Revision ‘A’ 20 Jun 2013 DHC-8 (DASH 8) SERVICE BULLETIN 84-28-12

Fuel - Fuel Tank System Design Left and Right Side (SFAR 88) - Replacement of Fitting p/n 82822074-951 - ModSum 4-126537 This page transmits Revision ‘A’ of Service Bulletin 84-28-12, pages 1 thru 20, dated 20 Jun 2013. This service bulletin is re-issued in its entirety for the reasons that follow:

- the Referencessection is revised to convey the latest revision of the service bulletin

- the Parts Required Per Aircraftsection is revised to add a NOTE in step (2) that indicates acceptable alternatives for the consumable materials

- step 3.B.(6) in theAccomplishment Instructionssection is revised to change “view A-A” to “view C-C” and to delete the text “51-80-00-760-801” at the end of the step. 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 84-28-12 and replace with attached. Previous issue(s) of Service Bulletin 84-28-12: Initial issue - Pages 1 thru 20 dated 23 Jul 2012

# D

S.B. 84-28-12

Page 1 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 

# SERVICE BULLETIN Customer Support
ATA SYSTEM: 2810 NUMBER: 84-28-12 

### BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Fuel - Fuel Tank System Design Left and Right Side (SFAR 88) - Replacement of Fitting p/n 82822074-951 - ModSum 4-126537

1. PLANNING INFORMATION A. Effectivity Aircraft Affected: In-Service: DHC-8 Aircraft Models 401 and 402 Serial Numbers 4063 thru 4118. 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 84-28-12

S.B. 84-28-12 Page 2 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 B. Reason This service bulletin is issued as a result of FAA certification requirement Special Federal Aviation Regulation 88 (SFAR 88) to enhance fuel tank system safety. Problem: An operator of a DHC 8 Q400 aircraft has reported finding a fitting p/n 82822074-951 installed through the rear spar (left and right side at station X-76.829) instead of fitting 82822074-007 or 82822074-005. The issue was discovered during incorporation of SB 84-57-09 (ModSum 4-126330). Fitting p/n 82822074-951 (installed by ModSum 4Y121542 and 82822074NIEO273101) does not comply with FAA certification requirements given in the SFAR 88 regulations. Solution: This service bulletin introduces ModSum 4-126537. The ModSum replaces existing fittings p/n 82822074-951 with new fittings p/n 82822074-009. The new fittings are designed to enhance fuel tank system safety and comply with SFAR 88 requirements. C. Description The procedures in this service bulletin give the instructions to do the tasks that follow: - lock pins are installed thru each main gear and main gear door mechanism - the nose gear ground lock is engaged - affected left and/or right side fuel tank is defueled as required - all aircraft electrical power is selected to the OFF position - electrically grounded work platforms or ladders are set-up around and/or under the left (and/or right) wing rear spar at approx. stn Y102D X-76.829 - left and/or right side fuel tank access panels are removed for access - on the rear spar (left and right hand side) the refuel control solenoid valve is located and removed from fitting p/n 82822074-951 - existing fitting(s) p/n 82822074-951 and related shroud, gasket and o-rings are removed. The shroud is kept and remaining items are discarded

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 3 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 - protective finish is removed from certain areas of the rear spar. The reworked areas are treated with Alodine 1132 - new fittings p/n 82822074-009, o-rings and kept shrouds are installed - an electrical bonding test from fitting 82822074-009 to adjacent aircraft structure is done - the fitting assembly 82822074-009 is sealed using DHMS S3.01 sealant to the rear spar - an operational test of the level control shutoff valve is done - Close-Out D. Compliance Bombardier Inc. recommends that ModSum 4-126537 be incorporated at the earliest opportunity unless otherwise directed by the operator’s airworthiness authority. An Airworthiness Directive from Transport Canada 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 8.50 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 *2.00 Procedure *4.00 Test / RTS 0.50 Close-Out 2.00

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 4 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 

### * Time to defuel aircraft and cure times of sealant not included.

NOTE: Many MAN-HOURS would be saved if this SB is accomplished concurrently with SB 84-57-09. 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. may be obtained from any Bombardier Aerospace Regional Aircraft authorized parts source. The price and availability will be quoted at the time of order. 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

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

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

..................................

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 5 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 L. References Revision ‘A’ of this service bulletin was prepared to the engineering drawings and related data that follows: DRAWING SHEET REV 8MK4626 1
-

8Z9626 1
- ModSum 4Q126537 Rev. ‘B’ ModSum 4-126537 Rev. ‘B’ ModSum 4-126330 Rev. ‘E’ (SB 84-57-09) PCA 40933 issue 3 (for internal reference only) Transport Canada Airworthiness Directive Pending
2. MATERIALINFORMATION A. Parts Required Per Aircraft (1) Detailed Parts List for 8MK4626-001:
Quantity Per Aircraft Part Number Description Remarks

4 MS29513-020 O-Ring 2 MS29513-014 O-Ring 2 MS29513-013 O-Ring 2 MS29512-08 O-Ring 2 82822032-101 Gasket 2 82822074-009 Fitting Assembly
NOTE: This service bulletin is self-contained (illustrated). No drawings will be supplied.

