the outer skin
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Cold expand the holes in the frame fork ends and the outer skin of AFT Cargo
Compartment Door.
Refer to Fig. A-GBAAA
.
In accordance with SRM 51-44-00, SRM 51-46-00 and SRM 51-48-00.
NOTE
: In case the existing hole diameter is more than or equal to the
minimum starting hole diameter, please contact AIRBUS for further
instructions before next flight.
1
 Oversize the holes to the starting hole diameter given in Fig. A-GBAAA Sheet
02
, Fig. A-GBAAA Sheet 03
 and Fig. A-GBAAA Sheet 04
 .
Refer to FTI tool list No.
DKA320521170-1 Durable tooling 1
or
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 34
6
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### Page 39

@A318/A319/A320/A321
SERVICE BULLETIN
Refer to WCI tool list No.
DKA320521170-1 Durable tooling 1
2
 Clean the drilled areas.
3
 Install the sleeves in accordance with the orientation given in the Fig. A-
GBAAA Sheet 02
, Fig. A-GBAAA Sheet 03
 and Fig. A-GBAAA Sheet 04
Refer to FTI tool list No.
EKA320521170-1 Expendable tooling 1
or
Refer to WCI tool list No.
EKA320521170-1 Expendable tooling 1
4
 Do the cold expansion of the holes.
Refer to FTI tool list No.
FTIA320521170-1 Capital tooling 1
or
Refer to WCI tool list No.
WCIA320521170-1 Capital tooling 1
5
 Remove the sleeves.
6
 Reams the holes to the final diameter given in the Fig. A-GBAAA Sheet 02
 ,
Fig. A-GBAAA Sheet 03
 and Fig. A-GBAAA Sheet 04
Refer to FTI tool list No.
DKA320521170-1 Durable tooling 1
or
Refer to WCI tool list No.
DKA320521170-1 Durable tooling 1
7
 Clean the drilled areas.
8
 If necessary rework the countersinks to the related fastener head size in
accordance with SRM 51-46-11.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 35
6
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### Page 40

@A318/A319/A320/A321
SERVICE BULLETIN
(10) Subtask 521170-831-205-001 - Install the Fasteners on the Frame Fork Ends and
the Outer Skin of AFT Cargo Compartment Door
Work Zones and Access Panels
Zone
 Access/Work location
826
 Access
 Door 826
Panel 826AR
Work location
 from Frame 52A to Frame 56
Manpower Resources
Manhours
 2.50
Minimum number of person
 1
Subtask elapsed time
 2.50
Skills
 AIRFRAME
Material necessary to do the job
Kit 521170D01R05
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
8
 ASNA2537-3
 66
 NUT
9
 ASNA2657K3-3
 26
 BOLT
10
 ASNA2657K3-4
 8
 BOLT
11
 ASNA2657K3-5
 18
 BOLT
12
 ASNA2657K3-6
 4
 BOLT
13
 ASNA2657K3-7
 6
 BOLT
14
 ASNA2657K3-8
 4
 BOLT
Component COMPD01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
15
 D5237125600000
 1
 Placard
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Primer Polyurethane Paint -
Corrosion Inhibiting
04EAC2
 As required
Top Coat Polyurethane
External - Structure
04JAA3
 As required
Polysulfide Sealant -
General Purpose Interfay
06AAC1
 As required
Corrosion Preventive
Compound - Water
Displacing
12ADB1
 As required
References
Aircraft Maintenance Manual (AMM)
 Task 20-21-11-911-801
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 36
6
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### Page 41

