SB 670BA ---32---040

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Nov 13/2014

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

SERVICE BULLETIN 670BA ---32 ---040

SUBJECT: Landing Gear --- Main Landing Gear (MLG) and Doors --- Increase the

Clearances Between the MLG Fairing and MLG Doors

This page transmits:

Revision E of Service Bulletin 670BA --- 32 --- 040, dated Nov 13/2014

and

Revision A of Appendix A, dated Jul 02/2014 and Revison B of Appendix B,

dated Jul 02/2014.

The changes in this revision have no effect on aircraft that have

had this service bulletin incorporated.

Reason:

Revised Planning Information, paragraph 1., to:

Add some references in PART C and PART D.

Revised Accomplishment Instructions, paragraph 2., to:

Add some steps in Part C and Part D.

Change an illustration.

Revised Material Information, paragraph 3., to:

Add two notes.

This revision includes small editorial changes that do not have an effect on the

technical content.

Instructions:

Discard the copy of Service Bulletin 670BA --- 32 --- 040, Revision D, dated Jul 02 /2014.

Replace with the copy attached.
SB 670BA ---32---040

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Nov 13/2014

Service Bulletin History:

Initial issue, dated Oct 12/2012.

Revision A, dated Mar 13/2013.

Revision B, dated Aug 6/2013.

Revision C, dated Nov 01/2013.

Revision D, dated Jul 02/2014.

1 A
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SERVICE BULLETIN

Technical

Publications

THIS SERVICE BULLETIN IS SENT TO EACH OPERATOR. IF THE OPERATOR HAS LEASED AIRCRAFT,

TRANSFERRED SPARES IN THE LAST SIX MONTHS, SEND THIS SERVICE BULLETIN TO THE NEW

OWNER, UNLESS CONFIRMATION WAS RECEIVED THAT BOMBARDIER COMMERCIAL AIRCRAFT

HAS INCLUDED THE NEW OPERATOR ON THE DISTRIBUTION LIST.

SEND THIS SERVICE BULLETIN TO THE LESSEE. IF THE OPERATOR HAS SOLD AIRCRAFT OR

ATA SYSTEM: 32-10 NUMBER: 670BA-32-040

SUBJECT: Landing Gear --- Main Landing Gear (MLG) and Doors --- Increase the

Clearances Between the MLG Fairing and the MLG Doors

1. PLANNING INFORMATION

A. Effectivity

(1) Aircraft Affected:

AIRCRAFT MODEL SERVICE AIRCRAFT

SERIAL NUMBERS

PRODUCTION

AIRCRAFT SERIAL

NUMBERS

CL-600-2C10 10002 Thru 10333 10334 and subsequent

serial numbers [1]

CL-600-2D15 and

CL-600-2D24

15001 Thru 15284 15285 and subsequent

serial numbers [1]

[1] Aircraft will have this change incorporated before delivery.

NOTE: The instructions in this service bulletin are only applicable to the systems

and parts installed at the time of delivery of the aircraft or as changed

by Bombardier Service Bulletins. Before you do this service bulletin,

examine all Supplemental Type Certificates (STCs), Supplemental

Type Approvals (STAs), or equivalent action changes to make sure you

can complete this service bulletin.

NOTE: The procedure in this service bulletin was validated on aircraft serial number

15272.
SERVICE BULLETIN 670BA---32---040

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B. Reason

(1) Condition

During the retraction phase of the landing gears, the left and/or the right

(MLG) inboard door can travel past the internal metallic stiffener in the forward

rubber seal of the MLG fairing. If this occurs, it is possible for the MLG

inboard doors to get caught in the MLG fairing and prevent the full extension

of the MLG.

(2) Evidence

Two landings with one main landing gear-up occurred in service.

(3) Objective/Benefit

This service bulletin gives the procedure to make changes to the MLG

inboard doors, the MLG fairing and the adjacent structure of the MLG doors.

This service bulletin also gives the procedure to do the adjustment of the MLG

doors.

The incorporation of this service bulletin will increase the clearances between

the fairing and the doors of the MLG. This will prevent the MLG doors from

getting caught in the MLG fairing during the extension of the landing gears.

C. Description

This service bulletin is divided into four parts: PART A, PART B, PART C, and

PART D.

PART A --- Increase of the Clearance Between the Left MLG Inboard-Door and

the MLG Fairing

Circuit breakers are opened. The aircraft is put on jacks. The MLG door

hinge-fairing is removed. A detailed visual inspection of the MLG inboard doors, the

MLG fairing and the MLG inboard-door adjacent structure is done. The diameter of

two holes in the aft member, that hold the roller, are increased. The bushing and the

roller are installed. The clearance between the inboard MLG door and the aft

attachment of the outboard MLG door is corrected. A clearance check of the MLG

door is done.

