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

S.B. 8-57-47 Page 1 of 30 16 Mar 2012 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

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 2 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR 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 a re 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, Gr ade 2) or equivalent) with new P.L.I. washer and associated hardware utilizi ng 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.

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 3 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR - 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 fu el 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 thi s 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.

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 4 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR 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 s ervice 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 s ervice 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

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 5 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR 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 s ervice 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 pur chase 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.

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 6 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR 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

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 7 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR 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

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 8 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR Quantity Per Aircraft

Q100/200 Q300 Remarks Description Part Number

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 Sealant PR 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.

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 9 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR 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.

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 10 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR 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, 263C L 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.

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 11 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR 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.

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 12 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR (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.

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 13 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR (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.

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 14 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR (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.

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 15 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR 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.

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 16 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR Barrel Nut Inserts and Retainers - GA Figure 1

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 17 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR 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

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 18 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR Barrel Nut Installation Figure 3 BARREL NUT HOLE SEATING SURFACE

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 19 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR Potting Barrel Nut Holes Figure 4PLUG 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 - ONLYSEALANTSEALANT GUN NOZZLEMASKINGTAPEBARRELNUTSEALANTMASKINGTAPE0.10 in.0.20 in.0.25 in.. (OVERLAPFILLET SEAL WITHDHMS S3.0/A2Y42.00Y41.40AT BARREL NUTHOLES, WET SIDE(FUEL) ONLY(OUTBD)0.25 in.ONE FULLTHREAD MIN.VERIFY BEFOREPOTTINGRIB85710082(REF)DRAIN HOLE0.20 in.(TYPICAL -BOTH SIDES)0.10 in.(TYPICAL -BOTH SIDES)101010

### 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 T HE 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 PR OCEDURES. 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 16 Mar 2012 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 SEE VIEW D BOLT

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 T HE 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 PR OCEDURES. 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 17 12

8 4

### SERVICE BULLETIN 8-57-47

S.B. 8-57-47 Page 29 of 30 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

S.B. 8-57-47 Page 30 of 30 16 Mar 2012 Revision ‘A’ 29 May 2013 JR 

### 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 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