# Bombardier Service Bulletin 8-55-27

Copy: Revision A ("SB 8-55-27 RevA"), 30 pages: PDF https://openairdocs.org/files/sha256/07/08/0708614eb66d8d2cb2059710eeaedeb5eed01b149e4ad81bc895126a30f5e492; text https://openairdocs.org/service-documents/bombardier/sb-8-55-27/file/0708614eb66d.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2019-0189; AD 2019-12-17 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: 8-55-27
- Latest revision known: 8-55-27, Revision A, dated August 15, 2018 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/sb-8-55-27

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

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

- [AD 2019-12-17](https://openairdocs.org/ad/2019-12-17.md), effective Aug 12, 2019: Revision A

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-8-55-27/proposed.md).

## Text (30 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2019-0189; AD 2019-12-17 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 ‘A’ 15 Aug 2018
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 --- 5 5 --- 2 7
Stabilizers - - - Elevator - - - Spring T abs - - - Balance Weights and Hinge
Arms - - - Special Inspection and Rectification - - - ModSum 8Q113034
This page transmits Revision ‘A’ of Service Bulletin 8- - -55- - -27, pages 1 thru
26, dated 15 Aug 2018
This service bulletin is re- - -issued in its entirety for the reasons that follow:
--- t h eReason section is revised to include additional information
--- t h eDescription section is revised to include additional steps in Part A and
Part C for locknut inspection
--- t h eReferences section is revised to convey the latest revision of the service
bulletin and engineering documentation
--- t h eMATERIAL INFORMATION section, detailed kit content table and the
consumable table are revised to update the part list per revised kit drawing
--- t h eProcedure section Part A - - - Inspectionis revised to add additional
steps.
--- t h eProcedure section Part B Balance Weight and Shim Installation step
(2) and (5) are revised to add additional references and correct consumable
ref. number respectively. Steps are resequenced to move step 3 to the end.
--- Part C - - - Inspection (if Mod 8Q113034 Rev. B or Rev C is embodied ) is
added in Procedure section
--- Close Out section is revised to include additional steps and the ModSum
revision number as applicable.
--- t h eFigure 7 is revised per drawing update.
The Compliance in the previous issue of this service bulletin is affected by
this revision. Additional rework to the aircraft is introduced by this revision.
Remove the previous issue of Service Bulletin 8- - -55- - -27 and replace with
attached.
Previous issue(s) of Service Bulletin 8- - -55- - -27:
Initial issue - - - Pages 1 thru 24 dated 17 Apr 2018

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(No text on this page.)

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D
S . B . 8 --- 5 5 --- 2 7
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Revision ‘A’ 15 Aug 2018
SERVICE BULLETIN
Customer
Support
ATA SYSTEM: 5521 NUMBER: 8- - -55- - -27
BOMBARDIER AEROSPACE CONSIDER THIS
SERVICE BULLETIN TO BE PARTICULARL Y SIGNIFICANT AND
URGE OPERATORS TO PROMPTL Y EVALUATE THE CONTENTS
SUBJECT : Stabilizers - - - Elevator - - - Spring T abs - - - Balance Weights and Hinge
Arms - - - Special Inspection and Rectification - - - ModSum 8Q113034
1. PLANNING INFORMA TION
A. Effectivity
Aircraft Affected:
In- - -Service: DHC- - -8 Aircraft Models 102, 103, 106, 201, 202, 301, 311, 314
and 315 Serial Numbers 003 thru 672 with Mod 8/0468
incorporated.
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 Bombardier Aerospace Service Bulletin(s). Before you do
this bulletin, examine all STC or equivalent action changes to make
sure this bulletin can be completed.

### Page 4

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Revision ‘A’ 15 Aug 2018
NOTE: Make sure that the Mod 8/0468 is incorporated on Aircraft S/N 15 thru
2 4 v i a S B 8 --- 5 5 --- 3 a n d A i r c r a f t 3 t h r u 1 4 v i a S B 8 --- 5 5 --- 4 .
Spares Affected:
NOTE: If spring tabs are held in spares, inspect and repair before installation
on aircraft.
B. Reason
Problem: One operator has reported the loss of a spring tab balance weight prior to
takeoff. Loss of spring tab balance weight during flight can lead to flutter
and loss of control of the aircraft.
Solution: This service bulletin gives instructions to do a one- - -time inspection to
make sure the security of the spring tab balance weights on both the port
and starboard spring tab assemblies.
If the balance weights are found loose, instructions are given to repair any
damage to the hinge arm, and to permanently secure balance weights.
Hardware specified for balance weight attachment has reduced
susceptibility to hydrogen embrittlement.
C. Description
The procedures in this service bulletin give the instructions to do the tasks that follow:
- - - aircraft electrical power is removed
- - - hydraulic systems are depressurized
- - - the nose landing gear lock is engaged
- - - the main landing gear lock pins are installed through each main gear and main gear
door mechanism
- - - wheel chocks are set
- - - work scissor lift(s) or platforms around and/or under the left (and/or right) elevator are
set up
- - - elevator gust lock is engaged and rudder, and elevator controls in flight compartment
are placarded.