@A318/A319/A320/A321
SERVICE BULLETIN
References
Structural Repair Manual (SRM)
 51-24-00
51-42-00
51-75-12
Fig. A-GBAAA
Cold working of fasteners holes in the
frame fork ends and the outer skin
Sheet 01
Sheet 02
Sheet 03
Sheet 04
(a) Install the fasteners on the frame fork Ends between Frame 52A and Frame 56 at
AFT Cargo Compartment Door as shown in View D, E , F and G of Fig. A-GBAAA
Sheet 02
, Fig. A-GBAAA Sheet 03
 and Fig. A-GBAAA Sheet 04
 .
Refer to AMM Task 20-21-11-911-801 and in accordance with SRM 51-24-00 and
SRM 51-42-00.
66 Nut ASNA2537-3 Item 8
26 Bolt ASNA2657K3-3 Item 9
8 Bolt ASNA2657K3-4 Item 10
18 Bolt ASNA2657K3-5 Item 11
4 Bolt ASNA2657K3-6 Item 12
6 Bolt ASNA2657K3-7 Item 13
4 Bolt ASNA2657K3-8 Item 14
Do the installation of the fasteners (wet assembly) with:
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
(b) Renew the protective finish with:
In accordance with SRM 51-75-12.
Primer
Polyurethane Paint
- Corrosion
Inhibiting
04EAC2 As required
Top Coat
Polyurethane
External - Structure
04JAA3 As required
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 37
6
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### Page 42

@A318/A319/A320/A321
SERVICE BULLETIN
(c) Apply on work area:
Corrosion
Preventive
Compound - Water
Displacing
12ADB1 As required
(d) Install as shown on Fig. A-GBAAA Sheet 01
 and View C of Fig. A-GBAAA Sheet
02
:
1 Placard D5237125600000 Item 15
D. TEST
None
E. CLOSE-UP
(1) Subtask 521170-942-201-001 - Close-up
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 Task 52-31-13-400-001
Task 52-31-14-400-801
Task 52-32-13-400-001
Task 52-32-14-000-801
Task 52-32-14-400-801
Task 53-31-14-000-801
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Install the FWD cargo-compartment door access-panel 825AR, refer to AMM Task
52-31-14-400-801.
(c) Install the AFT cargo-compartment door access-panel 826AR, refer to AMM Task
52-32-14-400-801.
(d) Install the FWD cargo compartment door linings and insulations, refer to AMM Task
52-31-13-400-001.
(e) Install the AFT cargo compartment door linings and insulations, refer to AMM Task
52-32-13-400-001.
(f) Remove the access platform(s).
(g) Put the aircraft back to its initial configuration.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 38
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 43

@A318/A319/A320/A321
SERVICE BULLETIN
**CONF ALL
FR28
FR24A
A
BFWD
BEAM4
ACCESS PANEL
FR56
FR52A
VIEW LOOKING INBOARD
B
FR52AFR53FR53AFR54FR54AFR55FR55AFR56
BEAM4
FR24AFR25FR25AFR26FR26AFR27FR27AFR28
Z825
Z826
A
A
C
D E F G
N_SB_521170_6_BAAA_01_02
Figure A-GBAAA - Sheet 01
Cold working of fasteners holes in the frame fork ends and the outer skin
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 39
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 44

@A318/A319/A320/A321
SERVICE BULLETIN
**CONF ALL
15
FR55A
FR27
FR55
FR26A
FR54A
FR27A
9
8
(1)
9
8
(1)
11
8
(2)
(3)
(1)
9
8
(1)
9
8
(2)
(3)
11
8
(2)
(3)
11
8
(1)
10
8
FR54
FR26
10
8
(1)
10
8
(1)
10
8
(1)
TYPICAL
D E
NOTE:
POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION.
4% COLD WORKING.01
02 REFER TO APPENDIX 02 − ALTERNATIVE FASTENERS FOR ASNA2657K3 SERIES.
MAX
SIZE / FIT TYPESTARTING HOLE DIAMETER
MINDESCRIPTIONP/NITEMOLD
(1)
(2)
(3)
(1)
P/N
NAS1097KE5−00
DAN6−5−5
NSA5075−5
NAS1097KE5−00
HOLE
SYMBOL DESCRIPTION
RIVET
PIN
NUT
RIVET
NEW
ITEM STDN MAX NOTEMINFINAL HOLE DIAMETER
9
8
ASNA2657K3−3
ASNA2537−3
BOLT
NUT 4−4−N
4.29 mm
(0.169 in)
4.34 mm
(0.171 in)
4.733 mm
(0.186 in)
4.758 mm
(0.187 in)
NOMINAL SIZE
INTERFERENCE FIT
NOMINAL SIZE
INTERFERENCE FIT
NOMINAL SIZE
INTERFERENCE FIT
01
01
01
8
11 ASNA2657K3−5
ASNA2537−3
BOLT
NUT
4−4−N 4.29 mm(0.169 in) 4.34 mm(0.171 in) 4.733 mm(0.186 in) 4.758 mm(0.187 in)
8
ASNA2657K3−4
ASNA2537−3
BOLT
NUT 4−4−N 4.29 mm(0.169 in) 4.34 mm(0.171 in) 4.733 mm(0.186 in) 4.758 mm(0.187 in)10
02
02
02
SB52 − 1170
MOD 157312 K18115
C/W FRAME FORKS
C
11
8
(3)
(2)
9
8
(1)
9
8
(1)
N_SB_521170_6_BAAA_02_04
Figure A-GBAAA - Sheet 02
Cold working of fasteners holes in the frame fork ends and the outer skin
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 40
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 45

