Revision ‘A’ 11 Jul 2013

DHC-8 (DASH 8)

SERVICE BULLETIN 84-52-75

Doors - Aft Entry and Aft Service Doors - Translating Door Bolts not

Properly Installed - Inspection and Rectification

This page transmits Revision ‘A’ of Service Bulletin 84-52-75, pages 1 thru

12, dated: 11 Jul 2013.

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

- the Description section is revised to include additional information

regarding the inspection procedure

- the Manpower section is revised to include an additional table for the

inspection procedure

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

bulletin and engineering documentation

- the Parts Required Per Aircraft section is revised to add an equivalent

marker

- the ACCOMPLISHMENT INSTRUCTIONS section is revised to add an

inspection Part A, a rectification Part B, a reference to four washers and

add a CAUTION note

- Figures 1 & 2 are revised to add four washers

- Figure 3 is added

The Compliance in the previous issue of this service bulletin is not affected

by this revision. Additional work to the aircraft is introduced by this revision.

Remove the initial issue of Service Bulletin 84-52-75 and replace with

attached.

Previous issues of Service Bulletin 84-52-75:

Initial issue - Pages 1 thru 10 dated 27 Jul 2012

D

S.B. 84-52-75

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SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 5200 NUMBER: 84-52-75

BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS

SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND

URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Doors - Aft Entry and Aft Service Doors - Translating Door Bolts not

Properly Installed - Inspection and Rectification

1. PLANNING INFORMATION

A. Effectivity

Aircraft Affected:

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

4002 thru 4411.

Production: The intent of this service bulletin will be done before delivery

on applicable DHC-8 Aircraft at Serial Number 4412 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:

None
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B. Reason

Problem: There have been reports of loose or missing bolts on the door handle close

mechanism crank assembly on some translating doors.

Solution: This service bulletin gives instructions to inspect the secure state of the

bolts attaching the crank assembly to the outside handle shaft and, if

necessary, remove the two bolts on the crank assembly and re-install them

using Loctite.

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 latch caps from the aft entry and aft service doors are removed

- two bolts securing the door close mechanism crank assembly are visually and

feel inspected for improper installation (Eg. bolt head not sitting properly, or

loose)

- If bolts are not installed properly, they are rectified immediately as follows:

- the liner from the aft entry and aft service doors is removed

- two bolts securing the door close mechanism crank assembly are removed

- bolts are cleaned to remove any existing loctite

- bolts are re-installed using loctite

- if bolts have been installed properly the rectification is done at a later time

- an operational test of the door is done

- 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 1.00 man-hour per door to complete the inspection. The

breakdown of the man-hours is shown in the table that follows:

TASK MAN-HOURS

Job Set-Up 0.25

Procedure 0.50

Test / RTS 0.00

Close-Out 0.25

Part B - Rectification

It will take an estimated 6.75 man-hours per door to complete the rectification. The

breakdown of the man-hours is shown in the table that follows:

TASK MAN-HOURS

Job Set-Up 0.25

Procedure 6.00

Test / RTS 0.25

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 Technical

Help Desk by telephone at 416-375-4000 or email at:

thd.qseries@aero.bombardier.com
SERVICE BULLETIN 84-52-75

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G. Material - Price and Availability

None

H. Tooling - Price and Availability

None

I. Weight and Balance

None

J. Electrical Load Data

Not affected

K. Publications Affected

Maintenance Manual PSM 1-84-2 ................................

L. References

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

related data that follows:

Drawings 85217901

PCA 44073 Revision 0 (for internal reference only)

Transport Canada Airworthiness Directive Pending.

2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

(1) The following material is required for the completion of this service bulletin

and may be procured as single items from Bombardier Aerospace Regional

Aircraft or purchased directly from industry sources.

Addresses of manufacturers and suppliers not shown below are listed in

either Maintenance Manual Chapter 20 or in Structural Repair Manual Chapter

51 or, for 400 Series Aircraft, in Consumable Products Manual PSM 1-84-18.
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Part Number Qty. Per Aircraft Description Remarks

Loctite 222MS

Grade M

as required Sealant MIL-S-46163

MK-Dalo-B3

(13-06)

1 Dalo Marker or

equivalent

B. Parts Required to Modify Spares

None

C. Special Tools and Equipment Required

None

D. Existing Parts Accountability

None

3. ACCOMPLISHMENT INSTRUCTIONS

Part A - INSPECTION

A. Job Set-Up

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.

(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 that lock pins are installed through each main gear and main gear

door mechanism.
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(3) Make sure the nose gear ground lock is engaged.

(4) Set up work platforms or ladders as required to gain access to the aft entry and

aft service doors. Make sure the work platforms or ladders are electrically

grounded.

B. Procedure

(1) On the aft entry door and aft service door, remove the outer latch cap and the

inner main latch cap as follows: Refer to Figure 3

(a) Remove and keep pan head screw NAS603-8 & washer NAS1149D0332H.

