# De Havilland Canada Service Bulletin 84-54-32

Copy: No revision named ("84-54-32 - Released Copy"), 12 pages: PDF https://openairdocs.org/files/sha256/29/16/2916713cc91ff29ba241c1a72ea8e2190b627340d4afc867219bac0a00324c66; text https://openairdocs.org/service-documents/bombardier/sb-84-54-32/file/2916713cc91f.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2021-0183; AD 2021-12-02 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md) (issued as De Havilland Canada)
- Type: Service bulletin (Service Bulletin)
- Number: 84-54-32
- Page: https://openairdocs.org/service-documents/bombardier/sb-84-54-32

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

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

- [AD 2021-12-02](https://openairdocs.org/ad/2021-12-02.md), effective Jul 20, 2021: No revision named

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-84-54-32/proposed.md).

## Text (12 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2021-0183; AD 2021-12-02 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.

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SERVICE BULLETIN
Customer
Support
ATA SYSTEM: 54136 NUMBER: 84- - -54- - -32
DE HAVILLAND AIRCRAFT OF CANADA LIMITED (DHC) CONSIDERS
URGES OPERATORS TO PROMPTL Y EVALUATE THE CONTENTS
THIS SERVICE BULLETIN TO BE PARTICULARL Y SIGNIFICANT AND
SUBJECT : Nacelle - - - MLG Side Brace Fitting to ’A’ Frame Joint - - - Cold Working of
Holes - - - ModSum 4- - - 114003
1. PLANNING INFORMA TION
A. Effectivity
Aircraft Affected:
In- - -Service: DHC- - -8 Aircraft Models 401 and 402 Serial Numbers 4081 - - -
4591.
NOTE 1: The following A/C were reworked using NCRs. These aircraft will be
require to be part marked via instructions in this service bulletin.
A/C 4583 reworked per NCR D118010372
A/C 4584 reworked per NCR D118010373
A/C 4585 reworked per NCR D118010374
A/C 4586 reworked per NCR D118009871 (LHS) and D118009873
(RHS)
A/C 4587 reworked per NCR D118010415
A/C 4588 reworked per NCR D118010413
A/C 4589 reworked per NCR V018052076 (LHS) V018052072 (RHS)

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A/C 4590 reworked per NCR D118009769
A/C 4591 reworked per NCR V018053449 (LHS) and V018053452
(RHS)
NOTE 2: All the reworked parts are life limited and the accumulated life of the
parts pre- - -worked is to be transferred to the reworked parts
NOTE 3: The instructions in this service bulletin are only applicable to the
systems and parts installed at the time of delivery on the aircraft or as
changed by DeHavilland Aircraft of Canada Service Bulletin(s). Before
you do this bulletin, examine all STC or equivalent action changes to
make sure this bulletin can be completed.
Spares Affected:
None
B. Reason
Problem: The part manufacturer has reported that the Side Brace fittings to
’A’- - -frame joint on the nacelle that some fastener holes were not cold
worked (eight holes per nacelle).
As a result the side brace fitting might not meet its fatigue life. This could
lead to cracking on the ’A’ frame.
This problem affects both the left hand and right hand nacelles.
Cause: The parts were not manufactured according to engineering drawings.
Solution: This service bulletin introduces ModSum 4- - -114003. The ModSum directs
operators to remove fasteners on the ’A’ frame and side brace assembly,
cold work the holes and re- - -install oversize fasteners.
C. Description
The procedures in this service bulletin give the instructions to do the tasks that follow:
- - - aircraft electrical power is removed
- - - the aircraft is put on jacks
- - - the nose landing gear lock is engaged
- - - the main landing gear lock pins are installed thru each main gear door mechanism

