Revision ‘A’ 29 May 2013

DHC-8 (DASH 8)

SERVICE BULLETIN 8-57-47

Wings - Special Inspection and Replacement - Wing / Fuselage Joint

Bolts

This page transmits Revision ‘A’ of Service Bulletin 8-57-47, pages 1 thru 30,

dated 29 May 2013

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

- to add a Note to the PLANNING INFORMATION and ACCOMPLISHMENT

INSTRUCTIONS section

The Compliance 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 initial issue of Service Bulletin 8-57-47 and replace with

attached.

Previous issue of Service Bulletin 8-57-47:

Initial issue - Pages 1 thru 30 dated 16 Mar 2012

D

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Revision ‘A’ 29 May 2013 JR

SERVICE BULLETIN

Customer

Support

ATA SYSTEM: 5700 NUMBER: 8-57-47

BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS

SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND

URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Wings - Special Inspection and Replacement - Wing / Fuselage Joint

Bolts

1. PLANNING INFORMATION

NOTE: Operators that have performed inspection per PSM 1-8-7TC or 1-82-7TC

or 1-83-7TC Task Card 5730/04B dated Feb 06, 2012 or later revisions,

have met the intent of this service bulletin.

A. Effectivity

Aircraft Affected:

In-Service: DHC-8 Aircraft Models 102, 103, 106, 201, 202, 301, 311, 314

and 315 Serial Numbers 003 thru 672.

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

Problem: An Operator doing an inspection discovered that the head of a

Wing/Fuselage strut attachment joint bolt was broken due to corrosion.

Further inspection showed corrosion on the remainder of bolts in the

wing/fuselage strut attachments.

Solution: This Service Bulletin provides an initial inspection and a disposition if

corrosion and/or damage is found on wing/fuse joints, bolts and barrel

nuts.

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 thru each main gear and main gear

door mechanism

- for long range option aircraft only, defuel aircraft

- stands and/or ladders are installed and electrically grounded

- access panels are opened

- inspect bolt heads for structural integrity

- the bolt, P.L.I. washers are removed, one at a time

- bolt and washer are visually inspected for corrosion and damage

- bolt hole surface and barrel nut threads are visually inspected for corrosion and

damage using a borescope

- if no corrosion or damage to bolt, bolt hole surface, barrel nut and applicable

hardware then reinstall serviceable bolt (make sure you coat bolt with corrosion

inhibiting compounds DHMS C4.12 (F13, Grade 2) or equivalent) with new P.L.I.

washer and associated hardware utilizing existing serviceable barrel nut

NOTE: Serviceable hardware is defined as a new part or a part with no visible

damage or corrosion and is fit for installation.
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- if corrosion is found replace all unserviceable hardware, (Bolt, barrel nut, P.L.I.

washer and retainer)

NOTE: An unserviceable hardware is defined as a part that has visible damage or

corrosion and is NOT fit for installation.

- if corrosion/damage is found on barrel nut then remove engine weight using

applicable instruction in PSM 1-8-2, 1-83-2 57-30-10 or PSM 1-82-2 Task

57-30-00-04,

- if applicable, defuel aircraft as per applicable instructions in PSM 1-8-2, 1-83-2

Chapter 28 or PSM 1-82-2 Task 28-25-00-05

- remove wing fuel panels 522AT and/or 622AT

- if applicable, vent fuel vapors prior to barrel nut removal

- newly installed barrel nut in long range fuel tank option aircraft is sealed with DHMS

S3.01 sealant

- repeat removal/inspection and appropriate reassembly procedures of the

remainder wing/joint locations to complete this service bulletin

- safety wire bolt heads

- engine sling is disconnected and removed, if installed

- all panels are reinstalled

- stands and or ladders are removed

- all tools are removed

- close out procedure are completed

D. Compliance

Bombardier Inc. highly recommends that this Special Inspection Service Bulletin

be incorporated at the earliest opportunity unless otherwise directed by the

operator’s airworthiness authority.

A Transport Canada Airworthiness Directive 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.
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This Service Bulletin is associated with Airworthiness Limitations (AWLs) Revisions

to the Task Card Manuals PSM 1-8-7TC, PSM 1-82-7TC and PSM 1-83-7TC.

