# Bombardier Service Bulletin 84-32-110 Copy: Revision A ("U.S. DOT/FAA - Service Bulletin 84-32-110 Revision A"), 12 pages: PDF https://openairdocs.org/files/sha256/54/f7/54f729bea9dde2cf1ce238848209593def841c0d30db21e37e96ee8265d591fd; text https://openairdocs.org/service-documents/bombardier/sb-84-32-110/file/54f729bea9dd.md. Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2013-1029; AD 2014-25-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Bombardier](https://openairdocs.org/service-documents/bombardier.md) - Type: Service bulletin (Service Bulletin) - Number: 84-32-110 - Latest revision known: 84-32-110, Revision A, dated April 8, 2013 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/bombardier/sb-84-32-110 ## ADs that cite it (2) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2017-19-09](https://openairdocs.org/ad/2017-19-09.md), effective Oct 24, 2017: No revision named - [AD 2014-25-01](https://openairdocs.org/ad/2014-25-01.md), effective Jan 16, 2015: Revision A Also cited in [2 proposed ADs](https://openairdocs.org/service-documents/bombardier/sb-84-32-110/proposed.md). ## Text (12 pages) Rights: © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2013-1029; AD 2014-25-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 (OCR) de HAVILLAND BOMBARDIER DASI18 SERVICE BULLETIN Customer_ Support ATA SYSTEM: 3221 NUMBER: 84-32-110 BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND URGE OPERATORS TO PROMPTLY EVALUATE THE CONTENTS SUBJECT: Landing Gear - Nose Landing Gear Installation - Introduction of New Pivot Pin Retention Mechanism to Shock Strut Assembly - ModSum 4-113749 1. PLANNING INFORMATION A. Effectivity Aircraft Affected: In-Service: DHC-8 Aircraft Models 401 and 402 Serial Numbers 4001, 4003 thru 4435. Production: ModSum 4-113749 will be installed before delivery on applicable DHC-8 Aircraft at Serial Numbers 4436 and subsequent. 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 21 Dec 2012 S.B. 84-32-110 Revision 'A' 08 Apr 2013 Page 1 of 6 NB ### Page 2 (OCR) SERVICE BULLETIN 84-32-110 B. Reason Problem: In 2008 an operator experienced a NLG tire failure due to tire contact with the pivot pin. Investigations revealed the retention bolt had sheared allowing the pivot pin to migrate and contact the tire. The operator inspected their fleet and found four other aircraft with damage to the retention bolts. The root cause was determined to be contact with the towbar. To address this, ModSum 4N113599 was issued to reverse the bolt orientation allowing the bolt head to be protected by larger tow fitting bolt and also improve corrosion resistance by changing the material from 4140 to CRES A286. Recently, operators with aircraft at approximately 1500 flight cycles after incorporation of the ModSum have reported the pivot pin retention bolt either missing or damaged. Assessment of the load in the area of the pivot pin indicate the current retention bolt can be subjected to excessive localized contact stresses. Furthermore, an adverse tolerance condition exists that could potentially create interference during assembly of the retention bolt. This change caters for the loading conditions, tolerances and towbar to ensure full life to the new retention mechanism. Solution: Remove the existing pivot pin retention bolt, rotate the pivot pin and install a pivot pin adapter, special bolt, pivot pin link and flanged bushing according to the enclosed vendor service bulletin. 