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- - - the main landing gear stabilizer strut is removed
For aircraft not previously reworked by an NCR
- - - existing fasteners are removed on the side brace assembly
- - - the holes are cold worked
- - - new oversized fasteners are installed
- - - the main landing gear stabilizer strut is re- - -installed
For all aircraft, whether or not they were previously reworked
--- t h e S t a b i l i z e r B r a c e F i t t i n g a n d A --- F r a m e a r e r e --- i d e n t i f i e d
- - - close out.
D. Compliance
DeHavilland Aircraft of Canada Ltd. highly recommend that ModSum 4- - -114003 be
incorporated at the earliest opportunity unless otherwise directed by the operator’s
airworthiness authority.
A Transport Canada Airworthiness Directive is Pending.
E. Approval
The technical content of this service bulletin has been approved under the authority of
the Transport Canada Civil Aviation (TCCA) Design Approval Organization No: DAO
# 1 9 --- Q --- 0 1 .
F. M a n p o w e r
It will take an estimated 14.50 man- - -hour s to complete this service bulletin. The
breakdown of the man- - -hours is shown in the table that follows:
TASK M A N --- H O U R S
J o b S e t --- U p 7.00
Procedure 4.00
T e s t/R T S 1.50
Close- - -Out 2.00

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This estimate is for direct labor done by an experienced crew and it does not include,
planning, familiarization, cure time, part fabrication, tool acquisition or lost time.
G. Material - - - Price and Availability
The ModKit(s) required to do this service bulletin is/are listed in the table below:
Kit Number Description
8MK4862- - -001 Kit - - - Cold Working if Holes - - - MLG ’A’
Frame Nacelle
Operators should submit a purchase orde r through the Customer Response Center
(CRC) to the Customer Accounts Service T eam (CAST) at DeHavilland Aircraft of
Canada specifying aircraft serial number(s) to:
DE HAVILLAND AIRCRAFT OF CANADA LIMITED
Material Services
123 Garratt Blvd.
To r o n t o
Ontario
Canada M3K- - -1Y5
DHC Phone Numbers :
North America:T oll Free: 1 (844)- - -CRC- - -CRC0 (1 (844) 272- - -2720) or
Direct: 1 (514) 855- - -8500
DHC Emails:
Parts: Europe, Middle East, Africa, and Russia: emear.parts@dehavilland.com
Americas and Rest of World: parts@dehavilland.com
H. T ooling - - - Price and Availability
None

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I. Weight and Balance
Not affected
J. Electrical Load Data
Not affected
K. Publications Affected
Aircraft Maintenance Manual PSM 1- - -84- - -2.........................
Aircraft Illustrated Parts Catalog PSM 1- - -84- - -4......................
Maintenance Requirement Manual PSM 1- - -84- - -7....................
ModSums Manual PSM 1- - -84- - -12..................................
L. References
The initial issue of this service bulletin was prepared to the engineering drawings and
related data that follows:
DRAWING SHEET REV
8MK4862 1 ---
8Z7318 1 --- D
ModSum 4Q114003 Rev. ‘F’
ModSum 4- - -114003 Rev. ‘F’
NCR D118010372
NCR D118010373
NCR D118010374
NCR D118009871 (LHS) and D118009873 (RHS)
NCR D118010415
NCR D118010413

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NCR V018052076 (LHS) V018052072 (RHS)
NCR D118009769
NCR V018053449 (LHS) AND V018053452 (RHS)
PCA 47275 Revision - - - (for internal reference only)
Transport Canada Airworthiness Directive Pending.
2. MATERIAL INFORMA TION
A. Parts Required Per Aircraft
(1) Modification Kit 8MK4862- - -001
(2) Detailed Kit Content:
Quantity Per Kit
--- 0 0 1
Part Number Description Remarks
16 B0203016- - -6 Nut
16 HST410AG12- - -11 H i --- L i t e
1 8Z7318 Ref Drawing
B. Parts Required to Modify Spares
None
C. Special T ools and Equipment Required
Refer to SRM TASK 51- - -24- - -55, 4. T ools and Equipment.
D. Existing Parts Accountability
Refer to drawing 8Z7318 Note 15 and 16.

