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DHC ---8 (DASH 8)

SERVICE BULLETIN 84 ---32 ---108

Landing Gear --- MLG Door Actuator --- Incorrect Scraper Installation --- Special

Inspection and Rectification

This page transmits Bombardier PDF Merged Document SB 84 ---32 ---108 Revision

‘A’ dated: 01 Oct 2012 & Goodrich VSB 46830 ---32 ---106 Revision 1 dated: Sep

12/12

This service bulletin is re ---issued in its entirety for the reasons that follow:

--- the Effectivity section is revised to include MLG door actuator affected serial

numbers

--- the Description, Material --- Price and Availability, Existing Parts Accountability

and ACCOMPLISHMENT INSTRUCTIONS sections have been revised to show

latest issue of Goodrich service bulletin

--- the References section is revised to convey the latest revision of the service

bulletin and engineering documentation

--- Goodrich VSB 46830 ---32 ---106 has been revised

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 Bombardier PDF Merged Document SB 84 ---32 ---108_06 Sep 2012 &

Goodrich VSB 46830 ---32 ---106_Aug 24/12 and replace with attached.

Previous issues of Bombardier PDF Merged Document SB 84 ---32 ---108 &

Goodrich VSB 46830 ---32 ---106:

Initial issue --- Pages 1 thru 20 dated 06 Sep 2012 & Aug 24/12 respectively.

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SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 3212 NUMBER: 84 ---32 ---108

BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS

SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND

URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Landing Gear --- MLG Door Actuator --- Incorrect Scraper Installation

--- Special Inspection and Rectification

1. PLANNING INFORMATION

A. Effectivity

Aircraft Affected:

In ---Service: DHC ---8 Aircraft Models 401 and 402 Serial Numbers 4001

thru 4415 with Main Landing Gear Door Actuator Assembly

P/N 46830 ---7 containing the following serial numbers:

MAL ---NMC0001 to MAL ---NMC0006, MAL ---NMC0008 to MAL ---NMC0010,

MAL ---NMC0012 to MAL ---NMC0019, MAL ---NMC0021, MAL ---NMC0031,

MAL ---NMC0033, MAL ---NMC0039, MAL ---NMC0040, MAL ---NMC0042,

MAL ---NMC0045 to MAL ---NMC0052, MAL ---NMC0054, MAL ---NMC0056 to

MAL ---NMC0074, MAL ---NMC0076 to MAL ---NMC0078, MAL ---NMC0080,

MAL ---NMC0082, MAL ---NMC0086 to MAL ---NMC0089, MAL ---NMC0094 to

MAL ---NMC0100, MAL ---NMC0102, MAL ---NMC0103, MAL ---NMC0105,

MAL ---NMC0107 to MAL ---NMC0109, MAL ---NMC0112, MAL ---NMC0127,

MAL ---NMC0150.

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.

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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.

Part Number Description

46830 ---7 MLG Door Actuator

B. Reason

Problem: The main landing gear door actuator P/N 46830 ---7 may have had the

scraper installed backwards. If the scraper is installed backwards, the

function of the actuator may be adversely affected.

Solution: This service bulletin provides instructions for an inspection and

rectification for aircraft that have a suspect unit.

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

--- the MLG door actuator in each nacelle is inspected to determine if it carries a

specific serial number as per the effectivity section of Goodrich Service Bulletin

46830 ---32 ---106 R1

--- if aircraft does not have a matching serial number the aircraft can be returned to

service

--- affected aircraft will require repeat inspections until affected unit is replaced

--- if aircraft has an affected unit, it must be replaced

--- close out.

D. Compliance

Bombardier Inc. recommends incorporation of this service bulletin at the earliest

opportunity unless otherwise directed by the operator’s airworthiness authority.

Transport Canada Airworthiness Directive Pending

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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 #93 ---Q ---02.

This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage

Tolerance Inspections (DTIs).

