Revision ‘B’ 17 Jun 2013

DHC-8 (DASH 8)

SERVICE BULLETIN 84-28-16

Fuel System - Center Wing - Engine Fuel Feed Installation - Introduction

of Restrictor - ModSum 4-113736

This page transmits Revision ‘B’ of Service Bulletin 84-28-16, pages 1 thru

16 dated 17 Jun 2013.

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

-- the In-Service part of the Effectivity section is revised to add the text “with

installed engine fuel feed ejector pump P/N 2960008-102”

-- the Cause part of the Reason section is revised to add the P/N of engine fuel

feed ejector pump (P/N 2960008-102)

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

bulletin

-- the Procedures section is revised to add the P/N of the ejector fuel pump

(2960008-102) in Figure 1 Sheets 1 and 2.

The Compliance recommendation 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 the previous issue of this Service Bulletin and replace with

attached.

Previous issue of Service Bulletin 84-28-16:

Initial issue - Pages 1 thru 16 dated 16 Jul 2012

Revision ‘A’ - Pages 1 thru 16 dated 23 May 2013

D

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SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 2800 NUMBER: 84-28-16

BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS

SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND

URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Fuel System - Center Wing - Engine Fuel Feed Installation -

Introduction of Restrictor - ModSum 4-113736

1. PLANNING INFORMATION

A. Effectivity

Aircraft Affected:

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

4003 thru 4417 with installed engine fuel feed ejector pump

P/N 2960008-102.

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:

None

B. Reason

Problem: Several operators of a Q400 aircraft have advised BA of the low fuel

pressure caution light indication in flight regarding power lever position.

The caution light was extinguished after the AUX fuel pump was selected

to ON.

Cause: Investigation has determined that the low fuel pressure caution light was

caused by a partially blocked fuel feed line. The ejector swing arm (flapper

valve) part of the engine fuel feed ejector pump P/N 2960008-102 became

detached and partially blocked engine fuel feed flow.

Solution: This Service Bulletin introduces ModSum 4-113736. The ModSum installs

a containment device (restrictor) into the fuel feed line that is designed to

catch a detached ejector swing arm assembly (flapper valve) preventing

it from traveling downstream and blocking AUX fuel pump flow to the

engine.

C. Description

The procedures in this service bulletin give the instructions to do the tasks that

follow:

- No. 1 and No. 2 fuel tanks are defueled

- main landing gear lock pins are installed thru each main gear and main gear door

mechanism

- nose landing gear lock is engaged

- aircraft electrical power is de-energized

- electrically grounded work stands are set in position around and/or under the left

and right wing

- wet bay fuel access panels are removed

- fuel tube assemblies inside the No. 1 and No. 2 fuel tanks are disconnected

- sealants are applied to the inside surface of the fuel tube assemblies

- restrictors are inserted into fuel tube assemblies and fuel tube assemblies are

re-identified
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- electrical bonding check between the front face of the restrictor and outer

surface of the ferrule is done

- fuel tube assemblies inside the No. 1 and No. 2 fuel tanks are connected

- an operational check of the engine fuel feed pressure is done

- wet bay fuel access panels are installed

- close out.

D. Compliance

Bombardier Inc. highly recommend that ModSum 4-113736 be incorporated at the

earliest opportunity unless otherwise directed by the operator’s airworthiness

authority.

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 affects Airworthiness Limitations (AWLs) and/or Damage

Tolerance Inspections (DTIs). Reference applicable Post/Pre ModSum 4-113736

and Service Bulletin 84-28-16 in the Maintenance Requirements Manual.

F. Manpower

It will take an estimated 12 man-hours to complete both PART A and PART B of this

service bulletin. The breakdown of the man-hours is shown in the table that follows:

TASK MAN-HOURS

Job Set-Up 3.0*

Procedure 2.00**

Test / RTS 4.00

Close-Out 3.0
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*Does not include time to drain the fuel tanks.