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3. ACCOMPLISHMENT INSTRUCTIONS
If it is not possible to complete all the instructions of this service bulletin because of the
configuration of the aircraft, speak with a representative of DHC in the CRC at 1 (844)
272- - -2720 (1 (844) CRC- - -CRC0) or email at thd@dehavilland.comfor analysis and to get an
approved disposition to complete this service bulletin.
A . J o b S e t --- U p
WARNING: MAKE SURE YOU INSTALL THE LOCKPINS ON THE MAIN LANDING
GEAR. MAKE SURE YOU ENGAGE THE NOSE GEAR LOCK. IF YOU
DO NOT DO THIS, THE LANDING GEAR CAN ACCIDENTALL Y
RETRACT . THIS CAN CAUSE INJURIES TO PERSONS AND
DAMAGE TO THE EQUIPMENT .
WARNING: MAKE SURE YOU INSTALL THE LOCKPINS IN THE DOOR
MECHANISMS OF THE MLG AND NLG. THE DOOR MECHANISMS
CAN ACCIDENTALL Y CLOSE THE LANDING GEAR DOORS. THIS
CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE
EQUIPMENT .
NOTE 1: When doing structural rework make sure to deburr affected fastener
holes then apply a layer of alodine and touch up with epoxy chromate
primer as required.
NOTE 2: Make sure to put a protective cover on any disconnected electrical
connector or any tube, hose, duct and/or line.
(1) Placard and select all aircraft electrical power to OFF . Obey all relevant
W A R N I N G S a n d C A U T I O N S ( r e f e r t o A M M T A S K ’ S 2 4 --- 0 0 --- 0 0 --- 8 6 1 --- 8 0 2 a n d
24- - -00- - -00- - -910- - -801)
(2) Make sure that lock pins are installed through each main gear and main gear
door mechanism.
(3) Make sure the nose gear ground lock is engaged.

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(4) Set wheel chocks in front and behind the landing gear tires.
(5) Set up the work platforms or ladders as required to gain access to nacelle. Make
sure the work platforms or ladders are electrically grounded.
B. Procedure
Part A - - - All aircraft previously not reworked at Bombardier, applicable to 4081- - - 4582.
NOTE 1: The following procedure is applicable to only those aircraft not
previously reworked at DeHavilland Aircraft of Canada.
NOTE 2: This rework can be done with the MLG in place. If the MLG is not
removed then a maximum of 2 fasteners can be removed and
reworked at a time for each side brace assembly.
NOTE 3: The instruction that follow are for the Left Hand nacelle. Right hand
side instructions are similar.
(1) Remove the MLG stabilizer brace and retain hardware. (refer to AMM TASK
32- - -11- - -16- - -000- - -801)
(2) Remove and discard fasteners (8 off) on the side brace sub assemblies. (refer to
drw 8Z7318, SECTION B- - -B, flagnote 10 a n d S R M T A S K 5 1 --- 4 0 --- 1 5 --- 0 2 --- 0 1 )
(3) Remove support angle P/N 82974295- - -103 and rework holes. (refer to drw
8Z7318, SECTION B- - -B and flagnote 9 )
NOTE: The support angle is removed to allow the hydraulic tubes it connects
with to be slightly displaced which will give access for the drilling and
cold working operations.
(4) Drill and ream (8 off) holes using the instructions that follow:(refer to drw
8Z7318, SECTION B- - -B, flagnote 11 a n d S R M T A S K 5 1 --- 4 0 --- 0 7 --- 0 2 --- 0 1 )
(a) For the split sleeve process open holes to 0.375” - - - 0.378”.
(b) For split mandrel process open holes to 0.380 - - - 0.382”.

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(5) For aircraft at 30,000 cycles or above, inspect (8 off) bolt holes using eddy
current inspection refer to NDT manual PSM 1- - -84- - -7A, Part 6, T ask
51- - -00- - -05- - -250- - -801. No crack indications permitted.
(6) Cold work the holes using the instructions that follow: (refer to drw 8Z7318,
S E C T I O N B --- B , f l a g n o t e12 a n d S R M T A S K 5 1 --- 2 4 --- 5 5 --- 0 0 --- 0 1 )
(a) For the split sleeve process use kit STDN 12- - -1.
(b) For the split mandrel process use kit STDN 12- - -2.
(7) Ream holes to 0.4000” to 0.4040” for second oversize 3/8” hi- - -lites. (refer to SRM
T A S K 5 1 --- 4 0 --- 1 5 --- 0 2 --- 0 1 )
(8) Locate and install support angle P/N 82974295- - -103 using the instructions that
follow:
(a) Open holes in the support angle to 0.4062” - - - 0.4097” to match the holes drilled
i n t h e a s s e m b l y. ( r e f e r t o S R M T A S K 5 1 --- 4 0 --- 0 7 --- 0 2 --- 0 1 a n d f l a g n o t e9 )
NOTE: It is acceptable for support angle to have a hole slightly larger then the
A- - -frame / side brace fitting.
(b) Install two hi- - -lites P/N HST410AG12- - -11. (refer to SRM TASK
5 1 --- 4 0 --- 1 5 --- 0 2 --- 0 1 a n d f l a g n o t e13 )
(c) Install two nuts P/N B0203016- - -6.
(9) Install remaining six hi- - -lites P/N HST410AG12- - -11. (refer to SRM TASK
5 1 --- 4 0 --- 1 5 --- 0 2 --- 0 1 a n d f l a g n o t e13 )
(10) Install six nuts P/N B0203016- - -6.