F. Manpower

Refer to applicable Part statement for estimated Man-hours to complete this service

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

PART A - Removal/Inspection of bolt, bolt hole, P.L.I. washer, barrel nut and

attaching hardware.

It will take an estimated 11 man-hours to complete PART A of the

ACCOMPLISHMENT instructions in this service bulletin. The breakdown of man

-hours is shown in the table that follows:

TASK MAN-HOURS

Job Set-Up 1.00

Procedure in Part A 9.00

Test / RTS 0.00

Close-Out 1.00

PART B - Installation of bolt, P.L.I. washer and attaching hardware.

It will take an estimated 26 man-hours to complete PART B of the

ACCOMPLISHMENT instructions in this service bulletin. The breakdown of man

-hours is shown in the table that follows:

TASK MAN-HOURS

Job Set-Up 2.00

Procedure in Part

B

22.00

Test / RTS 0.00

Close-Out 2.00
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PART C - Removal/Installation instruction for unserviceable barrel nuts.

It will take an estimated 70 man-hours to complete PART C of the

ACCOMPLISHMENT instructions in this service bulletin. The breakdown of man

-hours is shown in the table that follows:

TASK MAN-HOURS

Job Set-Up 3.00*

Procedure in Part C 64.00**

Test / RTS 0.00

Close-Out 3.00

* - Does not include time for venting fuel fumes from fuel tank.

** - Does not include sealant cure time for aircraft with long range fuel

tanks option.

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

All costs to incorporate this modification are the responsibility of the Operator

G. Material - Price and Availability

The parts necessary to perform this service bulletin are 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

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.
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H. Tooling - Price and Availability

None

I. Weight and Balance

None

J. Electrical Load Data

Not affected

K. Publications Affected

Modifications Manual PSM 1-813-12 ...............................

L. References

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

related data that follows:

Production Drawing 85300006 (for internal reference only)

PCA 06833 Revision 1 (for internal reference only)

Transport Canada Airworthiness Directive Pending
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2. MATERIAL INFORMATION

A. Parts Required Per Aircraft

(1) Detailed Part List:

Quantity Per Aircraft

Q100/200 Q300

Part Number Description Remarks

8 8 62523-7-12.4 WASHER P.L.I.

(Front Spar)

8 8 62523-8-17.0 WASHER P.L.I.

(Rear Spar)

8 8 DSC228-7 NUT, BARREL (Front Spar)

8 8 DSC228-8 NUT, BARREL (Rear Spar)

8 MS21250H07050 * BOLT, TENSION (Front Spar)

8 MS21250H08056 * BOLT, TENSION (Rear Spar)

8 MS21250H07066 * BOLT, 12 POINT HD (Front Spar)

8 MS21250H08070 * BOLT, 12 POINT HD (Rear Spar)

8 8 NAS578-7A RETAINER, FLOATING BARREL NUT

8 8 NAS578-8A RETAINER, FLOATING BARREL NUT

8 16 85300068-101 WASHER, 0.040 THK (Front Spar)

Refer to Note

8 16 85300068-103 WASHER, 0.060 THK (Front Spar)

Refer to Note

8 16 85300068-105 WASHER, 0.080 THK (Front Spar)

Refer to Note

8 16 85300068-107 WASHER, 0.100 THK (Front Spar)

Refer to Note

8 16 85300068-109 WASHER, 0.120 THK (Front Spar)

Refer to Note

8 8 85300069-101 WASHER, 0.040 THK (Rear Spar)

Refer to Note

8 8 85300069-103 WASHER, 0.060 THK (Rear Spar)

Refer to Note

8 8 85300069-105 WASHER, 0.080 THK (Rear Spar)

Refer to Note
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Quantity Per Aircraft

Q100/200 Q300

Part Number Description Remarks

8 8 85300069-107 WASHER, 0.100 THK (Rear Spar)

Refer to Note

8 8 85300069-109 WASHER, 0.120 THK (Rear Spar)

Refer to Note

A/R A/R MS20995-C32 LOCK WIRE As Required

NOTE : Use only one of these washers to achieve thread provision

requirements as shown in Figure 8, Sheet 4.

* Part numbers MS21250H07050, MS21250H08056, MS21250H07066,

MS21250H08070 are referenced as P/N MS21250-HXXXX within the

instructions of this service bulletin.

