# Bombardier Service Bulletin 84-32-100

Copy: Revision A ("U.S. DOT/FAA - SB 84-32-100 Rev A"), 14 pages: PDF https://openairdocs.org/files/sha256/e3/65/e365aef43061e530bc22fce6c8992899ced11be6db2a78a21ce0588caab63f30; text https://openairdocs.org/service-documents/bombardier/sb-84-32-100/file/e365aef43061.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2014-0129; AD 2014-16-07 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: 84-32-100
- Latest revision known: 84-32-100, Revision A, dated August 30, 2012 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/bombardier/sb-84-32-100

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

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

- [AD 2014-16-07](https://openairdocs.org/ad/2014-16-07.md), effective Sep 23, 2014: Revision A

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/bombardier/sb-84-32-100/proposed.md).

## Text (14 pages)

Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2014-0129; AD 2014-16-07 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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Revision ‘A’ 30 Aug 2012
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L a n d i n g G e a r --- M L G --- E m e r g e n c y E x t e n s i o n S y s t e m --- I n s t a l l a t i o n o f n e w
Cam Mechanism Assembly 48510- - - 5 - - - ModSum 4- - - 113765
This page transmits Revision ‘A’ of Service Bulletin 84- - -32- - -100, pages 1 thru 6,
dated: 30 Aug 2012
This service bulletin is re- - -issued in its entirety for the reasons that follow:
--- t h eEffectivity section has been revised
--- t h eReferences section is revised to convey the latest revision of the service
bulletin and engineering documentation
The Compliance in the previous issue of this service bulletin is not affected by this
revision. No additional rework to the aircraft is introduced by this revision.
Remove Service Bulletin 84- - -32- - -100 initial issue dated: 15 Aug 2012 and replace
with attached.
Previous issues of Service Bulletin 84- - -32- - -100:
Initial issue - - - Pages 1 thru 6 dated: 15 Aug 2012
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D
S.B. 84- - -32- - -100
Page 1 of 6
15 Aug 2012
Revision ‘A’ 30 Aug 2012 JR
SERVICE BULLETIN
Customer
Support
ATA SYSTEM: 3211 NUMBER: 84- - -32- - -100
S U B J E C T: L a n d i n g G e a r --- M L G --- E m e r g e n c y E x t e n s i o n S y s t e m --- I n s t a l l a t i o n
of new Cam Mechanism Assembly 48510- - - 5 - - - ModSum 4- - - 113765
1. PLANNING INFORMA TION
A. Effectivity
Aircraft Affected:
In- - -Service: DHC- - -8 Aircraft Models 401 and 402 Serial Numbers 4001,
4003 thru 4418, 4422 and 4423.
Production: ModSum 4- - -113765 will be installed before delivery on
applicable DHC- - -8 Aircraft at Serial Number 4419 thru 4421,
4424 and subsequent.
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:
The following is a list of spares affected by this change. Review spares and
procurement systems to determine the existence of any listed parts. See
Paragraph 2.D., Existing Parts Accountability, for disposition.
Part Number Description
48510- - -1/- - -3 Cam Mechanism Assembly
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B. Reason
Problem: There have been instances of cam mechanism assembly input lever
fractures. In these instances, the MLG door would not open at line check.
Cause: Investigation revealed mechanical swelling of the lined bushings on the
input and cam follower lever shafts, increasing the force required to move
the lever. A contributing factor may be cold temperatures combined with
moisture ingress.
Solution: The new cam mechanism assembly incorporates new sealed roller
bearings in place of the lined bushings, and grease in the cavity between
the new bearings.
C. Description
The procedures in this service bulletin give the instructions to do the tasks that
follow:
- - - aircraft is put into standard configuration for maintenance