F. Manpower

PART A --- INSPECTION

It will take an estimated .75 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 MAN ---HOURS

Job Set ---Up 0.25

Procedure in Part A 0.25

Test / RTS 0.00

Close ---Out 0.25

PART B --- ACTUATOR REPLACEMENT

It will take an estimated 16.5 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 MAN ---HOURS

Job Set ---Up 0.25

Procedure in Part B 15.00*

Test / RTS 1.00

Close ---Out 0.25

* LH side 9 hours, RH side 6 hours.

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 Technical Help

Desk by telephone at 416---375---4000 or email at: thd.qseries@aero.bombardier.com

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G. Material --- Price and Availability

Refer to Goodrich Landing Gear Division service bulletin 46830 ---32 ---106 R1

H. Tooling --- Price and Availability

None

I. Weight and Balance

None

J. Electrical Load Data

Not affected

K. Publications Affected

None

L. References

Revision ‘A’ of this service bulletin was prepared to the engineering drawings and

related data that follows:

PCA 44332 Revision 0 (for internal reference only)

Goodrich Landing Gear Division service bulletin 46830 ---32 ---106 R1 dated: Sep

12/12

Transport Canada Airworthiness Directive Pending

2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

(1) Detailed Parts List:

Quantity

Per Aircraft

Part Number Description Remarks

2 NAS1611 ---123

or

Seal

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Quantity

Per Aircraft

Part Number Description Remarks

2 ---123E515 ---80

2 7115FS ---954 ---P4 Seal

2 R2301 ---017S041 Seal, MSE

B. Parts Required to Modify Spares

Quantity

Per Aircraft

Part Number Description Remarks

2 NAS1611 ---123

or

Seal

2 ---123E515 ---80

2 7115FS ---954 ---P4 Seal

2 R2301 ---017S041 Seal, MSE

C. Special Tools and Equipment Required

TOOL NO. NOMENCLATURE MANUFACTURER USE

AT 31846 Assembly Tool Goodrich Installation/removal of

gland nut

TF 31847 Test Fixture Goodrich Landing

Gear

Secure actuator

assembly during

testing

Force Gauge Commercially

Available

D. Existing Parts Accountability

Refer to Goodrich Landing Gear Division service bulletin 46830 ---32 ---106 R1

3. ACCOMPLISHMENT INSTRUCTIONS

A. Job Set ---Up

(1) Placard and select all aircraft electrical power to OFF. Obey all relevant

WARNINGS and CAUTIONS (refer to AMM TASK’S 24 ---00 ---00 ---861 ---802 and

24 ---00 ---00 ---910 ---801).

(2) Make sure the nose gear ground lock is engaged.

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(3) Make sure that lock pins are installed through each main gear and main gear

door mechanism.

(4) Set up work platforms or ladders as required to gain access to MLG door

actuator in each nacelle. Make sure work platforms or ladders are electrically

grounded.

(5) Check aircraft logbooks or the MLG door actuator in each nacelle to determine if

it carries any of the serial numbers stated in the effectivity section of Goodrich

Service Bulletin 46830 ---32 ---106 R1.

(6) If actuators do not match any of the serial numbers, go to Close Out section of

this service bulletin and return aircraft to service.

(7) If any actuator serial number matches the effectivity on Goodrich Service Bulletin

46830 ---32 ---106 R1, go to PART A --- INSPECTION of this service bulletin.

B. Procedure

PART A --- INSPECTION

(1) Remove lockpins from the main landing gear doors and close the doors.

(2) Open the MLG bypass door in the flight compartment ceiling, with a force gauge

attached pull the alternate release handle to open the MLG doors, the

approximate pull force to release the MLG aft doors is 52 lbf.

(3) If the doors do not release easily and the force exceeds 67 lbf, the MLG aft door

actuator will need to be replaced, go to PART B of this service bulletin.

PART B --- ACTUATOR REPLACEMENT

(1) Make sure that lock pins are installed through each main gear and main gear

door mechanism.

NOTE: Actuator is to be replaced with a unit supplied by Goodrich or reworked in

accordance with the enclosed procedure.

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 ACCIDENTALLY 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 ACCIDENTALLY CLOSE THE LANDING GEAR DOORS. THIS CAN

CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT.

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(2) Remove the MLG Doors Actuator. Refer to Appendix A at the back of this service

bulletin.