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 - access is gained to the nose landing gear - a jack is installed at the jacking point of the nose fuselage - the existing pivot pin retention bolt is removed, the pivot pin is rotated and a pivot pin adapter, special bolt, pivot pin link and flanged bushing is installed according to the enclosed vendor service bulletin - the shock strut is re-identified with a new part number 21 Dec 2012 S.B. 84-32-110 Revision 'A' 08 Apr 2013 Page 2 of 6 NB ### Page 3 (OCR) SERVICE BULLETIN 84-32-110 - close out. D. Compliance Bombardier Inc. highly recommends that ModSum 4-113749 be incorporated at the earliest opportunity unless otherwise directed by the operator's airworthiness authority. A Transport Canada Airworthiness Directive is pending. E. Approval The technical content of this service bulletin has been approved under the authority of the Transport Canada Civil Aviation (TCCA) Design Approval Organization No: DAO #93-Q-02. This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage Tolerance Inspections (DTIs). F. Manpower It will take an estimated 2.00 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 0.50 Procedure 1.00 Test / RTS 0.00 Close-Out 0.50 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 Refer to enclosed Goodrich Service Bulletin 47100-32-96. H. Tooling - Price and Availability None 21 Dec 2012 S.B. 84-32-110 Revision 'A' 08 Apr 2013 Page 3 of 6 NB ### Page 4 (OCR) SERVICE BULLETIN 84-32-110 Weight and Balance Moment A/C Type and Weight (Lb) Arm (Inches) (Inches x Lb) Model × 0.001 DHC-8 Model 401 +0.10 - 119.92 -0.01 DHC-8 Model 402 +0.10 - 119.92 -0.01 Refer to enclosed Goodrich Service Bulletin 47100-32-96. J. Electrical Load Data Not affected K. Publications Affected Maintenance Manual ..... Dash 8 Illustrated Parts Catalogue .. ModSums Manual . ............. PSM 1-84-2 ............. PSM 1-84-4 ............ PSM 1-84-12 References Revision 'A' of this service bulletin was prepared to the engineering drawings and related data that follows: ModSum 4N113749 Rev. 'J' ModSum 4Q113749 Rev. 'C' ModSum 4-113749 Rev. 'F' PCA 43508 Revision 2 (for internal reterence only) Goodrich Service Bulletin 47100-32-96 R2 dated Mar 20/13 Transport Canada Airworthiness Directive Pending 21 Dec 2012 S.B. 84-32-110 Revision 'A' 08 Apr 2013 Page 4 of 6 NB ### Page 5 (OCR) SERVICE BULLETIN 84-32-110 2. MATERIAL INFORMATION A. Parts Required Per Aircraft Refer to enclosed Goodrich Service Bulletin 47100-32-96. B. Parts Required to Modify Spares None C. Special Tools and Equipment Required None D. Existing Parts Accountability Refer to enclosed Goodrich Service Bulletin 47100-32-96. 3. ACCOMPLISHMENT INSTRUCTIONS A. Job Set-Up WARNING: MAKE SURE YOU 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. WARNING: MAKE SURE YOU INSTALL THE LOCKPINS IN THE DOOR MECHANISMS OF THE MLG AND NG. THE DOOR MECHANISMS CAN ACCIDENTALLY CLOSE THE LANDING GEAR DOORS. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. WARNING: MAKE SURE YOU INSTALL THE LOCKPINS ON THE LANDING GEAR DOORS. MAKE SURE YOU DISCONNECT THE LANDING GEAR DOORS. IF YOU DO NOT DO THIS THE LANDING GEAR DOORS WILL CLOSE WHEN YOU APPLY THE HYDRAULIC PRESSURE. