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# 01 01 BOMBARDI ER REPAIR DRAWING (RD) 1 TITLE 2 RD NUMBER 

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

### 4851 0-1/-3) Free-play Inspection and Cam Assembly Overh au l 3 SECTION 4 SHEET 

### 1 ' 

### 1 5 PRIME DESIGN ACTIVITY 6 ADDITIONAL LIMITATIONS 7 SERIES 8 APPLICABILITY

BO M BARD I E R I NC ., 

### Ref TC AD CF-2011 -01 DHC-8-400 

### SIN All DOW NSVI EW 71867

··-

9 DESCRIPTIONTH IS RD IS MA NDA TE D BY TRAN S PORT CANADA AD CF-20 1 1 -01 "This RD affects compliance with AD CF-2011 -0lRl, dated 20 May 2011 . Canadian registe red 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 al t ernate ext ension cam assembly was found to be fractured, resulting i n the inabil i ty to open the doors. The following RD provides instructions to perfo rm a free -play inspecti on 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 assemb ly 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 iss ue 

### -i2:M 5 and NOTE removed

- reference added to TC AD in Desc ription sheet 

### 3 issue 

### -i2-4 - On sht 4, opti on to replace section and in Box 6 - Additional Limitations sheet 

### 4 issue 

### -iJ5 cam assembly added

- Description revised to include replacement of sheet 

### 5 issu e 1 - On sht 7, il l ustration revised to defi ne bushing wear the cam assembly sheet 6 issue 

### 1 tolera nce and add cam Follower 

## - Step #6 on sheet 2 revised to allow sheet 7 issue 

### -1- 2-3 tol erance 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 

### 10 issue 1 tolerance

····-- 

### sheet 11 

### issue -i 

### 2o 3 - On sht 9 , Surface Finish Repairs ' N ote ' 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, Illustrati on revi sed to show locati on to operat e cam assembly ' new ' bolt remo ved

..... ·-··- 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 Vog el D. de Vogel 

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# A." . **u~n-~. lt·C...~**  THE TECHNICAL CONTENT OF THIS DOCUMENT IS APPROVED UNDER THE BA ENGINEER I N G DISPOSinON FOR APPROVAL BY OPERA TOR'S 1 8 DESIGN AU f HORI rY OF TRANSPORT CANADA DES I GN APPROVAL ORGANIZAT ION DAO NO . 93 · 0.02 LOCAL AIRWORTHINESS AUTHORITY THIS REPA IR DRAW ING HAS BEEN PREPA RED ON T HE BASIS OF INFORMATION SUPPLIED TO THE INFORMATION . TECHNICAL DA TA AND DE SIGN S D ISC LOS E D HERE I N AR E T HE EXCLUS IV E PROPERTY BOMBARD I ER I NC. BY THE OPERATOR OR HIS AGEN T. IT IS THE RES?ONS I BILITY OF T HE OF BO M BARD I ER INC . OR CONTA I N PROPRIETARY RIGHTS OF OTHERS AND ARE NOT TO BE USED OR OPERATOR OR HIS AGENT TO VERIFY THAT THE I NFORMAnON SUPPLIED IS COMPLETE AND DI SCLOS ED TO OTH ERS WITHOUT TH E WRITTEN CONSENT OF BOMBARDIER INC. THE RECIPIENT OF THIS ACC URATE . BOMBARDIER INC . DOES NOT ACCEPT RESPONSIBILITY FOR AN Y DOCUMENT, BY ITS RErENTION AND U SE AGREES TO HO LD I N CONF I DENCE THE TECHNICAL DATA AND CON SEQUENCE RESULTI NG FROM INCOMPLETE OR INACCURATE REPORnNG OF THE DES IGNS CONTAINED HERE I N. THE FO REGOING SHALL NOT APPLY TO PERSONS HAVING PROPRIETARY DAMAGE I DISCREPAN CY . RIGHTS TO SUCH INFORMATION , TECH N ICAL DATA OR SUCH DESIGNS TO THE EXTENT THAT SUCH RIGHTS EXIST . D.3J63.27 REV 1 999-0 7 BT0214-11 MW REV 2006-08 © Bom bard ier 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", revi sed 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 PREPAR E D BY D. de Voge:_L D. de Voge_L .I



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**L..1m...C~** • Jl. •(,. •t,;.J\.LuM THE TECHNICAL CON I ENT OF THIS DOCUMENT IS APPROVED UNDER THE BA ENGINEERING DISPOSI TION FOR APPROVAL BY OPERATOR ' S 18 DESIGN AUTHORITY OF TRANSPOR r CANADA DESIGN APPROVAL ORGAN13ATION DAO NO.. 93-0.{)2 LOCAL AIRWORTHINESS AUTHORITY TH IS REPAIR DRAWING HAS BEE N PREPARED ON THE BASIS OF IN FORMATIO N SU PP LIED TO THE INFORMATION, TECHNICAL DATA AND DESIGNS DISCLOSED HE , qEIN ARE THE EXCLUSIVE PROPERTY BOM B ARDI ER INC.. BY THE OPERA TOR OR H IS AG ENT. IT IS THE RESPONS I BILITY OF TH E OF BOMBARD IER INC.. OR CONTAIN PROPRIETARY RIGHTS OF OTHERS AND ... RE NOT TO BE USED OR OPERATO R OR HIS AG E NT TO VE RI FY THAl Tl1E IN FORMATION SU PPLI ED IS COMPL ETE AND DISCLOSED 1 0 OTHERS WITHOU1 THE WRITTEN CONSENT OF BOMBARDIER INC.. 1HE REC I PIENT OF THIS ACCU RATE.. BOM BAR DIER INC . DOE S NOT ACC EPT RES PONSI BILITY FO R ANY DOCUMENT, BY ITS RETENTI ON AND USE AGREES TO HOLD IN CONFIDENCE THE TECHNICAL DATA AND CONSEQUENCE RES U LT ING FRO M INCOMPLETE D R I NACC U RATE RE P O RTI NG 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 cl i p . 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:\ 4 

### pulling lever in the forward direction 

# \.J

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 Mounti ng Plate , 48515- 1 Tie Plate, and 48513-1 Shafts using any of the fol lowing solvents to remove any/all dirt/F .O.D from the parts;



## ·- NOMENCLATURE SPECIFICATION/PRODUCT Cleaning Solvents- (Ge n eral Purpose) MIL-PRF-680 MI L-T-81533 Clean ing Solvents - (Final, for use prior to Acetone, ASTM-0-329 painting , plating , sealing) DS-108 F (V1MFE1) Isopropyl Alcohol, TT-1-735* Methyl -ethyl-ketone , ASTM-0-740 • 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 wi t h cleaning solvent . Dry components using a l i nt 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

2

## x 

## e;· 7505J

. 7495 

### REPAIR DRAWING (RD) 3 SECTION 4 SHEET 

### 1 8



## A---- 

# I 0'7SZOmu 

# 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 polyamid e 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! 485 12-1 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