- - - 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
- - - MLG alternate extension system cam mechanism assemblies are replaced.
- - - rigging of the alternate extension MLG cables is done
- - - a test of the MLG alternate release system is done
- - - close out.
NOTE: Before incorporating this service bulletin operators are to contact
Goodrich Landing Gear to determine availability of Cam Mechanism
Assembly 48510- - -5. Refer to Goodrich Service Bulletin 48510- - -32- - -94 R1
for further details.
D. Compliance
Bombardier Inc. recommends incorpora tion of ModSum 4- - -113765 at the earliest
opportunity unless otherwise directed by the operator’s airworthiness authority.
E. Approval
The technical content of this service bulletin has been approved under the
authority of the Transport Canada Civil Aviation (TCCA) Design Approval
O r g a n i z a t i o n N o : D A O # 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
It will take an estimated 4.5 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 0.25
Procedure 3.00
T e s t/R T S 1.00
Close- - -Out 0.25
For any on- - -site labor assistance, please speak with a Fleet Services representative for
a quote. The Fleet Services group can be contacted via the Q Series T echnical Help
Desk by telephone at 416- - -375- - -4000 or email at: thd.qseries@aero.bombardier.com
G. Material - - - Price and Availability
Refer to Goodrich Service Bulletin 48510- - -32- - -94 R1.
H. T ooling - - - Price and Availability
None
I. Weight and Balance
None
J. Electrical Load Data
Not affected
K. Publications Affected
Dash 8 Illustrated Parts Catalogue PSM 1- - -84- - -4....................
ModSums Manual PSM 1- - -84- - -12..................................
Maintenance Requirement Manual PSM 1- - -84- - -7....................
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L. References
The initial issue of this service bulletin was prepared to the engineering drawings
and related data that follows:
ModSum 4- - -113765 Rev. ‘D’
PCA 43597 Revision 0 (for internal reference only)
Goodrich Service Bulletin 48510- - -32- - -94 R1 dated: Apr 19/12
2. MATERIAL INFORMA TION
A. Parts Required Per Aircraft
(1) Detailed Parts List:
Quantity
Per Aircraft
Part Number Description Remarks
2 48510- - -5 Cam Mechanism
Assembly
Supplied by
Goodrich
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
p e rn e x th i g h e ra s s e m b l yf o ri n d e n t e dp a r t s .
Existing
Part Number Description Qty. IC DC
New Part
Number PNC
48510- - -1/- - -3 Cam Mecha-
nism Assembly
2 A DIS 48510- - -5 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.
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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.
PNC Part Number Code
N No equivalent Bombardier Inc. 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
A . J o b S e t --- U p
WARNING: YOU MUST 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: YOU MUST 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 .
(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 up the work platforms or ladders as required to gain access to the main
landing gear alternate extension sys tem. Make sure the work platforms or
ladders are electrically grounded.
B. Procedure
(1) Remove existing Cam Mechanism Assembly 48510- - -1 or - - -3. Refer to
Maintenance Manual TASK 32- - -34- - -26- - -000- - -801.
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(2) Install new Cam Mechanism Assembly 48510- - -5. Refer to Maintenance Manual
TASK 32- - -34- - -26- - -400- - -801.
(3) Do the rigging of the alternate extension MLG cables. Refer to Maintenance
Manual TASK 32- - -34- - -16- - -830- - -802.
(4) Do a test of the MLG alternate release system as per Maintenance Manual TASK
32- - -34- - -16- - -830- - -802.
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.
1
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48510-32-94 R1 
 