NOTE: It may be necessary to remove the SPU to gain additional access for the

removal and installation of the MLG door actuator on the left hand

nacelle. Ref AMM tasks 29 ---11 ---36 ---000 ---801 & 29 ---11 ---36 ---400 ---801.

(3) Rework MLG Doors Actuator as follows: (Refer to Figure 1)

(a) Cut lock wire and remove two flat fillister head screws (20) and lock tab

(30).

(b) Cut lock wire and loosen jam nut (50). Remove rod end assembly from

piston (140) and remove jam nut (50) and lock key (40).

(c) Using tool AT 31846, remove gland nut (100).

NOTE: Do not remove piston 46835 ---1 (140) from actuator cylinder assembly.

(d) Remove seals M83461/1 ---123 (110), 7115FS ---954 ---P4 (120) and

R2301 ---017S041 (130) from gland nut.

(e) Install new seals NAS1611 ---123 (110) or 2 ---123E515 ---80 (110) and

7115FS ---954 ---P4 (120) to gland nut 46833 ---1 (100).

(f) Install new seal R2301 ---017S041 (130) to gland nut 46833 ---1 (100). Refer

to Figure 2 for correct seal orientation.

(g) Install gland nut (100) over the piston (140). Using tool AT 31846, thread

and torque gland nut (100), 200 --- 250 in. lbs.

(h) Assemble jam nut (50) onto rod end assembly. Thread rod end assembly

onto piston rod (140).

(i) Install actuator assembly into test fixture TF ---31847. Push piston (140)

down and make sure it is bottomed. Measure the fully retracted length and

adjust rod end assembly as required (7.802 --- 7.822 inches) retracted

length.

(j) If necessary, adjust rod end assembly one quarter turn at a time. Make

sure the actuator meets retract and extend length requirements.

NOTE: Make sure locking features in the rod end assembly and the piston are

aligned. Do not fully tighten the jam nut.

(k) Pull the piston (140) and measure the fully extended length (11.33 --- 11.37

inches).

NOTE: The difference between the two measurements shall be the actual stroke.

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(l) Install rod end lock key (40) and torque jam nut (50), 160 --- 190 in. lbs.

(m) Disconnect and remove actuator assembly from test fixture.

(n) Install lock tab (30) and secure with two flat fillister head screws (20).

Torque screws (20).

(o) Vibropeen SB 32 ---106 and date accomplished in the MOD STATUS field of

nameplate (10).

CAUTION: DO NOT LETTER STAMP NAMEPLATE ON ASSEMBLY. THIS CAN

DAMAGE ASSEMBLY.

(4) Install the MLG Doors Actuator. Refer to Appendix B at the back of this service

bulletin.

(5) Bleed the No. 2 Hydraulic System. Refer to AMM Task 29 ---10 ---00 ---870 ---802.

(6) Remove the lockpins from the door mechanism of the MLG.

(7) Do an operational check of the Main Landing Gear aft door actuator as follows:

(a) Pressurize hydraulic system #2. Refer to AMM Task 29 ---00 ---00 ---863 ---801.

(b) Make sure the amber LDG door light on the LDG gear selector panel

extinguishes and the MLG doors are closed.

(c) In the flight compartment ceiling, set the landing ---gear inhibit switch to the

INHIBIT position.

(d) Make sure that the amber lights on the LDG selector panel illuminate and

the MLG doors open.

(e) Set the landing ---gear inhibit switch to the NORMAL position make sure the

amber LDG door lights extinguish and the MLG doors close.

(f) Repeat the above check 3 times to help bleed the hydraulic system.

(g) Check for leaks.

C. Close Out

(1) Remove all tools and equipment from the work area.

(2) On completion of this service bulletin, make the following entry in the

appropriate logbooks: “Service Bulletin 84 ---32 ---108 Landing Gear --- MLG

Door Actuator --- Incorrect Scraper Installation --- Special Inspection and

Rectification accomplished.”

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Scraper Installation

Figure 2

GLAND NUT (100)

SEAL (SCRAPER) R2301 ---017S041 (130)

PISTON (140)

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Appendix A

Removal of the MLG Doors Actuator

1. General

A.