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 6 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 (2) In addition to the above part(s), the following material(s) are required for 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 07-29A 1 Tube Alodine 1132 Touch-N Prep Pen (592939) 06-01A 2 Cartridges Sealant Class B Type II (DHMS S3.01) Temperature-Resistant Integral FuelTanks

04-14 AR Petroleum Jelly 3⁄4 Petrolatum B0816019-003. 2 Tiedown strap MS20995C32 A/R Lock Wire
NOTE: Refer to CPM PSM 1-84-18 for the list of approved consumable products under each Product ID No., any of which can be used unless a note states otherwise.
B. Parts Required to Modify Spares
None C. Special Tools and Equipment Required
None

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 7 of 20 23 Jul 2012 NB Rev. ‘A’ 20 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

------- O-Ring 4 D DIS MS29513-020 S

------- O-Ring 2 D DIS MS29513-014 S

------- O-Ring 2 D DIS MS29513-013 S O-Ring 2 D DIS MS29512-08 S

------- Gasket 2 D DIS 82822032-101 S 82822074-951 Fitting Assembly 2 C DIS 82822074-009 X 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. D Existing p/n number and new p/n are the same 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.

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 8 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 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 Existing p/n number and new p/n are the same X The old part and the new part are similar in appearance but only the new part is SFAR 88 compliant. 3. ACCOMPLISHMENT INSTRUCTIONS A. Job Set-Up The procedure that follows gives the instructions to replace existing fitting 82822074-951. The existing fitting is part of the refuel control solenoid valve assembly and is installed through the left & right side rear spar at approx. stn Y102D X-76.829. The instructions to replace an existing fitting 82822074-951 in the left side rear spar are given. The instructions to replace an existing fitting in the right side rear spar are the same. 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) Make sure that lock pins are installed thru each main gear and main gear door mechanism. (2) Make sure the nose gear ground lock is engaged. (3) Connect ground hydraulic power to the number 1 system (refer to AMM TASK 12-00-16-490-801). Set the pressure to 3000 psi (20684 kPa) and a flow rate of 2.5 gal/min. (9.5 L/min.).
WARNING: MAKE SURE THAT THERE ARE NO PERSONS OR EQUIPMENT ON OR NEAR THE FLAPS OR ANY OTHER FLIGHT CONTROL. ACCIDENTAL MOVEMENT OF THE FLIGHT CONTROLS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT.

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 9 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 (4) Make sure the area around each flap is clear then lower flaps to the 35 ̊ position. (5) Remove the ground hydraulic power (refer to AMM TASK 12-00-16-090-801). (6) Pressure defuel the aircraft (refer to AMM TASK 12-10-28-650-802). (7) Make sure to de-energize the aircraft electrical system (refer to AMM TASK 24-00-00-861-802). (8) Set up work platforms or ladders around and/or under the left (and/or right) wing to permit access to the refuel control solenoid valve on rear spar (at approx. stn Y102D X-76.829) and wing fuel access panel 522AT (622AT right side) (refer to TASK 06-41-00-992-808 for access panel location). Make sure that the work platforms or ladders are electrically grounded (refer to Figure 1). (9) Make sure to obey the fuel system safety precautions (refer to AMM TASK 28-00-00-910-801). (10) Obey the electrical/electronic safety precautions (refer to AMM TASK 24-00-00-910-801). (11) Obey the electrostatic discharge safety precautions (refer to AMM TASK 24-00-00-910-802). CAUTION: MAKE SURE ALL FUEL IS DRAINED FROM THE FUEL TANK BEFORE YOU REMOVE FUEL TANK ACCESS PANELS. IF YOU DO NOT DO THIS, YOU CAN CAUSE DAMAGE TO THE WING STRUCTURE. (12) Drain remaining fuel from the applicable fuel tank using the water drains (refer to AMM TASK 28-11-00-680-801). (13) Remove the left (and/or right side) wing fuel access panel that follow using applicable instructions in AMM TASK 57-11-01-000-801. ACCESS DESIGNATION 522AT (and/or 622AT right wing) Wet Bay Fuel Access Panels (14) Remove the fuel fumes from the fuel tank (refer to AMM TASK 28-10-00-840-802).