Addresses of manufacturers and suppliers not shown below are listed in either

Maintenance Manual Chapter 20 or in Structural Repair Manual Chapter 51.

Part Number Qty. Per Aircraft Description Remarks

DHMS C4.12

MIL-C-16173

2 oz. Corrosion Preventive

Compound

F13 (Grade 2)

DHMS S5.01 As required Dynamold - DS108F,

Solvent - Degreaser

DHMS S3.01 A/R Type I Class B SealantPR 1776M B2

B. Parts Required to Modify Spares

None

C. Special Tools and Equipment Required

Reference Designation Remarks

None specified Load Cell Must have capabilities

of measuring a 2200

LBS (997 kg) load.

None specified Borescope

None specified Torque Wrench Must have capabilities

of applying 1500

inch-pounds

minimum.
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D. Existing Parts Accountability

None

3. ACCOMPLISHMENT INSTRUCTIONS

NOTE: Operators that have performed inspection per PSM 1-8-7TC or 1-82-7TC

or 1-83-7TC Task Card 5730/04B dated Feb 06, 2012 or later revisions,

have met the intent of this service bulletin.

A. Job Set-Up

WARNING: YOU MUST 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.

(1) Make sure that lock pins are installed through each main gear and main gear

door mechanism. Refer to applicable instructions in PSM 1-8-2, 1-83-2 Chapter

10 and 32 or PSM 1-82-2 TASK 10-11-00-400-802.

(2) Make sure the nose gear ground lock is engaged. Refer to applicable

instructions in PSM 1-8-2, 1-83-2 Chapter 10 and 32 or PSM 1-82-2 TASK

10-11-00-400-801.

(3) Make sure the lock pins are installed as per applicable instructions in PSM 1-8-2,

1-83-2 Chapter 10 and 32 or PSM 1-82-2 TASK 32-00-00-840-801.

(4) For long range option aircraft only, Defuel aircraft. Refer to applicable instruction

in PSM 1-8-2, 1-83-2 Chapter 28 or PSM 1-82-2 TASK 28-25-00-05.

(5) Placard and select all aircraft electrical power to OFF. Obey all relevant

WARNINGS and CAUTIONS. Refer to applicable instruction in PSM 1-8-2, 1-83-2

Chapters 12 and 24 or PSM 1-82-2 TASK 12-00-05-03 and TASK 24-00-00-02.

NOTE: The following procedures are for removal/installation instructions for

unserviceable barrel nuts as shown in Part C.

(6) Remove wing access panels by setting up the work platforms or ladders as

required to remove engine access panels 412AT, 412CT and lower cowl 417AB.

Refer to applicable inspections in PSM 1-8-2, 1-83-2 Chapter 6 or PSM 1-82-2

TASK 06-41-00-00. Make sure the work platforms or ladders are electrically

grounded. Refer to Figure 5.

NOTE: Wing access panels are not required to be removed, except if barrel nut

needs to be replaced.
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NOTE: Make sure the aircraft is in a stable symmetric condition either on jacks or

gear but not a combination of the two prior to proceeding with the

removal of any bolts.

(7) Set up the work platforms or ladders as required to gain access to the following

panels; left side: 263AL, 263BL, 263CL and 263DL, right side: 264AR, 264BR,

264CR and 264DR. Make sure the work platforms or ladders are electrically

grounded. Refer to Figure 6.

NOTE: It will be necessary to remove panel 522AT and 622AT if corrosion is

found on barrel nut threads after borescope inspection. Refer to Figure 6.

CAUTION: DO NOT CHANGE THE CONFIGURATION OF THE AIRCRAFT

(EXAMPLE: REMOVE OR INSTALL ENGINES OR PROPELLERS) OR

MOVE AIRCRAFT WHEN THE OVERWING ACCESS PANELS ARE NOT

INSTALLED. IF YOU DO THIS, YOU CAN CAUSE DAMAGE TO THE

AIRCRAFT WING STRUCTURE.

(8) For replacement of barrel nuts only, lift engine using applicable instruction in

PSM 1-8-2, 1-83-2 Chapter 57-30-10 or PSM 1-82-2 TASK 57-30-00-04.

NOTE: It is necessary to lift the engines in order to remove the engine weight

from the bolts, prevent wing twist and allow removal of wing access

panels when replacing the barrel nuts at the attachment points.

