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BOMBARDIER 

REPAIR DRAWING (RD) 

1 TITLE 2 RD NUMBER 

Procedure for MLG Alternate Extension System Cam Assembly (P/N 8/4-32-0160 

4851 0-1/-3) Free-play Inspection and Cam Assembly 

Overhaul 3 SECTION 4 SHEET 

1 

' 

1 

5 PRIME DESIGN ACTIVITY 6 ADDITIONAL LIMITATIONS 7 SERIES 8 APPLICABILITY 

BOMBARDIER INC., 

DOWNSVIEW 71867 Ref TC AD CF-2011-01 DHC-8-400 SIN All 

··-

9 DESCRIPTION 

THIS RD IS MANDATED BY TRANSPORT CANADA AD CF-2011-01 

"This RD affects compliance with AD CF-2011-0lRl, dated 20 May 2011. Canadian registered aircraft will require an AMOC 

approved by Transport Canada. Depending under which authority the aircraft is operated, an AMOC may still be required" "' 

Two operators have reported that, while performing a line check, they were unable to open the MLG 

doors in one nacelle using the MLG alternate extension system. During troubleshooting of the affected 

MLG doors, t he alternate extension cam assembly was found to be fractured, resulting in the inability 

to open the doors. 

The following RD provides instructions to perform a free-play inspection of the MLG alternate release 

cam assembly, PIN 48510-1/-3 to ensure full, unrestricted movement when using the MLG alternate 

release system. If sticking or binding is found, a procedure is provided to remove, and replace, or 

overhaul, and reinstall the cam assembly to ensure full, unrestricted movement. 

sheet 1 A issue 1 At Revision 3: The details of this procedure are covered by RDB/4-32-0160 section 1 - On sht 2, step 3 and 4 of 

sheet 1 issue -i2-5 procedure revised for clarity AT Revision 2: sheet 2 issue -i2:M 5 and NOTE removed 

- reference added to TC AD in Description sheet 3 issue -i2-4 - On sht 4, option to replace 

section and in Box 6 - Additional Limitations sheet 4 issue -iJ5 cam assembly added 

- Description revised to include replacement of sheet 5 issue 1 - On sht 7, illustration revised 

the cam assembly to define bushing wear 

sheet 6 issue 1 tolerance and add cam Follower - Step #6 on sheet 2 revised to allow sheet 7 issue -1- 2-3 tolerance 

replacement of the Cam Assembly sheet 8 issue -1-2-3 -On sht 8, Step 5 revised to - Reference to AMM Installation Task of Cam sheet 9 issue -1-2-3 add Shank straightness 

Assembly corrected on Sheet 3 and 11 sheet 1 0 issue 1 tolerance 

····-- sheet 11 issue -i 2o 3 - On sht 9, Surface Finish 

·--- Repairs 'Note' revised 

At Revision 4: On sht 2, NOTE added to not operate cam assembly using release cable - On sht 11 , item #4, ref. to a On sht 3, Illustration revised to show location to operate cam assembly 'new' bolt removed 

..... ·-··- 10 ISSUE 1 2 3 4 ---····· -· ····-··-·· I 

11 DATE 14 Jan, 2011 18 Jan, 2011 15 Feb, 2011 Sept 6, 2011 \ I 

12 PREPARED BY D.j e Vogel D. de Vogel D. de Vogel D. de Vogel \ I 

13 STRESS <''( / l.fl.lf;y .. .:. _AIT/""'""J II 9a~~!l~ FI ~Xs;,, ~?"' l:-t~f /ff \ ; ··-···-······· 

16 DESIGN AUTHORITY 'J;:/(;(;'f~ I:..Z.J..1i ttttlJJ/ I 'zfJ7 r)~/ j jj1;f:! ~~' -<.!~ :2.d;; ~ 1f.1/iil!~~fo~ ~ 'X 

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I ~ THE TECHNICAL CONTENT OF THIS DOCUMENT IS APPROVED UNDER THE 

18 DESIGN AU f HORI rY OF TRANSPORT CANADA DESIGN APPROVAL BA ENGINEERING DISPOSinON FOR APPROVAL BY OPERATOR'S 

ORGANIZATION DAO NO. 93·0.02 LOCAL AIRWORTHINESS AUTHORITY 

BOMBARD

THIS REPAIR DRAWING HAS BEEN PREPARED ON THE BASIS OF INFORMATION SUPPLIED TO THE INFORMATION. TECHNICAL DATA AND DESIGNS DISCLOSED HEREIN ARE THE EXCLUSIVE PROPERTY 

OPERATOR 

IER 

OR 

INC. 