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Revision ‘A’ 15 Aug 2018
Part A - - - Special Inspection for security of the Balance Weight and Hinge Arm on
the Spring T abs
- - - access is gained to the balance weight and the hinge arm by removing lower skin
fairing 85520062 and disconnecting the control rod and swinging the spring tab
- - - a detailed visual inspection of the nuts used to hold the balance weights on is
conducted.
- - - if the nuts are fractured, missing or loose, go to Part B - - - Rectificationbefore next
flight
- - - balance weight on each spring tab (LH & RH) are inspected
- - - if balance weight are not loose, rectification per Part B is required within compliance
time specified in Airworthiness Directive (AD)
- - - if weights are loose on the hinge arm, refer to Part B - - - Rectification.
Part B - - - Rectification
- - - fairings 85520062 and 85620113 are removed
- - - balance weights are removed
- - - the holes in hinge arm used to secure balance weights are inspected for size and
roundness
- - - the hinge arm is inspected for signs of corrosion or chafing
NOTE: If holes are within design limits specified on drawing 8Z7315, no hinge
arm rework is required.
- - - if the holes in the hinge arm are within specified limits given in the Generic RD
8- - -55- - -154 Issue 4 or subsequent and/or hinge arm has no damage, bushings are
installed to instructions given within RD 8- - -55- - -154 Issue 4 or subsequent and a solid
shim is installed
- - - If holes in the hinge arm are elongated bey ond specified limits given in the Generic
RD 8- - -55- - -154 Issue 4 or subsequent, the hinge arm is replaced or an acceptable
alternative is to conduct a temporary repair per RD 8- - -55- - -3153 Issue 1 or subsequent
- - - if hinge arm corrosion or chafing is observed outside the area of the attachment holes,
repair is done per RD8- - -55- - -154 issue 4 or subsequent. If damage exceeds limits,
Bombardier help desk is contacted for an approved repair or replace the hinge arm.

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Revision ‘A’ 15 Aug 2018
- - - a solid shim is installed
- - - balance weights are re- - -installed and sealed per drawing 8Z7315 instructions
- - - lower skin fairing 85520062 is re- - -installed
- - - if removed, fairing 85520113 is re- - -installed
- - - spring tab and elevator are rebalanced per SRM
- - - control rod is reconnected
- - - close out.
Part C - - - If ModSum 8Q113034 Rev. B or Rev. C is embodied per SB 8- - - 55- - - 27
Rev NC, then do a visual inspection of all four balance weight locknuts P/N
MS21042 - - - 4
- - - access is gained to the balance weight and the hinge arm by removing the lower skin
fairing 85520062 and disconnecting the control rod and swinging the spring tab
- - - all four locknuts attaching the balance weight to the hinge arm are visually inspected
for any cracks
- - - if any cracks are found or any nut is missing or loose, all four nuts are replaced with
new nut P/N NAS 9926- - -4L and close out
- - - if no cracks are found close out.
D. Compliance
Bombardier Inc. highly recommend that the s pecial inspection and if required, the
rectification in this service bulletin be completed at the earliest opportunity unless
otherwise directed by the operator’s airworthiness authority.
A Transport Canada Airworthiness Directive 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
# 9 3 --- Q --- 0 2 .
This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage
T olerance Inspections (DTIs).

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F. M a n p o w e r
P a r t A --- I n s p e c t i o n
It will take an estimated 2.00 man- - -hours to complete PART A of the
ACCOMPLISHMENT instructions in this service bulletin. The breakdown of 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 0.50
Procedure in Part A 1.00
T e s t/R T S 0.00
Close- - -Out 0.50
Part B - - - Rectification
It will take an estimated 6 man- - -hours to complete PART B of the
ACCOMPLISHMENT instructions in this service bulletin. The breakdown of 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 0.50
Procedure in Part B 3.50
T e s t/R T S 1.50
Close- - -Out 0.50
This estimate is for direct labour done by an experienced crew and it does not
include, planning, familiarization, cure tim e, part fabrication, tool acquisition or lost
time.
G. Material - - - Price and Availability
Kit Number Description
8DK4338- - -001 Drawing Kit - - - Elevator, Spring T ab
Mass Balance Hinge Arm, Inspection &
Rectification