@A318/A319/A320/A321
SERVICE BULLETIN
**CONF ALL
MAX
SIZE / FIT TYPESTARTING HOLE DIAMETER
MINDESCRIPTIONP/N
(1)
(1)
(3)
(5)
(3)
(4)
ITEM
OLD P/NHOLESYMBOL
NAS1097KE5−00
NAS1097KE5−00
DAN6−5−7
NSA5075−5
DAN6−5−6
NSA5075−5
DESCRIPTION
PIN
NUT
NUT
PIN
RIVET
RIVET
NEW
ITEM STDN MAX NOTEMINFINAL HOLE DIAMETER
8
8
10
11
ASNA2657K3−4
ASNA2537−3
ASNA2657K3−5
ASNA2537−3
BOLT
NUT
BOLT
NUT
4−4−N
4−4−N
NOMINAL SIZE
INTERFERENCE FIT
NOMINAL SIZE
INTERFERENCE FIT
4.29 mm
(0.169 in)
4.34 mm
(0.171 in)
4.733 mm
(0.186 in)
4.758 mm
(0.187 in)
4.29 mm
(0.169 in)
4.34 mm
(0.171 in)
4.733 mm
(0.186 in)
4.758 mm
(0.187 in)
8
13 ASNA2657K3−7
ASNA2537−3
BOLT
NUT 4−4−N NOMINAL SIZEINTERFERENCE FIT4.29 mm(0.169 in) 4.34 mm(0.171 in) 4.733 mm(0.186 in) 4.758 mm(0.187 in)
01
01
01
8
12 ASNA2657K3−6
ASNA2537−3
BOLT
NUT 4−4−N NOMINAL SIZEINTERFERENCE FIT4.29 mm(0.169 in) 4.34 mm(0.171 in) 4.733 mm(0.186 in) 4.758 mm(0.187 in) 01
02
02
02
02
(3)
(4)
12
8
(3)
(5)
13
8
(3)
(4)
12
8
(1)
10
8
(3)
(5)
8
13
(1)
10
8
FR53A
FR25A
8
11
(1)
11
8
(1)
NOTE:
POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION.
4% COLD WORKING.01
02 REFER TO APPENDIX 02 − ALTERNATIVE FASTENERS FOR ASNA2657K3 SERIES.
F
N_SB_521170_6_BAAA_03_05
Figure A-GBAAA - Sheet 03
Cold working of fasteners holes in the frame fork ends and the outer skin
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 41
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 46