H

BY THE OPERATOR OR HIS AGENT. IT IS THE RES?ONSIBILITY OF THE OF BOMBARDIER INC. OR CONTAIN PROPRIETARY RIGHTS OF OTHERS AND ARE NOT TO BE USED OR 

ACCURATE

IS AGENT TO VERIFY THAT THE INFORMAnON SUPPLIED IS COMPLETE AND DISCLOSED TO OTHERS WITHOUT THE WRITTEN CONSENT OF BOMBARDIER INC. THE RECIPIENT OF THIS 

CONSEQUENCE 

. BOMBARDIER 

RESULT

INC. DOES NOT ACCEPT RESPONSIBILITY FOR ANY DOCUMENT, BY ITS RErENTION AND USE AGREES TO HOLD IN CONFIDENCE THE TECHNICAL DATA AND 

DAMAGE 

ING FROM INCOMPLETE OR INACCURATE REPORnNG OF THE DESIGNS CONTAINED HEREIN. THE FOREGOING SHALL NOT APPLY TO PERSONS HAVING PROPRIETARY I DISCREPANCY. RIGHTS TO SUCH INFORMATION, TECHNICAL DATA OR SUCH DESIGNS TO THE EXTENT THAT SUCH RIGHTS EXIST. D.3J63.27 REV 1999-07 

BT0214-11 MW REV 2006-08 © Bombardier Inc. 
BOMBARDIER 

REPAIR DRAWING (RD) 

10 ISSUE 1 6 12 RD NUMBER 13 SECTION 4 SHEET 

1 8/4-32-0160 I 1 tA 

At Issue 5: 

• Sheet 1 revised to Issue 5 

0 On Sheet 1, Title block revised, PIN 4851 0-1 revised to 48510-1/-3 

0 On Sheet 1, Description revised to include the following under the AD Title: 

"This RD affects compliance with AD CF-2011-01 R1, dated 20 May 2011. Canadian 

registered aircraft will require an AMOC approved by Transport Canada. Depending under 

which authority the aircraft is operated, an AMOC may still be required" 

0 On Sheet 1, Description revised, paragraph 2 states "PIN 48510-1", revised to "48510-1/-3" 

• Sheet 2 revised to Issue 5 

0 On Sheet 2 Section A- procedure #6, part (b) revised to state "replace with another 

serviceable cam assembly, PIN 4851 0-1 I- 3 ". 

• Sheet 4 revised to Issue 5 

0 On Sheet 4 Option 1 revised to state, "Replace cam assembly P/N 48510-1 with a new or 

overhauled cam assembly P/N 48150-1, or a new cam assembly P/N 48150-3 and install per 

section C of this RD." 

0 NOTE added stating, "Cam assembly P/N 48510-3 to be replaced with a new or serviceable 

cam assembly P/N 48510-3". 

At Issue 6: 

0 On Sheet 1A, DAO Authority (block 17) signed off with incorrect date, RD revised to issue 6 

to correct "clerical error". 

10 RD ISSUE 5 6 " ···-·--- ----""' ________ .. f---...... --.... , ·····-···-··---·- -................... --- - ---·-·.··-······-- 11 DATE June 6, 2012 Juue 27, 2012 

12 PREPARED BY D. de Voge:_L D. de Voge_L .I 

~~-~ 12-2~ -··· 

13 STRESS 

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I /1{-D '7.- 'If ,...7'5 ~:- ~.{_. f---- --·······-~~ 16 DESIGN AUTHORITY _ ' ~? ' ,? ;.. I> .. 

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14 v "'-··· 1--- 15 

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17 DAO AUTHORITY ":Jv,:o.k 26 II ~"" 'Z.C'>\ "Z.. 