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Drawing Kit(s) (DKs) listed in the table above are drawings only. No parts will be
supplied.
The part(s) and material(s) required are listed in Paragraph 2.A. The parts required
may be either furnished or fabricated from the operator’s existing stock, purchased as
single items from Bombardier Aerospace Commercial Aircraft or purchased directly
from industry sources. DK parts are to be manufactured and approved locally (refer to
disclaimer in the related text or illustra tion). In some cases, an equivalent to the DK
part may be available from Bombardier under the production part number shown as
reference in Parts Required Per Aircraft.
See the contact information below.
Bombardier Aerospace
Customer Accounts Services T eam (Mail Stop N11- - -32)
123 Garratt Blvd.
To r o n t o
Ontario
Canada M3K- - -1Y5
E- - -mail addresses:
International: cast.international@aero.bombardier.com
European: ps_emea@aero.bombardier.com
Americas East: cast.americaseast@aero.bombardier.com
Americas West: cast.americaswest@aero.bombardier.com
T elephone:
North America:T oll Free +1- - -844- - -CRC- - -CRC0 (+1- - -844- - -272- - -2720) or direct
+1- - -514- - -855- - -8500
Facsimile:
International: (416) 373- - -5966
Americas East: (416) 373- - -5964
Americas West: (416) 375- - -5965
If required, the related 8DK drawings listed in the T able above can be requested by
writing to the e- - -mail address that follows:
qseriesdwgrequest@aero.bombardier.com
Follow the instructions per All Operator Messages (AOM) 914 (Q100/200/300)

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H. T ooling - - - Price and Availability
None
I. Weight and Balance
Negligible
J. Electrical Load Data
Not affected
K. Publications Affected
S t r u c t u r a l R e p a i r M a n u a l P S M 1 --- 8 --- 3 a n d............................
P S M 1 --- 8 2 --- 3 a n d
P S M 1 --- 8 3 --- 3
Aircraft Illustrated Parts Catalog PSM 1- - -8- - -4 and......................
P S M 1 --- 8 2 --- 4 a n d
P S M 1 --- 8 3 --- 4
Weight and Balance Manuals PSM 1- - -8- - -8 and........................
P S M 1 --- 8 2 --- 8 a n d
P S M 1 --- 8 3 --- 8
Modifications Manual PSM 1- - -813- - -12................................
L. References
Revision ‘A’ of this service bulletin was prepared to the engineering drawings and
related data that follows:
DRAWING SHEET REV
8DK4338 1 --- A
8Z7315 1 --- B
8Z7315 2 --- B
ModSum 8Q113034 Rev. ‘D’

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Revision ‘A’ 15 Aug 2018
PCA 8056 Revision 00 (for internal reference only)
Transport Canada Airworthiness Directive (AD) Pending
Repair Drawing (RD 8- - -55- - -154 Issue 4 or subsequent)
Repair Drawing (RD 8- - -55- - -3153 Issue 1 or subsequent)
Related ModSum 8Q113035
CR803SO00072 and CR803SO00073
2. MATERIAL INFORMA TION
A. Parts Required Per Aircraft
(1) Modification Kit 8DK4338- - -001 (drawing kit only)
(2) Detailed Kit Content:
Quantity Per Kit
--- 0 0 1
Part Number Description Remarks
64 NAS9304B- - -4- - -02 Rivet Alternative P/N
CR3243- - -4- - -2
see Note below
8 NAS6604- - -12 Bolt see Note below
8 NAS9926- - -4L Nut see Note below
8 MS35338- - -44 Washer Alternative P/N
AN935- - -416L
see Note below
24 NAS1149F0432P Washer Alternative P/N
AN960- - -416L
see Note below
4 8Z7315- - -103 Shim Solid see Note below
4 8Z7315- - -101 Shim Solid see Note below
1 8Z7315 Retrofit Drawing Drawing only
1 8DK4338 Kit Drawing

