# Airbus Canada Service Bulletin BD500-530012: Revision 001

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- Document: [Airbus Canada Service Bulletin BD500-530012](https://openairdocs.org/service-documents/airbus-canada/bd500-530012.md)
- Title as filed: BD500-530012_Issue001
- Pages: 30
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### Page 1

BD500-530012
 
 
 2023-09-13  Page 1
 
Service Bulletin
Fuselage - General - Verification of
Previous Aircraft Repairs and Damage for
Load Loop Analysis on the A220-300
BD500-530012
Issue No. 001
Copyright © 2023 Airbus Canada Limited Partnership
All rights reserved. No part of this work may be reproduced or copied in any form or by any means without written permission of Airbus
Canada Limited Partnership.
The Airbus and A220 logos are registered trademarks of Airbus Canada Limited Partnership.
The information, technical data and the designs disclosed herein are the exclusive property of Airbus Canada Limited Partnership or
contain proprietary rights of others and are not to be used or disclosed to others without the written consent of Airbus Canada Limited
Partnership. The recipient of this document, by its retention and use, agrees to hold in confidence the technical data and designs contained
herein. The foregoing shall not apply to persons having proprietary rights to such information, technical data or such designs to the extent
that such rights exist.
Manufacturer:
Airbus Canada Limited Partnership
Customer Services
13100 Henri-Fabre Blvd., Mirabel, Quebec
Canada J7N 3C6

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BD500-530012
 
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 2023-09-13  Page 2

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BD500-530012
 
 
 2023-09-13  Page 1
Table of contents
The listed documents are included in Issue 001, dated 2023-09-13, of this publication.
Document title Data module code Issue date Applicable
to
Fuselage - General - Verification of
Previous Aircraft Repairs and Damage
for Load Loop Analysis on the A220-300 -
Service Bulletin
BD500-A-J53-00-12-00AAA-930A-A 2023-09-13 55003-55191,
55193,
55195-55196,
55198-55202,
55205,
55209-55210,
55228,
55231,
55244,
55246-55248,
55250
Verification of Previous Aircraft Repairs
and Damage for Load Loop Analysis
on the A220-300 - Accomplishment
instruction
BD500-A-J53-00-12-01AAA-933A-A 2023-09-13 55003-55191,
55193,
55195-55196,
55198-55202,
55205,
55209-55210,
55228,
55231,
55244,
55246-55248,
55250
Appendix A - A220-300 Tailcone Missed
Loop 3 Inspection Areas
BD500-A-J53-00-12-01AAA-910B-A 2023-09-13 55003-55191,
55193,
55195-55196,
55198-55202,
55205,
55209-55210,
55228,
55231,
55244,
55246-55248,
55250
Appendix B - A220-300 VStab Missed
Loop 3 Inspection Areas
BD500-A-J53-00-12-02AAA-910B-A 2023-09-13 55003-55191,
55193,
55195-55196,
55198-55202,
55205,
55209-55210,
55228,
55231,
55244,
55246-55248,
55250

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BD500-530012
 
 
 2023-09-13  Page 2
Document title Data module code Issue date Applicable
to
Appendix C - A220-300 Wing Missed
Loop 3 Inspection Areas
BD500-A-J53-00-12-03AAA-910B-A 2023-09-13 55003-55191,
55193,
55195-55196,
55198-55202,
55205,
55209-55210,
55228,
55231,
55244,
55246-55248,
55250

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BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-00AAA-930A-A
BD500-A-J53-00-12-00AAA-930A-A
 2023-09-13  Page 1
Fuselage - General - Verification of Previous Aircraft Repairs and
Damage for Load Loop Analysis on the A220-300 - Service Bulletin
 
Applicability: 55003-55191, 55193, 55195-55196, 55198-55202, 55205, 55209-55210, 55228, 55231, 55244,
55246-55248, 55250
 
Table of contents Page
Fuselage - General - Verification of Previous Aircraft Repairs and Damage for Load Loop
Analysis on the A220-300 - Service Bulletin ............................................................................ 1
References................................................................................................................................ 1
Service Bulletin.......................................................................................................................... 1
Common information................................................................................................................. 1
1 Maintenance Publications........................................................................................... 5
2 Operational Publications............................................................................................. 5
List of tables Page
1 References.................................................................................................................. 1
References
Table 1  References
Data Module/Technical Publication Title
BD500-A-J53-00-12-01AAA-933A-A Verification of Previous Aircraft Repairs and
Damage for Load Loop Analysis on the A220-300 -
Accomplishment instruction
BD500-A-J53-00-12-01AAA-910B-A Appendix A - A220-300 Tailcone Missed Loop 3
Inspection Areas
BD500-A-J53-00-12-02AAA-910B-A Appendix B - A220-300 VStab Missed Loop 3
Inspection Areas
BD500-A-J53-00-12-03AAA-910B-A Appendix C - A220-300 Wing Missed Loop 3 Inspection
Areas
Service Bulletin
Common information
THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS
LEASED AIRCRAFT, SEND THE SERVICE BULLETIN TO THE LESSEE. IF THE OPERATOR
HAS SOLD AIRCRAFT OR TRANSFERRED SPARES IN THE LAST SIX MONTHS, SEND
THIS SERVICE BULLETIN TO THE NEW OWNER, UNLESS CONFIRMATION WAS
RECEIVED THAT AIRBUS HAS INCLUDED THE NEW OPERATOR ON THE DISTRIBUTION
LIST.