A. "- L..1m...C~ • Jl. • (,. • t,;.J\.LuM 

THE TECHNICAL CON I ENT OF THIS DOCUMENT IS APPROVED UNDER THE 18 DESIGN AUTHORITY OF TRANSPOR r CANADA DESIGN APPROVAL BA ENGINEERING DISPOSITION FOR APPROVAL BY OPERATOR'S 

ORGAN13ATION DAO NO .. 93-0.{)2 LOCAL AIRWORTHINESS AUTHORITY 

THIS REPAIR DRAWING HAS BEEN PREPARED ON THE BASIS OF INFORMATION SUPPLIED TO THE INFORMATION, TECHNICAL DATA AND DESIGNS DISCLOSED HE,qEIN ARE THE EXCLUSIVE PROPERTY BOMBARDIER INC .. BY THE OPERATOR OR HIS AGENT. IT IS THE RESPONSIBILITY OF THE OF BOMBARDIER INC .. OR CONTAIN PROPRIETARY RIGHTS OF OTHERS AND ... RE NOT TO BE USED OR OPERATOR OR HIS AGENT TO VERIFY THAl Tl1E INFORMATION SUPPLIED IS COMPLETE AND DISCLOSED 10 OTHERS WITHOU1 THE WRITTEN CONSENT OF BOMBARDIER INC .. 1HE RECIPIENT OF THIS ACCURATE .. BOMBARDIER INC. DOES NOT ACCEPT RESPONSIBILITY FOR ANY DOCUMENT, BY ITS RETENTION AND USE AGREES TO HOLD IN CONFIDENCE THE TECHNICAL DATA AND CONSEQUENCE RESULTING FROM INCOMPLETE DR INACCURATE REPORTING OF THE DESIGNS CONTAINED HEREIN .. THE FOREGOING SHALL NOT APPLY TO PERSONS HAVING PROPRIETARY DAMAGE I DISCREPANCY .. RIGHTS TO SUCH INFORMATION, TECHNICAL DATA OR SUCH DESIGNS TO THE EXTENT THAT SUCH RIGHTS EXIST D 3363-27 REV 1999-07 

BT0214-13 MW REV 2006-08 
BOMBARDIER REPAIR DRAWING (RD) 

10 ISSUE 1 2 3 I 4 2 RD NUMBER 3 SECTION 4 SHEET 

5 8/4-32-0160 1 2 

A) Procedure for Operational check of Alternate Release Cam Assembly for Freedom of Movement: 

1. 

2. 

01 3. 

01 

01 4. 

5. 

01 6. 

91 

Open and lock the MLG doors (ref AMM TASK 32-00-00-840-801). Ensure that lock pins are 

installed in each Main Landing Gear and the Nose Landing Gear down lock is engaged. 

Gain access to the alternate extension system 

In each nacelle, manually operate the cam assembly by rotating the input lever to the fully 

deployed position as shown in Fig 2. 

NOTE: Do not operate cam assembly by pulling on the alternate release cable, this can result 

in a bent cable end at the turnbuckle assembly 

Release the input lever and ensure the cam assembly moves smoothly without any binding or 

resistance to its fuly rested position as shown in Fig 1. 

If cam movement is full and unrestricted, no further action is required. 

If any binding or sticking is observed in the cam assembly when returning it to its full rested 

position, remove the cam assembly from the nacelle (ref AMM TASK 32-34-26-000-801 )and 

either (a) proceed to part B of this RD for instructions to dis-assemble, inspect, clean and reassemble the cam assembly P/N 48510-1, or (b) replace with another servicable cam assembly 

PN 48150-1/-3. Subsequent to performing 6(a) or 6(b) proceed to part C of this RD for 

installation instructions. 

Input Lever Input Lever 

Figure 1 Figure 2 

BT0214-13 MW REV 2006-08 
BOMBARDIER 

10 ISSUE 

lEGEND 

TO 

I... PLOCK 

ASSY 

Cam m~an sm assemb J. 

2.Cable . 

3. Loc:ldng clip. 

4. Turnbuckle. 

5 Cable. 

6. lodting dip. 

7. Turnbuckle. 

8 .. Caol~. 