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NOTE: Items are not included in the kit and must be supplied by the operator.
Listed drawings that are required to complete the kits above can be requested by
writing to the following e- - -mail address:
qseriesdwgrequest@aero.bombardier.com
(3) In addition to the above part(s), the f ollowing consumable products are required
for the completion of this service bulletin and may be procured as single items
from Bombardier Aerospace Commercial Aircraft or purchased directly from
industry sources.
Each consumable product listed in the table below is given its own unique “REF
ITEM” identification number that is used to identify a particular recommended
product, the specifications and the trade names any of which can be used
u n l e s s s p e c i f i e d o t h e r w i s e ( r e f e r t o P S M 1 --- 8 --- 2 , 1 --- 8 2 --- 2 o r 1 --- 8 3 --- 2 A i r c r a f t
Maintenance Manual (AMM) Chapter 51- - -31- - -00 CONSUMABLE MATERIALS - - -
MAINTENANCE PRACTICES).
REF ITEM Qty. Per Aircraft Description Remarks
06- - -07 As Required Sealant (Loctite Gr. M) MIL- - -S- - -46163 T y.2
07- - -08 As Required Polyurethane Enamel
(F24 White)
MIL- - -C- - -83286
07- - -01 As Required Corrosive Preventive
Compound
(F13 Grade 2)
MIL- - -C- - -16173 Gr.
2
07- - -02 As Required Chromate Epoxy
Primer (F19)
MIL- - -P- - -23377
07- - -21 As Required Alodine (C1) MIL- - -C- - -5541
06- - -02 As Required Sealant
(P/S 870C- - -80)
DHMS S3.06 T y.1
(P/S 870C- - -12) MIL- - -PRF- - -81733
DELETED DELETED DELETED

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REF ITEM Remarks DescriptionQty. Per Aircraft
06- - -12 As Required Sealant
(PR1428/B2)
(PR1428/B1/2)
(PR1428/A2)
(PR1428/A1/2)
DHMS S3.02
06- - -01 As Required Sealant
(PR1422- - -B2)
DHMS S3.01/B2
08- - -26 As Required Solvent, Degeaser MIL- - -T- - -81533
B. Parts Required to Modify Spares
None
C. Special T ools and Equipment Required
None
D. Existing Parts Accountability
None
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 Bombardier in the CRC at
1- - -844- - -272- - -2720 (1- - -844- - -CRC- - -CRC0) or email at thd.qseries@aero.bombardier.comfor
analysis and to get an approved disposition to complete this service bulletin.

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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 .
WARNING: INSTALL THE SAFETY DEVICES, THE WARNING SIGNS, AND THE
WARNING PLACARDS BEFORE YOU START A PROCEDURE ON OR
AROUND:
S FLIGHT CONTROLS
S FLIGHT CONTROL SURFACES
S COMPONENTS THAT MOVE
MAKE SURE THAT THERE ARE NO PERSONS OR EQUIPMENT ON
OR
NEAR THE SURFACES OF THE FLIGHT CONTROLS. ACCIDENTAL
MOVEMENT OF THE FLIGHT CONTROLS CAN CAUSE INJURIES TO
PERSONS AND DAMAGE TO THE EQUIPMENT .
WARNING: BE SURE THAT THE HYDRAULIC PRESSURE IS OFF , AND THAT
THERE IS NO PRESSURE IN THE HYDRAULIC SYSTEM. IF YOU DO
NOT DO THIS YOU CAN CAUSE INJURIES TO PERSONS AND
DAMAGE TO THE EQUIPMENT .
(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 P S M 1 --- 8 --- 2 o r 1 --- 8 3 --- 2 A M M C h a p t e r s 1 2
a n d 2 4 o r P S M 1 --- 8 2 --- 2 A M M T A S K 1 2 --- 0 0 --- 0 5 --- 0 3 a n d T A S K
24- - -00- - -00- - -910- - -803).

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( 2 ) D e p r e s s u r i z e h y d r a u l i c s y s t e m s ( r e f e r t o P S M 1 --- 8 --- 2 o r 1 --- 8 3 --- 2 o r P S M
1- - -82- - -2 Chapters 12 and 29).
(3) Make sure hydraulic power is off and placarded and ground cart is disconnected.
(4) Make sure that lock pins are installed through each main gear and main gear
door mechanism.
(5) Make sure the nose gear ground lock is engaged.
(6) Set wheel chocks in front and behind the landing gear tires.
(7) Make sure elevator gust lock is engaged and rudder and elevator controls in
f l i g h t c o m p a r t m e n t a r e p l a c a r d e d ( r e f e r t o P S M 1 --- 8 --- 2 o r 1 --- 8 3 --- 2 o r P S M
1 --- 8 2 --- 2 A M M 2 7 --- 7 0 --- 0 0 ) .
(8) Set up work scissor lift(s) or platforms around and/or under the left (and/or right)
elevator to permit access to the left and/or right elevator(s). Make sure that the
scissor lift(s) or work platforms are electrically grounded.
B. Procedure
Part A - - - Inspection
(1) Do a special inspection for security of the two balance weights and two hinge
arms on each spring tab (LH & RH) as follows (refer to Figures 1 thru 4 and
drawing 8Z7315 sheet 1 and 2):
(a) Get access to the balance weight and the hinge arm.
(b) Remove fairing cover 85520062 on lower elevator skin to gain access by
removing five bolts NAS5003- - -2 (refer to Figure 3 and and SRM 55- - -20- - -11).
(c) Remove control rod attachment bolt from the drive fitting on the spring tab and
support detached control rod drive for safety.
(d) Swing the spring tab so the balance weight and attachment bolts are
accessible.
(e) Inspect nuts used to attach the balance weight to the hinge arms. If fractured,
missing or loose, proceed to Part B - - - Rectificationbefore next flight.

