Revision ‘A’ 16 May 2013

DHC-8 (DASH 8)

SERVICE BULLETIN 84-24-53

This page transmits Revision ‘A’ of Service Bulletin 84-24-53, pages 1 thru 8,

dated 16 May 2013.

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

- the Description section revised to include inspection for chafing - PART B

expanded to include repairs per WDM and AMM

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

bulletin and engineering documentation

- the ACCOMPLISHMENT INSTRUCTIONS - Job Set-Up section revised to

change reference from PSM to AMM, for consistency

- the ACCOMPLISHMENT INSTRUCTIONS - Procedure section revised to

add extra steps

- content revised to change tube to line, for consistency, except for the

illustrations in order to expedite release of this Service Bulletin

- clerical error corrected

- boldfacing removed, where unecessary

The Compliance in the previous issue(s) of this service bulletin is not

affected by this revision. No additional rework to the aircraft is introduced by

this revision.

Remove the initial issue of Service Bulletin 84-24-53 and replace with

attached.

Previous issue(s) of Service Bulletin 84-24-53:

Initial issue - Pages 1 thru 8 dated 11 May 2012

D

S.B. 84-24-53

Page 1 of 8

11 May 2012

Revision ‘A’ 16 May 2013 RR

SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 2400 NUMBER: 84-24-53

BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS

SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND

URGE OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Electrical Power - Wiring Installation - Center Fuselage - Special

Inspection and Rectification to Ensure the Installation of Clamping

Hardware between AC Power Feeder Cables and Hydraulic Line

1. PLANNING INFORMATION

A. Effectivity

Aircraft Affected:

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

4347.

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
SERVICE BULLETIN 84-24-53

S.B. 84-24-53

Page 2 of 8

11 May 2012

Revision ‘A’ 16 May 2013 RR

B. Reason

Problem: A line check at the Bombardier manufacturing facility has discovered that

the AC power feeder cables and the hydraulic line (tube) of the landing

gear alternate extension installed under floor between station X321.000

and X341.000 on the LHS of the aircraft have not been secured with the

appropriate clamps.

Solution: This service bulletin gives the instructions to do a special inspection and

if necessary rectification to make sure that the clamps between AC power

feeder cables and the hydraulic line are installed to avoid possible chafing.

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 through each main gear and main

gear door mechanism

- the carpet, the passenger seats and floor path emergency lights between station

X321.000 and X341.000 (left hand side of passenger compartment) are removed

- PART A - INSPECTION - access is gained to the inspection area under the floor

between station X321.000 and X341.000 (left hand side of passenger

compartment).

- the area is inspected for missing clamping hardware and chafing between the AC

power feeder cables and the hydraulic line.

- if the clamps are installed, close out section is done

- if the clamps are not installed, PART B - RECTIFICATION is completed

- PART B - RECTIFICATION - damage to the AC power feeder cables or the hydraulic

line is repaired per Wiring Diagram Manual (WDM) or Aircraft Maintenance Manual

(AMM), respectively. Clamping hardware is installed between the AC power feeder

cables and the hydraulic line.

- the carpet, the passenger seats and floor path emergency lights are re-installed

- close out.
SERVICE BULLETIN 84-24-53

S.B. 84-24-53

Page 3 of 8

11 May 2012

Revision ‘A’ 16 May 2013 RR

D. Compliance

Bombardier Inc. recommends incorporation of Service Bulletin 84-24-53 at the

earliest opportunity unless otherwise directed by the operator’s airworthiness

authority.

NOTE: This service bulletin must be completed within 6,000 Flight Hours (FH)

from the release of this service bulletin.

A Transport Canada Airworthiness Directive is 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 #93-Q-02.

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

Tolerance Inspections (DTIs).

