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

bulletin

- the Parts Required Per Aircraft section is revised to add a NOTE in step (2)

that indicates acceptable alternatives for the consumable materials

- step 3.B.(6) in the Accomplishment Instructions section 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

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NB

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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
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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
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- 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
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* 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 ..................................
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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. MATERIAL INFORMATION

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.
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(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
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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

------- 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.
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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

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(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).
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(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.
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(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.
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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.
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Locator View

Figure 1 Sheet 1
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Locator View

Figure 1 Sheet 2
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Locator View

Figure 1 Sheet 3

VIEW LOOKING FWDON REAR SPAR

FUEL TANK ACCESSPANEL 522AT (622AT)
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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
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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
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Figure 4

Rework Location - VIEW D-D

NOTES:

FITTING ASSEMBLY

82822074-009

LOCK WIRE

MS20995C32
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Figure 5

VIEW E-E

Rework Location - VIEW E-E
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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