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. (1) Placard and select all aircraft electrical power to OFF. Obey all relevant WARNINGS and CAUTIONS (refer to AMM TASK'S 24-00-00-861-802 and 24-00-00-910-801). (2) Make sure that lock pins are installed through each main gear and main gear door mechanism. 21 Dec 2012 S.B. 84-32-110 Revision 'A' 08 Apr 2013 Page 5 of 6 NB ### Page 6 (OCR) SERVICE BULLETIN 84-32-110 (3) Make sure the nose gear ground lock is engaged. (4) Gain access to the nose landing gear. (5) Refer to the applicable steps in AMM TASK 07-10-00-582-803 and install a jack at the jacking point of the nose fuselage (Sta. X-39.00, aft of the nose landing gear). B. Procedure (1) Refer to enclosed Goodrich Service Bulletin 47100-32-96 and do the installation of the new pivot pin retention mechanism to the shock strut assembly. (2) If a sheared bolt is found, no additional inspection is necessary. C. Close Out (1) Refer to the applicable steps in AMM TASK 07-10-00-582-803, lower the aircraft and remove the jack from the jacking point of the nose fuselage. (2) Remove all tools and equipment from the work area. (3) On incorporation of this ModSum, make an entry that conforms to local regulatory requirements in the applicable logbook(s). Enter component serial numbers if applicable. Enter this ModSum number only after complete and functional incorporation of all work defined in this service bulletin. 21 Dec 2012 S.B. 84-32-110 Revision 'A' 08 Apr 2013 Page 6 of 6 I NB ### Page 7 (OCR) GOODRICH SERVICE BULLETIN DASH 8 Q400 NG SHOCK STRUT - PIVOT PIN RETENTION - REDESIGNED RETENTION MECHANISM AND INTRODUCTION OF NEW CONFIGURATION (47100-19) REVISION NO.2 - March 20, 2013 Service Bulletin 47100-32-96 R2 supersedes Service Bulletin 47100-32-96 R1 dated Jan 14/13 and is re-issued in its entirety to reflect the changes listed below. No adorare wo this revoduced by fire ence Bulein is not afected by this revision. Please destroy all copies of SB 47100-32-96 R1 dated Jan 14/13. Page/Para Change Page 4, Paragraph 2.C. Instructions for re-identification of dressed shock strut assembly clarified. 47100-32-96 R2 HIGHLIGHTS Mar 20/13 Page 1 of 1 THESE COMMODITIES, SOFTWARE OR TECHNOLOGY WERE EXPORTED/RE-EXPORTED IN ACCORDANCE WITH U.S. EXPORT ADMINISTRATION REGULATION. DIVERSION CONTRARY TO U.S. LAW IS PROHIBITED. ### Page 8 (OCR) GOODRICH SERVICE BULLETIN DASH 8 Q400 NG SHOCK STRUT - PIVOT PIN RETENTION - REDESIGNED RETENTION MECHANISM AND INTRODUCTION OF NEW CONFIGURATION (47100-19) SECTION I - PLANNING INFORMATION 1. EFFECTIVITY All NLG Shock Strut Assemblies PN 47100-9/-11/-13/-15/-17. 2. CONCURRENT REQUIREMENTS NA 3. REASON Reports have been received of pivot pin retention bolts missing or damaged. Investigation revealed retention bolts can fail when subjected to localized contact stresses. A redesigned pivot pin retention is introduced and includes a pivot pin adapter, special bolt, a pivot pin link and flanged bushing 4. DESCRIPTION The existing pivot pin retention bolt is removed, the pivot pin is rotated for installation of a pivot pin adapter, special bolt, a pivot pin link and flanged bushing. 5. COMPLIANCE Goodrich Landing Gear in concurrence with the aircraft manufacturer recommends incorporation of this bulletin at operator's earliest convenience. 