# Bombardier Service Bulletin 84-32-145

Copy: Revision A ("SB 84-32-145 Rev A"), 12 pages: PDF https://openairdocs.org/files/sha256/6b/9a/6b9ad6880a574a5545a12aa69138e8f3969578c2053a313a43c046b1d7c1df57; text https://openairdocs.org/service-documents/bombardier/sb-84-32-145/file/6b9ad6880a57.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2017-0334; AD 2017-19-09 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: 84-32-145
- Latest revision known: 84-32-145, Revision A, dated October 18, 2016 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/sb-84-32-145

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

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

- [AD 2017-19-09](https://openairdocs.org/ad/2017-19-09.md), effective Oct 24, 2017: Revision A

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-84-32-145/proposed.md).

## Text (12 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2017-0334; AD 2017-19-09 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

T x L t r S B 8 4 --- 3 2 --- 1 4 5
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Revision ‘A’ 18 Oct 2016
NB
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 --- 3 2 --- 1 4 5
Landing Gear - - - Nose Landing Gear Insta llation - - - Introduction of Redesigned
Retention Mechanism and Introduct ion of New Pivot Pin Retention Bolt - - -
ModSum 4- - - 168127
This page transmits Revision ‘A’ of Service Bulletin 84- - -32- - -145, pages 1 thru 8,
dated 18 Oct 2016.
This service bulletin is re- - -issued in its entirety for the reasons that follow:
--- s e c t i o n1. PLANNING INFORMATION para D. Compliance is revised to include
the new para that follows:
“This service bulletin supersedes service bulletin 84- - -32- - -110 (ModSum
4- - -113749).”
--- t h eReferences section is revised to convey the latest revision of the service
bulletin and engineering documentation.
--- s e c t i o n3. ACCOMPLISHMENT INSTRUCTIONS is revised to include a new para
before A . J o b S e t --- U pthat reads:
‘‘If it is not possible to complete all the instructions of this service bulletin because
of the configuration of the aircraft, speak w ith a representative of Bombardier in the
CRC at 1- - -844- - -272- - -2720 (1- - -844- - -CRC- - -CRC0) or email at
thd.qseries@aero.bombardier.com for analysis and to get an approved disposition
to complete this service bulletin’’.
Remove the initial issue of Service Bulletin 84- - -32- - -145 and attached VSB, and
replace with attached.
Initial issue - - - Pages 1 thru 8 dated 26 Jul 2016

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1

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D
S.B. 84- - -32- - -145
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Revision ‘A’ 18 Oct 2016
SERVICE BULLETIN
Customer
Support
ATA SYSTEM: 3221 NUMBER: 84- - -32- - -145
BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS
SERVICE BULLETIN TO BE PARTICULARL Y SIGNIFICANT AND
URGE OPERATORS TO PROMPTL Y EVALUATE THE CONTENTS
SUBJECT : Landing Gear - - - Nose Landing Gear Installation - - - Introduction of
Redesigned Retention Mechanism and Introduction of New Pivot Pin
Retention Bolt - - - ModSum 4- - - 168127
1. PLANNING INFORMA TION
A. Effectivity
Aircraft Affected:
In- - -Service: All DHC- - -8 Aircraft Models 401 and 402 Serial Numbers 4001,
4003 thru 4533, 4535 with NLG Shock Strut Assembly with
either Part Number 47100- - -9 or - - -11 or - - -13 or - - -15 or - - -17 or
- - -19 installed.
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.
Spares Affected:
None