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 10 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 (15) Remove the inboard flap closure panel that follows (refer to applicable instructions in AMM TASK 57-51-01-000-801). ACCESS DESIGNATION

531AB Flap Closure Panel (left side) 631AB Flap Closure Panel (right side)
B. Procedure (1) Gain access to the refuel control solenoid valve located on the aft side of the rear spar at approx. stn Y102D X-76.829 (refer to Figure 1 Sheets 1, 2 & 3). (2) Remove and retain the refuel control solenoid valve from existing fitting using applicable instructions in AMM TASK 28-23-11-000-801. Make sure to discard the existing o-rings. (3) Remove the parts that follow (refer to Figure 2 & 3): - shroud 82822077-005 (make sure to disconnect the drain line from the shroud prior to removal) - fitting 82822074-951 (discard) - gasket 82822032-101 (discard) - o-rings MS29512-08, MS29513-013, MS29513-014 and MS29513-020 (discard) (4) Remove protective finish from the mating surface on the aft side of the rear spar (dry side) to agree with applicable instructions given in the SRM PSM 1-84-3 51-26-10-02-01. The four rework areas are indicated with hash marks on the aft side of the rear spar shown on Figure 5 VIEW E-E. (5) Touch-up the reworked areas on the rear spar with a layer of alodine 1132 (refer to applicable instructions in SRM 51-21-10-02-02. Make sure to allow alodine to dry.

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 11 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 (6) Install the new parts that follow to agree with the detail views given on Figure 2 SECTION view C-C. Make sure to lubricate the o-rings with petrolatum before installation. - gasket 82822032-101 - fitting 82822074-009 - shroud 82822077-005 - new o-rings MS29512-08, MS29513-013, MS29513-014 and MS29513-020. (7) Re-attach the drain line to the shroud and secure with a tiedown strap p/n B0816019-003. (8) Install the refuel control solenoid valve (previously removed) to fitting 82822074-009 (refer to Figure 2 and applicable instructions in AMM TASK 28-23-11-400-801). Make sure to install lockwire from solenoid valve to one of the bolts on the fitting (refer Figure 4 and applicable instructions in AMM TASK 20-10-30-400-801). (9) Re-Identify installation as 8Z9626-001 (refer to applicable instructions in AMM TASK 20-00-01-910-801). (10) Do an electrical bonding test from fitting 82822074-009 to aircraft structure. Reading to be less than 20 milliohms (see Flagnote 2 on Figure 2 and refer to SRM TASK 51-80-00-02-01). (11) Connect the electrical connector to the refuel control solenoid valve. (12) Make sure to fillet profile seal fitting assembly 82822074-009 and aft face of rear spar at location depicted (see Flagnote 1 on Figure 2) refer to applicable instructions in SRM PSM 1-84-3 Chapter 51-23-20-02-01.

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 12 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 C. Close Out (1) Install the left (and/or right side) wing access panels that follow (refer to applicable instructions in AMM TASK 57-11-01-400-801. ACCESS DESIGNATION 522AT (and/or 622AT right wing) Wet Bay Fuel Access Panels (2) Do an operational test of the level control shutoff valve (refer to AMM TASK 28-24-00-710-802). (3) Do a visual check for any signs of leakage at the rework site. Rectify as required. (4) Install the inboard flap closure panels that follows (refer to applicable instructions in AMM TASK 57-51-01-400-801). ACCESS DESIGNATION

531AB Flap Closure Panel (left side) 631AB Flap Closure Panel (right side) (5) Remove all tools, equipment and unwanted materials from the work area. (6) On incorporation of this ModSum make an entry that conforms to local regulatory requirements in the applicable logbook(s). If only part of this ModSum is completed, use only this service bulletin number as reference and detail exact limit of work completed. Enter component serial numbers if applicable. Enter this ModSum number only after complete and functional incorporation of all work defined in this service bulletin.

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 13 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 Locator View Figure 1 Sheet 1

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 14 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 Locator View Figure 1 Sheet 2

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 15 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 Locator View Figure 1 Sheet 3VIEW LOOKING FWDON REAR SPARFUEL TANK ACCESSPANEL 522AT (622AT)

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 16 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 Figure 2 MS29512-08 O-RING O-RING MS29513-020 O-RING MS29513-014 O-RING MS29513-013

FITTING WAS 82822074-951 NOW 82822074-009

GASKET 82822032-101 SHROUD 82822077-005 REFUEL CONTROL D

D

DRAIN LINE

TIEDOWN STRAP B0816019-003

ELECTRICAL BONDING BY DIRECT CONTACT PER SRM CHAPTER 51-80-00-02-01 2 NOTES: FILLET PROFILE SEAL WITH DHMS S3.01 CLASS B TYPE II SEALANT PER SRM 51-23-20-02-01 1 2 REAR SIDE OF REAR SPAR

Fitting & Solenoid Valve - Installation FOR O-RING INSTLN DETAILS SEE FIGURE 3

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 17 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 O-Ring & Gasket - Location Figure 3 O-RING MS29513-013 O-RING MS29513-020

O-RING MS29513-014 MS29512-08 O-RING

GASKET 82822032-101

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 18 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 Figure 4 Rework Location - VIEW D-D NOTES: FITTING ASSEMBLY 82822074-009 LOCK WIRE MS20995C32

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 19 of 20 23 Jul 2012 NB Rev. ‘A’ 20 Jun 2013 Figure 5 VIEW E-E

Rework Location - VIEW E-E

### SERVICE BULLETIN 84-28-12

S.B. 84-28-12 Page 20 of 20 23 Jul 2012 NB Rev. ‘A’ 20 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 V Job 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