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Part B - - - This step is applicable to aircraft 4081 - - - 4591
(11) Re- - -identify the reworked side brace fitting and A Frame (refer to drw 8Z7318,
T able 1 and AMM T ask 20- - -00- - -01- - -910- - -802)
NOTE: This step is applicable to all aircraft, even the ones where an in- - -house
rework was previously accomplished.
(12) Install the MLG stabilizer brace using retained hardware. (refer to AMM TASK
32- - -11- - -16- - -400- - -801)
C. Close Out
(1) Remove all tools and equipment from the work area.
(2) On incorporation of this ModSum, make an entry that conforms to local
regulatory requirements in the applicable logbook(s). Enter component serial
numbers if applicable. Enter this ModSum number only after complete and
functional incorporation of all work defined in this service bulletin.
(3) Make sure to update life limitations tracking of parts listed in the MRM that are
re- - -identified.
1

### Page 11

Jun 2019
SERVICE BULLETIN (SB) - - - COMMENT SHEET - - - Q SERIES DASH 8 AIRCRAFT
To : SB Focal, DE HAVILLAND AIRCRAFT OF CANADA LIMITED
Phone: 1 (416) 373 - - -5098
Email: george.moffatt@dehavilland.com
From:
Company:
Phone: Extn:
Facsimile: Date:
Email:
Select appropriate box(es) and add comments or suggestions you would like us to know
that may enhance the quality of our service bulletins.
Service Bulletin: Revision: ModSum:
1. PLANNING INFORMATION
V Effectivity V Reason V Description V Compliance
V Approval V Manpower V Material V Weight and Balance
V Electrical Load V T ooling V References V Publications Affected
2. MATERIAL INFORMATION
V Kit Content V Special T ools/Equipment V Parts to Modify Spares
V Consumables V Disposition of Existing Parts V Other
3. ACCOMPLISHMENT INSTRUCTIONS
V J o b S e t --- U p V Procedure V Close- - -Out V Te s t
V Illustration(s) V Other
4. COMMENTS, REMARKS, SUGGESTIONS
Email PDF to:
george.moffatt@dehavilland.com

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Jun 2019
SERVICE BULLETIN (SB)  - - -  RECORD OF INCORPORATION
- - -  Q SERIES DASH 8 AIRCRAFT
To: CMDB Focal
Email: cmdb.requests@dehavilland.com
From:
Company:
Phone: Extn:
Facsimile: Date:
Email:
The data that you provide below will help us record the incorporation of this ModSum
and the aircraft effectivity in the maintenance manual.
Operator: Service Bulletin: __________________ Revision: _________
Aircraft Serial Number:                           Model Number:                           Date Bulletin Completed:
Aircraft Serial Number:                           Model Number:                           Date Bulletin Completed:
Aircraft Serial Number:                           Model Number:                           Date Bulletin Completed:
Aircraft Serial Number:                           Model Number:                           Date Bulletin Completed:
Aircraft Serial Number:                           Model Number:                           Date Bulletin Completed:
Aircraft Serial Number:                           Model Number:                           Date Bulletin Completed:
Aircraft Serial Number:                           Model Number:                           Date Bulletin Completed:
Aircraft Serial Number:                           Model Number:                           Date Bulletin Completed:
Aircraft Serial Number:                           Model Number:                           Date Bulletin Completed:
Aircraft Serial Number:                           Model Number:                           Date Bulletin Completed:
Aircraft Serial Number:                           Model Number:                           Date Bulletin Completed:
Aircraft Serial Number:                           Model Number:                           Date Bulletin Completed:
Email PDF to:
cmdb.request@dehavilland.com

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