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(f) Inspect the balance weight for security, by gripping balance weight and
attempting to move it in the vertical direction and also in the direction of parallel
to the length of the attachment bolts without moving the hinge arm.
NOTE: If wear is found beyond the limits or other damage or corrosion is
present before proceeding further, contact the Q Series T echnical Help
Desk by telephone at 514- - -885- - -8500 / 1- - -844- - -272- - -2720 (toll free) or
email at: thd.qseries@aero.bombardier.com for approved repair
/disposition / action.
(g) If the balance weight is secure and has no perceived looseness, do P a r t B ---
Rectification within the compliance times specified in AD.
(h) If the balance weight is not secure and there is a perceived looseness, do Part B
- - - Rectification.
If only Part (A) of this service bulletin is to be completed, do as follows:
(i) Connect the spring tab operating rod to the drive fitting on the spring tab and
lock with new cotter pin MS24665- - -153 (refer to applicable instructions in PSM
1 --- 8 --- 2 o r 1 --- 8 3 --- 2 o r P S M 1 --- 8 2 --- 2 A M M 2 7 --- 3 4 --- 1 1 ) .
(j) Complete installation (refer to applicable instructions in PSM 1- - -8- - -2 or
1- - -83- - -2 or PSM 1- - -82- - -2 AMM 27- - -34- - -11 and drawing 8Z7315).
(k) Re- - -install the lower skin fairing 85520062 using five bolts NAS5003- - -2 (refer to
Figure 3 and and SRM 55- - -20- - -11).
(l) If removed, re- - -install the fairing 85520113 as follows (refer to applicable
instructions in drawing 8Z7315):
1 Clean all residual sealant off elevator skin. Clean all bare metal using
clean, cotton cloths dampened with approved solvent 08- - -26. Reprotect
the metal using Alodine and Epoxy base Chromate primer as detailed in
P S M 1 --- 8 --- 2 o r 1 --- 8 3 --- 2 o r P S M 1 --- 8 2 --- 2 A M M 1 --- 8 --- 2 C h a p t e r 2 0 .
2 Clean and apply a coat of fay sealant 06- - -02 or equivalent to mating
surfaces of fairing and elevator (refer to Maintenance Manual PSM 1- - -8- - -2
o r 1 --- 8 3 --- 2 o r P S M 1 --- 8 2 --- 2 C h a p t e r 2 0 ) .

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3 Re- - -install the fairing cover 85520113 to vacated rivet pattern in elevator
top skin. Use rivets NAS9304B- - -4- - -02 or CR3243- - -4- - -2 (refer to
applicable views and instructions in drawing 8Z7315 sheet 1 and 2, Flag
note 13 a n d S e c t i o n B --- B F i g u r e 4 ) .
4 Apply a fillet of sealant 06- - -01 or equivalent around jointing edge of fairing
( r e f e r t o M a i n t e n a n c e M a n u a l P S M 1 --- 8 --- 2 o r 1 --- 8 3 --- 2 o r P S M 1 --- 8 2 --- 2
Chapter 20).
Part B - - - Rectification
Gain Access to Balance W eights
(1) Gain access to balance weights as follows:
(a) Remove fairing cover 85520062 on lower elevator skin to gain access by
removing five bolts NAS5003- - -2 (refer to Figure 3 and and SRM 55- - -20- - -11).
(b) Remove control rod attachment bolt from the drive fitting on the spring tab and
support detached control rod drive for safety.
(c) Swing the spring tab so that the balance weight and attachment bolts are
accessible.
(2) If necessary, for optional access to balance weights; remove fairing 85520113 as
follows:
(a) Disconnect the spring tab operating rod from the drive fitting on the spring tab
( 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 P S M 1 --- 8 --- 2 o r 1 --- 8 3 --- 2 o r P S M 1 --- 8 2 --- 2
A M M 2 7 --- 3 4 --- 1 1 ) .
NOTE: It may be necessary to swing and suitably support the spring tab so
that the weights and attachment bolts are accessible while performing
the retrofit.
(b) Drill out rivets securing fairing 85520113- - -001, - - -003, - - -007 or - - -009 to top skin
of left or right- - -hand elevator over spring tab balance weights (two per
elevator). Use a No. 27 (0.0144 inch diameter) drill.