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BD500-A-J53-00-12-00AAA-930A-A
BD500-A-J53-00-12-00AAA-930A-A
 2023-09-13  Page 2
Management information
Compliance category: Recommended (Service bulletin recommended to be accomplished to
prevent significant operational disruptions)
Task category: Administrative
Original issue date: 2023-09-13
Impact list
Impact (Maintenance publications):
Refer to the Documentation affected section of the Planning Information section.
Accomplishment limits
None
Replacement service bulletin
None
Revision information
Initial issue
Summary
Applicability
BD-500-1A11, Aircraft 55003 thru 55191, 55193, 55195, 55196, 55198 thru 55202, 55205,
55209, 55210, 55228, 55231, 55244, 55246 thru 55248, and 55250
Reason
In-service repairs in the tailcone, the Vertical Stabilizer (VStab) and the wing structural areas
can cause negative margins for the load envelopes, which will make it necessary to get
verification from Airbus.
Description
The identification of the previous aircraft repairs and damage is done. When applicable, the
previous aircraft repairs and damage are reported to Airbus for analysis.
Concurrent requirements
None
Manpower
It will take an estimated 1.5 h to complete this service bulletin.
Note
These estimates do not include the man-hours necessary to do an inspection of the
structure.
Material information
None

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BD500-A-J53-00-12-00AAA-930A-A
BD500-A-J53-00-12-00AAA-930A-A
 2023-09-13  Page 3
Planning information
Applicability
Aircraft affected:
AIRCRAFT MODEL SERVICE AIRCRAFT
SERIAL NUMBER
PRODUCTION AIRCRAFT SERIAL
NUMBERS
BD-500-1A11 55003 thru 55191, 55193,
55195, 55196, 55198 thru
55202, 55205, 55209, 55210,
55228, 55231, 55244, 55246
thru 55248, and 55250
There is no production effectivity.
Note
The instructions in this service bulletin are only applicable to the systems and parts
installed at the time of delivery of the aircraft or as changed by Airbus Service Bulletins.
Before you do this service bulletin, examine all Supplemental Type Certificates (STCs),
Supplemental Type Approvals (STAs), or equivalent action changes to make sure you can
complete this service bulletin.
Reason
Problem and effect
In-service repairs in the tailcone, the Vertical Stabilizer (VStab) and the wing structural areas
can cause negative margins for the load envelopes, which will make it necessary to get verifica-
tion from Airbus.
Objective/Solution
This service bulletin gives the instructions to do a verification/record check and, if necessary, an
inspection of previous damage and/or repairs done after the aircraft received its Certificate of
Airworthiness (CofA). When applicable, the previous aircraft repairs and damage are reported to
Airbus for analysis and approved disposition if necessary.
Description
The identification of the previous aircraft repairs and damage is done. When applicable, the
previous aircraft repairs and damage are reported to Airbus for analysis.
Compliance
Recommended Service Bulletin
Airbus recommends that this service bulletin be done within 48 months from the release date of
this service bulletin, unless otherwise directed by the airworthiness authority of the operator.
Note
If it is not possible to complete all the instructions in this service bulletin because of
the configuration of the aircraft, speak with a CRC representative at 1 866 A220 CRC
(1-866-222-0272) or 1-450-476-7676 or e-mail at A220_crc@abc.airbus for analysis and to
get approved instructions to complete this service bulletin.

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BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-00AAA-930A-A
BD500-A-J53-00-12-00AAA-930A-A
 2023-09-13  Page 4
Note
This service bulletin does not affect Airworthiness Limitations Items (ALIs) or Damage
Tolerance Inspections (DTIs).
Concurrent requirements
None
Approval
The technical content of this service bulletin has been approved under the authority of the TC-
CA Design Approval Organization No: DAO #19-Q-02.
Manpower
The man-hours given below are estimates for direct labor done by an experienced crew on an
aircraft prepared for maintenance.
These estimates do not include the time necessary for:
- Administrative functions such as planning, liaising, familiarization, and report writing.
- Non-productive elapsed time such as rest time, having meals, and crew shift changes.
- Elapsed time such as for paint to dry, sealant to cure, and fuel tank venting.
- Preparation for modification (unless specified in the Accomplishment Instructions) such as
cleaning and getting parts, tools, consumables, and ground equipment.
- Quality assurance inspections, troubleshooting and/or correction of discrepancies found
when a task is done.
- All other activities that are not considered by Airbus as directly related to the accomplish-
ment of this procedure.
It will take an estimated 1.5 h to complete this service bulletin. The man-hours are divided as
shown in the table that follows:
TASK MAN-HOURS
Job Set-Up 0.0 h
Procedure 1.5 h
Test 0.0 h
Job Close-Up 0.0 h
Note
These estimates do not include the man-hours necessary to do an inspection of the
structure.
Weight and balance
Not changed
Electrical load data
Not changed