6. APPROVAL This bulletin contains no modification information that revises approved configurations, and therefore does not require governmental or other regulatory approval. The technical content of this Service Bulletin has been reviewed and accepted by Bombardier Aerospace. 7. MANPOWER NA 8. TOOLING NA 9. WEIGHT AND BALANCE A weight increase of approximately 0.10 pounds is calculated as follows: Kit 47100-19 approximately +0.12 pounds. Bolt NAS6204-12D/NAS6304U12D approximately -0.02 pounds 10. ELECTRICAL LOAD DATA NA 11. REFERENCES Goodrich Landing Gear Component Maintenance Manual 32-21-04 Bombardier Aerospace (BA) Aircraft Maintenance Manual (AMM) PSM 1-84-2 47100-32-96 R2 Page 1 of 5 Mar 20/13 THESE COMMODITIES, SOFTWARE OR TECHNOLOGY WERE EXPORTED/RE-EXPORTED IN ACCORDANCE WITH U.S. EXPORT ADMINISTRATION REGULATION. DIVERSION CONTRARY TO U.S. LAW IS PROHIBITED Reference Goodrich CMM for proprietary information ### Page 9 (OCR) Goodrich Landing Gear Division Goodrich Aerospace Canada Ltd. 12. OTHER PUBLICATIONS AFFECTED NA SECTION II - MATERIAL INFORMATION 1. MATERIAL COST AND AVAILABILITY A. Material Cost and Availability Refer to Goodrich Landing Gear Service Information Letter (SIL 02121-32-53) for material cost and availability related to this Service Bulletin including kit PN K47100-19. 2. MATERIAL INFORMATION New P/N Qty Keyword Old P/N Qty Disposition K47100-19 Repair Kit, NG Shock Strut contains the following: 47204-1 1 Flanged Bushing 47205-1 1 Special Bolt 47206-3 1 Pivot Pin Link 47208-1 1 Pivot Pin Adapter MS14145L4 2 Nut MS14145L4 1 Discard MS24665-153 2 Cotter Pin MS24665-153 1 Discard NAS1149C0416R 1 Washer NAS1149C0432R 1 Washer NAS1149C0463R 2 Washer NAS6304U4D 1 Bolt Bolt NAS6304U12D 1 Discard OR Bolt NAS6204-12D 1 Discard SECTION III - ACCOMPLISHMENT INSTRUCTIONS 1. Procedure (Ref Figure 1) NOTE: Numbers in parenthesis refer to CMM 32-21-04 IPL Figure-Item Number. NOTE: Accomplishment of this Service Bulletin on-wing will require jacking of the NG to achieve a weight-off-wheels condition. Refer to BA AMM for instructions regarding maintenance configuration. A. Remove bolts (1-280 or 1A-270) and washers (1-290 or 1A-280) on WOW cover (1-300A or 1A-290A) and move WOW cover to gain access to pivot pin retention hardware. B. Remove and discard cotter pin (4-280), nut (4-290A), washers (4-300B), (4-305) and bolt (4-310A) (Ref CMM 32-21-04 DISASSEMBLY). 47100-32-96 R2 Mar 20/13 Page 2 of 5 Reference Goodrich CMM for proprietary information ### Page 10 (OCR) Goodrich Landing Gear Division Goodrich Aerospace Canada Ltd. CAUTION: DO NOT REMOVE PIVOT PIN (4-270) FROM SHOCK STRUT. C. Rotate pivot pin (4-270) approximately 25° clockwise. WARNING: USE PROTECTIVE EQUIPMENT WHEN WORKING WITH CORROSION INHIBITING COMPOUND SUCH AS MASTINOX 6856K. SKIN CONTACT CAN BE HAZARDOUS TO YOUR HEALTH. D. Apply corrosion inhibiting compound (CIC, Mastinox 6856K or Cor Ban 27L) over mating surfaces and threads of special bolt PN 47205-1, washer NAS1149C0463R, bushing PN 47204-1, pivot pin link PN 47206-3, nut MS14145L4 and local area of shock strut inner cylinder. E. Apply corrosion inhibiting compound (CIC, Mastinox 6856K or Cor Ban 27L) over mating surfaces of pivot pin adapter PN 47208-1, pivot pin (4-270), washer NAS1149C0416R and bolt NAS6304U4D. F. Insert bushing PN 47204-1 in pivot pin link PN 47206-3. Align pivot pin link with shock strut inner cylinder and install special bolt PN 47205-1 with washer