@A318/A319/A320/A321
SERVICE BULLETIN
**CONF ALL
(3)
(6)
14
8
(1)
10
8
(1)
10
8
(3)
(6)
14
8
(3)
(5)
13
8
(3)
(5)
13
8
FR53
FR25
12
8
(1)
12
8
(1)
MAX
SIZE / FIT TYPESTARTING HOLE DIAMETER
MINDESCRIPTIONP/NNEWITEM STDN MAX NOTEMINFINAL HOLE DIAMETER
(1)
(1)
(3)
(5)
(3)
(6)
ITEM
OLD P/NHOLE
NAS1097KE5−00
NAS1097KE5−00
DAN6−5−8
DAN6−5−7
NSA5075−5
NSA5075−5
DESCRIPTION
RIVET
RIVET
NUT
NUT
PIN
PIN
8
10 ASNA2657K3−4
ASNA2537−3
BOLT
NUT 4−4−N NOMINAL SIZEINTERFERENCE FIT4.29 mm(0.169 in) 4.34 mm(0.171 in) 4.733 mm(0.186 in) 4.758 mm(0.187 in) 01
8
ASNA2657K3−6
ASNA2537−3
BOLT
NUT 4−4−N NOMINAL SIZEINTERFERENCE FIT4.29 mm(0.169 in) 4.34 mm(0.171 in) 4.733 mm(0.186 in) 4.758 mm(0.187 in) 01
8
13 ASNA2657K3−7
ASNA2537−3
BOLT
NUT 4−4−N NOMINAL SIZEINTERFERENCE FIT4.29 mm(0.169 in) 4.34 mm(0.171 in) 4.733 mm(0.186 in) 4.758 mm(0.187 in) 01
8
ASNA2657K3−8
ASNA2537−3
BOLT
NUT 4−4−N NOMINAL SIZEINTERFERENCE FIT4.29 mm(0.169 in) 4.34 mm(0.171 in) 4.733 mm(0.186 in) 4.758 mm(0.187 in) 01
12
14
02
02
02
02
NOTE:
POSITION OF SPLIT IN EXPANSION SLEEVE DURING COLD EXPANSION.
4% COLD WORKING.01
02 REFER TO APPENDIX 02 − ALTERNATIVE FASTENERS FOR ASNA2657K3 SERIES.
G
N_SB_521170_6_BAAA_04_03
Figure A-GBAAA - Sheet 04
Cold working of fasteners holes in the frame fork ends and the outer skin
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 42
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 47

@A318/A319/A320/A321
SERVICE BULLETIN
Appendix 01 - Manpower Gantt Chart
**CONF ALL
For an explanation of the manhours and elapsed time, refer to the next page(s).
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 48

@A318/A319/A320/A321
SERVICE BULLETIN
Appendix 01 - Manpower Gantt Chart
**CONF ALL
3.00 1.502
1.50 1.501
1.50 1.501REMOVE THE FASTENERS FROM FRAME FORK
ENDS AND THE OUTER SKIN OF FWD CARGO 
COMPARTMENT DOOR
0.50 0.501INSPECT THE HOLES IN THE FRAME FORK ENDS
OF AFT CARGO COMPARTMENT DOOR
3.00 3.001COLD EXPAND THE HOLES IN THE FRAME FORK
ENDS AND THE OUTER SKIN OF FWD CARGO 
COMPARTMENT DOOR
2.50 2.501INSTALL THE FASTENERS ON THE FRAME
FORK ENDS AND THE OUTER SKIN OF AFT
CARGO COMPARTMENT DOOR
0.50 0.501
3.00 3.001COLD EXPAND THE HOLES IN THE FRAME FORK
ENDS AND THE OUTER SKIN OF AFT CARGO 
COMPARTMENT DOOR
2.50 2.501INSTALL THE FASTENERS ON THE FRAME
FORK ENDS AND THE OUTER SKIN OF FWD
CARGO COMPARTMENT DOOR
REMOVE THE FASTENERS FROM FRAME FORK
ENDS AND THE OUTER SKIN OF AFT CARGO 
COMPARTMENT DOOR
INSPECT THE HOLES IN THE FRAME FORK ENDS
OF FWD CARGO COMPARTMENT DOOR
5.00 2.502CLOSE−UP
MH ET/SPERSTEPS
0 1
TOTAL MANHOURS
SB ELAPSED TIME
23.50
11.75
SB ELAPSED TIME
(HOURS)
GET ACCESS
ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320−52−1170 0102
MH
ET/S:
PER
MANHOURS
ELAPSED TIME PER STEP
NUMBER OF PERSONS
THIS CHART IS ONLY A PROPOSAL.
OPERATORS MAY DETERMINE THAT ANOTHER WAY
TO DO THE WORK IS MORE SUITABLE FOR THEM.
01
02
NOTE:
IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS
ARE NOT REFLECTED IN THIS GANTT CHART.
:
:
IDENTIFY THE PART NUMBERS OF THE AFT
CARGO COMPARTMENT DOOR
IDENTIFY THE PART NUMBERS OF THE FWD
CARGO COMPARTMENT DOOR
0.25 1 0.25
0.25 1 0.25
23 45 6 7 8 9 10 11
N_SB_521170_6_AAAA_01_02
Figure A-GAAAA - Sheet 01
Manpower Gantt Chart
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 49