The aft stop-fitting, the seal and the seal retainer are removed. The aft stop-fitting is

cut and the stop pad is relocated. The aft stop-fitting is installed. The aft seal of the

MLG door is replaced. The clearance between the MLG fairing and the MLG

inboard and outboard doors is done. The forward seal is replaced. The seal

retainer is cut and installed. The safety guide is installed with the forward seal and

the seal retainer. The nameplate of the MLG door is installed.

The lockpins are removed from the MLG. The circuit breakers are closed. The

clearance check of the MLG inboard doors is done. The MLG door hinge-fairing is

installed. The lockpins are installed in the MLG. The aircraft is lowered.
SERVICE BULLETIN 670BA---32---040

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PART B --- Increase of the Clearance Between the Right MLG Inboard-Door

and the MLG Fairing

Circuit breakers are opened. The aircraft is put on jacks. The MLG door

hinge-fairing is removed. A detailed visual inspection of the MLG inboard doors, the

MLG fairing and the MLG inboard-door adjacent structure is done. Two holes in the

aft member, that hold the roller, are increased. The bushing and the roller are

installed. The clearance between the inboard MLG door and the aft attachment of

the outboard MLG door is corrected. A clearance check of the MLG door is done.

The aft stop-fitting, the seal and the seal retainer are removed. The aft stop-fitting is

cut and the stop pad is relocated. The aft stop-fitting is installed. The aft seal of the

MLG door is replaced. The clearance between the MLG fairing and the MLG

inboard and outboard doors is done. The forward seal is replaced. The seal

retainer is cut and installed. The safety guide is installed with the forward seal and

the seal retainer. The nameplate of the MLG door is installed.

The lockpins are removed from the MLG. The circuit breakers are closed. The

clearance check of the MLG inboard doors is done. The MLG door hinge-fairing is

installed. The lockpins are installed in the MLG. The aircraft is lowered.

For Aircraft that Install Inboard MLG Door Part Number CC670-10520-15 and/or

CC670-10520-16

PART C --- Installation of the Inboard MLG Door Part Number CC670-10520-15

and Increase of the Clearance Between the Left MLG Inboard-Door and the

MLG Fairing

For all aircraft

Circuit breakers are opened. The aircraft is put on jacks. A detailed visual

inspection of the MLG fairing is done. If installed the left inboard MLG door is

removed.

For Aircraft 10002 thru 10217, 15002 thru 15043 and 15991

In Service (IS) Modification Summary IS670528200033 is done

For all aircraft

The left inboard MLG door is installed. The clearance between the inboard MLG

door and the aft attachment of the outboard MLG door is adjusted. A clearance

check of the inboard MLG door and the outboard MLG door is done.The aft

stop-fitting, the seal, and the seal retainer are removed. The aft stop-fitting is cut

and the stop pad is relocated. The aft stop-fitting is installed. The material between

the MLG fairing and the inboard MLG door and outboard MLG door is removed.

The forward seal is replaced. The seal retainer is cut and installed. The safety guide

is installed with the forward seal and the seal retainer.The lockpins are removed

from the MLG. The circuit breakers are closed. The clearance check of the inboard

MLG door and outboard MLG door is done. The MLG door hinge-fairing is

installed. The lockpins are installed in the MLG. The aircraft is lowered.
SERVICE BULLETIN 670BA---32---040

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PART D --- Installation of the Inboard MLG Door Part Number CC670-10520-16

and Increase of the Clearance Between the Right MLG Inboard-Door and the

MLG Fairing

For all aircraft

Circuit breakers are opened. The aircraft is put on jacks. A detailed visual

inspection of the MLG fairing is done. If installed the right inboard MLG door is

removed.

For Aircraft 10002 thru 10217, 15002 thru 15043 and 15991

In Service (IS) Modification Summary IS670528200033 is done

For all aircraft

The right inboard MLG door is installed. The clearance between the inboard MLG

door and the aft attachment of the outboard MLG door is adjusted. A clearance

check of the inboard MLG door and the outboard MLG door is done.The aft

stop-fitting, the seal, and the seal retainer are removed. The aft stop-fitting is cut

and the stop pad is relocated. The aft stop-fitting is installed. The material between

the MLG fairing and the inboard MLG door and outboard MLG door is removed.

The forward seal is replaced. The seal retainer is cut and installed. The safety guide

is installed with the forward seal and the seal retainer.

The lockpins are removed from the MLG. The circuit breakers are closed. The

clearance check of the inboard MLG door and outboard MLG door is done. The

MLG door hinge-fairing is installed. The lockpins are installed in the MLG. The

aircraft is lowered.

For all aircraft

D. Compliance

Recommended Service Bulletin.