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S . B . 8 --- 5 5 --- 2 7
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(c) Remove the fairing cover 85520113 to get access to the hinge arm (refer to
applicable views and instructions in drawing 8Z7315 sheet 1 and 2, Flag note
13 , S e c t i o n B --- B F i g u r e 4 ) .
(d) Remove control rod attachment bolt from the drive fitting on the spring tab and
support detached control rod drive for safety.
(e) Swing the spring tab so that the balance weight and attachment bolts are
accessible.
(3) Remove the balance weight from the hinge arm (refer to applicable instructions in
P S M 1 --- 8 --- 2 o r 1 --- 8 3 --- 2 o r P S M 1 --- 8 2 --- 2 A M M 2 7 --- 3 4 --- 1 1 ) .
Inspection
(1) Inspect the hinge arm for damage and rectify as follows:
(a) Measure hole diameter of the balance weight attachment holes and ensure that
they are within tolerance of the drawing 8Z7315 or RD 8- - -55- - -154 Issue 4 or
subsequent if it was incorporated. If no damage is observed, proceed to
Balance Weight and Shim Installation.
(b) If the holes are elongated but can be repaired in accordance with RD
8- - -55- - -154 Issue 4 or subsequent, proceed with the repair (refer to RD
8- - -55- - -154 Issue 4 or subsequent).
(c) If the damage is beyond repair detailed in RD 8- - -55- - -154 Issue 4 or
subsequent, incorporate temporary RD 8- - -55- - -3153 Issue 1 or subsequent or
replace the hinge arm (refer to RD 8- - -55- - -3153 Issue 1 or subsequent and
applicable views and instructions in drawing 8Z7315 sheet 1 and 2).
(d) Check the hinge arm area away from attachment holes to ensure that it is free of
other damages such as chafing, wear or corrosion. Repair damage if within
specified limits on RD 8- - -55- - -154 Issue 4 or subsequent.
(e) Contact the Q Series T echnical Help Desk by telephone at 514- - -885- - -8500 /
1- - -844- - -272- - -2720 (toll free) or email at: thd.qseries@aero.bombardier.com for
approved repair / disposition / action, before proceeding further, if damage found
exceeds the damage limits specified in RD 8- - -55- - -154 issue 4 or subsequent or
if RD 8- - -55- - -3153 Issue 1 or subsequent to replace the hinge arm cannot be
incorporated. Alternatively, replace the hinge arm or spring tab.

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S . B . 8 --- 5 5 --- 2 7
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Balance Weight and Shim Installation
(1) Install a solid shim 8Z7315- - -103 or 8Z7315- - -101 (refer to applicable views and
instructions in drawing 8Z7315 sheet 1, Flag note 4 , 5 , 6 , 16 and
Figure 6) after measuring the gaps to select appropriate shim thickness.
(2) Re- - -install the balance weights using new hardware (refer to applicable
i n s t r u c t i o n s i n P S M 1 --- 8 --- 2 o r 1 --- 8 3 --- 2 o r P S M 1 --- 8 2 --- 2 A M M 2 7 --- 3 4 --- 1 1 a n d
applicable instructions. notes and views in drawing 8Z7315, Flag note 9 ,
18 and Section D- - -D Figure 7) and re seal as follows:
(a) Coat shank of bolts with F13 (Grade 2) 07- - -01 (refer to applicable views and
instructions in drawing 8Z7315 sheet 1 and 2, Flag note 8 a n d S e c t i o n D --- D
Figure 7).
(b) Fay surface seal balance weight halves (refer to applicable views and
instructions in drawing 8Z7315 sheet 1 and 2, Flag note 7 a n d S e c t i o n D --- D
Figure 7).
(c) Install nuts NAS9926- - -4L with Loctite (Grade M) 06- - -07 (refer to applicable
i n s t r u c t i o n s i n P S M 1 --- 8 --- 3 o r 1 --- 8 3 --- 3 o r P S M 1 --- 8 2 --- 3 S R M 5 5 --- 2 0 --- 6 1 ) .
NOTE: Similar nut MS21042- - -4 nut is not a suitable replacement for
NAS9926- - -4L.
( 3 ) C o m p l e t e i n s t a l l a t i o n ( 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 P S M 1 --- 8 --- 2 o r 1 --- 8 3 --- 2
or PSM 1- - -82- - -2 AMM 27- - -34- - -11 and drawing 8Z7315).
(4) Re- - -install the lower skin fairing 85520062 using five bolts NAS5003- - -2 (refer to
Figure 3 and and SRM 55- - -20- - -11).