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Revision ‘A’ 18 Oct 2016
B. Reason
Problem: On aircraft with NLG Shock Strut Assembly with either Part Number
47100- - -9 or - - -11 or - - -13 or - - -15 or - - -17 installed without the service
bulletin 84- - -32- - -110 incorporated, reports of missing or damaged pivot
pin retention bolts have been received. Investigation revealed retention
bolts fail when subjected to localized contact stresses.
On aircraft with NLG Shock Strut Assembly part number 47100- - -19 or any
assembly with service bulletin 84- - -32- - -110 incorporated, reports of
chrome peeling on special bolt P/N 47205- - -1 at the pivot pin link resulting
in corrosion of the bolt substrate layer have been received.
Solution: On aircraft with NLG Shock Strut Assembly with either part number
47100- - -9 or - - -11 or - - -13 or - - -15 or - - -17 installed without the service
bulletin 84- - -32- - -110 incorporated, this service bulletin introduces a
redesigned pivot pin retention mechanism that includes a pivot pin
adapter, special bolt, a pivot pin link and flanged mechanism.
On aircraft with NLG Shock Strut Assembly part number 47100- - -19 or any
assembly with service bulletin 84- - -32- - -110 incorporated, this service
bulletin introduces special bolt P/ N 47205- - -3 with additional processing
for increased chrome plating adhesion and replaces special bolt P/N
47205- - -1.
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 thru each main gear and main gear door
mechanism
- - - access is gained to the nose landing gear
- - - the part number of the NLG Shock Strut Assembly is verified and checked for SB
84- - -32- - -110 incorporation
- - - on aircraft with NLG Shock Strut Assembly with either part number 47100- - -9 or - - -11
or - - -13 or - - -15 or - - -17 installed without the service bulletin 84- - -32- - -110 incorporated,
a jack is installed at the jacking point of the nose fuselage and a redesigned pivot pin
retention mechanism is installed

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Revision ‘A’ 18 Oct 2016
- - - on aircraft with NLG Shock Strut Assembly part number 47100- - -19 or any assembly
with service bulletin 84- - -32- - -110 incorporated, special bolt 47205- - -1 is replaced with
special bolt 47205- - -3
- - - close out.
D. Compliance
Bombardier Inc. highly recommend incorporation of ModSum 4- - -168127 at the
earliest opportunity unless otherwise directed by the operator’s airworthiness
authority.
This service bulletin supersedes service bulletin 84- - -32- - -110 (ModSum 4- - -113749).
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).
F. M a n p o w e r
Part A - - - Redesigned Pivot Pin Retention Mechanism Installation
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

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Revision ‘A’ 18 Oct 2016
Part B - - - Special Bolt Replacement
It will take an estimated 0.75/1.25 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 0.25
Procedure in Part B 0.25/75*
T e s t/R T S 0.00
Close- - -Out 0.25
*If jacking the NLG becomes necessary during bolt replacement.
G. Material - - - Price and Availability
Refer to attached UTC Aerospace Systems Service Bulletin 47100- - -32- - -130.
H. T ooling - - - Price and Availability
None
I. Weight and Balance
PART A:
A/C T ype and
Model
Weight (Lb) Arm (Inches)
Moment
(Inches x Lb)
x 0.001
D H C --- 8 M o d e l 4 0 1 +0.10 - - -119.92 - - -0.01
D H C --- 8 M o d e l 4 0 2 +0.10 - - -119.92 - - -0.01
PART B:
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..................................
Weight and Balance Manual (Imperial) PSM 1- - -84- - -8................
Weight and Balance Manual (Metric) PSM 1- - -84- - -8M..................
L. References
Rev. ‘A’ of this service bulletin was prepared to the related data that follows:
ModSum 4N168127 Rev. ‘D’
ModSum 4- - -168127 Rev. ‘D’
ModSum 4N113749 Rev. ‘L’
UTC Aerospace Systems Service Bulletin 47100- - -32- - -130 dated May 24/16
PCA 46096 Revision 0 (for internal reference only)
Transport Canada Airworthiness Directive Pending
2. MATERIAL INFORMA TION
A. Parts Required Per Aircraft
Refer to attached UTC Aerospace Systems Service Bulletin 47100- - -32- - -130.
B. Parts Required to Modify Spares
None
C. Special T ools and Equipment Required
None
D. Existing Parts Accountability
Refer to attached UTC Aerospace Systems Service Bulletin 47100- - -32- - -130.