Bombardier recommends that this service bulletin be done at no more than 6600

flight hours or three years, from the release date of Revision A of this service

bulletin, whichever comes first, unless otherwise directed by the airworthiness

authority of the operator.

For aircraft that have the MLG doors removed at 6600 flight hours or three years,

after the release date of Revision A of this service bulletin

At the installation of the left MLG and/or the right MLG door(s), it is necessary to do

this service bulletin before next flight, unless otherwise directed by the

airworthiness authority of the operator.
SERVICE BULLETIN 670BA---32---040

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For Aircraft 10002 thru 10230 and Aircraft 15002 thru 15053,15055, and 15056

NOTE: Service Bulletin 670BA-32-017, Landing Gear - Main Landing Gear Door

and Mechanism System - Replacement of the Cross Member and aft

Member of the Inboard Main Landing Gear (MLG) Doors

CC670-10520-2003, -2004, -2005, -2006, -2007,-2008, -2009, -2010,

-965, -966, -11, -12, MLG doors repaired with the REO 670-52-82-014,

and CC670-10520-3, -4, -9, -10, -951, -952, -963 and -964 MLG doors

repaired with the REO 670-52-82-016, is a prerequisite to this service

bulletin.

For all aircraft

NOTE: It is not necessary to do service bulletin 670BA-32-030 when this Service

Bulletin, Landing Gear - Main Landing Gear (MLG) and Doors -

Inspection of the MLG Inboard Doors and MLG Fairing, is done.

NOTE: If it is not possible to complete all the instructions in this service bulletin

because of the configuration of the aircraft, speak with a representative

of Bombardier Customer Response Centre at phone number

514---855---8500 or send an e-mail at thd.crj@bombardier.com for

analysis and to get an approved disposition to complete this service

bulletin.

This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage

Tolerance Inspections (DTIs).

E. Approval

The technical content of this service bulletin has been approved under the authority

of the TCCA Design Approval Organization No: DAO #93-Q-02.

F. Manpower

The man-hours given below are estimates for direct labor done by an experienced

crew on an aircraft prepared for maintenance.

These estimates do not include the time necessary for:

---Administrative functions such as planning, liaising, familiarization, and report writing.

---Non-productive elapsed time such as rest time, having meals, and crew shift

changes.

---Elapsed time such as for paint to dry, sealant to cure, and fuel tank venting.

---Preparation for modification (unless specified in the Accomplishment

Instructions) such as cleaning and getting parts, tools, consumables, and

ground equipment.
SERVICE BULLETIN 670BA---32---040

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---Quality assurance inspections, troubleshooting and/or correction of

discrepancies found when a task is done.

---All other activities that are not considered by Bombardier as directly related to the

accomplishment of this procedure.

NOTE: For on-site labor assistance, please speak with a Fleet Services

representative for a quote. Contact the Fleet Services Team

through the CRC at 514-855-8500 or email at

thd.crj@aero.bombardier.com.

For PART A

It will take an estimated 24.0 man-hours to complete PART A of this service bulletin.

The man-hours are divided in the table that follows (elapsed cure time is not

included in the man-hour summary given above):

TASK MAN-HOURS

(1) Job Set-Up 3.0

(2) Procedure 12.0

(3) Test 6.0

(4) Job Close-Out 3.0

For PART B

It will take an estimated 24.0 man-hours to complete PART B of this service bulletin.

The man-hours are divided in the table that follows (elapsed cure time is not

included in the man-hour summary given above):

TASK MAN-HOURS

(1) Job Set-Up 3.0

(2) Procedure 12.0

(3) Test 6.0

(4) Job Close-Out 3.0
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For PART C

It will take an estimated 20.0 man-hours to complete PART C of this service bulletin.

The man-hours are divided in the table that follows (elapsed cure time is not

included in the man-hour summary given above):

TASK MAN-HOURS

(1) Job Set-Up 3.0

(2) Procedure 8.0

(3) Test 6.0

(4) Job Close-Out 3.0

NOTE: The man-hours for the procedure do not include the hours to do

IS Modification Summary IS670528200033

For PART D

It will take an estimated 20.0 man-hours to complete PART D of this service bulletin.

The man-hours are divided in the table that follows (elapsed cure time is not

included in the man-hour summary given above):

TASK MAN-HOURS

(1) Job Set-Up 3.0

(2) Procedure 8.0

(3) Test 6.0

(4) Job Close-Out 3.0

NOTE: The man-hours for the procedure do not include the hours to do

IS Modification Summary IS670528200033
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G. Material --- Price and Availability

(1) The kits in the tables that follow are available from Bombardier Commercial

Aircraft. Refer to the paragraphs below for the terms and conditions.

NOTE: For a list of kit contents, refer to paragraph 3.A.