SERVICE BULLETIN 
                           HIGHLIGHTS 
Apr 19/12 
              Page 1 of 1  
THESE COMMODITIES, SOFTWARE OR TECHNOLOGY WERE EXPORTED/RE-EXPORTED IN ACCORDANCE WITH U.S. EXPORT 
ADMINISTRATION REGULATION.  DIVERSION CONTRARY TO U.S. LAW IS PROHIBITED. 
 
DASH 8 Q400 
MLG ALTERNATE EXTENSION SYSTEM – NEW CAM MECHANISM ASSEMBLY 
PN 48510-5 
 
 
REVISION NO.1 – April 19, 2012 
 
 
Service Bulletin 48510-32-94 R1 supersedes Service Bulletin 48510-32-94 dated Dec 2/11 and is 
re-issued in its entirety to reflect the changes listed below. 
 
The compliance in the previous issue of this Service Bulletin is not affected by this revision.   
No additional rework is introduced by this revision. 
 
Please destroy all copies of SB 48510-32-94 dated Dec 2/11. 
 
 
 
Page/Para     Change 
 
 
Page 1, Section I, Para1, Para 3, Para 4 Effectivity and Part number revised.  Reason revised to 
give additional information on 46510-3 assembly. 
Page 2, Section I, Para 11 Reference added. 
Page 2, Section II, Para 1 Material cost and Availability updated. 
 
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48510-32-94 R1 
 SERVICE BULLETIN 
Apr 19/12 
Page 1 of 2 
THESE COMMODITIES, SOFTW ARE OR TECHNOLOGY W ERE EXPORTED/RE -EXPORTED IN ACCORDANCE W ITH U.S. EXPORT 
ADMINISTRATION REGULATION. DIVERSION CONTRARY TO U.S. LAW  IS PROHIBITED.  
Reference Goodrich CMM for proprietary information 
DASH 8 Q400 
MLG ALTERNATE EXTENSION SYSTEM – NEW CAM MECHANISM ASSEMBLY 
PN 48510-5 
------------------------------------------------------------------------------------------------------------------------------------------ 
SECTION I - PLANNING INFORMATION 
1. EFFECTIVITY  
All MLG Alternate Extension System Cam Mechanism Assemblies PN 48510-1/-3. 
2. CONCURRENT REQUIREMENTS 
NA 
3. REASON 
There ha ve been instances of cam mechanism assembly input lever fractures.  In these 
instances, the MLG door would not open at line check. 
Investigation revealed mechanical swelling of the lined bushings on the input and cam follower 
lever shafts, increasing the force required to move the lever.  A contributing factor may be cold 
temperatures combined with moisture ingress in the cavity between the shaft bushings. 
Cam mechanism assembly 48510-3 has sealed 51200 steel roller bearings in place of the 
lined bushings, and grease per MIL-PRF-81322 in the cavity between the bearings. 
The new cam mechanism assembly 48510-5 incorporates CRES roller bearings and grease 
per MIL-PRF-23827 in the cavity between the new bearings. 
4.  DESCRIPTION 
The PN 48510-1/-3 cam mechanism assembly is replaced by a new 48510-5 cam mechanism 
assembly. 
5. COMPLIANCE  
Goodrich Landing Gear in concurrence with the aircraft manufacturer recommends 
incorporation of this bulletin at operator’s earliest convenience. 
6. APPROVAL  
This bulletin contains no modification information that revises approved configurations, and 
therefore does not require governmental or other regulatory approval. 
The technical content of this Service Bulletin has been reviewed and accepted by Bombardier 
Aerospace. 
7. MANPOWER 
NA 
8. TOOLING  
NA 
9. WEIGHT AND BALANCE  
NA 
10. ELECTRICAL LOAD DATA  
NA 
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48510-32-94 R1 
 
Goodrich Landing Gear Division 
Goodrich Aerospace Canada Ltd. 
Apr 19/12 
Page 2 of 2 
Reference Goodrich CMM for proprietary information 
11. REFERENCES  
Goodrich Reference Modification Summary Package (MODSUM) 4N113765 
Goodrich Landing Gear Service Information Letter (SIL) 02121-32-53 
 
12. OTHER PUBLICATIONS AFFECTED 
NA 
---------------------------------------------------------------------------------------------------------------------------------------- 
SECTION II – MATERIAL INFORMATION 
1. MATERIAL COST AND AVAILABILITY 
A. Material Cost and Availability 
Refer to Goodrich Landing Gear Service Information Letter (SIL 02121-32-53) for material 
cost and availability related to this Service Bulletin. 
Parts are available from: 
Goodrich Landing Gear Division,  
1400 South Service Rd,  
Oakville, ON, Canada L6L 5Y7 
Phone: 905-827-7777 
Fax: 905-825-1583 
Att: Warranty Administrator 
---------------------------------------------------------------------------------------------------------------------------------------- 
SECTION III - ACCOMPLISHMENT INSTRUCTIONS 
1. General 
A. Contact Goodrich Landing Gear at coordinates detailed in SECTION II to determine 
availability. 
B. Goodrich Landing Gear will request a no charge purchase order for total number of unit s, 
with aircraft S/Ns and anticipated new cam mechanism installation date. 
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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 14

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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