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BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-00AAA-930A-A
BD500-A-J53-00-12-00AAA-930A-A
End of data module
 2023-09-13  Page 5
Referenced documentation
Refer to the SB Introduction document BD500-000000 for definition or explanation of service
bulletin content.
For Airbus reference only: Restriction and/or Special Instruction RSI C-500-000-51-0014,
Revision C
For Airbus reference only: PCR 62592
Documentation affected
1 Maintenance Publications
None
2 Operational Publications
None
Industry support information
This Service Bulletin is part of an AIRBUS monitored retrofit campaign.
For the organization of this retrofit, contact your AIRBUS Customer Services Program Support
Program Manager.
For aircraft under warranty and for aircraft out of warranty at the time of the initial issue date of
this Service Bulletin:
AIRBUS will credit up to 1.5 man-hours at the agreed in-house warranty labor rate for claims
received no later than 90 days after completion of the last affected aircraft of your fleet, for
the accomplishment of this Service Bulletin within 48 months after the initial issue date of the
Service Bulletin.
Material information
None
Accomplishment instructions
BD500-A-J53-00-12-01AAA-933A-A
Additional information
Additional information
Appendix A: Refer to BD500-A-J53-00-12-01AAA-910B-A
Appendix B: Refer to BD500-A-J53-00-12-02AAA-910B-A
Appendix C: Refer to BD500-A-J53-00-12-03AAA-910B-A

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BD500-A-J53-00-12-00AAA-930A-A
BD500-A-J53-00-12-00AAA-930A-A
 2023-09-13  Page 6

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BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-01AAA-933A-A
BD500-A-J53-00-12-01AAA-933A-A
 2023-09-13  Page 1
Verification of Previous Aircraft Repairs and Damage for Load
Loop Analysis on the A220-300 - Accomplishment instruction
 
Applicability: 55003-55191, 55193, 55195-55196, 55198-55202, 55205, 55209-55210, 55228, 55231, 55244,
55246-55248, 55250
 
Table of contents Page
Verification of Previous Aircraft Repairs and Damage for Load Loop Analysis on the
A220-300 - Accomplishment instruction ................................................................................... 1
References................................................................................................................................ 1
Preliminary requirements.......................................................................................................... 1
Procedure.................................................................................................................................. 2
1 Procedure.................................................................................................................... 2
2 Administrative.............................................................................................................. 4
Requirements after job completion ........................................................................................... 4
List of tables Page
1 References.................................................................................................................. 1
2 Required conditions.................................................................................................... 1
3 Support equipment...................................................................................................... 2
4 Consumables, materials, and expendables ................................................................ 2
5 Spares......................................................................................................................... 2
6 Applicable ATA for Repair or Damages ...................................................................... 3
7 Required conditions.................................................................................................... 4
References
Table 1  References
Data Module/Technical Publication Title
BD500-A-J53-00-12-01AAA-910B-A Appendix A - A220-300 Tailcone Missed Loop 3
Inspection Areas
BD500-A-J53-00-12-02AAA-910B-A Appendix B - A220-300 VStab Missed Loop 3
Inspection Areas
BD500-A-J53-00-12-03AAA-910B-A Appendix C - A220-300 Wing Missed Loop 3 Inspection
Areas
Preliminary requirements
Required conditions
Table 2  Required conditions
Action/Condition Data Module/Technical publication
None

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BD500-530012
 
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first page of the DM
BD500-A-J53-00-12-01AAA-933A-A
BD500-A-J53-00-12-01AAA-933A-A
 2023-09-13  Page 2
Support equipment
Table 3  Support equipment
Name Identification/Reference Quantity Remark
None
Consumables, materials, and expendables
Table 4  Consumables, materials, and expendables
Name Identification/Reference Quantity Remark
None
Spares
Table 5  Spares
Name Identification/Reference Quantity Remark
None
Safety conditions
None
Procedure
1 Procedure
1.1 If it is not possible to complete all the instructions in this service bulletin
because of the configuration of the aircraft, speak with a CRC representative
at 1 866 A220 CRC (1-866-222-0272) or 1-450-476-7676 or e-mail at
A220_crc@abc.airbus for analysis and to get an approved disposition to
complete this service bulletin.
1.2 Identify previous in-service repairs, damage and non-conformity as follows:
Note
Speak with a CRC representative at 1 866 A220 CRC (1-866-222-0272) or
1-450-476-7676 or e-mail at A220_crc@abc.airbus for acceptance of the
method used to do these steps.
Note
If it is not possible to correctly identify pre-existing repairs and/or damage
within ASRP-permitted damage limits from the aircraft maintenance