For PART A

KIT NUMBER NAME

670BA32040K1A Fairing and Left MLG door -

Parts

KIT NUMBER NAME

670BA32040K3A Fairing and Left MLG door -

Hardware

KIT NUMBER NAME

670BA32040K5 Left Fairing Forward Seal

For PART B

KIT NUMBER NAME

670BA32040K2A Fairing and Right MLG door -

Parts

KIT NUMBER NAME

670BA32040K4A Fairing and Right MLG door -

Hardware

KIT NUMBER NAME

670BA32040K6 Right Fairing Forward Seal
SERVICE BULLETIN 670BA---32---040

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For PART A and/or PART B

KIT NUMBER NAME

670BA32040K9 Oversize and Next Size

Fasteners

For PART C

KIT NUMBER NAME

670BA32040K5 Left MLG Fairing Forward Seal

KIT NUMBER NAME

670BA32040K7 Left MLG Fairing, Seal and

Hardware

For PART D

KIT NUMBER NAME

670BA32040K6 Right MLG Fairing Forward Seal

KIT NUMBER NAME

670BA32040K8 Right MLG Fairing, Seal and

Hardware

(2) One kit 670BA32040K9 is necessary for each operator that are incorporating

Part A and Part B of this service bulletin. To replace parts from Kit

670BA32040K9, speak with a representative of the Service Bulletin Kit Support

Team at the address below.
SERVICE BULLETIN 670BA---32---040

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(3) Please send a purchase order to the address below to schedule kit delivery:

Bombardier

Service Bulletin Kit Support Team

123 Garratt Blvd, N42-24

Toronto, Ontario

Canada M3K 1Y5

Fax: 416-375-3060

Phone: 416-375-3920

Email: sbkits@aero.bombardier.com

Please contact the Service Bulletin Kit Support Team at the address above for

terms and conditions.

(4) Refer to paragraph 3.B. for a list of consumables for this service bulletin.

H. Tooling --- Price and Availability

(1) The tool kit in the table that follows is available from Bombardier.

NOTE: For a list of the kit contents, refer to paragraph 3.A.

For PART A and PART B

KIT NUMBER NAME

670BA32040K90 DRILL JIG MLG DOOR ROLLER

For PART C and PART D

None.

(2) Please send a purchase order to the address below to schedule kit delivery:

Bombardier

Service Bulletin Kit Support Team

123 Garratt Blvd, N42-24

Toronto, Ontario

Canada M3K 1Y5

Fax: 416-375-3060

Phone: 416-375-3920

Email: sbkits@aero.bombardier.com

Please contact the Service Bulletin Kit Support Team at the address above for

terms and conditions.

(3) Refer to paragraph 3.C. for a list of special tools and equipment for this

service bulletin. Refer to the paragraphs below for terms and conditions.
SERVICE BULLETIN 670BA---32---040

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I. Weight and Balance

For CL-600-2C10 aircraft

For aircraft that had PART A of this service bulletin incorporated

WEIGHT ARM MOMENT ¡

+ 0.2 lb + 823.5 in. + 0.165 (1000 lb-in.)

+ 0.09 kg + 20.92 m + 0.0019 (1000 kg-m)

¡ The value in the Moment column is divided by 1000.

Refer to Weight and Balance Manual CSP A-041.

For aircraft that had PART B of this service bulletin incorporated

WEIGHT ARM MOMENT ¡

+ 0.2 lb + 823.5 in. + 0.165 (1000 lb-in.)

+ 0.09 kg + 20.92 m + 0.0019 (1000 kg-m)

¡ The value in the Moment column is divided by 1000.

Refer to Weight and Balance Manual CSP A-041.

For aircraft that had PART C of this service bulletin incorporated

WEIGHT ARM MOMENT ¡

+ 0.2 lb + 823.5 in. + 0.165 (1000 lb-in.)

+ 0.09 kg + 20.92 m + 0.0019 (1000 kg-m)

¡ The value in the Moment column is divided by 1000.

Refer to Weight and Balance Manual CSP A-041.

For aircraft that had PART D of this service bulletin incorporated

WEIGHT ARM MOMENT ¡

+ 0.2 lb + 823.5 in. + 0.165 (1000 lb-in.)

+ 0.09 kg + 20.92 m + 0.0019 (1000 kg-m)

¡ The value in the Moment column is divided by 1000.

Refer to Weight and Balance Manual CSP A-041.
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For CL-600-2D15 and CL-600-2D24 aircraft

For aircraft that had PART A of this service bulletin incorporated

WEIGHT ARM MOMENT ¡

+ 0.2 lb + 913.5 in. + 0.183 (1000 lb-in.)