**Does not include curing time of sealants.

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 Modkit listed below is available through the Customer Accounts Service Team

at Bombardier Aerospace Regional Aircraft division. Operators should submit a

purchase order specifying aircraft serial number(s) to:

Bombardier Aerospace

Customer Accounts Services Team (Mail Stop N11-32)

123 Garratt Blvd.

Toronto

Ontario

Canada M3K-1Y5

Facsimile: (416) 375-3060

Telephone: (416) 375-3920

Kit Number Description Price (US$) Delivery

8MK4487-001 Retrofit Kit - Engine Fuel

Feed Line

Quoted at

time of order

Will be given

at time of

order

H. Tooling - Price and Availability

None
SERVICE BULLETIN 84-28-16

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I. Weight and Balance

None

J. Electrical Load Data

Not affected

K. Publications Affected

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

Dash 8 Illustrated Parts Catalogue PSM 1-84-4 ....................

ModSums Manual PSM 1-84-12 ..................................

L. References

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

related data that follows:

DRAWING SHEET REV

8MK4487 1 -

8Z9462 1 A

ModSum 4Q113736 Rev. ‘D’

ModSum 4-113736 Rev. ‘D’

PCA 43732 Revision 1 (for internal reference only)

Transport Canada Airworthiness Directive Pending.

2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

(1) Modification Kit 8MK4487-001
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(2) Detailed Kit Content:

Quantity Per Kit

-001

Part Number Description Remarks

8 MS29513-214 Packing, O-ring

2 82820159-101 Restrictor

1 8Z9462 Retrofit - Dwg Drawing only

1 8MK4487 Retrofit - Kit Drawing only

(3) In addition to the above parts, 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.

Part Number Qty. Per Aircraft Description Remarks

DHMS S3.01 A/R Type II Class B

Sealant

PR 1776 B2 or

Equivalent

B. Parts Required to Modify Spares

None

C. Special Tools and Equipment Required

None
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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

per next higher assembly for indented parts.

Existing

Part Number Description Qty. IC DC

New Part

Number PNC

82822018-003 Tube Assembly 1 A RWK 8Z9462-001 R

82822145-001 Tube Assembly 1 A RWK 8Z9462-003 R

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.

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.
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3. ACCOMPLISHMENT INSTRUCTIONS

A. Job Set-Up

WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK

ON THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF

YOU DO NOT YOU CAN CAUSE INJURIES TO PERSONS AND/OR

DAMAGE TO EQUIPMENT.

(1) Pressure defuel the No. 1 and No. 2 fuel tanks (refer to applicable instructions in

AMM TASK 12-10-28-650-802).

(2) Make sure that lock pins are installed thru each main gear and main gear door

mechanism.

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

(4) Make sure to de-energize the aircraft electrical system (refer to AMM TASK

24-00-00-861-802).

(5) Set up the work platforms or ladders as required to gain access to wing access

panels 522AT and 622AT (refer to AMM PSM 1-84-2, TASKs 06-41-00-992-808

and 06-41-00-992-809 for location). Make sure the work platforms or ladders are

electrically grounded.

(6) Make sure to obey the fuel system safety precautions (refer to AMM TASK

28-00-00-910-801).

(7) Make sure to obey the electrical/electronic safety precautions (refer to AMM

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

(8) Obey the electrostatic discharge safety precautions (refer to AMM TASK

24-00-00-910-802).

CAUTION: MAKE SURE THAT THE FUEL TANKS ARE DRAINED BEFORE YOU

REMOVE THE ACCESS PANELS. IF YOU DO NOT DO THIS, YOU CAN

CAUSE DAMAGE TO THE WING STRUCTURE.

(9) Remove and retain the wet bay fuel access panels 522AT and 622AT (refer to

applicable instructions in AMM TASK 57-11-01-000-801).
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(10) Make sure no fuel or fuel vapors are present before working on aircraft or in the

fuel tanks (refer to applicable instructions in AMM TASK 28-10-00-840-801).

B. Procedure

PART A - Left Wing Fuel Tank Engine Fuel Feed Line Restrictor

82820159-101 - Installation

(1) Remove and retain the screws NAS1801-3-8, washers NAS1149F0332P and

clamps MS21919WDF16 from the left wing fuel feed line tubes located at

Y=-60.900 (refer to Figure 1 Sheet 1).

(2) Disconnect left wing fuel tube assembly 82822019-001 from tee assembly

located at Y=-70.285 (refer to Figure 1 Sheet 1 and applicable instructions in

AMM TASK 28-21-06-000-801). Keep coupling B0305080A16 for re-installation

and discard O-ring.