(b) Remove and keep outer latch cap 9505179, spacer NAS43DD3-8 and

nylon washer 5610-609-31.

(c) Remove and keep four screws MS24693S51, washers NAS1169C8L and

inner main latch cap 9505179.

(d) Do a detailed visual inspection of the two bolts NAS6204-3 (eg. bolt head

not sitting properly, or loose) securing the crank assembly 85217919 to the

housing to see if they are improperly installed. Open and close the door

while visually inspecting both bolts for secure fit. Refer to Figure 1 & 2.

(e) At the end of the close and open cycle, (once the crank assembly has

stopped rotating) continue to hold the handle and feel the bolt heads for

looseness while applying a slight load to the handle.

(f) If there is any visual indication or feeling of the bolts being improperly

installed, go to Part B RECTIFICATION of this service bulletin.

(g) If there is no visual indication or feeling of the bolts being improperly

installed, go to Close Out section of this Part A.

C. Close Out

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

(2) Install the outer latch cap and the inner main latch cap using kept hardware.

Refer to Figure 3.
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(3) On completion of this service bulletin, make the following entry in the

appropriate logbook(s): “Service Bulletin 84-52-75 - Doors - Aft Entry and Aft

Service Doors - Translating Door Bolts not Properly Installed - Inspection and

Rectification - Part A INSPECTION incorporated’’.

Part B - RECTIFICATION

A. Job Set-Up

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.

(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 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 work platforms or ladders as required to gain access to the aft entry and

aft service doors. Make sure the work platforms or ladders are electrically

grounded.

B. Procedure

(1) Remove aft entry door liner. Refer to Maintenance Manual Task

25-26-21-000-801.

(2) Remove aft service door liner. Refer to Maintenance Manual Task

25-26-26-000-801.

(3) On the aft entry door and aft service door, remove two bolts NAS6204-3 and four

washers NAS1149C0432R from crank assembly 85217919. Refer to Figures 1 &

2.
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CAUTION: IN ORDER TO REMOVE ONE OR BOTH OF THE BOLTS, THE HANDLE

MAY HAVE TO BE ROTATED TO GET ACCESS TO THE BOLTS, IN

SUCH CASE BE CAREFUL THAT THE HANDLE DOES NOT SNAP

BACK WHILE REMOVING THE BOLTS.

(4) Clean bolts to remove any existing Loctite.

(5) Apply Loctite 222 Grade M to the thread areas of the bolts and thread holes of

the outside handle shaft. Refer to Maintenance Manual Task 51-23-11-390-801.

(6) Re-install bolts and washers and torque to the required specifications. Refer to

Maintenance Manual Task 20-10-01-430-801.

(7) Recheck bolts per instructions in Part A, B. (1) (d) (e).

(8) Identify part by applying a small red dot, adjacent to the sealed part using a

Dalo marker or equivalent.

C. Close Out

(1) Install aft entry door liner. Refer to Maintenance Manual Task 25-26-21-400-801.

(2) Install aft service door liner. Refer to Maintenance Manual Task

25-26-26-400-801.

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

(4) Do an operational test of the aft entry (passenger) door. Refer to Maintenance

Manual Task 52-12-00-710-802, section 3.B. is not necessary.

(5) Do an operational test of the aft service door. Refer to Maintenance Manual Task

52-41-00-710-801, section 3.B. is not necessary.

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

appropriate logbook(s): “Service Bulletin 84-52-75 - Doors - Aft Entry and Aft

Service Doors - Translating Door Bolts not Properly Installed - Inspection and

Rectification - Part B RECTIFICATION incorporated.”
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Aft Entry Door Close Mechanism

Figure 1

BOLT

NAS6204-3

BOLT

NAS6204-3

CRANK ASSEMBLY

85217919

OUTSIDE HANDLE

SHAFT

Mechanism shown in the closed position

WASHER

NAS1149C0432R

2 REQUIRED

WASHER

NAS1149C0432R

2 REQUIRED
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Aft Service Door Close Mechanism

Figure 2

BOLT

NAS6204-3

BOLT

NAS6204-3

CRANK ASSEMBLY

85217919

OUTSIDE HANDLE

SHAFT

Mechanism shown in the closed position

1

WASHER

NAS1149C0432R

2 REQUIRED

WASHER

NAS1149C0432R

2 REQUIRED
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Outer and Inner Latch Cap

Figure 3

SCREW

PAN HEAD

NAS603-8

WASHER

NAS1149D0332H

SPACER

NAS43DD3-8

NYLON WASHER

5610-609-31

INNER MAIN LATCH

CAP

9505179

WASHER

DIMPLED

NAS1169C8L

SCREW COUNTERSUNK

MS24693S51

OUTER LATCH

CAP

9505179

1
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This Page Intentionally Blank

1
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