+ 0.09 kg + 23.20 m + 0.0021 (1000 kg-m)

¡ The value in the Moment column is divided by 1000.

Refer to Weight and Balance Manual CSP A-041.

For aircraft that had PART B of this service bulletin incorporated

WEIGHT ARM MOMENT ¡

+ 0.2 lb + 913.5 in. + 0.183 (1000 lb-in.)

+ 0.09 kg + 23.20 m + 0.0021 (1000 kg-m)

¡ The value in the Moment column is divided by 1000.

Refer to Weight and Balance Manual CSP A-041.

For aircraft that had PART C of this service bulletin incorporated

WEIGHT ARM MOMENT ¡

+ 0.2 lb + 913.5 in. + 0.183 (1000 lb-in.)

+ 0.09 kg + 23.20 m + 0.0021 (1000 kg-m)

¡ The value in the Moment column is divided by 1000.

Refer to Weight and Balance Manual CSP A-041.

For aircraft that had PART D of this service bulletin incorporated

WEIGHT ARM MOMENT ¡

+ 0.2 lb + 913.5 in. + 0.183 (1000 lb-in.)

+ 0.09 kg + 23.20 m + 0.0021 (1000 kg-m)

¡ The value in the Moment column is divided by 1000.

Refer to Weight and Balance Manual CSP A-041.
SERVICE BULLETIN 670BA---32---040

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For all aircraft

J. Electrical Load Data

Not changed.

K. References

Modification Summary 670T001677, Revision K

Modification Summary 670T014111, Revision A-1

Restriction and/or Special Instruction (RSI) C-32-1330-00, Revision H

In Service Modification Summary IS670528200033

Aircraft Flight Manual (AFM)

Aircraft Maintenance Manual (AMM)

Structural Repair Manual (SRM)

Non-destructive Testing Manual (NDTM)

For Bombardier reference only: PCA 74689.

Refer to the SB Introduction document for definition or explanation of Service

Bulletin content.

L. Other Publications Affected

Aircraft Maintenance Manual (AMM)

Aircraft Illustrated Parts Catalogue (AIPC)

Weight and Balance Manual (WBM)
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M. Relationship Chart

PRE-SB

PART NUMBER NAME POST-SBPART NUMBER NAME

CC670-10520-967 Inboard MLG

Door Assembly

KBA670-10500-23 [1]

or

CC670-10520-15 [4]

Inboard MLG Door

Assembly

CC670-10520-968 Inboard MLG

Door Assembly

KBA670-10500-24 [2]

or

CC670-10520-16 [5]

Inboard MLG Door

Assembly

CC670-10520-2011 Inboard MLG

Door Assembly

KBA670-10500-25 [1]

or

CC670-10520-15 [4]

Inboard MLG Door

Assembly

CC670-10520-2012 Inboard MLG

Door Assembly

KBA670-10500-26 [2]

or

CC670-10520-16 [5]

Inboard MLG Door

Assembly

CC670-10520-2013 Inboard MLG

Door Assembly

KBA670-10500-27 [1]

or

CC670-10520-15 [4]

Inboard MLG Door

Assembly

CC670-10520-2014 Inboard MLG

Door Assembly

KBA670-10500-28 [2]

or

CC670-10520-16 [5]

Inboard MLG Door

Assembly

CC670-10520-2015 Inboard MLG

Door Assembly

KBA670-10500-29 [1]

or

CC670-10520-15 [4]

Inboard MLG Door

Assembly

CC670-10520-2016 Inboard MLG

Door Assembly

KBA670-10500-30 [2]

or

CC670-10520-16 [5]

Inboard MLG Door

Assembly

CC670-10520-13 Inboard MLG

Door Assembly

KBA670-10500-31 [1]

or

CC670-10520-15 [4]

Inboard MLG Door

Assembly

CC670-10520-14 Inboard MLG

Door Assembly

KBA670-10500-32 [2]

or

CC670-10520-16 [5]

Inboard MLG Door

Assembly
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PRE-SB

PART NUMBER NAME POST-SBPART NUMBER NAME

KCC670-10900-1 Inboard MLG

Door Assembly

KBA670-10500-33 [1]

or

CC670-10520-15 [4]

Inboard MLG Door

Assembly

KCC670-10900-2 Inboard MLG

Door Assembly

KBA670-10500-34 [2]

or

CC670-10520-16 [5]

Inboard MLG Door

Assembly

KCC670-10900-3 Inboard MLG

Door Assembly

KBA670-10500-35 [1]

or

CC670-10520-15 [4]

Inboard MLG Door

Assembly

KCC670-10900-4 Inboard MLG

Door Assembly

KBA670-10500-36 [2]

or

CC670-10520-16 [5]