F. Manpower

It will take an estimated 2 man-hours to complete this service bulletin. The

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

TASK MAN-HOURS

Job Set-Up 1.00

Procedure 0.50

Close-Out 0.50

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

G. Material - Price and Availability

The part(s) detailed in Paragraph(s) 2.A. and 2.B. may be obtained from any

Bombardier Aerospace Regional Aircraft authorized parts source. The price and

availability will be quoted at the time of order.
SERVICE BULLETIN 84-24-53

S.B. 84-24-53

Page 4 of 8

11 May 2012

Revision ‘A’ 16 May 2013 RR

H. Tooling - 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 ....................

L. References

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

related data that follows:

DRAWING SHEET REV

82420102 19 D

82420102 33 A

PCA 43701 Revision 2 (for internal reference only)

Transport Canada Airworthiness Directive Pending.

2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

(1) Detailed Parts List:

Quantity

Per Aircraft

Part Number Description Remarks

1 MS21919WDG7 Clamp

1 M85052/2-6 Clamp

1 MS35207-263 Screw
SERVICE BULLETIN 84-24-53

S.B. 84-24-53

Page 5 of 8

11 May 2012

Revision ‘A’ 16 May 2013 RR

Quantity

Per Aircraft

Part Number Description Remarks

1 AN960D10L Washer

1 MS21042L3 Nut

B. Parts Required to Modify Spares

None

C. Special Tools and Equipment Required

D. Existing Parts Accountability

None

3. ACCOMPLISHMENT INSTRUCTIONS

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 24-00-00-861-802 and TASK

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) Gain access to the passenger compartment.
SERVICE BULLETIN 84-24-53

S.B. 84-24-53

Page 6 of 8

11 May 2012

Revision ‘A’ 16 May 2013 RR

(5) Remove the passenger compartment carpet, floor path emergency lights, seats,

and floor panels between X321.000 to X341.000 (refer to AMM TASK

25-25-06-000-801).

B. Procedure

PART A - INSPECTION (Configuration Check)

(1) In the underfloor (left side) area, locate frame at station X321.000 and station

X341.000 (refer to Figure 1).

(2) Do a visual inspection to confirm if the clamps between AC power feeder cables

and the hydraulic line are installed or not installed (refer to Figure 1 and Figure

2).

(3) If the clamps are installed, as shown in the Figure 2, do the Close Out section.

(4) If the clamps are not installed, do the PART B - RECTIFICATION.

PART B - RECTIFICATION (Damage Repair and Clamp Installation)

(1) Do a visual inspection of the AC power feeder cables and the hydraulic line for

damage due to chafing. Repair AC power feeder cables in accordance with

wiring standard practices (refer to WDM Chapter 20). Repair the hydraulic tube

(refer to AMM Task 20-20-00-220-801).

(2) Install the clamp MS21919WDG7 on the AC power feeder cables (refer to Figure

2).

(3) Install the clamp M85052/2-6 on the hydraulic line (emergency landing gear

down line).

(4) Attach both clamps together using screw MS35207-263, washer AN960D10L

and nut MS21042L3 (refer to Figure 2).

C. Close Out

(1) Install the passenger compartment carpet, floor path emergency lights, seats,

and floor panels between X321.000 to X341.000 (refer to AMM TASK

25-25-06-400-801).

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

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

appropriate logbooks: “Service Bulletin 84-24-53 {i.e. Electrical Power - Wiring

Installation - Center Fuselage - Special Inspection and Rectification to Ensure

the Installation of Clamping Hardware between AC Power Feeder Cables and

Hydraulic Line} accomplished.”
SERVICE BULLETIN 84-24-53

S.B. 84-24-53

Page 7 of 8

11 May 2012

Revision ‘A’ 16 May 2013 RR

Inspection Area

Figure 1

FWD

AC POWER FEEDER CABLES

INSPECT THE AREA FOR CLAMP INSTALLATION

IF FOUND MISSING, INSTALL THE CLAMPS (REFER TO FIGURE 2).

1 BETWEEN AC POWER FEEDER CABLES AND THE HYDRAULIC TUBE.

1
SERVICE BULLETIN 84-24-53

S.B. 84-24-53

Page 8 of 8

11 May 2012

Revision ‘A’ 16 May 2013 RR

Clamp Installation

Figure 2

INSTALL

MS21919WDG7

M85052/2-6

MS35207-263

CLAMP

CLAMP

SCREW

WASHER

AN960D10L

NUT

MS21042L3

AC POWER FEEDER CABLES

FWD

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