The maintenance procedure that follows is for the removal of the actuator for the aft

doors of the main landing gear (written as the ”MLG” in these procedures). The

MLG doors actuator is installed in the engine nacelle and is connected to the MLG

aft doors mechanism. The procedures for the MLG doors actuator of the left and

the right nacelle are the same. The procedure for the MLG doors actuator of the left

nacelle is given.

2. Job Set ---Up Information

A. Tools & Equipment

(1) Commercially Available

Container, Minimum 1 Imperial gallon (1.2 US gallon, 4.5 liter) capacity

B. Reference Information

AMM TASK 29 ---00 ---00 ---910 ---801 Hydraulic Safety Precautions

AMM TASK 32 ---00 ---00 ---840 ---801 Open and Lock the Landing Gear Doors

3. Job Set ---Up

A. Obey all the hydraulic safety precautions (Refer to AMM TASK

29 ---00 ---00 ---910 ---801.

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.

B. Make sure that all the hydraulic power is off.

WARNING:

YOU MUST INSTALL THE LOCKPINS IN THE DOOR MECHANISMS OF THE MLG

AND NLG. THE DOOR MECHANISMS CAN ACCIDENTALLY CLOSE THE

LANDINGGEAR DOORS. THIS CAN CAUSE INJURIES TO PERSONS AND

DAMAGE TO THE EQUIPMENT.

C. Open and lock the landing gear doors (Refer to AMM TASK 32---00---00---840---801).

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4. Procedure

Refer to Figure 402.

A. Remove the MLG doors actuator as follows:

(1) Disconnect the hydraulic hoses (1) and (2) from the MLG doors actuator (3) as

follows:

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.

(a) Put the container below the MLG doors actuator (3) to collect the hydraulic

fluid.

(b) Disconnect the hydraulic hoses (1) and (2) from the unions (4) and (5).

(c) Seal the hydraulic hoses (1) and (2) and the unions (4) and (5) with caps.

(2) Disconnect the MLG doors actuator (3) from the lock link assembly (6)

as follows:

(a) Remove the cotter pin (7) from the nut (8). Discard the cotter pin (7).

(b) Remove the nut (8), the washer (9), and the bushing (10) from the bolt (11).

(c) Remove the bolt (11) from the lock link assembly (6).

(3) Disconnect the MLG doors actuator (3) from the frame assembly (12) as

follows:

(a) Remove the cotter pin (13), the nut (14), and the washer (15) from the bolt (16).

Discard the cotter pin (13).

NOTE: In order to remove the actuator, it may be necessary to pull the door

mechanism spring out of the way, use a strap to pull the spring enough to remove

the actuator. It is difficult to re ---install the spring if removed.

(b) Hold the MLG doors actuator (3) in position. Remove the bolt (16) and the

sleeve bushing (17) from the frame assembly (12) and the MLG doors actuator (3).

(c) Remove the MLG doors actuator (3) from the frame assembly (12).

(4) Remove the MLG doors actuator (3) from the nacelle.

(5) Rework or replace with serviceable unit.

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Appendix B

Installation of the MLG Doors Actuator

General

A.

The maintenance procedure that follows is for the installation of the actuator for the

aft doors of the main landing gear (written as the ”MLG” in these procedures). The

MLG doors actuator is installed in the engine nacelle and is connected to the MLG

aft doors mechanism. The procedures for the MLG doors actuator of the left and

the right nacelle are the same. The procedure for the MLG doors actuator of the left

nacelle is given.

2. Job Set ---Up Information

A. Tools & Equipment

(1) Commercially Available

Wrench, Torque 10 to 200 lbf in (1.13 to 11.3 Nm)

(2) Commercially Available

Wrench, Torque 200 to 500 lbf in (22.6 to 56.49 Nm)

(3) Commercially Available

Grease Gun

B. Consumable Materials

(1) 04 ---03 Synthetic grease

(2) 05 ---15 Adhesive

(3) 07 ---01A F13 Coating ---compound, corrosion preventive

(4) 10 ---09 Tamper ---proof sealant

3. Job Set ---Up

A. Make sure that the aircraft is in the same configuration as in the removal task.

4. Procedure

Refer to Figure 402.

