# Bombardier Service Bulletin 84-52-94

Copy: Revision B ("84-52-94B"), 20 pages: PDF https://openairdocs.org/files/sha256/d4/5c/d45c4b55067d16364bf835488aa81bb83070198368399a0c0b111dd5e77de359; text https://openairdocs.org/service-documents/bombardier/sb-84-52-94/file/d45c4b55067d.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2020-0200; AD 2020-21-03 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md)
- Type: Service bulletin (Service Bulletin)
- Number: 84-52-94
- Latest revision known: 84-52-94, Revision B, dated February 26, 2020 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/sb-84-52-94

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

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

- [AD 2020-21-03](https://openairdocs.org/ad/2020-21-03.md), effective Nov 18, 2020: Revisions A and B

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-84-52-94/proposed.md).

## Text (20 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2020-0200; AD 2020-21-03 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

Revision ‘B’ 26 Feb 2020
T x L t r S B 8 4 --- 5 2 --- 9 4
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D H C --- 8 ( D A S H 8 )
S E R V I C E B U L L E T I N 8 4 --- 5 2 --- 9 4
Doors - - - Translating - - - T ype 1 Emergency Door Handle Installation - - -
Introduction of a New Bracket to Secure Crank Assy Bolts - - - ModSum
4 - - - 113962
This page transmits Revision ‘B’ of Service Bulletin 84- - -52- - -94, pages 1 thru
16 dated 26 Feb 2020.
This service bulletin is re- - -issued in its entirety for the reasons that follow:
- - - The format of the SB is updated in accordance to the new De Havilland
format
--- T h eEffectivity section revised to include the related ModSums
--- t h eCompliance section is revised to add a reference to Transport Canada
Airworthiness Directive AD CF- - -2014- - -08R1
--- T h eReferences section is revised to convey the latest revision of the
service bulletin and to add a reference to Transport Canada Airworthiness
Directive AD CF- - -2014- - -08R1. Also the related ModSums are removed from
the references section and added in the effectivity section.
--- T h eProcedure section is revised to update Note and AMM TASKs
The Compliance in the previous issues of this service bulletin is not affected
by this revision. No additional rework to the aircraft is introduced by this
revision.
Remove the previous revision of Service Bulletin 84- - -52- - -94 and replace
with attached.
Previous issues of Service Bulletin 84- - -52- - -94:
Initial issue - - - Pages 1 thru 14 dated 10 May 2017
Revision ‘A’ - - - Pages 1 thru 14 dated 24 Jan 2018

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SERVICE BULLETIN
ATA SYSTEM: 5200 NUMBER: 84- - -52- - -94
DE HAVILLAND AIRCRAFT OF CANADA LIMITED (DHC) CONSIDERS
URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS
THIS SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND
S U B J E C T: D o o r s --- T r a n s l a t i n g --- Ty p e 1 E m e r g e n c y D o o r H a n d l e I n s t a l l a t i o n ---
Introduction of a New Bracket to Secure Crank Assy Bolts - - - ModSum
4 - - -113962
1. PLANNING INFORMA TION
A. Effectivity
Aircraft Affected:
In- - - Service: DHC- - - 8 Aircraft Models 401 and 402 Serial Numbers 4455,
4458, 4479, 4480, 4504 thru 4506, 4519, 4528 and 4530.
Related ModSum Title
4- - - 190460 D o o r s --- Tr a n s l a t i n g --- H a n d l e I n s t a l l a t i o n ---
Introduction of a New bracket to Secure Crank Assy
Bolts
4- - - 113923 D o o r s --- Tr a n s l a t i n g --- A f t E n t r y --- H a n d l e I n s t a l l a -
tion - - - Introduction of a New bracket to Secure
Crank Assy Bolts - - - Retrofit only

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Related ModSum Title
4- - - 113960 D o o r s --- Tr a n s l a t i n g --- A f t S e r v i c e D o o r --- H a n d l e
Installation - - - Introduction of a New bracket to Se-
cure Crank Assy Bolts - - - (Retrofit only)
4- - - 113961 D o o r s --- Tr a n s l a t i n g --- F w d B a g g a g e D o o r --- H a n -
dle Installation - - - Introduction of a New bracket to
Secure Crank Assy Bolts - - - (Retrofit only)
NOTE: 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 DHC 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: Operators have reported instances of the bolts securing the crank
assembly (85217919) on the Type 1 emergency exit door becoming loose
during operation.
Solution: This service bulletin introduces ModSum 4- - - 113962. The ModSum installs
a new bracket, new bolts and washers to secure the crank assembly. The
bolts will be lock- - -wired to the bracket to prevent any rotation.
C. Description
The procedures in this service bulletin give the instructions to do the tasks that follow:
- - - Aircraft electrical power is removed
- - - The nose landing gear lock is engaged
- - - The main landing gear lock pins are installed through each main gear and main gear
door mechanism
- - - Access the forward Type 1 emergency exit door crank assembly