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first page of the DM
BD500-A-J53-00-12-01AAA-933A-A
BD500-A-J53-00-12-01AAA-933A-A
 2023-09-13  Page 3
records, it is necessary to do a detailed inspection of the affected structures
shown in Table 6. If this is necessary, speak with a CRC representative to
get a detailed inspection procedure.
1.2.1 Identify all repairs for the Air Transport Association (ATA)
structures in Table 6 that were done after the aircraft received
its Certificate of Airworthiness (CofA). If a repair was done in an
ATA given in Table 6, speak with a CRC representative at 1 866
A220 CRC (1-866-222-0272) or 1-450-476-7676 or e-mail at
A220_crc@abc.airbus for analysis and to get an approved disposition
to complete this service bulletin. Airbus Canada specific Repair
Engineering Order (REO) with an issue date later than December 31,
2022 have already been validated and therefore do not require an
additional approved disposition.
1.2.2 Identify all damage for the ATA structures in Table 6 that were
within ASRP-permitted damage limits dispositioned after the
aircraft received its CofA. If you find damage that does not agree
with the ASRP-permitted damage limits in ASRP issue 136.01
or later approved, speak with a CRC representative at  1 866
A220 CRC (1-866-222-0272) or 1-450-476-7676 or e-mail at
A220_crc@abc.airbus for analysis and to get an approved disposition
to complete this service bulletin.
Table 6 Applicable ATA for Repair or Damages
STRUCTURE ATA LOCATION STRUCTURE AREA DETAILS
Tailcone 53-84 Entire Tail-
cone
All external surfaces
(except doors), attach-
ments to aft fuselage,
longerons and forward
lower frame within APU
bay
Internal structure:
(between doghouse
walls and skins) frames/
stringers/skins if area has
ever been accessed by
operator
Appendix A
(refer to BD500-A-
J53-00-12-01AAA-910B-A).
1
Vertical Stabi-
lizer (VStab)
55-31 Upper
VStab main
box and
leading
edge, above
station 412,
Rib 10
Skins and spars
Note
- Skins: Exter-
nal surfaces
only
- Front spar:
only if lead-
ing edge has
been removed
by operator
Internal surfaces (skins,
spars, and ribs) only if
operator has accessed
area
Appendix B
(refer to BD500-A-
J53-00-12-02AAA-910B-A).
1

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BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-01AAA-933A-A
BD500-A-J53-00-12-01AAA-933A-A
End of data module
 2023-09-13  Page 4
STRUCTURE ATA LOCATION STRUCTURE AREA DETAILS
Wing 57-21 Wing Main torque box lower
skin, spars, ribs
Winglet 57-31 Winglet Skins external surfaces
Internal surfaces (skins,
spars) only if operator
has accessed area
Appendix C
(refer to BD500-A-
J53-00-12-03AAA-910B-A).
1
1 If it cannot be confirmed from the maintenance records if there was or was not damage on the
applicable ATA structure, an inspection sufficient to determine if there is rework/repair and/or
permitted damage, (either, General Visual Inspection (GVI), Detailed Visual Inspection (DVI), or
Non Destructive Inspection (NDI), of these areas may be necessary to confirm that there were no
previous damage dispositions.
1.2.3 Contact the CRC to identify any pre CofA Report of Non-Conformance
(RNCs) that require further action, and to get an approved disposition,
if applicable, to complete this service bulletin.
2 Administrative
When this service bulletin is completed, record in the applicable aircraft records that
you have completed this service bulletin.
Note
The service bulletin cannot be closed until RNC check and repairs check are
complete. If any disposition is required, that must also be implemented prior
to closure of SB. The aircraft can continue operating pending confirmation
from Airbus engineering and CRC that all RNCs and repairs are reviewed and
dispositioned.
Requirements after job completion
Required conditions
Table 7  Required conditions
Action/Condition Data Module/Technical publication
None

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BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-01AAA-910B-A
BD500-A-J53-00-12-01AAA-910B-A
 2023-09-13  Page 1
Appendix A - A220-300 Tailcone Missed Loop 3 Inspection Areas
 
Applicability: 55003-55191, 55193, 55195-55196, 55198-55202, 55205, 55209-55210, 55228, 55231, 55244,
55246-55248, 55250
 
Table of contents Page
Appendix A - A220-300 Tailcone Missed Loop 3 Inspection Areas .......................................... 1
References................................................................................................................................ 1
Description................................................................................................................................. 1
List of tables Page
1 References.................................................................................................................. 1
List of figures Page
1 Tailcone Inspection Areas........................................................................................... 2
References
Table 1  References
Data Module/Technical Publication Title
None
Description