Inboard MLG Door

Assembly

KCC670-10900-5 Inboard MLG

Door Assembly

KBA670-10500-37 [1]

or

CC670-10520-15 [4]

Inboard MLG Door

Assembly

KCC670-10900-6 Inboard MLG

Door Assembly

KBA670-10500-38 [2]

or

CC670-10520-16 [5]

Inboard MLG Door

Assembly

KCC670-10901-1 Inboard MLG

Door Assembly

KBA670-10500-51 [1]

or

CC670-10520-15 [4]

Inboard MLG Door

Assembly

KCC670-10901-2 Inboard MLG

Door Assembly

KBA670-10500-52 [2]

or

CC670-10520-16 [5]

Inboard MLG Door

Assembly

KCC670-10901-3 Inboard MLG

Door Assembly

KBA670-10500-53 [1]

or

CC670-10520-15 [4]

Inboard MLG Door

Assembly

KCC670-10901-4 Inboard MLG

Door Assembly

KBA670-10500-54 [2]

or

CC670-10520-16 [5]

Inboard MLG Door

Assembly

CC670-10571-13 Aft Member KBA670-10500-45 [1] Aft Member

CC670-10571-14 Aft Member KBA670-10500-46 [2] Aft Member
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PRE-SB

PART NUMBER NAME POST-SBPART NUMBER NAME

CC670-10570-1 Forward

Member

MLG Door

KBA670-10500-47 [1] Forward Member

MLG Door

CC670-10570-2 Forward

Member MLG

Door

KBA670-10500-48 [2] Forward Member

MLG Door

CC670-10570-5 Forward

Member MLG

Door

KBA670-10500-49 [1] Forward Member

MLG Door

CC670-10570-6 Forward

Member MLG

Door

KBA670-10500-50 [2] Forward Member

MLG Door

BA670-00001-2085 MLG Fairing

Assembly

KBA670-10500-300

[1] or [4]

MLG Fairing

Assembly

BA670-00001-2085 MLG Fairing

Assembly

KBA670-10500-350

[2] or [5]

MLG Fairing

Assembly

BA670-00001-2085 MLG Fairing

Assembly

KBA670-10500-3

[3] or [6]

[1] and [5]

[2] and [4]

MLG Fairing

Assembly

CC670-39005-951 MLG Fairing

Assembly

KBA670-10500-500

[1] or [4]

MLG Fairing

Assembly

CC670-39005-951 MLG Fairing

Assembly

KBA670-10500-550

[2] or [5]

MLG Fairing

Assembly

CC670-39005-951 MLG Fairing

Assembly

KBA670-10500-5

[3] or [6]

[1] and [5]

[2] and [4]

MLG Fairing

Assembly

CC670-39005-3 MLG Fairing

Assembly

KBA670-10500-700

[1] or [4]

MLG Fairing

Assembly
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PRE-SB

PART NUMBER NAME POST-SBPART NUMBER NAME

CC670-39005-3 MLG Fairing

Assembly

KBA670-10500-750

[2] or [5]

MLG Fairing

Assembly

CC670-39005-3 MLG Fairing

Assembly

KBA670-10500-7

[3] or [6]

[1] and [5]

[2] and [4]

MLG Fairing

Assembly

CC670-39005-5 MLG Fairing

Assembly

KBA670-10500-130

[1] or [4]

MLG Fairing

Assembly

CC670-39005-5 MLG Fairing

Assembly

KBA670-10500-135

[2] or [5]

MLG Fairing

Assembly [2] or [5]

CC670-39005-5 MLG Fairing

Assembly

KBA670-10500-13

[3] or [6]

[1] and [5]

[2] and [4]

MLG Fairing

Assembly

CC670-39019-49 MLG Fairing

Assembly

KBA670-10500-190

[1] or [4]

MLG Fairing

Assembly

CC670-39019-49 MLG Fairing

Assembly

KBA670-10500-195

[2] or [5]

MLG Fairing

Assembly

CC670-39019-49 MLG Fairing

Assembly

KBA670-10500-19

[3] or [6]

[1] and [5]

[2] and [4]

MLG Fairing

Assembly

CC670-39019-963 MLG Fairing

Assembly

KBA670-10500-150

[1] or [4]

MLG Fairing

Assembly

CC670-39019-963 MLG Fairing

Assembly

KBA670-10500-155

[2] or [5]

MLG Fairing

Assembly
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PRE-SB

PART NUMBER NAME POST-SBPART NUMBER NAME

CC670-39019-963 MLG Fairing

Assembly

KBA670-10500-15

[3] or [6]

[1] and [5]

[2] and [4]

MLG Fairing

Assembly

CC670-39019-965 MLG Fairing

Assembly

KBA670-10500-170

[1] or [4]