NOTE: You do not have to do this procedure if engine is not installed.

B. Procedure

CAUTION: DO NOT REMOVE MORE THAN ONE TENSION BOLT AT A TIME,

DAMAGE TO THE MOUNTING STRUTS BRACKETS, THE WING SPAR

STRUCTURE AND THE CENTER FUSELAGE STRUCTURE MAY

RESULT.

CAUTION: DURING THE REMOVAL OR INSTALLATION OF THE TENSION BOLTS.

DO NOT MAKE CONTACT OR HIT THE CONTROL CABLES, TORQUE

TUBES OR DEICER/HYDRAULIC TUBES THAT ARE IN THE AREA OF

REWORK. IF YOU DO YOU CAN CAUSE DAMAGE.
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PART A - Removal/Inspection of bolt, bolt hole, P.L.I. washer, barrel nut and

attaching hardware.

(1) Prior to the removal the Wing/Fuse Joint bolts. Perform a torque check of all 16

bolt heads to make sure that they are intact. Do the following:

(a) For each (P/N MS21250-H07XX bolt) of eight (8) bolts, use a torque

wrench and apply 900 inch-pounds of torque.

(b) Then continue torque check for remainder of MS21250-H08XX (8) bolts by

applying 1350 inch-pounds of torque.

NOTE: Complete torque check of all 16 bolts before proceeding to the following

steps.

(2) If more than one bolt has failed the torque check, prior to next fight contact the

‘‘Toronto Help Desk” in Toronto at telephone number (416) 375-4000 or

facsimile (416) 375-4539’’ or E-mail: thd.qseries@aero.bombardier.com for

approved repair/disposition.

(3) If only one bolt has failed the torque check then replace that one first.

(4) Remove ONLY one bolt (P/N MS21250-HXXXX) and associated hardware at a

time. Visually inspect the removed bolt and all associated hardware for

corrosion, damage and/or wear. Replace bolt and/or hardware that is

unserviceable. Refer to Figure 8, Sheet 2 (Front Spar View) and Sheet 6 (Rear

Spar View).

NOTE: Refer to Section 2. Para A step (1) Detailed Part List: within this service

bulletin for appropriate associated hardware part numbers.

NOTE: For ease of visual inspection for corrosion on bolt and hole. Remove

corrosion preventive compound from bolt shaft and bolt hole by using

Dynamold - DS108F, Solvent - Degreaser or equivalent.

(5) Visually inspect the bore of the hole (refer to Figure 8 Sheet 3) and the barrel nut

threads for corrosion using a borescope. If any corrosion is found on barrel nut

threads then replace barrel nut using applicable instructions in Part C of this

service bulletin. If corrosion/damage is found in bore of the hole then contact the

‘‘Toronto Help Desk” in Toronto at telephone number (416) 375-4000 or

facsimile (416) 375-4539’’ or E-mail: thd.qseries@aero.bombardier.com for

approved repair/disposition.
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(6) If no corrosion is observed on bolt and associated hardware then reinstall bolt

using applicable instructions in PART B of this service bulletin.

NOTE: No damage and/or wear is acceptable on the hardware. If any signs of

damage/wear is found then hardware is deemed unserviceable and must

be replaced.

PART B - Installation of bolt, P.L.I. washer and attaching hardware.

NOTE: Steps in Part B of this service bulletin is for serviceable barrel nuts that

have not been removed. If barrel nuts have been removed refer to PART

C - Removal/Installation instruction for unserviceable barrel nuts.

(1) Apply corrosion protective compound DHMS C4.12 (F13 Grade 2) or equivalent

to the shank of the bolt serviceable. Make sure bolt threads are not coated with

DHMS C4.12 (F13 Grade 2) or equivalent prior to installing. Clean with

Dynamold - DS108F, Solvent - Degreaser or equivalent if accidently applied.

Refer to Figure 2.

CAUTION: WHEN INSTALLING BOLT HAND TIGHTEN BOLT UNTIL THE LOCKING

ELEMENT OF BARREL NUT IS ENGAGED. THIS WILL AVOID CROSS

THREADING.