9. Lcdcing clip. 

1 0. Turnbuckle. 

BT0:214-13 MW REV 2000-08 

Figure 3 

REPAIR DRAWING (RD) 

3 SECTION 4 SHEET 

8/4--32-0160 1 3 

Operate cam assembly at this location by f:\

pulling lever in the forward direction \.J 4 

1 

I 

Ref: AMM TASK 32-34-26-000-801 

Removal of the MLG AlternateExtension-Cam Assembly 

Ref: AMM TASK 32-34-26-400-801 

Installation of the MLG AlternateExtension-Cam Assembly 

Ref: AMM TASK 32-34-16-830-802 

Rigging of the Alternate Extension 

MLG Cables 
0 

BOMBARDIER REPAIR DRAWING (RD) 

10 ISSUE I 1 3 5 2 RD NUMBER 3 SECTION 4 SHEET 

I 8/4- -32-0160 1 4 

B) Repair/replacement' Procedure for Alternate Extension System Cam Assembly: 

Option 1: Replace cam assembly P/N 48510-1 with a new or overhauled cam assembly P/N 48150-1, 

or a new cam assembly P/N 48150-3 and install per section C of this RD. 

NOTE: Cam assembly P/N 48510-3 to be replaced with a new or serviceable cam assembly PIN 48510-3. 

Option 2: Overhaul cam assembly P/N 48510-1 and install per section C of this RD 

The following procedure can be used to disassemble, clean, inspect and re-assemble the 48510-1 cam 

assembly. Please note that the cleaning solutions called out in this procedure are recommended by 

Goodrich. If deviations, or equivalent solutions are required, contact the Bombardier Technical Help 

Desk. 

FWD 

Figure 1 - Cam Assembly 

BT0214-13 MW REV 2006-08 
BOMBARDIER REPAIR DRAWING (RD) 

10 ISSUE 1 2 RD NUMBER 3 SECTION 4 SHEET 

Disassembly 

8/4-32-0160 

J.J\ A-A 

Figure 2: Section A-A 

I 

I 

\ 

r 

.J 

1 

1. Remove cotter pins from 2 x MS14144L4 Nuts and NAS6604D36 bolts and discard 2 x 

MS24665-153 cotter pins. 

5 

2. Disassemble as required to remove 2 x NAS6604D36 bolts. Discard MS14144L4 nuts, and 

retain 4 x NAS1149F0463P washers. 

3. Remove and retain Tie Plate P/N 48515-1, and 2 x CSP192-131 washers 

4. Remove Cam lever assembly P/N 48512-1 from assembly. 

5. Remove lever assembly PIN 48514-1 from assembly. 

6. Remove 2 x shafts P/N 48513-1 from assembly, and retain 2 x MS200002C8 washers, 2 x CSP 

192-120 washers. and 48511-1 mounting plate. 

BT0214-13 t.WV REV 2006-QS 
BOMBARDIER REPAIR DRAWING (RD) 

10 ISSUE l 2 RDNUMBER 3 SECTION 4 SHEET 

8/4-32-0160 1 6 

Cleaning 

1. Clean the 48512-1 & 48514-1 lever assemblies using Isopropyl Alcohol to remove any/all 

dirt/F.O.D from parts. Ensure the bushings inside diameters are also cleaned using a rag and 

Isopropyl Alcohol, TT-1-735. 

Note: Ultrasonic cleaning of these assemblies is an acceptable alternative. 

2. Clean the 48511-1 Mounting Plate, 48515-1 Tie Plate, and 48513-1 Shafts using any of the 

following solvents to remove any/all dirt/F.O.D from the parts; 

·- NOMENCLATURE SPECIFICATION/PRODUCT 

Cleaning Solvents- (General Purpose) MIL-PRF-680 

MIL-T-81533 

Cleaning Solvents - (Final, for use prior to Acetone, ASTM-0-329 

painting, plating, sealing) DS-108F (V1MFE1) 

Isopropyl Alcohol, TT-1-735* 

Methyl-ethyl-ketone, ASTM-0-7 40 

• Do not use on aluminum alloys 

Cloth, Lint Free Commercially Available 

I Corrosion Preventative Fingerprint Remover MIL-C-15074 

WARNING; USE CLEANING SOLVENT IN A WELL VENTILATED AREA. AVOID 

PROLONGED INHALATION OF FUMES AND SOLVENT CONTACT WITH 

SKIN. OBSERVE FIRE PRECAUTIONS. 