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BD500-530012
 
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first page of the DM
BD500-A-J53-00-12-01AAA-910B-A
BD500-A-J53-00-12-01AAA-910B-A
 2023-09-13  Page 2
DOC: MAS-BA500-667
REV: --
PAGE: 4-6 of 4-10
DATE: 2023-05-03
ECCN: N/A
Interim Loads Loop Factors and Instructions Development Report 
SECTION 4 - WP 6.13 & 31  - Composite & Metallic Tailcone 
© AIRBUS CANADA LIMITED PARTNERSHIP. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
© SOCIÉTÉ EN COMMANDITE AIRBUS CANADA. TOUS DROITS RESERVES. DOCUMENT CONFIDENTIEL ET CONTENANT DES RENSEIGNEMENTS COMMERCIAUX EXCLUSIFS.
ACT0120-25 GT 2019-05 
4. IMPACTED AREAS BY MISSED LOOP 3 CASES 
All below schematics are extracted from Ref [5.4] and [5.5]. 
4.1 EXTERNAL STRUCTURE IMPACTED  
All skin panels are impacted by A220-100 & A220-300 missed loop 3 cases. 
FIGURE 4-1 –TAILCONE SKINS 
The structure shown on this figure,  skins 1-4 
are impacted by increased loads
Note 1:  
If existence or absence of damages on these 
components cannot be ascertained from a check 
of maintenance records, a General Visual 
Inspection (GVI) of these areas may be required 
to confirm absence of previous damage 
dispositions. 
ICN-BD500-A-J530012-F-3AB48-93365-A-002-01
Figure 1 Tailcone Inspection Areas

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BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-01AAA-910B-A
BD500-A-J53-00-12-01AAA-910B-A
 2023-09-13  Page 3
DOC: MAS-BA500-667
REV: --
PAGE: 4-7 of 4-10
DATE: 2023-05-03
ECCN: N/A
Interim Loads Loop Factors and Instructions Development Report 
SECTION 4 - WP 6.13 & 31  - Composite & Metallic Tailcone 
© AIRBUS CANADA LIMITED PARTNERSHIP. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
© SOCIÉTÉ EN COMMANDITE AIRBUS CANADA. TOUS DROITS RESERVES. DOCUMENT CONFIDENTIEL ET CONTENANT DES RENSEIGNEMENTS COMMERCIAUX EXCLUSIFS.
ACT0120-25 GT 2019-05 
4.2 INTERNAL STRUCTURES IMPACTED (TO BE INSPECTED ONLY IF ACCESSED 
BY OPERATOR DURING MAINTENANCE OR REPAIR ACTIVITY) 
All stringers, frames, and longerons are impacted by A220-100 & A220-300 missed loop 3 
cases. Note that stringer clips are not considered affected by missed loop 3. 
FIGURE 4-2 –TAILCONE STRINGERS 
The internal tailcone Stringers 1-29 shown on this 
figure are impacted by increased loads
Note 2:  
Inspection of these stringers required only if 
internal structure has accessed by the operator 
(expected only for implementation of a major 
repair) 
In this event, if existence or absence of damages 
on these components cannot be ascertained from 
a check of maintenance records, a General Visual 
Inspection (GVI) of these areas may be required to 
confirm absence of previous damage dispositions. 
ICN-BD500-A-J530012-F-3AB48-93365-A-002-01
Figure 1 Tailcone Inspection Areas

### Page 18

BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-01AAA-910B-A
BD500-A-J53-00-12-01AAA-910B-A
 2023-09-13  Page 4
DOC: MAS-BA500-667
REV: --
PAGE: 4-8 of 4-10
DATE: 2023-05-03
ECCN: N/A
Interim Loads Loop Factors and Instructions Development Report 
SECTION 4 - WP 6.13 & 31  - Composite & Metallic Tailcone 
© AIRBUS CANADA LIMITED PARTNERSHIP. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
© SOCIÉTÉ EN COMMANDITE AIRBUS CANADA. TOUS DROITS RESERVES. DOCUMENT CONFIDENTIEL ET CONTENANT DES RENSEIGNEMENTS COMMERCIAUX EXCLUSIFS.
ACT0120-25 GT 2019-05 
All frames are impacted by A220-100 & A220-300 missed loop 3 cases. 
FIGURE 4-3 - TAILCONE FRAMES, INTERCOSTALS, AND LONGERONS 
The internal  Intercostals and Frames (items 
number 2 and 3 on this figure), are impacted by 
increased loads
Note 3:  
Inspection of these frames required only if internal 
structure has accessed by the operator (expected 
only for implementation of a major repair) 
In this event, if existence or absence of damages 
on these components cannot be ascertained from 
a check of maintenance records, a General Visual 
Inspection (GVI) of these areas may be required to 
confirm absence of previous damage dispositions. 
ICN-BD500-A-J530012-F-3AB48-93365-A-002-01
Figure 1 Tailcone Inspection Areas