(2) Reinstall serviceable hardware at the strut (bolt, new P.L.I. washer and

applicable hardware) at Yw42 immediately after removing hardware. Change

saddle washer and retainer if required. Refer to Figure 8, Sheet 2, Sheet 6 and

applicable instructions for required preload of P.L.I. washer in PSM 1-8-2, 1-83-2

Chapter 20, 20-14-04 or PSM 1-82-2 Chapter 20 TASK 20-14-04-02.

NOTE: Do not leave any bolts out and continue with any other type of work to the

aircraft.

NOTE: Use one washer of equivalent thickness (refer to Figure 8 Sheet 4) if

saddle washer is replaced.

(3) Inspect to make sure that a minimum of 1 full thread of bolt is showing above

barrel nut and that the bolt threads do not extend beyond barrel nut bore. Refer

to Figure 8 Sheet 4.

(4) Remove any excess corrosion preventive compound from around the head of

the bolt and/or from the barrel nut hole using Dynamold solvent - DS108F,

Solvent - Degreaser or equivalent to make sure that P.L.I. washer, saddle

washer and bolt head are visible.
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(5) Wire lock bolt heads (P/N MS21250-HXXXX) with lock wire MS 20995C32. Refer

to PSM 1-8-2, 1-83-2 Chapter 20 or PSM 1-82-2, TASK 20-09-10-02.

(6) Continue inspections as stated in Para B Procedure, Part A of this service

bulletin for remainder of bolt, bolt hole, P.L.I. washer, barrel nut and attaching

hardware (if applicable).

(7) Continue all steps for opposite side of aircraft. Once completed go to Close Out

procedures.

PART C - Removal/Installation instruction for barrel nuts.

NOTE: This procedure is required if barrel nut is deemed unserviceable in PART

A or if new barrel nut is installed.

NOTE: For long range fuel tank option aircraft, it will be necessary to defuel and

defume fuel tanks prior to removal of panels 522AT and 622AT to gain

access for barrel nut removal and replacement. Refer to applicable

instruction for defueling and defuming in PSM 1-8-2, 1-83-2 Chapter 28 or

PSM 1-82-2 TASK 28-25-00-05 and Figure 6 .

NOTE: For long range fuel tank option aircraft (if applicable) there will be the

need for additional fillet sealant at station Y42.00, barrel nuts (8 locations

per side).

(1) Carefully remove unserviceable barrel nut.

NOTE: For long range fuel option aircraft. Special care is required when

removing sealant from barrel nut location.

(2) Make sure that barrel nut hole is not coated with DHMS C4.12 (F13 Grade 2)

compound or equivalent. If required clean the surface with Dynamold - DS108F,

Solvent - Degreaser or equivalent. Refer to Figure 3.

(3) Inspect barrel nut hole seating surface for corrosion/damage. If

corrosion/damage is found in barrel nut hole then contact the ‘‘Toronto Help

Desk” in Toronto at telephone number (416) 375-4000 or facsimile (416)

375-4539’’ or E-mail: thd.qseries@aero.bombardier.com for approved

repair/disposition.

(4) Apply DHMS C4.12 (F13 Grade 2) corrosion preventive compound or equivalent

to the seating surface of serviceable barrel nut. Do not apply compound to areas

of the barrel nut other than the seating surface. Refer to Figure 2.

(5) Make sure the threads of the barrel nut are free of DHMS C4.12 (F13 Grade 2)

compound or equivalent. Refer to Figure 2.

(6) Make sure that barrel nut hole is clear of debris and clean.
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(7) Install serviceable barrel nut as to applicable instructions in PSM 1-8-3, 1-83-3

Chapter 51-42-85 or PSM 1-82-3 Chapter 51 TASK 51-42-85-02-01.

NOTE: Make sure bolt threads are not coated. If coated then clean with

Dynamold - DS108F, Solvent - Degreaser or equivalent.

(8) Insert serviceable bolt, new P.L.I. washer, associated hardware and tighten bolt.

Refer to applicable instructions for required preload of P.L.I. washer in PSM

1-8-2, 1-83-2 Chapter 20, 20-14-04 or PSM 1-82-2 Chapter 20 TASK

20-14-04-02.

(9) Inspect to make sure that a minimum of 1 full thread of bolt is showing above

barrel nut and that the bolt threads do not extend beyond barrel nut bore. Refer

to Figure 8 Sheet 4.