A . Clean all components by washing with cleaning solvent. Dry components using a lint free 

cloth. 

BT021 4-13 MW REV 2006-08 
BOMBARDIER 

REPAIR DRAWING (RD) 

10 ISSUE 1 3 2 RD NUMBER 3 SECTION 4 SHEET 

8/4-32-0160 1 7 

Inspection 

The following provides dimensions for inspection prior to return to service. The grey boxes provide inservice wear limits for tile noted dimensions. If dimensions fall outside of the specified limits, and 

cannot be rectified in accordance with the General Repair guidelines on sheet 9 of this Repair Drawing, 

contact the Bombardier Technical Help Desk. 

1. Inspect the following dimensions for the 48512-1 cam lever assembly; 

a. Ensure no damage to cam follower profile 

0.196 max In Service Wenr 

Diameter 

Cam Follower Profile: 

0.50110.505 inch width. 

0.515 inch max. allowable 

in service profile \\oidth 

: g~i-~~-~ 0.090 min In Service Wear Thickness 

2. Inspect the following dimensions for the 48514-1 lever assembly; 

0.081 min - 089 _ -083 

BT0214-13 MW REV 2006-08 

0 .1 5).4 

0 ,190 

O .S01S 

0 .150015 

+ 

0.196 max Wear Tolerance 

0.5035 max In Service Bushing Wear Tolerance 
BOMBARDIER 

10 ISSUE 1 3 2 RDNUMBER 

8/4-32-0160 

3. Inspect the following dimensions for the 48513-1 shafts; 

k' • [ 0.2660 max 

4. Inspect the following dimensions for the 48511-1 mounting plate; 

- --------Jr. 

• 

4X 0. 194 ~~ . 190 0.196 max 

2x e;· 7505J 

. 7495 

REPAIR DRAWING (RD) 

3 SECTION 4 SHEET 

1 8 

A---- I 0

'

7

SZOmu I SECT I ON A-A 

5. Inspect the 2 x NAS6604D36 bolts for evidence of corrosion or cadmium coating degradation. 

Also ensure the shank outside diameter meets the correct dimension and that the shank is 

straight. 

a) Diameter: 0.2485/0.2495 inch 

b) Straightness: 0.003 inch per inch of length (Full Dial Indicator Movement) 

NOTE: Discard those bolts which have exceeded the wear limits and replace with new ones 

6. Ensure the Cam Follower P/N NAS562-3R03G installed on Lever Assembly P/N 48514-1 rotates 

freely with no evidence of binding. 

7. Note any areas of removed finishes (primer/paint) and reapply per section 2 of General repair. 

BT0214-13 MW REV 2006-08 
BOMBARDIER 

REPAIR DRAWING (RO) 

10 ISSUE 1 3 2 RD NUMBER 3 SECTION 4 SHEET 

8/4-32-0160 1 9 

General Repair 

1. Bushing Removal & Replacement (Ref. P/N 48512-1 & 48514-1) 

a. Remove out of tolerance bushings using a press and discard 

b. Inspect lever arm bores for size (0.6255/0.6260 dia) and ensure no evidence of corrosion 

or damage. 

i. If bore is damaged machine 0/S to 0.6355/0.6360 dia 

ii. Liquid Penetrant Inspect reworked areas per ASTM E-1417, Type I, Sensitivity 

level3. Defects not to exceed MIL-STD- 1907, Grade 'A' limits 

iii. Locally protect reworked areas using Alodine Solution No. 1200 per MIL-DTL5541 

c. Install new bushings P/N M81934/2-08A012, QTY(2) per lever arm; 

Note: 0.010 0/S bushings reference P/N M81934/2-08A012T 

i. Immerse in dry ice for a minimum of 20 minutes 

ii. Coat the bore inside diameter with MASTlNOX 6856K 

iii. Install bearing into bore using appropriate tooling. 