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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 Bombardier in the CRC at
1- - -844- - -272- - -2720 (1- - -844- - -CRC- - -CRCO) or email at thd.qseries@aero.bombardier.com
for 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 .
WARNING: MAKE SURE YOU INSTALL THE LOCKPINS ON THE LANDING
GEAR DOORS. MAKE SURE YOU DISCONNECT THE LANDING
GEAR DOORS. IF YOU DO NOT DO THIS THE LANDING GEAR
DOORS WILL CLOSE WHEN YOU APPL Y THE HYDRAULIC
PRESSURE. THIS 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 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 the nose gear ground lock is engaged.
(3) Make sure that lock pins are installed through each main gear and main gear
door mechanism.
(4) Set wheel chocks in front and behind the landing gear tires.

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Revision ‘A’ 18 Oct 2016
B. Procedure
(1) Verify the part number of the installed NLG Shock Strut Assembly.
(2) If the part number of the NLG Shock Strut Assembly is either 47100- - -9 or - - -11 or
- - -13 or - - -15 or - - -17, verify if a pivot pin retention mechanism is installed per SB
84- - -32- - -110. If not installed, go toPart A. If installed, go to Part B.
(3) If the part number of the NLG Shock Strut Assembly is 47100- - -19, go to Part B.
Part A - - - Redesigned Pivot Pin Retention Mechanism Installation
(aircraft with NLG Shock Strut Assembly with either part number 47100- - -9 or
--- 1 1 o r --- 1 3 o r --- 1 5 o r --- 1 7 i n s t a l l e d w i t h o u t t h e s e r v i c e b u l l e t i n 8 4 --- 3 2 --- 1 1 0
incorporated)
(1) Jack the aircraft at the nose fuselage (refer to the applicable instructions in AMM
TASK 07- - -10- - -00- - -582- - -803)
(2) Install the new pivot pin retention mechanism to the shock strut (refer to Part A of
the ACCOMPLISHMENT INSTRUCTIONS section in the attached UTC Aerospace
Systems Service Bulletin 47100- - -32- - -130).
(3) Lower the aircraft and remove the jack from the jacking point of the nose
fuselage (refer to the applicable instructions in AMM TASK
07- - -10- - -00- - -582- - -803).
(4) Re- - -identify the NLG Shock Strut Assembly per the applicable instructions given
in the RE- - -IDENTIFICATION section in the attached UTC Aerospace Systems
Service Bulletin 47100- - -32- - -130.
Part B - - - Special Bolt Replacement
(aircraft with NLG Shock Strut Assembly part number 47100- - -19 or any
assembly with service bulletin 84- - -32- - -110 incorporated)
(1) Replace the existing pivot pin retention bolt P/N 47205- - -1 with the new bolt P/N
47205- - -3 (refer to Part B of the ACCOMPLISHMENT INSTRUCTIONS section in
the attached UTC Aerospace Systems Service Bulletin 47100- - -32- - -130). If
necessary, jack the aircraft at the nose fuselage if the bolt cannot be replaced
easily (refer to the applicable instructions in AMM TASK 07- - -10- - -00- - -582- - -803).

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(2) If aircraft was lifted at the nose fuselage, lower the aircraft and remove the jack
(refer to the applicable instructions in AMM TASK 07- - -10- - -00- - -582- - -803).
(3) Re- - -identify the NLG Shock Strut Assembly per the applicable instructions given
in the RE- - -IDENTIFICATION section in the attached UTC Aerospace Systems
Service Bulletin 47100- - -32- - -130.
C. Close Out
(1) Remove all tools and equipment from the work area.
(2) On incorporation of this ModSum/Modification, add the weight and balance data
shown in Section 1.I of this service bulletin to the Weight and Balance Manual
P S M 1 --- 8 4 --- 8 o r 1 --- 8 4 --- 8 M . U n d e r ‘ D e s c r i p t i o n o f C h a n g e ’ e n t e r “ M o d S u m
4- - -168127 incorporated.”
(3) 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.
1

### Page 11

Jan 2009
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 12

Feb 2009
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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