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 theReasonsection is revised to add the P/N of engine fuel feed ejector pump (P/N 2960008-102)

-- the Referencessection 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

S.B. 84-28-16

Page 1 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 

# 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.

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 2 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 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

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 3 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 - 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

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 4 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 *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

S.B. 84-28-16 Page 5 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 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. MATERIALINFORMATION A. Parts Required Per Aircraft (1) Modification Kit 8MK4487-001

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 6 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 (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

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 7 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 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.

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 8 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 3. ACCOMPLISHMENTINSTRUCTIONS 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).

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 9 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 (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).

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 10 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 (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.

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 11 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 (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).

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 12 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 (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.

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 13 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 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

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 14 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 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 ASSEMBLYX 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

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 15 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 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 ISAPPLIED IN THE INTERFACE BETWEEN FERRULE AND RESTRICTOR AND THERE IS NO SEALANT VISIBLE IN THE RESTRICTOR OPENING. RESTRICTOR 82820159-101 NOTES:

### SERVICE BULLETIN 84-28-16

S.B. 84-28-16 Page 16 of 16 16 Jul 2012 NB Revision ‘B’ 17 Jun 2013 

### This Page Intentionally Blank 1Jan 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.comFeb 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 VApproval V Manpower V Material VWeight and Balance V Electrical Load VTooling 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 VJob Set ---Up V Procedure V Close---Out VTest 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