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Revision ‘B’ 26 Feb 2020
- - - Existing bolts and washers are removed on the crank assembly
- - - A new bracket is installed with new bolts and washers
- - - New bolts are lockwired to the new bracket
- - - Operational test of the door is done
--- D o o r l i n e r i s r e --- i n s t a l l e d
--- C l o s e o u t .
D. Compliance
DE HAVILLAND AIRCRAFT OF CANADA LIMITED highly recommends that ModSum
4- - - 113962 be incorporated at the earliest opportunity unless otherwise directed by the
operator’s airworthiness authority.
Transport Canada Airworthiness Directive AD CF- - - 2014- - - 08R1.
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
# 9 3 --- Q --- 0 2 .
This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage
T olerance Inspections (DTIs).
F. M a n p o w e r
It will take an estimated 8.00 man- - -hours 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 1.50
Procedure 4.00
T e s t/R T S 0.50
Close- - -Out 2.00
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.

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G. Material - - - Price and Availability
The ModKit required to do this service bulletin is listed in the table below:
Kit Number Description
8MK4803- - - 007 Kit B r a c k e t --- B o l t L o c k i n g , D o o r H a n d l e ---
Fuse
Operators should submit a purchase order through the Customer Response Center
(CRC) to the Customer Accounts Service T eam (CAST) at DHC specifying aircraft
serial number(s). Submit the purchase order 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
I. Weight and Balance
Not affected

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J. Electrical Load Data
Not affected
K. Publications Affected
Aircraft Maintenance Manual PSM 1- - - 84- - - 2.........................
Aircraft Illustrated Parts Catalog PSM 1- - -84- - -4......................
ModSums Manual PSM 1- - - 84- - - 12..................................
L. References
The revision ‘B’ of this service bulletin was prepared to the engineering drawings and
related data that follows:
DRAWING SHEET REV
8MK4803 1 A
8Z8451 1 B
8Z8451 2 A
ModSum 4Q113962 Rev. ‘C’
ModSum 4- - - 113962 Rev. ‘C’
PCA 46188 Revision 0 (for internal reference only)
Transport Canada Airworthiness Directive AD CF- - - 2014- - - 08R1.
2. MATERIAL INFORMA TION
A. Parts Required Per Aircraft
(1) Modification Kit 8MK4803- - - 007

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(2) Detailed Kit Content:
Quantity Per Kit
--- 0 0 7
Part Number Description Remarks
2 NAS1149C0416R Washer NOTE
2 NAS6204- - - 3H Bolt NOTE
1 85210534- - - 103 Bracket
1 8Z8451 R e t r o f i t --- B r a c k e t
Instl
Drawing Only
NOTE: Item to be procured by the operator .
(3) In addition to the above part(s), the following material(s) are required for the
completion of this service bulletin and may be procured as single items from
DHC or purchased directly from industry sources.
Each consumable product listed in the table below is given its own unique
Product ID Number. The number is used to identify a particular recommended
product, the specifications and the trade names any of which can be used unless
specified otherwise (refer to PSM 1- - -84- - -18, Consumable Products Manual).
Consumable
Product ID
Number
Qty. Per Aircraft Description Remarks
14- - - 46 A/R Lockwire MS20995C20
AS3510- - - 0106K 2 Safety Cable NOTE
NOTE: AS3510- - - 0106K safety Cable may be used as an alternate to lockwire.

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B. Parts Required to Modify Spares
None
C. Special T ools and Equipment Required
None
D. Existing Parts Accountability
The following parts may be affected by this service bulletin. Indented parts are
components of the next higher assembly. The quantity (Qty.) column lists the quantity
that may be affected per aircraft for non- - - indented parts and the quantity per next
higher assembly for indented parts.
Existing
Part Number Description Qty. IC DC
New Part
Number PNC
NAS6204- - - 3 Bolt 2 B DIS NAS6204- - - 3H S
AN960C416L Washer 4 B DIS NAS1149C0416R S
IC Interchangeability Code
A Not interchangeable.
B Removed Part. No direct replacement.
C Conditionally Interchangeable. Installation of superseded part negates the
intent of this service bulletin.
DC Disposition
DIS Discard Part.
MUI Multiple Usage Item: Return to stock if serviceable.
RWK Rework existing part in accordance with this service bulletin.
RWI Rework existing part per .....
SAL Salvage. Return to operator’s stores for salvage consideration.

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PNC Part Number Code
N No equivalent DHC part number for reworked part. Indicate on part that
this service bulletin has been accomplished.
R Part number after rework.
S Superseding or equivalent part number.
X Reworked part and superseding part are functionally and physically
equivalent but not identical.
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: This installation forms part of an Aircraft interior. Make sure highest
standard of fit, form and function is maintained.
NOTE 1: The steps in the Job Set- - -Up section of this service bulletin are
recommended steps. The steps give a recommendation to get access
to the work area. This recommendation is to give a safe work area and
to minimize possible damage to surrounding aircraft parts. Alternative
steps can be used at the operator’s discretion.