A. Apply finger pressure to the flanged bushes (18), and the plain bushes (19) in

the frame assembly (12) to make sure that there is no movement. If there is

movement, do as follows:

(1) Remove the bush from the frame assembly (12), (Refer to AMM TASK

20 ---10 ---40 ---400 ---801).

(2) Apply adhesive to the bush and replace in the frame assembly (12), (Refer to

AMM TASK 20 ---10 ---40 ---400 ---801).

B. Install the MLG doors actuator as follows:

NOTE: Make sure that the surfaces are clean with no corrosion, paint, or

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preservation fluids.

(1) Connect the MLG doors actuator (3) to the frame assembly (12) as follows:

(a) Compress the piston of the MLG doors actuator (3) and put it in the frame

assembly (12).

(b) Hold the MLG doors actuator (3) in position in the frame assembly (12). Install

the sleeve bushing (17) through the frame assembly (12) and the MLG doors

actuator (3).

(c) Apply corrosion preventive compound to the shank of the bolt (16) (Refer to

AMM TASK 51 ---25 ---01 ---390 ---801 ).

(d) Install the bolt (16) through the frame assembly (12), and the MLG doors

actuator (3).

(e) Install the washer (15) and the nut (14) on the bolt (16). Safety the nut (14)

with a new cotter pin (13).

(f) Apply a 1/8 in. (3.17 mm) wide stripe of torque seal across the nut (14) and on

the frame assembly (12).

(2) Connect the MLG doors actuator (3) to the lock link assembly (6) as follows:

(a) Apply grease to the shank of the bolt (11).

(b) Align the rod end of the MLG doors actuator (3) with the lock link assembly (6).

(c) Put the bolt (11) through the lock link assembly (6) and the rod end of the MLG

doors actuator (3).

(d) Install the bushing (10), the washer (9), and the nut (8) on the bolt (11).

(e) Torque the nut (8) from 40 to 60 lbf in (4.52 to 6.78 Nm). Safety the nut (8) with

a new cotter pin (13).

(f) Apply a 1/8 in. (3.17 mm) wide stripe of torque seal across the nut (8) and on

the lock link assembly (6).

(3) Connect the hydraulic hoses (1) and (2) to the MLG doors actuator (3) as

follows:

(a) Remove the caps from the hydraulic hoses (1) and (2) and the unions (4) and

(5).

(b) Connect the hydraulic hoses (1) and (2) to the unions (4) and (5).

(c) Torque the hydraulic hose (1) from 270 to 300 lbf in (30.51 to 33.90 Nm).

(d) Torque the hydraulic hose (2) from 170 to 200 lbf in (19.21 to 22.60 Nm).

(e) Apply a 1/8 in. (3.17 mm) wide stripe of torque seal across the hydraulic hoses

(1), (2) and on the unions (4), (5).

(4) Lubricate the grease fittings on the MLG actuator (3) with a grease gun.

(5)If the SPU was removed, reinstall IAW AMM 29 ---11 ---36 ---400 ---801, if not

proceed to close ---out .

1

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 HIGHLIGHTS 

Sep 12/12 

 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 DOOR ACTUATOR – INCORRECT SCRAPER INSTALLATION 

REVISION NO.1 – September 12, 2012 

Service Bulletin 46830-32-106 R1 supersedes Service Bulletin 46830-32-106 dated Aug 24/12 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 46830-32-106 dated Aug 24/12. 

Page/Para Change 

Page 1, Para1.A. Effectivity revised. 

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SERVICE BULLETIN 

Sep 12/12 

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THESE COMMODITIES, SOFTW ARE OR TECHNOLOGY W ERE EXPORTED/RE -EXPORTED IN ACCORDANCE WITH U.S. EXPORT 

ADMINISTRATION REGULATION. DIVERSION CONTRARY TO U.S. LAW IS PROHIBITED. 