(10) If barrel nuts on the outboard (Wet Side of rib at station Y42.00) have been

remove and replace in aircraft with long range fuel tanks option then there will

be the need for additional sealing using DHMS S3.01/B2 sealant at barrel nut

locations. Refer to applicable instructions in PSM 1-8-3, 1-83-3 Chapter 51-42-85

or PSM 1-82-3 Chapter 51 TASK 51-42-85-02-01 and Figure 4.

(11) Wire lock bolt heads (P/N MS21250-HXX) with lock wire MS 20995C32. Refer to

PSM 1-8-2, 1-83-2 Chapter 20 or PSM 1-82-2, TASK 20-09-10-02.

(12) Continue inspections as stated in Para B Procedure, Part A of this service

bulletin for remainder of bolt, bolt hole, P.L.I. washer, barrel nut and attaching

hardware (if applicable).

(13) Continue all steps for opposite side of aircraft. Once completed go to Close Out

procedures.
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C. Close Out

(1) If installed, remove engine sling using applicable instruction in PSM 1-82-1,

1-83-2 Chapter 57-30-10 or PSM 1-82-2 TASK 57-30-00-04. Refer to Figure 5.

(2) If removed, install engine access panels 412AT, 412CT and lower cowl 417AB.

Refer to PSM 1-8-2, 1-82-2 and 1-83-2 Chapter 6-41-10 . Refer to Figure 5.

(3) If lower cowl cover installed then remove the engine cowl cover. Raise the lower

cowl 417AB and install engine access panel 412AT, if required.

(4) Reinstall all exterior panels that where removed.

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

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

appropriate logbooks: “Service Bulletin 8-57-47, Wings - Special Inspection and

Replacement - Wing / Fuselage Joint Bolts.
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Barrel Nut Inserts and Retainers - GA

Figure 1
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Application of F13 Grade 2 Type 2 to Bolt and Barrel Nut

Figure 2

F13 ON BOLT SHANK

FAY SEAL UNDER

SADDLE WASHER

PLI WASHER OMITTED FOR CLARITY

F13 ON SEATING SURFACE
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Barrel Nut Installation

Figure 3

BARREL NUT HOLE

SEATING SURFACE
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Potting Barrel Nut Holes

Figure 4

PLUG SEAL USING DHMS S3.01/B2 SEALING COMPOUND TO PSM1-8-2, 1-83-2 CHAPTER 20-21-20 OR PSM 1-82-2 TASK 20-21-20-02FOR CLEANING AND POTTING PROCEDURE REFER TO PSM 1-8-2,1-83-2 CHAPTER 20 GENERAL SEALING PRACTICES OR PSM 1-82-2TASK 20-21-21-02.MAKE SURE YOU OVERLAP FILLET SEAL 0.25 MINIMUM WITHDHMS S3.01/A2 BRUSH COAT TO PSM 1-8-2, 1-83-2 CHAPTER 20 -GENERAL SEALING PRACTICES OR PSM 1-82-2 TASK 20-21-21-02 -GENERAL SEALING PRACTICES - MAINTENANCE PRACTICES.

FOR AIRCRAFT WITH LONG RANGE FUEL TANK OPTION - ONLY

SEALANT

SEALANT GUN NOZZLE

MASKINGTAPE

BARRELNUT

SEALANT

MASKINGTAPE

0.10 in.

0.20 in.

0.25 in.. (OVERLAPFILLET SEAL WITHDHMS S3.0/A2

Y42.00

Y41.40

AT BARREL NUTHOLES, WET SIDE(FUEL) ONLY(OUTBD)0.25 in.

ONE FULLTHREAD MIN.VERIFY BEFOREPOTTING

RIB

85710082

(REF)

DRAIN HOLE

0.20 in.

(TYPICAL -

BOTH SIDES)

0.10 in.