### Page 19

BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-01AAA-910B-A
BD500-A-J53-00-12-01AAA-910B-A
 2023-09-13  Page 5
DOC: MAS-BA500-667
REV: --
PAGE: 4-9 of 4-10
DATE: 2023-05-03
ECCN: N/A
Interim Loads Loop Factors and Instructions Development Report 
SECTION 4 - WP 6.13 & 31  - Composite & Metallic Tailcone 
© AIRBUS CANADA LIMITED PARTNERSHIP. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
© SOCIÉTÉ EN COMMANDITE AIRBUS CANADA. TOUS DROITS RESERVES. DOCUMENT CONFIDENTIEL ET CONTENANT DES RENSEIGNEMENTS COMMERCIAUX EXCLUSIFS.
ACT0120-25 GT 2019-05 
4.3 STRUCTURE WITHIN APU BAY 
The following structure within the APU bay is impacted: fwd lower frame, the longeron, and the fwd longeron 
fitting shown below :
FIGURE 4-4 – STRUCTURE WITHIN APU BAY (LONGERONS, LOWER FRAME) 
(View looking Up and Forward into Tailcone APU Bay 
Left Hand Side Longeron shown, both left and right sides are impacted)
The structure shown on this figure, the LHS & RHS longeron 
and fwd longeron fitting (item 8 within the Blue box), and   the 
fwd lower portion of frame 86 (within the Green box) are 
impacted by increased loads
Note 4:  
If existence or absence of damages on applicable these 
components cannot be ascertained from a check of 
maintenance records, a General Visual Inspection (GVI) of the 
section of the longerons & fittings and Lower Frame  visible from 
the APU bay may be required to confirm absence of previous 
damage dispositions. 
Note 5: 
The portion of the longerons and fittings and frame that are 
inaccessible from the APU bay need only be inspected if the 
operator has accessed this area, such as during a major repair  
View looking Up and Forward 
into Tailcone APU Bay 
ICN-BD500-A-J530012-F-3AB48-93365-A-002-01
Figure 1 Tailcone Inspection Areas

### Page 20

BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-01AAA-910B-A
BD500-A-J53-00-12-01AAA-910B-A
End of data module
 2023-09-13  Page 6
DOC: MAS-BA500-667
REV: --
PAGE: 4-10 of 4-10
DATE: 2023-05-03
ECCN: N/A
Interim Loads Loop Factors and Instructions Development Report 
SECTION 4 - WP 6.13 & 31  - Composite & Metallic Tailcone 
© AIRBUS CANADA LIMITED PARTNERSHIP. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
© SOCIÉTÉ EN COMMANDITE AIRBUS CANADA. TOUS DROITS RESERVES. DOCUMENT CONFIDENTIEL ET CONTENANT DES RENSEIGNEMENTS COMMERCIAUX EXCLUSIFS.
ACT0120-25 GT 2019-05 
4.4 AFT FUSELAGE ATTACHMENT FITTINGS 
All following aft fuselage attachment fittings are impacted by A220-100 & A220-300 missed 
loop 3 cases. 
FIGURE 4-5 – AFT FUSELAGE ATTACHMENT FITTINGS 
The aft fuselage attach fittings, items 1 and 2 upper lugs, item 3 
lower lug, item 5 lower spigot and item 6 links on the figure below, 
(both sides of joint, tailcone and aft fuse side) are impacted by 
increased loads
Note 5:  
If existence or absence of damages on these components cannot 
be ascertained from a check of maintenance records, a General 
Visual Inspection (GVI) of may be required to confirm absence of 
previous damage dispositions. 
Joint disassembly not required unless there are visual indications 
of rework 
ICN-BD500-A-J530012-F-3AB48-93365-A-002-01
Figure 1 Tailcone Inspection Areas

### Page 21

BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-02AAA-910B-A
BD500-A-J53-00-12-02AAA-910B-A
 2023-09-13  Page 1
Appendix B - A220-300 VStab Missed Loop 3 Inspection Areas
 
Applicability: 55003-55191, 55193, 55195-55196, 55198-55202, 55205, 55209-55210, 55228, 55231, 55244,
55246-55248, 55250
 
Table of contents Page
Appendix B - A220-300 VStab Missed Loop 3 Inspection Areas ............................................. 1
References................................................................................................................................ 1
Description................................................................................................................................. 1
List of tables Page
1 References.................................................................................................................. 1
List of figures Page
1 VStab Inspection Areas .............................................................................................. 2
References
Table 1  References
Data Module/Technical Publication Title
None
Description

### Page 22

BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-02AAA-910B-A
BD500-A-J53-00-12-02AAA-910B-A
 2023-09-13  Page 2
 
Final 
 
DOC: MAS-BA500-667 
REV: -- 
PAGE: 4-17  of  3-18 
DATE: 2023-04-18 
ECCN: N/A 
Interim Loads Loop Factors and Instructions Development Report 
SECTION 3 - Vertical Stabilizer (VStab) 
 
© AIRBUS CANADA LIMITED PARTNERSHIP. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 
© SOCIÉTÉ EN COMMANDITE AIRBUS CANADA. TOUS DROITS RESERVES. DOCUMENT CONFIDENTIEL ET CONTENANT DES RENSEIGNEMENTS COMMERCIAUX EXCLUSIFS. 
ACT0120-25 GT 2019-05 
 