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S . B . 8 --- 5 5 --- 2 7
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(5) If removed, re- - -install the fairing 85520113 as follows (refer to applicable
instructions in drawing 8Z7315):
(a) Clean all residual sealant off elevator skin. Clean all bare metal using clean,
cotton cloths dampened with approved solvent 08- - -26. Reprotect the metal
using Alodine and Epoxy base Chromate primer as detailed in Maintenance
Manual PSM 1- - -8- - -2 Chapter 20.
(b) Clean and apply a coat of fay sealant 06- - -02 or equivalent to mating surfaces of
f a i r i n g a n d e l e v a t o r ( r e f e r t o M a i n t e n a n c e M a n u a l P S M 1 --- 8 --- 2 o r 1 --- 8 3 --- 2 o r
PSM 1- - -82- - -2 Chapter 20).
(c) Re- - -install the fairing cover 85520113 to vacated rivet pattern in elevator top
skin. Use rivets NAS9304B- - -4- - -02 or CR3243- - -4- - -2 (refer to applicable views
and instructions in drawing 8Z7315 sheet 1 and 2, Flag note 13 and Section
B --- B F i g u r e 4 ) .
(d) Apply a fillet of sealant 06- - -01 or equivalent around jointing edge of fairing (refer
t o M a i n t e n a n c e M a n u a l P S M 1 --- 8 --- 2 o r 1 --- 8 3 --- 2 o r P S M 1 --- 8 2 --- 2 C h a p t e r 2 0 ) .
(6) Rebalance spring tab and elevator (refer to applicable instructions in PSM
1 --- 8 --- 3 o r 1 --- 8 3 --- 3 o r P S M 1 --- 8 2 --- 3 S R M 5 5 --- 2 0 --- 6 1 ) .
(7) If either the spring tab and/or elevator cannot be balanced, contact the Q Series
T echnical Help Desk by telephone at 514- - -885- - -8500 / 1- - -844- - -272- - -2720 (toll free).
or email at: thd.qseries@aero.bombardier.com for approved disposition/action.
(8) Connect the spring tab operating rod to the drive fitting on the spring tab and
lock with new cotter pin MS24665- - -153 (refer to applicable instructions in PSM
1 --- 8 --- 2 o r 1 --- 8 3 --- 2 o r P S M 1 --- 8 2 --- 2 A M M 2 7 --- 3 4 --- 1 1 ) .
Part C - - - Inspection (if Mod 8Q113034 Rev. B or Rev. C is embodied)
NOTE: This is a one time inspection of all four balance weight lock nuts
(P/N MS21042- - - 4), if SB 8- - - 55- - - 27 rev NC is already accomplished.
(1) Do a detailed visual inspection of the four balance weight locknuts (P/N
MS21042- - -4):
(a) Get access to the balance weight and the hinge arm.

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S . B . 8 --- 5 5 --- 2 7
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(b) Remove fairing cover 85520062 on lower elevator skin to gain access by
removing five bolts NAS5003- - -2 (refer to Figure 3 and SRM 55- - -20- - -11).
(c) Remove control rod attachment bolt from the drive fitting on the spring tab and
support detached control rod drive for safety.
(d) Swing the spring tab so the balance weight and attachment bolts are
accessible.
(e) Inspect the four lock nuts MS21042- - -4 for sign of cracking.
(f) If there is cracking, missing or loose nuts, replace the four nuts with P/N NAS
9926- - -4L and re- - -install the balance weights using new hardware per steps (2)
to (8) of Part (B) Balance weight and Shim Installation.
(g) If there is no cracking, missing or loose nuts, then connect the spring tab
operating rod to the drive fitting on the spring tab and lock with new cotter pin
MS24665- - -153 (refer to applicable instructions in PSM 1- - -8- - -3 or 1- - -83- - -3 or
P S M 1 --- 8 2 --- 3 S R M 5 5 --- 2 0 --- 6 1 ) .
(h) Re- - -install the lower skin fairing 85520062 using five bolts NAS5003- - -2 (refer to
Figure 3 and SRM 55- - -20- - -11 and drawing 8Z7315).
C. Close Out
(1) Remove all tools and equipment from the work area.
(2) On incorporation of this ModSum 8Q113034 Rev D, make an entry that conforms
to local regulatory requirements in the applicable logbook(s). If only Part A of this
service bulletin is completed, use only Service Bulletin 8 - - - 55 - - - 27 {Stabilizers - - -
E l e v a t o r --- S p r i n g Ta b s --- B a l a n c e W e i g h t s a n d H i n g e A r m s --- S p e c i a l I n s p e c t i o n
and rectification} Part A as reference and detail exact limit of work completed.
Enter component serial numbers if applicable.
(3) Enter this ModSum number 8Q113034 Rev D, only after complete and functional
i n c o r p o r a t i o n o f a l l w o r k d e f i n e d i n t h i s S e r v i c e B u l l e t i n 8 --- 5 5 --- 2 7 { S t a b i l i z e r s ---
E l e v a t o r --- S p r i n g Ta b s --- B a l a n c e W e i g h t s a n d H i n g e A r m s --- S p e c i a l I n s p e c t i o n
and rectification} Part B is embodied.