(TYPICAL -

BOTH SIDES)

10

10

10
SERVICE BULLETIN 8-57-47

S.B. 8-57-47

Page 20 of 30

16 Mar 2012

Revision ‘A’ 29 May 2013 JR

Engine lifting

Figure 5
SERVICE BULLETIN 8-57-47

S.B. 8-57-47

Page 21 of 30

16 Mar 2012

Revision ‘A’ 29 May 2013 JR

Access Panels and Doors - Center Fuselage & Left Wing Top View

Figure 6

TOP LEFT

FWD

522AT

622AT -

OPPOSITE WING
SERVICE BULLETIN 8-57-47

S.B. 8-57-47

Page 22 of 30

16 Mar 2012

Revision ‘A’ 29 May 2013 JR

Wing to Fuselage - GA

Figure 7

X384.500

X387.350

X426.974

X424.124

FUSELAGE COMPLETE

(REF)

X403.757

Z181.400

VIEW LOOKING ON LEFT HAND SIDE

MS21250H080XX (QTY 8)

REAR SPAR LH AND RH OUTBOARD

MS21250H070XX (8 REQ)

FRONT SPAR LH AND

RH OUTBOARD

MS21250H070XX (8 REQ)

FRONT SPAR LH AND RH OUTBOARD

FWD VIEW

LOOKING ON RIGHT

HAND SIDE

MS21250H080XX (QTY 8)

REAR SPAR LH AND RH OUTBOARD
SERVICE BULLETIN 8-57-47

S.B. 8-57-47

Page 23 of 30

16 Mar 2012

Revision ‘A’ 29 May 2013 JR

VIEW A LOOKING AFT ON FRONT SPAR FRAME - LH SIDE GA

Figure 8 Sheet 1

FRONT SPAR ASSY

85710060

Y42.000

FRONT SPAR FRAME

ASSY 85320009

(REF)

(REF)

Z175.750

B
SERVICE BULLETIN 8-57-47

S.B. 8-57-47

Page 24 of 30

16 Mar 2012

Revision ‘A’ 29 May 2013 JR

VIEW B LOOKING AFT ON FRONT SPAR FRAME - LEFT SIDE OUTBOARD SHOWN,

OPPOSITE SIDE SIMILAR

Figure 8 Sheet 2

9 12

9 13 14

Z175.750

8

Y42.000

FRONT SPAR ASSY

85710060

(REF)

FRONT SPAR FRAME

ASSY 85320009

(REF)

85300068--101

85300068--105

85300068--109

MS20995C32

62523--7--12.4

WASHER

SEE DETAIL G

BOLT

P.L.I. WASHER

8 REQ’D

LOCKWIRE

MS21250--H07050

8 REQ’D

BOLT

MS21250--H07066

8 REQ’D

85300068--103

85300068--107

9

13

14

12

B

C

C

APPLY F13 GRADE 2 TO BOLT SHANK PRIOR TO INSTALLATION. REFER TO APPLICABLE INSTRUCTION IN: FOR PSM

1-8-2, 1-83-2 CHAPTER 20 & FOR PSM 1-82-2 REFER TO TASK 20-16-01-02.

INSTALLATION OF BARREL NUTS. REFER TO APPLICABLE INSTRUCTIONS FROM THE VENDOR SUPPLIER.

USED ONLY ON 100 AND 200 SERIES AIRCRAFT ONLY.

USED ONLY ON 300 SERIES AIRCRAFT ONLY.

USED ONLY ON SERIES 300A ONLY.

FOR INSTALLATION OF PRELOAD INDICATING WASHERS. REFER TO APPLICABLE INSTRUCTIONS IN: FOR PSM 1-8-2,

1-83-2 CHAPTER 20 & FOR PSM 1-83-2 CHAPTER 20, TASK 20-14-04-02.

8

4

17

17 TO ELIMINATE DETRIMENTAL EFFECTS ON THE BOLTS AT THE WING/FUSE INTERFACE, THE FUSELAGE AND WING

MUST BE SUPPORTED IN THEIR RESPECTIVE FIXTURES WHILE TORQUING SAID FASTENERS.

FOR WIRELOCK (SAFETY WIRE) HEAD TO HEAD. INSTALL PROCEDURES. REFER TO APPLICABLE INSTRUCTIONS IN

PSM 1-82, 183-2 CHAPTER 20 AND FOR PSM 1-82-2 TASK 20-09-10-02.