 EC_NotTechnical US_EC_NoUSContent 
Airbus Amber / EC_NotTechnical 
 
 
Figure 9: External structure to be reviewed at VStab; LH-/RH-Skin (structure within red box) 
Note 1: If existence or absence of damages 
on applicable ATA structure cannot be 
ascertained from a check of maintenance 
records, an external inspection sufficient to 
determine presence or lack of rework/repair 
and/or permitted damage, (either GVI, DVI , 
or NDI) of these areas may be required to 
confirm absence of previous damage 
dispositions. 
For the structure within the red box on this 
figure this means an external inspection of 
left and right hand side main torque box 
skins. 
ICN-BD500-A-J530012-F-3AB48-93366-A-002-01
Figure 1 VStab Inspection Areas

### Page 23

BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-02AAA-910B-A
BD500-A-J53-00-12-02AAA-910B-A
End of data module
 2023-09-13  Page 3
 
Final 
 
DOC: MAS-BA500-667 
REV: -- 
PAGE: 4-18  of  3-18 
DATE: 2023-04-18 
ECCN: N/A 
Interim Loads Loop Factors and Instructions Development Report 
SECTION 3 - Vertical Stabilizer (VStab) 
 
© AIRBUS CANADA LIMITED PARTNERSHIP. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 
© SOCIÉTÉ EN COMMANDITE AIRBUS CANADA. TOUS DROITS RESERVES. DOCUMENT CONFIDENTIEL ET CONTENANT DES RENSEIGNEMENTS COMMERCIAUX EXCLUSIFS. 
ACT0120-25 GT 2019-05 
 
 EC_NotTechnical US_EC_NoUSContent 
Airbus Amber / EC_NotTechnical 
 
Figure 10: Internal structure to be reviewed at VStab; Front-/Rear-Spar, Tip Closure Rib (required only if internal 
structure has been accessed by operator) 
 
Note 2: If operator has accessed the 
interior of the VStab box as part of a 
major repair operation, it must be 
verified if there is damage to the main 
torque-box IML, stringers, ribs, and 
spars in the area within the red box. 
Note 3: If operator has accessed 
the VStab front spar by removing 
the leading edge, it must be verified 
if there is damage to the main 
torque-box front spar in the area 
within the red box.  
ICN-BD500-A-J530012-F-3AB48-93366-A-002-01
Figure 1 VStab Inspection Areas

### Page 24

BD500-530012
 
Intentionally left blank
See applicability on the
first page of the DM
BD500-A-J53-00-12-02AAA-910B-A
BD500-A-J53-00-12-02AAA-910B-A
 2023-09-13  Page 4

### Page 25

BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-03AAA-910B-A
BD500-A-J53-00-12-03AAA-910B-A
 2023-09-13  Page 1
Appendix C - A220-300 Wing Missed Loop 3 Inspection Areas
 
Applicability: 55003-55191, 55193, 55195-55196, 55198-55202, 55205, 55209-55210, 55228, 55231, 55244,
55246-55248, 55250
 
Table of contents Page
Appendix C - A220-300 Wing Missed Loop 3 Inspection Areas .............................................. 1
References................................................................................................................................ 1
Description................................................................................................................................. 1
List of tables Page
1 References.................................................................................................................. 1
List of figures Page
1 Wing Inspection Areas ................................................................................................ 2
References
Table 1  References
Data Module/Technical Publication Title
None
Description

### Page 26

BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-03AAA-910B-A
BD500-A-J53-00-12-03AAA-910B-A
 2023-09-13  Page 2
 
Final 
DOC: MAS-BA500-667 
REV: -- 
PAGE: 5-20  of  2-23 
DATE: 2023-04-25 
ECCN: US_EC_EAR99, 
UK_EC_DU_PL9009.C 
Interim Loads Loop Factors and Instructions Development Report 
SECTION 2 - Wing 
 
© AIRBUS CANADA LIMITED PARTNERSHIP. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 
© SOCIÉTÉ EN COMMANDITE AIRBUS CANADA. TOUS DROITS RESERVES. DOCUMENT CONFIDENTIEL ET CONTENANT DES RENSEIGNEMENTS COMMERCIAUX EXCLUSIFS. 
ACT0120-25 GT 2019-05 
 
 
FIGURE 5-1: FCBS TO BE REVIEWED ON WING – LOWER SKIN AND ACCESS HOLES 
 
Note: 
If existence or absence of damages on applicable ATA structure cannot be ascertained from a 
check of maintenance records, an inspection sufficient to determine presence or lack of 
rework/repair and/or permitted damage, (either GVI, DVI, or NDI) of these areas may be 
required to confirm absence of previous damage dispositions. 
For the structure shown on this figure, areas in red are to be inspected inside the tank and 
externally. Ensure access holes are inspected with the fuel tank access panels removed.  
Note 2: Reporting of lightning strike protection copper mesh rework/repair not required per this 
SB. 
ICN-BD500-A-J530012-F-3AB48-93367-A-002-01
Figure 1 Wing Inspection Areas