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S . B . 8 --- 5 5 --- 2 7
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(4) If ModSum 8Q113034 Rev. B or Rev C (per SB 8- - -55- - -27 rev NC) was already
embodied, enter this ModSum number (8Q113034 Rev D) only after complete
and functional incorporation of all work defined in this Service Bulletin 8- - -55 - - -27
{ S t a b i l i z e r s --- E l e v a t o r --- S p r i n g Ta b s --- B a l a n c e W e i g h t s a n d H i n g e A r m s ---
Special Inspection and rectification} Part C is embodied.
THE DESIGN OF THE PART IN THIS DRAWING HAS BEEN APPROVED BY DE HAVILLAND INC. FOR MANUFACTURE BY OR ON BE-
HALF OF THE RECIPIENT . THE RECIPIENT IS RESPONSIBLE FOR (A) PROPER MANUFACTURE OF THE PART USING THE SPECI-
FIED MATERIALS AND FOR INCORPORATION OF THE MODIFICATION, ALL IN ACCORDANCE WITH THE DRAWING AND RELATED
INSTRUCTIONS, AND (B) APPROVAL OF THE FINAL INSTALLATI ON BY THE RELEVANT AIRWORTHINESS AUTHORITY . DE HAVIL-
LAND INC. AND BOMBARDIER INC. (BOMBARDIER AEROSPACE) DISCLAIM ANY RESPONSIBILITY FOR INCIDENTAL OR CONSE-
QUENTIAL DAMAGES, INCLUDING WITHOUT LIMITATION LOSS OR USE, LOSS OF REVENUE OR LOSS OF PROFIT , ARISING FROM
SUCH MANUFACTURE, INCORPORATION AND INSTALLATION.

### Page 22

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S . B . 8 --- 5 5 --- 2 7
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Location Diagram
Figure 1

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S . B . 8 --- 5 5 --- 2 7
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Detail A
Figure 2
REFER TO FIGURE 3

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S . B . 8 --- 5 5 --- 2 7
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Lower Skin Fairing 85520062
Figure 3
LH SHOWN (RH SIMILAR)

### Page 25

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S . B . 8 --- 5 5 --- 2 7
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Section B - - - B
Figure 4
ALL FLAGNOTES AND PART NUMBERS (REFER TO 8Z7315 SHEET 1)

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S . B . 8 --- 5 5 --- 2 7
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Detail C
Figure 5
ALL DIMENSIONS ARE IN INCHES

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S . B . 8 --- 5 5 --- 2 7
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Installation of Shims
Figure 6
ALL FLAGNOTES AND PART NUMBERS (REFER TO 8Z7315 SHEET 1)
ALL DIMENSIONS ARE IN INCHES

### Page 28

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S . B . 8 --- 5 5 --- 2 7
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Section D- - - D
Figure 7
ALL FLAGNOTES AND PART NUMBERS (REFER TO 8Z7315 SHEET 1)
ALL DIMENSIONS ARE IN INCHES
1

### Page 29

May2018
SERVICE BULLETIN (SB) - - - RECORD OF INCORPORATION
- - - Q SERIES DASH 8 AIRCRAFT
To : CMDB Focal
Facsimile: (1) 416 375 4538
E- -mai l: cmdb.requests@aero.bombardier .com
From:
Company:
Phone: Extn:
Facsimile: Date:
E- -mai l:
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:
Fax this sheet to (1) 416 375 4538 or Email PDF to:
cmdb.requests@aero.bombardier.com

### Page 30

May 2018
SERVICE BULLETIN (SB) - - - COMMENT SHEET - - - Q SERIES DASH 8 AIRCRAFT
To : SB Focal (T oronto), Bombardier Aerospace Commercial Aircraft
Phone: (1) 416 375 4078 Facsimile: (1) 416 375 4538
E- -mai l: syed.rizvi@aero.bombardier .com
From:
Company:
Phone: Extn:
Facsimile: Date:
E- -mai l:
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
Fax this sheet to (1) 416 375 4538 or Email PDF to:
syed.rizvi@aero.bombardier.com

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