NAS1149C0463R and nut MS14145L4 (Ref Figure 1). NOTE: Do not torque nut at this stage. G. Align pivot pin (4-270) with pivot pin link PN 47206-3 and pivot pin adapter PN 47208-1. With pivot pin and pivot pin link aligned insert pivot pin adapter (Ref. Figure 1). H. Install washer NAS1149C0416R on bolt NAS6304U4D and install at pivot pin link PN 47206-3 and pivot pin adapter PN 47208-1 and install washer NAS1149C0432R and nut MS14145L4 as shown (Ref. Figure 1). NOTE: Washer NAS1149C0463R may be used, as required, to achieve cotter pin alignment on nut MS14145L4 (Ref. Figure 1). NOTE: Make sure pivot pin (4-270) is fully inserted. CAUTION: ENSURE THAT SPECIAL BOLT PN 47205-1 IS POSITIONED SO THAT COTTER PIN WILL NOT CONTACT TRAILING ARM THROUGHOUT TRAILING ARM RANGE OF MOTION. CAUTION: ENSURE THAT SPECIAL BOLT PN 47205-1 CANNOT ROTATE FREELY. TORQUE REQUIRED TO ROTATE MUST BE GREATER THAN 10 LBF IN Tighten and torque nut MS14145L4 at two locations as shown (Ref. Figure 1). NOTE: Torque value quoted is in addition to run-on torque. NOTE: Torque nuts to the minimum value required, continue tightening nut to the nearest locking feature until it aligns with the cotter pin hole. If locking feature does not align with cotter pin hole before the maximum torque value is reached, back off nut to the nearest locking feature. J. Safety with cotter pin MS24665-153 at two locations (Ref Figure 1). K. Remove excess corrosion inhibiting compound with a clean cloth. L. Align WOW cover and install bolts (1-280 or 1A-270) and washers (1-290 or 1A-280) (Ref CMM 32-21-04 ASSEMBLY). 2. Re-identification NOTE: Numbers in parenthesis refer to CMM 32-21-04 IPL Figure-Item Number. A. Re-identify shock strut 47100-17 as 47100-19 on nameplate (1-15). 47100-32-96 R2 Mar 20/13 Page 3 of 5 Reference Goodrich CMM for proprietary information ### Page 11 (OCR) Goodrich Landing Gear Division Goodrich Aerospace Canada Ltd. B. For all other shock struts record incorporation of this Service Bulletin and date accomplished on nameplate (1-15). C. Re-identify dressed shock strut assembly 47200-25 with shock strut 47100-19 installed as 47200-27 on nameplate (4-10). D. For all other dressed shock strut assemblies record incorporation of this Service Bulletin and date accomplished on nameplate (4-10). DETAIL A SB47200-32-96-A01 ASSEMBLED Pivot Pin Retention - Redesigned Retention Mechanism Figure 1 (Sheet 1 of 2) 47100-32-96 R2 Mar 20/13 Page 4 of 5 Reference Goodrich CMM for proprietary information ### Page 12 (OCR) Goodrich Landing Gear Division Goodrich Aerospace Canada Ltd. SHOCK STRUT WOW COVER ASSEMBLY (1-300) (1A-280) BOLT WASHER (1-280) (1-290) (1A-270) (1A-280) WASHER NAS1149C0416R COTTER PIN BOLT 1 MS24665-153 NAS6304U4D PIVOT PIN 1 ADAPTER 47208-1 PIVOT PIN DO NOT REMOVE (REF) (4-270) NUT MS14145L4 1 COTTER PIN MS24665-153 WASHER NUT 3 NAS1149C0463R MS14145L4 WASHER NAS1149C0432R BUSHING OR 47204-1 NAS1149C0463R PIVOT PIN LINK DETAIL A 47206-3 NOTES BREAKDOWN SPECIAL BOLT 47205-1 /1 APPLY CORROSION INHIBITING COMPOUND TO MATING SURFACES. 2 TORQUE 20-30 LBF IN (2.3 - 3.4 Nm). /3 TORQUE 10-15 LBF IN (1,1 - 1,7 Nm). SB47200-32-96-B02 Pivot Pin Retention - Redesigned Retention Mechanism Figure 1 (Sheet 2 of 2) 47100-32-96 R2 Page 5 of 5 Mar 20/13 Reference Goodrich CMM for proprietary information --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.