### Page 27

BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-03AAA-910B-A
BD500-A-J53-00-12-03AAA-910B-A
 2023-09-13  Page 3
 
Final 
DOC: MAS-BA500-667 
REV: -- 
PAGE: 5-21  of  2-23 
DATE: 2023-04-25 
ECCN: US_EC_EAR99, 
UK_EC_DU_PL9009.C 
Interim Loads Loop Factors and Instructions Development Report 
SECTION 2 - Wing 
 
© AIRBUS CANADA LIMITED PARTNERSHIP. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 
© SOCIÉTÉ EN COMMANDITE AIRBUS CANADA. TOUS DROITS RESERVES. DOCUMENT CONFIDENTIEL ET CONTENANT DES RENSEIGNEMENTS COMMERCIAUX EXCLUSIFS. 
ACT0120-25 GT 2019-05 
 
 
FIGURE 5-2: FCBS TO BE REVIEWED ON WING – FRONT SPAR 
 
Note: 
If existence or absence of damages on applicable ATA structure cannot be ascertained from a 
check of maintenance records, an inspection sufficient to determine presence or lack of 
rework/repair and/or permitted damage, (either GVI, DVI, or NDI) of these areas may be 
required to confirm absence of previous damage dispositions. 
For the structure shown on this figure, the area in red is to be inspected from inside the tank. 
 
ICN-BD500-A-J530012-F-3AB48-93367-A-002-01
Figure 1 Wing Inspection Areas

### Page 28

BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-03AAA-910B-A
BD500-A-J53-00-12-03AAA-910B-A
 2023-09-13  Page 4
 
Final 
DOC: MAS-BA500-667 
REV: -- 
PAGE: 5-22  of  2-23 
DATE: 2023-04-25 
ECCN: US_EC_EAR99, 
UK_EC_DU_PL9009.C 
Interim Loads Loop Factors and Instructions Development Report 
SECTION 2 - Wing 
 
© AIRBUS CANADA LIMITED PARTNERSHIP. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 
© SOCIÉTÉ EN COMMANDITE AIRBUS CANADA. TOUS DROITS RESERVES. DOCUMENT CONFIDENTIEL ET CONTENANT DES RENSEIGNEMENTS COMMERCIAUX EXCLUSIFS. 
ACT0120-25 GT 2019-05 
 
 
FIGURE 5-3: FCBS TO BE REVIEWED ON WING – WINGLET 
 
Note: 
If existence or absence of damages on applicable ATA structure cannot be ascertained from a 
check of maintenance records, an inspection sufficient to determine presence or lack of 
rework/repair and/or permitted damage, (either GVI, DVI, or NDI) of these areas may be 
required to confirm absence of previous damage dispositions. 
For the structure shown on this figure, the upper and lower skins are to be inspected externally. 
The areas in red (spars, root fitting) are to be internally inspected if the area has ever been 
accessed by an operator. 
ICN-BD500-A-J530012-F-3AB48-93367-A-002-01
Figure 1 Wing Inspection Areas

### Page 29

BD500-530012
 
See applicability on the
first page of the DM
BD500-A-J53-00-12-03AAA-910B-A
BD500-A-J53-00-12-03AAA-910B-A
End of data module
 2023-09-13  Page 5
 
Final 
DOC: MAS-BA500-667 
REV: -- 
PAGE: 5-23  of  2-23 
DATE: 2023-04-25 
ECCN: US_EC_EAR99, 
UK_EC_DU_PL9009.C 
Interim Loads Loop Factors and Instructions Development Report 
SECTION 2 - Wing 
 
© AIRBUS CANADA LIMITED PARTNERSHIP. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 
© SOCIÉTÉ EN COMMANDITE AIRBUS CANADA. TOUS DROITS RESERVES. DOCUMENT CONFIDENTIEL ET CONTENANT DES RENSEIGNEMENTS COMMERCIAUX EXCLUSIFS. 
ACT0120-25 GT 2019-05 
 
 
FIGURE 5-4: FCBS TO BE REVIEWED ON WING – SLATS AND FIXED LEADING EDGE 
 
Note: 
If existence or absence of damages on applicable ATA structure cannot be ascertained from a 
check of maintenance records, an inspection sufficient to determine presence or lack of 
rework/repair and/or permitted damage, (either GVI, DVI, or NDI) of these areas may be 
required to confirm absence of previous damage dispositions. 
For the structure shown on this figure, areas in red are to be inspected externally. Internal 
structure (ribs) are to be internally inspected if the area has ever been accessed by an 
operator. 
 
ICN-BD500-A-J530012-F-3AB48-93367-A-002-01
Figure 1 Wing Inspection Areas

### Page 30

BD500-530012
 
Intentionally left blank
See applicability on the
first page of the DM
BD500-A-J53-00-12-03AAA-910B-A
BD500-A-J53-00-12-03AAA-910B-A
 2023-09-13  Page 6

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