(3) Disconnect left wing fuel tube assembly 82822018-003 from ejector fuel pump

located at Y=-48.000 (refer to Figure 1 Sheet 1 and applicable instructions in

AMM TASK 28-21-06-000-801). Keep coupling B0305080A16 for re-installation

and discard O-ring.

NOTE: Do not remove swaged union connecting left wing fuel tube assembly

82822018-003 with tube assembly 82822019-001.

(4) Apply sealant DHMS S3.01 to the inside surface of the left wing fuel tube

assembly P/N 82822018-003, approximately 1.00 inch (2.54 cm) from the end of

the tube (refer to Figure 1 Sheet 3 SECTION C-C and flagnote 1 ).

(5) Insert the restrictor 82820159-101 into the left wing fuel tube assembly

82822018-003 (refer to Figure 1 Sheet 3 DETAIL A and SECTION C-C).

Re-identify tube assembly as 8Z9462-001 (refer to applicable instructions in

AMM TASK 20-00-01-910-801).
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(6) Make sure no sealant is applied in the interface between the tube assembly

ferrule and restrictor 82820159-101 and there is no sealant visible in the

restrictor opening (refer to Figure 1 Sheet 3 SECTION C-C flagnote 2 ).

(7) Secure the restrictor 82820159-101 to the tube with tape to provide direct

contact between the restrictor and front of ferrule until sealant is cured.

(8) Do an electrical bonding check between the front face of the restrictor

82820159-101 and the outer surface of the ferrule (refer to Figure 1 Sheet 3

SECTION C-C and applicable instructions in AMM TASK 51-80-00-760-801).

Make sure the measured bonding resistance is 750 milliohms or less.

(9) Connect left wing fuel tube assembly 8Z9462-001 using coupling B0305080A16

and new O-ring MS29513-214 to the left fuel tank ejector fuel pump located at

Y=-48.000.

(10) Connect left wing fuel tube assembly 82822019-001 using coupling

B0305080A16 and new O-ring MS29513-214 to the left fuel tank tee assembly

located at Y=-70.285 (refer to Figure 1 Sheet 1 and applicable instructions in

AMM TASK 28-21-06-400-801).

(11) Secure the left wing fuel feed line tube assemblies with clamps

MS21919WDF16, screws NAS1801-3-8 and washers NAS1149F0332P at

location Y=-60.900 (refer to Figure 1 Sheet 1). Tighten clamp fastener (refer to

applicable instructions in AMM TASK 20-10-01-430-801).

PART B - Right Wing Fuel Tank Engine Fuel Feed Line Restrictor

82820159-101 - Installation

(1) Remove and retain the screws NAS1801-3-8, washers NAS1149F0332P and

clamps MS21919WDF16 from the right wing fuel feed line tubes located

Y=60.900 (refer to Figure 1 Sheet 2).

(2) Disconnect right wing fuel tube assembly 82822019-001 from tee assembly

located at Y=70.285 (refer to Figure 1 Sheet 2 and applicable instructions in

AMM TASK 28-21-06-000-801). Keep coupling B0305080A16 for re-installation

and discard O-ring.
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(3) Disconnect right wing fuel tube assembly 82822145-001 from ejector fuel pump

located at Y=48.000 (refer to Figure 1 Sheet 2 and applicable instructions in

AMM TASK 28-21-06-000-801). Keep coupling B0305080A16 for re-installation

and discard O-ring.

NOTE: Do not remove swaged union connecting right wing fuel tube assembly

82822145-001 with tube assembly 82822019-001.

(4) Apply sealant DHMS S3.01 to the inside surface of the right wing fuel tube

assembly 82822145-001, approximately 1.00 inch (2.54 cm) from the end of the

tube (refer to Figure 1 Sheet 3 SECTION C-C and flagnote 1 ).

(5) Insert the restrictor 82820159-101 into right wing fuel tube assembly

82822145-001 (refer to Figure 1 Sheet 3 DETAIL B and SECTION C-C).

Re-identify tube assembly as 8Z9462-003 (refer to applicable instructions in

AMM TASK 20-00-01-910-801).

(6) Make sure no sealant is applied in the interface between the tube assembly

ferrule and restrictor 82820159-101 and there is no sealant visible in the

restrictor opening (refer to Figure 1 Sheet 3 SECTION C-C flagnote 2 ).