4

2

2

2
SERVICE BULLETIN 8-57-47

S.B. 8-57-47

Page 25 of 30

16 Mar 2012

Revision ‘A’ 29 May 2013 JR

VIEW C-C LOOKING INBOARD ON OUTBOARD LH FRONT SPAR FRAME (TYPICAL)

Figure 8 Sheet 3

FRONT SPAR

X384.500

RIB

WING MOUNTING PAD

STRUT ASSEMBLY

D

C C

AFTER BOLT/HARDWARE IS

REMOVED. INSERT

BORESCOPE THROUGH BOLT

HOLE TO INSPECT BORE OF

HOLE AND BARREL NUT

THREADS.
SERVICE BULLETIN 8-57-47

S.B. 8-57-47

Page 26 of 30

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Revision ‘A’ 29 May 2013 JR

VIEW D

Figure 8 Sheet 4

MINIMUM ONE

FULL THREAD

SHOWING

MAXIMUM TO DIA.

OF BARREL

NUT BORE

85300068--* 85300069--*

ONLY ONE OF THE ABOVE

WASHERS TO BE USED

PER BOLT LOCATION.

D

P.L.I. WASHER

BOLT
SERVICE BULLETIN 8-57-47

S.B. 8-57-47

Page 27 of 30

16 Mar 2012

Revision ‘A’ 29 May 2013 JR

VIEW E LOOKING FWD ON REAR SPAR FRAME- LH SIDE GA

Figure 8 Sheet 5

REAR SPAR ASSY

85710065

Y42.000

REAR SPAR FRAME

ASSY 85320010

(REF)

(REF)

Z175.750

E

F
SERVICE BULLETIN 8-57-47

S.B. 8-57-47

Page 28 of 30

16 Mar 2012

Revision ‘A’ 29 May 2013 JR

VIEW F LOOKING FWD ON REAR SPAR - LEFT SIDE INBOARD

Figure 8 Sheet 6

Z174.540

Y42.000

REAR SPAR ASSY

85710065

(REF)

REAR SPAR FRAME

ASSY 85320010

(REF)

85300069--101

85300069--105

85300069--109

MS20995C32

62523--8--17.0

WASHER BOLT SEE VIEW D

P.L.I. WASHER

8 REQ’D

LOCKWIRE

MS21250--H08070

8 REQ’D

BOLT

MS21250--H08056

8 REQ’D

85300069--103

85300069--107

F

G

G

9

13

14

12

APPLY F13 GRADE 2 TO BOLT SHANK PRIOR TO INSTALLATION. REFER TO APPLICABLE INSTRUCTION IN: FOR PSM

1-8-2, 1-83-2 CHAPTER 20 & FOR PSM 1-82-2 REFER TO TASK 20-16-01-02.

INSTALLATION OF BARREL NUTS. REFER TO APPLICABLE INSTRUCTIONS FROM THE VENDOR SUPPLIER.

USED ONLY ON 100 AND 200 SERIES AIRCRAFT ONLY.

USED ONLY ON 300 SERIES AIRCRAFT ONLY.

USED ONLY ON SERIES 300A ONLY.

TO ELIMINATE DETRIMENTAL EFFECTS ON THE BOLTS AT THE WING/FUSE INTERFACE, THE FUSELAGE AND WING

MUST BE SUPPORTED IN THEIR RESPECTIVE FIXTURES WHILE TORQUING SAID FASTENERS.

FOR WIRELOCK (SAFETY WIRE) HEAD TO HEAD. INSTALL PROCEDURES. REFER TO APPLICABLE INSTRUCTIONS IN

PSM 1-82, 183-2 CHAPTER 20 AND FOR PSM 1-82-2 TASK 20-09-10-02.

4

2

FOR INSTALLATION OF PRELOAD INDICATING WASHERS. REFER TO APPLICABLE INSTRUCTIONS IN: FOR PSM 1-8-2,

1-83-2 CHAPTER 20 & FOR PSM 1-83-2 CHAPTER 20, TASK 20-14-04-02.

8

9

12

9

13 14 17

2

2 12 17

8

4
SERVICE BULLETIN 8-57-47

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16 Mar 2012

Revision ‘A’ 29 May 2013 JR

VIEW G-G LOOKING INBOARD ON REAR SPAR - LEFT SIDE SHOWN, OTHER

SIMILAR

Figure 8 Sheet 7

REAR SPAR

X426.974

G G

D

RIB

WING MOUNTING PAD

STRUT ASSEMBLY

1
SERVICE BULLETIN 8-57-47

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Revision ‘A’ 29 May 2013 JR

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