2. Surface Finish Repairs 

Note: repair of Scratches, nicks, Pitting AND Corrosion in the cam follower slot on lever P/N 48512-

1 is prohibited 

Note: Lever 48512-1 & 48514-1 are hard anodized. As described below, local repair is permitted 

using Alodine on blended areas or areas of worn coating, except in the cam slot on lever P/N 48512-

1, as noted above. 

CAUTION: THE ANODIZE LAYER ON ALUMINUM WILL BE DAMAGED IF SAND IS 

USED IN THE ABRASIVE BLAST PROCEDURE OR IF A WIRE BRUSH IS 

USED FOR CLEANING. 

(1) Remove scratches, nicks, pitting or corrosion by polishing lightly with 220 - grit or 

finer aluminum oxide cloth. Surface finish to be compatible with that of the 

surrounding surface. Refinish reworked areas as required for protection against 

corrosion. 

NOTE: On non-wear surfaces the defects to be polished out must not exceed 0.005 

inch and for wear surfaces defects must not exceed 0.0005 inch. 

(2) Clean minor defects in threads using a fine file or an appropriate thread chase. 

(3) Refinish reworked aluminum parts as required for protection against corrosion 

using AIOdine® or equivalent per MIL-DTL-5541. 

BT0214-13 MW REV 2006-08 
BOMBARDIER 

REPAIR DRAWING (RD) 

10 ISSUE 1 2 RD NUMBER 3 SECTION 4 SHEET 

8/4-32-0160 l 10 

(4) Liquid Penetrant Inspect reworked areas per ASTM E-1417, Type I, Sensitivity level 3. 

Defects not to exceed MIL-STD- 1907, Grade 'A' limits 

(5} Locally protect reworked areas using Alodine Solution No. 1200 per MIL-DTL-5541 

(6) Apply a coat of impact resistant epoxy polyamide primer per MIL-PRF-23377. Application 

per MIL-F-18264 

Re-assembly 

1. Install (press fit by hand) 2 x 48513-1 Shafts into 48511-1 mounting plate (Ref. figure 4). 

2. Install 2 x MS200002C8 washers onto 2 x 48513-1 Shafts, with the counter sink side of the 

washer facing the head of the shaft (Ref. Figure 4). 

SECTION A-A 

Figure 4. 

3. Instal! 48512-1 and 48514-1 levers onto shafts (Ref. Figure 5). 

BT0214·13 MW REV 2006-08 
BOMBARDIER REPAIR DRAWING (RD) 

10 ISSUE 1 2 3 

A 

2 RD NUMBER 3 SECTION 

Figure 5 

8/4-32-0160 

L; li<S l 4 l 

co~r -·····I..F:Vf":R nSSY 

f I 

; i 

\ 

1 

4. lnstall2 x CSP 192-120 washers onto NAS6604D36 bolts (QTY 2 required). 

5. lnstall2 x NAS6604D36 bolts into both 48513-1 shafts (ref. Figure 4 for orientation) 

4 SHEET 

11 

6. lnstall2 x CSP192-131 washers (Ref. Figure 4) and Tie Plate 48515-1, onto protruding ends of 

NAS6604D36 bolts. 

7. Install 4 x NAS1149F0463P washers (Maximum 2 washers may be used under nut to facilitate 

installation of cotter pin), 2 x new MS 14144L4 nuts. 

a. Thinly coat NAS6604D36 bolt threads with grease and Torque nuts 20-40 in-lbs (wet). 

8. Install 2 x new MS24665-153 cotter pins. 

9. Inspect- ensure operation of assembly is smooth and free of binding through out its full range of 

travel. 

7. Following completion of part B, proceed to part C of the RD. 

C) Procedure for Installation of Cam Assembly on Aircraft 

1. Re-install the cam assembly into the aircraft (ref AMM TASK 32-34-26-400-801 ). 

2. Following the rigging of the alternate extension system per AMM TASK 32-34-16-830-802, an 

operational test of the landing gear system as referenced in the Close Out (ref Sub TASK 

32-34-16-710-002) is not required. 

BT0214-13 MW REV 2006-08