MLG Fairing

Assembly

CC670-39019-965 MLG Fairing

Assembly

KBA670-10500-175

[2] or [5]

MLG Fairing

Assembly

CC670-39019-965 MLG Fairing

Assembly

KBA670-10500-17

[3] or [6]

[1] and [5]

[2] and [4]

MLG Fairing

Assembly

CC670-39019-51 MLG Fairing

Assembly

KBA670-10500-210

[1] or [4]

MLG Fairing

Assembly

CC670-39019-51 MLG Fairing

Assembly

KBA670-10500-215

[2] or [5]

MLG Fairing

Assembly

CC670-39019-51 MLG Fairing

Assembly

KBA670-10500-21

[3] or [6]

[1] and [5]

[2] and [4]

MLG Fairing

Assembly

KBA670-39005-3 MLG Fairing

Assembly

KBA670-10500-610

[1] or [4]

MLG Fairing

Assembly

KBA670-39005-3 MLG Fairing

Assembly

KBA670-10500-615

[2] or [5]

MLG Fairing

Assembly

KBA670-39005-3 MLG Fairing

Assembly

KBA670-10500-61

[3] or [6]

[1] and [5]

[2] and [4]

MLG Fairing

Assembly
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PRE-SB

PART NUMBER NAME POST-SBPART NUMBER NAME

KBA670-39005-5 MLG Fairing

Assembly

KBA670-10500-630

[1] or [4]

MLG Fairing

Assembly

KBA670-39005-5 MLG Fairing

Assembly

KBA670-10500-635

[2] or [5]

MLG Fairing

Assembly

KBA670-39005-5 MLG Fairing

Assembly

KBA670-10500-63

[3] or [6]

[1] and [5]

[2] and [4]

MLG Fairing

Assembly

KBA670-39005-7 MLG Fairing

Assembly

KBA670-10500-650

[1] or [4]

MLG Fairing

Assembly

KBA670-39005-7 MLG Fairing

Assembly

KBA670-10500-655

[2] or [5]

MLG Fairing

Assembly

KBA670-39005-7 MLG Fairing

Assembly

KBA670-10500-65

[3] or [6]

[1] and [5]

[2] and [4]

MLG Fairing

Assembly

KBA670-39005-9 MLG Fairing

Assembly

KBA670-10500-670

[1] or [4]

MLG Fairing

Assembly

KBA670-39005-9 MLG Fairing

Assembly

KBA670-10500-675

[2] or [5]

MLG Fairing

Assembly

KBA670-39005-9 MLG Fairing

Assembly

KBA670-10500-67

[3] or [6]

[1] and [5]

[2] and [4]

MLG Fairing

Assembly

CC670-39076-1

Fitting aft Stop

KBA670-10500-39

[1] or [4] Fitting aft Stop

CC670-39076-2

Fitting aft Stop

KBA670-10500-40

[2] or [5] Fitting aft Stop
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PRE-SB

PART NUMBER NAME POST-SBPART NUMBER NAME

CC670-39244-1 Fairing FWD

Seal LH

CC670-39244-5

[1] or [4]

Fairing FWD Seal

LH

CC670-39244-2 Fairing FWD

Seal RH

CC670-39244-6

[2] or [5]

Fairing FWD Seal

RH

CC670-39245-1 Seal Retainer

Forward

KBA670-10500-41/-43

[1] or [4]

Seal Retainer

Forward

CC670-39245-2 Seal Retainer

Forward

KBA670-10500-42/-44

[2] or [5]

Seal Retainer

Forward

CC670-39247-1 Aft Fairing Seal

LH

CC670-39163-1

[1] or [4] Aft Fairing Seal LH

CC670-39247-2 Aft Fairing Seal

RH

CC670-39163-2

[2] or [5] Aft Fairing Seal RH

[1] When PART A is done.

[2] When PART B is done.

[3] When PART A and PART B are done.

[4] When PART C is done

[5] When PART D is done

[6] When PART C and PART D is done
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2. ACCOMPLISHMENT INSTRUCTIONS

PART A --- Increase of the Clearance Between the Left MLG Inboard-Door and

the MLG Fairing

A. Job Set-Up

Reference Information

REFERENCE DESIGNATION

AMM 07-11-01-582-801 Jacking of the Aircraft

AMM 07-11-01-586-801 Lowering of the Aircraft

AMM 10-11-00-400-801 Installation of the Nose Landing Gear (NLG)

Lockpin

AMM 10-11-00-400-802 Installation of the Main Landing Gear (MLG)

Lockpins

AMM 12-00-00-867-801 Standard Aircraft Configuration for Maintenance

AMM 12-20-32-640-802 Lubrication of the Main Landing Gear (MLG)