Reference Goodrich CMM for proprietary information 

DASH 8 Q400 

MLG DOOR ACTUATOR – INCORRECT SCRAPER INSTALLATION 

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1. PLANNING INFORMATION

A. Effectivity 

Main Landing Gear Door Actuator Assembly PN 46830-7, Serial Numbers: 

MAL-NMC0001 to MAL-NMC0006, MAL-NMC0008 to MAL-NMC0010, MAL-NMC0012 to

MAL-NMC0019, MAL-NMC0021, MAL-NMC0031, MAL-NMC0033, MAL-NMC0039, 

MAL-NMC0040, MAL-NMC0042, MAL-NMC0045 to MAL-NMC0052, MAL-NMC0054, 

MAL-NMC0056 to MAL-NMC0074, MAL-NMC0076 to MAL-NMC0078, MAL-NMC0080, 

MAL-NMC0082, MAL-NMC0086 to MAL-NMC0089, MAL-NMC0094 to MAL-NMC0100, 

MAL-NMC0102, MAL-NMC0103, MAL-NMC0105, MAL-NMC0107 to MAL-NMC0109, 

MAL-NMC0112, MAL-NMC0127, MAL-NMC0150. 

B. Concurrent Requirements 

None. 

C. Reason 

There is a possibility that the scraper was installed backwards. If the scraper is installed 

backwards, the function of the actuator may be adversely affected. 

D. Description

The door actuator assembly is removed from the aircraft, returned to Goodrich for rework or 

reworked per Accomplishment Instructions, Paragraph 3.C. 

E. Compliance

Goodrich Landing Gear, in concurrence with the aircraft manufacturer, recommends 

incorporation of this bulletin at operator’s earliest convenience.

F. Approval

The technical content of this Service Bulletin has been reviewed and accepted by 

Bombardier Aerospace.

G. Manpower

Approximately 2.0 manhours are required to accomplish this Service Bulletin. 

H. Weight and Balance 

No effect.

I. Electrical Load Data 

No change.

J. Software Accomplishment Summary 

Does not apply.

K. References 

Goodrich Landing Gear Component Maintenance Manual 32-31-08

Bombardier Aerospace Service Bulletin 84-32-108 

L. Other Publications Affected

None. 

Bombardier PDF Merged Document SB 84-32-108A_01 Oct 2012 & Goodrich VSB 46830-32-106 R1_Sep 12/12 21 of 24
46830-32-106 R1

Goodrich Landing Gear Division 

Goodrich Aerospace Canada Ltd. 

Sep 12/12 

Page 2 of 4 

Reference Goodrich CMM for proprietary information 

M. Interchangeability or Intermixability of Parts 

Not applicable. 

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2. MATERIAL INFORMATION 

A. Material Cost and Availability

(1) Actuator Exchange 

A rotable pool of actuators has been provisioned; affected actuators will be exchanged 

at no charge to the operator by: 

Goodrich Corporation 

Customer Services 

4115 Corporate Center Drive 

Monroe, NC 28110-1313 USA 

ATT: Customer Services Administrator 

Phone: 1-704-282-2622

Fax: 1-704-290-5959

(2) Actuator Rework 

Seals required for bulletin incorporation are available on a FOC basis from: 

Goodrich Landing Gear 

1400 South Service Rd West 

Oakville, Ontario 

Canada L6L 5Y7

ATT: Warranty Administrator 

Phone: 1-905-827-7777

Fax: 1-905-825-1583

(3) Goodrich will offer credit of $320.00 (USD 2012) for each actuator removed from the 

aircraft in compliance with this Service Bulletin. Warranty claim may be submitted to 

Goodrich Landing Gear in accordance with Service Information Letter (SIL) 02121-32-

035. Spare/shelf units do not apply.

B. Material Required for each Component

Actuator Exchange 

Actuator Rework 

New Part No Qty Per 

Unit

Keyword Old Part No. Instructions / 

Disposition

46830-7 1 Actuator 46830-7 Exchange

New Part No Qty Per 

Unit

Keyword Old Part No. Instructions / 

Disposition

NAS1611-123

OR

2-123E515-80

1 Seal

NAS1611-123

OR

2-123E515-80

Discard

7115FS-954-P4 1 Seal 7115FS-954-P4 Discard

R2301-017S041 1 Seal, MSE R2301-017S041 Discard

Bombardier PDF Merged Document SB 84-32-108A_01 Oct 2012 & Goodrich VSB 46830-32-106 R1_Sep 12/12 22 of 24
46830-32-106 R1

Goodrich Landing Gear Division 

Goodrich Aerospace Canada Ltd. 