@A318/A319/A320/A321
SERVICE BULLETIN
Appendix 02 - Alternative Fasteners for ASNA2657K3 Series
**CONF ALL
For the alternative fasteners for ASNA2657K3 series, refer to the next page.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 50

@A318/A319/A320/A321
SERVICE BULLETIN
Appendix 02 - Alternative Fasteners for ASNA2657K3 Series
**CONF ALL
ORIGINAL
PART NUMBER ALTERNATIVE FASTENERS
ASNA2657K3−4
ASNA2657K3−5
ASNA2657K3−6
HST11AG6−4
HST11AG6−5
HST11AG6−6
HST11KM6−4 HST11AP6−4 HST11AZ6−4
HST11KM6−5
HST11KM6−6
HST11AP6−5
HST11AP6−6
HST11AZ6−5
HST11AZ6−6
ASNA2657K3−7
ASNA2657K3−8
HST11AG6−7
HST11AG6−8
HST11KM6−7
HST11KM6−8
HST11AP6−7
HST11AP6−8
HST11AZ6−7
HST11AZ6−8
ASNA2657K3−3 HST11AG6−3 HST11KM6−3 HST11AP6−3 HST11AZ6−3
N_SB_521170_6_ABAA_01_00
Figure A-GABAA - Sheet 01
Alternative Fasteners for ASNA2657K3 Series
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 51

@A318/A319/A320/A321
SERVICE BULLETIN
REPORTING SHEET
TITLE: DOORS - CARGO - INTRODUCE COLD WORKING AT THE FRAME OF
FWD/AFT CARGO DOOR
MODIFICATION No.: 157312K18115
Please complete the appropriate item (A or B):
A - SB WILL BE
 embodied YES/NO (if NO please comment)
If YES, aircraft concer ned (as per SB effectivity by default) and planned dates (month/year) of
embodiment:
B - SB HAS BEEN
 embodied on aircraft:
Operator comments:
From Airline:
Name/Title:
Signature: Date:
If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to
next normal revision or prior to SB embodiment, please indicate required service(s):
Either: Modification Operational Impact (MOI), if available YES/NO
Or : Intermediate revision YES/NO
Important Information:
 This SB will only be incorporated in your maintenance and operational
documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With
the next feasible revision, this will result in
- Updating of maintenance documentation to show pre and post SB data.
- Updating of maintenance and operational documentation to show post SB data after embodiment.
If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically
include them in the manual revisions. Refer to SIL 00-037 for detailed information.
Please return this completed sheet to:
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Attn: SDC32 Technical Data and Documentation Services
F A X :( + 3 3 )56 19 32 80 6
e-mail: sb.reporting@airbus.com
or via your Resident Customer Support Office.
Alternatively, SB lists via letters or fax are also accepted.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 1
6
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### Page 52

@A318/A319/A320/A321
SERVICE BULLETIN
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 Bulletins.
We thank you for the time you have taken in completing this form.
(Please rate on a scale of 1 to 4, with 4 being the highest score)
- Quality rating of this SB 4321
- Quality rating of the Accomplishment Instructions 4321
- Quality rating of the Illustrations 4321
- Is this SB easy to understand ? Y/N
If you have had 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 Effectivity X Kit content X Preparation
X Reason X List of Materials Operator Supplied X Mod/Inspection
X Manpower X Industry support X Test
X References X Re-identification X Close-Up
X Publication X Tooling X Illustrations
Comments:
Operator: Date:
Name/Title:
Please return this form to:
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX FRANCE
Attn : SEM4 Service Bulletins Management
F A X:( 3 3 )56 19 34 25 1
Or via your Resident Customer Support Office.
DATE: Sep 05/16 SERVICE BULLETIN No.: A320-52-1170
REVISION No.: 00 - Sep 05/16 Page: 1
6
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