I 

I 

de HAVIllAND 

BOMBARDIER DASH[J 

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: 

Production: 

DHC-8 Aircraft Models 401 and 402 Serial Numbers 4001, 

4003 thru 4435. 

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 

Revision 'A' 08 Apr 2013 

S.B. 84-32-110 

Page 1 of 6 

NB 
I 

I 

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 

Revision 'A' 08 Apr 2013 

S.B. 84-32-110 

Page 2 of 6 

NB 
I 

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. 

I 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 (OTis). 

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 I 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 

Revision 'A' 08 Apr 2013 

S.B. 84-32-11 0 

Page 3 of 6 

NB 
SERVICE BULLETIN 84-32-110 

I. Weight and Balance 

A/C Type and Weight (Lb) Arm (Inches) 

Model 

DHC-8 Model 401 +0.10 -119.92 

DHC-8 Model 402 +0.10 -119.92 

Refer to enclosed Goodrich Service Bulletin 47100-32-96. 

J. Electrical Load Data 

Not affected 

K. Publications Affected 

Moment 

(Inches x Lb) 

X 0.001 

-0.01 

-0.01 

Maintenance Manual ................................ PSM 1-84-2 

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

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

L. References 

1 Revision 'A' of this service bulletin was prepared to the engineering drawings and 

related data that follows: 

ModSum 4N113749 Rev. 'J' 

ModSum 40113749 Rev. 'C' 

ModSum 4-113749 Rev. 'F' 

PCA 43508 Revision 2 (for internal reference only) 

I Goodrich Service Bulletin 47100-32-96 R2 dated Mar 20/13 

Transport Canada Airworthiness Directive Pending 

21 Dec 2012 

Revision 'A' 08 Apr 2013 

S.B. 84-32-110 

Page 4 of 6 

NB 
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 NLG. 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 

Revision 'A' 08 Apr 2013 

S.B. 84-32-110 

Page 5 of 6 

NB 
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. 

I (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 

Revision 'A' 08 Apr 2013 

S.B. 84-32-110 

Page 6 of 6 

NB 
--------:::::=- ~-­

GOODRICH 

SERVICE BULLETIN 

DASH 8 0400 

NLG SHOCK STRUT- PIVOT PIN RETENTION- REDESIGNED RETENTION 

MECHANISM AND INTRODUCTION OF NEW CONFIGURATION (47100-19) 

REVISION N0.2 - 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. 

The compliance in the previous issue of this Service Bulletin is not affected by this revision . 

No additional rework is introduced by this revision. 

Please destroy all copies of SB 47100-32-96 R1 dated Jan 14/13. 

Page/Para 

Page 4, Paragraph 2.C. 

Change 

Instructions for re-identification of dressed shock strut 

assembly clarified. 

47100-32-96 R2 HIGHLIGHTS 

Mar 20/13 

Page 1 of 1 

THESE COMMODITIES, SOFlWARE OR TECHNOLOGY WERE EXPORTED/RE-EXPORTED IN ACCORDANCE WITH U.S. EXPORT 

ADMINISTRATION REGULATION. DIVERSION CONTRARY TO U.S. LAW IS PROHIBITED. 
GOODRICH 

SERVICE BULLETIN 

DASH 8 0400 

NLG SHOCK STRUT- PIVOT PIN RETENTION- REDESIGNED RETENTION 

MECHANISM AND INTRODUCTION OF NEW CONFIGURATION (47100-19) 

SECTION 1- 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/NAS6304U 120 approximately -0.02 pounds 

10. ELECTRICAL LOAD DATA 

NA 

11. REFERENCES 

Goodrich Landing Gear Component Maintenance Manual32-21 -04 

Bombardier Aerospace (BA) Aircraft Maintenance Manual (AMM) PSM 1-84-2 

47100-32-96 R2 Mar 20/13 

Page 1 of 5 

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 
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 1 Repair Kit, NLG 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 

NAS 1149C0463R 2 Washer 

NAS6304U4D 1 Bolt 

Bolt NAS6304U12D 1 Discard 

OR 

Bolt NAS6204-12D 1 Discard 

SECTION Ill- 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 NLG 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 Reference Goodrich CMM for proprietary information 

Mar 20/13 

Page 2 of 5 
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. 

I. Tighten and torque nut MS 14145L4 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 Reference Goodrich CMM for proprietary infonnation 

Mar 20/13 

Page 3 of 5 
I 

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 (4-1 0). 

D. For all other dressed shock strut assemblies record incorporation of this Service Bulletin 

and date accomplished on nameplate (4-10). 

SB4720D-32·96-A01 

DETAIL A 

ASSEMBLED 

Pivot Pin Retention - Redesigned Retention Mechanism 

Figure 1 (Sheet 1 of 2) 

47100-32-96 R2 Reference Goodrich CMM for proprietary information 

Mar 20/13 

Page 4 of 5 
NUT 

MS14145L4 

A\h\ 

Goodrich Landing Gear Division 

Goodrich Aerospace Canada Ltd. 

WASHER 

WOW COVER 

(1-300) 

(1A-280) 

SHOCK STRUT 

ASSEMBLY 

WASHER 

NAS 1149C0416R 

BOLTffi 

NAS6304U4D 

~/ PIVOT PIN 

DO NOT REMOVE 

(REF) 

(4-270) 

WASHER 

NAS 1149C0463R 

WASHER 

NAS1149C0432R BUSHING 

OR 47204-1 

NAS 1149C0463R ill 

PIVOT PIN LINK 

47206-3 ill 

SPECIAL BOLT 

47205-1 

ffiAPPLY CORROSION INHIBITING COMPOUND TO MATING SURFACES. 

NOTES 

DETAIL A 

BREAKDOWN 

& TORQUE 20-30 LBF IN (2.3 - 3.4 Nm). 

&. 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 Reference Goodrich CM M for proprietary infonnation 

Mar 20/13 

Page 5 of 5