Sep 12/12 

Page 3 of 4 

Reference Goodrich CMM for proprietary information 

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3. ACCOMPLISHMENT INSTRUCTIONS

NOTE: Numbers in parenthesis refer to CMM 32-31-08, IPL Figure-Item number.

A. General 

(1) Refer to Bombardier Aerospace Service Bulletin 84-32-108 for removal and installation 

of MLG door actuator. 

(2) Bombardier Aerospace Service Bulletin 84-32-108 also provides instructions for 

optional actuator rework procedure and alternate on-wing pressure test. 

B. Actuator Exchange

(1) Goodrich Customer Services will contact operators directly to coordinate exchange 

actuator availability, and incorporation scheduling. 

(2) Upon being contacted by Goodrich Customer Services, issue a No Charge Exchange 

Purchase Order to: 

Goodrich Corporation 

Customer Services 

4115 Corporate Center Drive 

Monroe, NC 28110-1313 USA 

ATT: Customer Services Administrator 

(3) Upon receipt of exchange actuators, replace existing MLG door actuators. 

(4) Ship removed MLG door actuators, along with a copy of the Exchange Purchase Order 

to address above. 

C. Actuator Rework (Ref Figure 1) 

(1) Disassemble actuator to remove gland nut (1-100) and seals (1-110), (1-120), 

and (1-130) (Ref CMM 32-31-08 DISASSEMBLY). 

NOTE: Do not remove piston (1-140) from actuator cylinder assembly (1-210). 

(2) Install seals (1-110A) or (1-110B), (1-120) and (1-130) into gland nut (1-100) 

(Ref CMM 32-31-08 ASSEMBLY). 

(3) Reassemble actuator (Ref CMM 32-31-08 ASSEMBLY). 

(4) Test actuator (Ref CMM 32-31-08 TESTING AND FAULT ISOLATION). 

D. Re-identification

CAUTION: DO NOT LETTER STAMP NAMEPLATE ON ASSEMBLY. THIS CAN DAMAGE 

ASSEMBLY. 

(1) Vibropeen SB 32-106 and date accomplished in the MOD STATUS field of 

nameplate (1-10). 

Bombardier PDF Merged Document SB 84-32-108A_01 Oct 2012 & Goodrich VSB 46830-32-106 R1_Sep 12/12 23 of 24
46830-32-106 R1

Goodrich Landing Gear Division 

Goodrich Aerospace Canada Ltd. 

Sep 12/12 

Page 4 of 4 

Reference Goodrich CMM for proprietary information 

MLG Door Actuator – Scraper Installation Details 

Figure 1 

Bombardier PDF Merged Document SB 84-32-108A_01 Oct 2012 & Goodrich VSB 46830-32-106 R1_Sep 12/12 24 of 24
Jan 2009

SERVICE BULLETIN (SB) --- RECORD OF INCORPORATION

--- Q SERIES DASH 8 AIRCRAFT

To: CMDB Focal

Facsimile: (1) 416 375 4538

E --mail: cmdb.requests@aero.bombardier.com

From:

Company:

Phone: Extn:

Facsimile: Date:

E --mail:

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
Feb 2009

SERVICE BULLETIN (SB) --- COMMENT SHEET --- Q SERIES DASH 8 AIRCRAFT

To: SB Focal (Toronto), Bombardier Aerospace Commercial Aircraft

Phone: (1) 416 375 4078 Facsimile: (1) 416 375 4538

E --mail: syed.rizvi@aero.bombardier.com

From:

Company:

Phone: Extn:

Facsimile: Date:

E --mail:

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 Tooling V References V Publications Affected

2. MATERIAL INFORMATION

V Kit Content V Special Tools/Equipment V Parts to Modify Spares

V Consumables V Disposition of Existing Parts V Other

3. ACCOMPLISHMENT INSTRUCTIONS

V Job Set ---Up V Procedure V Close---Out V Test

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