(7) Secure the restrictor 82820159-101 to the tube with tape to provide direct

contact between the restrictor and front of ferrule until sealant is cured.

(8) Do an electrical bonding check between the front face of the restrictor

82820159-101 and the outer surface of the ferrule (refer to Figure 1 Sheet 3

SECTION C-C and applicable instructions in AMM TASK 51-80-00-760-801).

Make sure the measured bonding resistance is 750 milliohms or less.

(9) Connect right wing fuel tube assembly 8Z9462-003 using couplings

B0305080A16 and new O-rings MS29513-214 to the right fuel tank ejector fuel

pump located at Y=48.000.

(10) Connect right wing fuel tube assembly 82822019-001 using coupling

B0305080A16 and new O-ring MS29513-214 to the right fuel tank tee assembly

located at Y=70.285 (refer to Figure 1 Sheet 2 and applicable instructions in

AMM TASK 28-21-06-400-801).
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(11) Secure the right wing fuel feed line tube assemblies with clamps

MS21919WDF16, screws NAS1801-3-8 and washers NAS1149F0332P at

location Y=60.900 (refer to Figure 1 Sheet 2). Tighten clamp fastener (refer to

applicable instructions in AMM TASK 20-10-01-430-801).

C. Close Out

(1) Do the Engine Fuel Feed Line Pressure Test (refer to applicable instructions in

AMM TASK 28-21-00-780-801).

(2) Install the wet bay fuel access panels 522AT and 622AT (refer to applicable

instructions in AMM TASK 57-11-01-400-801).

(3) Remove all tools, equipment and unwanted materials from the work area.
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TUBE ASSEMBLY

82822019--001

TUBE ASSEMBLY

82822018--003

WASHER NAS1149F0332P

SCREW NAS1801--3--8

CLAMP MS21919WDF16

TEE ASSEMBLY

VIEW LOOKING DOWN ON LEFT WING REAR SPAR

AIRCRAFT

ENGINE FUEL FEED LINE RESTRICTOR - INSTALLATION

Figure 1 (Sheet 1)

X 102D

374.405

F/SPAR

Y 102D

--60.900

Y 102D

--42.000

Y 102D

0.000

Y 102D

--79.700

EJECTOR TEE ASSEMBLY FUEL PUMP

COUPLING B0305080A16

O--RING MS29513--214

C/L

8Z9462-001 (p/n after rework)

2960008--102
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VIEW LOOKING DOWN ON RIGHT WING REAR SPAR

TEE ASSEMBLY

WASHER NAS1149F0332P

SCREW NAS1801--3--8

CLAMP MS21919WDF16

EJECTOR

TUBE ASSEMBLY

82822145--001

TUBE ASSEMBLY

82822019--001

TEE ASSEMBLY

X 102D

374.405

F/SPAR

AIRCRAFT

Y 102D

60.900

Y 102D

42.000

Y 102D

0.000

Y 102D

79.700

ENGINE FUEL FEED LINE RESTRICTOR - INSTALLATION

Figure 1 (Sheet 2)

FUEL PUMP

C/L

8Z9462--003

(p/n after rework)

COUPLING B0305080A16

O--RING MS29513--214

2960008--102
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RESTRICTOR

TUBE ASSEMBLY

ENGINE FUEL FEED LINE RESTRICTOR - INSTALLATION

Figure 1 (Sheet 3)

0.50 INCH (1.27 CM)

1.00 INCH (2.54 CM)

FERRULE 1

2

1

2

82820159-101

82822018-003 (LEFT SIDE)

82822145-001 (RIGHT SIDE)

(COUPLING AND O-RING

REMOVED FOR CLARITY)

(LEFT SIDE)

(RIGHT SIDE) - APPLY SEALANT DHMS S3.01 TO

INSIDE SURFACE OF TUBE,

APPROXIMATELY 1.00 IN. (2.54 CM)

FROM END OF TUBE, OVER THE

DISTANCE SHOWN IN SECTION C-C.

- MAKE SURE NO SEALANT IS

APPLIED IN THE INTERFACE BETWEEN FERRULE AND RESTRICTOR

AND THERE IS NO SEALANT VISIBLE

IN THE RESTRICTOR OPENING.

RESTRICTOR

82820159-101

NOTES:
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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