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(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.
(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 the doors.
Make sure the work platforms or ladders are electrically grounded.
B. Procedure
Refer to Figure 1 and Figure 2
NOTE: T ype 1 Emergency Door is applicable to the cargo combi and
increased capacity configuration only.
(1) Remove the internal door handle. and retain hardware (refer to the applicable
instructions in AMM TASK 52- - - 24- - - 01- - - 000- - - 803).
(2) Remove Type 1 emergency door liner (refer to applicable instructions in AMM
TASK 25- - - 26- - - 16- - - 000- - - 802).
(3) Gain access to the crank assembly 85217919. and retain parts and hardware
( r e f e r t o a p p l i c a b l e i n s t r u c t i o n s i n A M M T A S K 5 2 --- 2 4 --- 0 1 --- 0 0 0 --- 8 0 3 a n d d r a w i n g
8Z8451, SECTION B- - - B).
(a) Remove and discard existing bolts NAS6204- - - 3 (Qty. 2) and washers
NAS1149C0432R (Qty. 4).
(b) Install new bracket 85210534- - - 103 with bolts NAS6204- - - 3H (Qty. 2) and
washers NAS1149C0416R (Qty. 2). Refer to drw 8Z8451 sheets 1 & 2, flagnotes
15 , 16 and Figure 2 (Sheet 1).
(c) Secure bolts with adhesive (Loctite). (refer to the applicable instructions in AMM
TASK 51- - - 23- - - 28- - - 390- - - 802 and drw 8Z8451 Sht. 1 DETAIL C)
1 T orque the bolts NAS6204- - - 3H (Qty. 2) (refer to AMM TASK 20- - - 10- - - 01
430- - - 801).

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2 Make sure bolts do not bottom out on inside handle shaft 85217916.
NOTE: O n es i z ed o w no ng r i pl e n g t hm a yb eu s e df o rb o l t .
(d) Safety the bolts to bracket. using lock wire MS20995C20 (refer to applicable
instructions in AMM TASK 20- - - 10- - - 30- - - 400- - - 801).
NOTE: Safety cable AS3510- - - 0106K may be used as an alternate to lock wire.
(e) Make sure there is a 0.025 in. clearance between the rod assembly 85217726
and bolt head / lock wire when door mechanism is in the open position (refer to
Figure 2 (Sheet 2) and drawing 8Z8451, SECTION B- - - B).
(4) Reinstall parts and hardware removed to gain access (refer to applicable
instructions in AMM TASK 52- - - 24- - - 01- - - 400- - - 803).
(5) Re identify door after rework at location shown on Figure 3 (refer to drw 8Z8451
Sht. 1, TABLE II and AMM TASK 20- - - 00- - - 01- - - 910- - - 801).
(6) Install Type 1 emergency door liner (refer to applicable instructions in AMM TASK
25- - - 26- - - 16- - - 400- - - 802).
(7) Install the internal handle with retained hardware (refer to applicable instructions
in AMM TASK 52- - - 24- - - 01- - - 400- - - 803).
(8) Do an operational test of the Type 1 emergency door. (refer to AMM TASK
52- - - 24- - - 00- - - 710- - - 801).

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C. Close Out
NOTE: The steps in the Job Close- - -Out section of this service bulletin, except
for the return- - -to- - -service tests, are recommended steps. The steps
give a recommendation to install components removed during the Job
Set- - - Up. This recommendation is to make sure that the aircraft is safe
and ready to return to service. Alternative steps can be used at the
operator’s discretion.
(1) Remove all tools and equipment from the work area.
(2) Remove work platforms or ladders from the work area.
(3) On incorporation of this ModSum make an entry that conforms to local regulatory
requirements in the applicable logbook(s). If only part of this ModSum is
completed, use only this service bulletin number as reference and detail exact
limit of work completed. Enter component serial numbers if applicable. Enter this
ModSum number only after complete and functional incorporation of all work
defined in this service bulletin.

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Door Location
Figure 1

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Rod Assembly
F i g u r e2( S h e e t1o f2 )
LINK ASSEMBL Y
85217727 - - -001
ROD ASSEMBL Y
85217726 - - -001CRANK ASSEMBL Y85217919 - - -001
BOL T
NAS6204 - - -3H
(QTY 2)
WASHER
NAS1149C416R
(QTY 2)
BRACKET
85210534 - - -103

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Door Mechanism in Open Position
F i g u r e2( S h e e t2o f2 )
0.025 IN MINIMUM
CLEARANCE
ROD ASSEMBL Y
85217726 - - -001
LINK ASSEMBL Y
85217727 - - -001

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New Part Number Location
Figure 3
LOCATION OF NEW
PART NUMBER
1

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This Page Intentionally Blank
1

### Page 19

Oct 2019
SERVICE BULLETIN (SB) - - - RECORD OF INCORPORATION
DASH 8 AIRCRAFT
To : CMDB Focal
Email: cmdb.request@dehavilland.com
From:
Company:
Phone: Extn:
Facsimile: Date:
Email:
The data that you provide below will help us record the incorporation of this Service
Bulletin 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

### Page 20

Oct 2019
SERVICE BULLETIN (SB) - - - COMMENT SHEET - - - 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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