AMM 20-21-00-910-801 Torquing of Threaded Fasteners

AMM 20-31-00-400-801 Thermal Installation of Interference

Fit Bushings

AMM 20-51-00-000-801 Removal of Cotter Pins

AMM 20-51-00-000-802 Removal of Lockwire

AMM 20-51-00-400-801 Installation of Cotter Pins

AMM 20-51-00-400-802 Installation of Lockwire

AMM 20-60-13-930-801 Identification of Aircraft Parts and Assemblies

AMM 32-12-01-000-802 Removal of the Inboard MLG Doors

AMM 32-12-01-220-801 Clearance Check of the MLG Doors

AMM 32-12-01-400-802 Installation of the Inboard MLG Doors

AMM 32-12-01-820-801 Adjustment of the MLG Doors
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REFERENCE DESIGNATION

AMM 32-30-00-710-801 Operational Test of the Landing-Gear Extension/

Retraction System

AMM 51-23-00-100-801 Removal of Sealants

AMM 57-80-85-000-802 Removal of the Main Landing Gear Door-Hinge

Fairing (542AB/642AB)

AMM 57-80-85-400-802 Installation of the Main Landing Gear DoorHinge Fairing (542AB/642AB)

NDT 51-20-006-250 Eddy Current- Inspection Procedures

NDT 51-20-008-230 Liquid Penetrant - Inspection Procedures

NDT 51-20-009-210 Visual - Inspection Procedures

SRM 51-21-11-001-001 Corrosion Prevention Procedures

SRM 51-21-16-001-001 Finish Codes

SRM 51-23-00-001-001 Pressure, Environmental, Fuel Tank and Firewall

Sealing

SRM 51-25-06-001-001 Fluid-Resistant (FR) Epoxy Primer

SRM 51-25-16-001-001 Fluid-Resistant (FR) Polyurethane Topcoat

SRM 51-25-52-001-001 Composite-Laminate Coatings

SRM 51-26-00-001-001 Cleaning

SRM 51-40-06-001-001 Fastener Edge Distance and Pitch

SRM 51-40-11-001-001 Preparation of Fastener Holes

SRM 51-41-02-001-001 Bolts, Screws and Related Items

SRM 51-42-06-001-001 Solid Rivets

SRM 51-42-13-001-001 CherryMax and CherryMax A Blind Rivets

SRM 51-42-21-001-001 Hi-Lite Fasteners

SRM 51-71-00-001-001 Typical Structural Repairs

SRM 51-75-00-001-001 Graphite Repairs
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Tolerance Information

Linear Tolerances Angular Tolerance

X.XX in. (X.X mm) X.X in. (X mm)

+/-0 30” +/- 0.03 in. +/- 0.1 in.

+/- 0.8 mm +/- 3 mm

NOTE: The tolerances above apply to the dimensions given in this service

bulletin, except when specified differently.

(1) Make sure that the aircraft is in standard configuration for maintenance

(refer to AMM 12-00-00-867-801).

WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO

MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC

EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS,

INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN

OCCUR.

(2) Open, safety, and tag the circuit breakers that follow:

CB PANEL CB NO. NAME

CBP-1 A12 HEATERS TAT

CBP-1 A13 HEATERS AOA R

CBP-1 A14 HEATERS PITOT R

CBP-1 C13 ADG HEATER

CBP-1 G1 PSEU CH A

CBP-1 G2 NOSE STEER

CBP-1 G13 HEATERS ADS CONT 2

CBP-1 G14 HEATERS STATIC R

CBP-1 LOWER T7 HEATERS PITOT L

CBP-1 LOWER T8 HEATERS AOA L

CBP-1 LOWER T9 HEATERS PITOT STBY

CBP-1 LOWER U7 ENG IGN A

CBP-2 G1 PSEU CH B

CBP-2 G2 NOSE STEER
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CB PANEL CB NO. NAME

CBP-2 N6 ADG DEPLOY AUTO

CBP-2 N9 MLG BAYOVHT DET

CBP-2 P1 PSEU CH A

CBP-2 P2 PSEU CH B

CBP-2 LOWER S1 HEATERS STATIC L

CBP-2 LOWER S2 HEATERS ADS CONT 1

CBP-2 LOWER S3 HEATERS ADS CONT STBY

CBP-5 B10 ENG IGN B

(3) Put the aircraft on jacks (refer to AMM 07-11-01-582-801).

(4) Remove MLG door-hinge fairing 542AB

(refer to AMM 57-80-85-000-802).

(5) If necessary, remove the left MLG wheel bin (refer to AMM 53-83-89-000-801).

(6) If necessary, remove the left inboard MLG door (refer to AMM

32-12-01-000-802).
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B. Procedure

For all aircraft

Refer to Figure 1.

(1) Do a detailed visual inspection of the left section of the MLG fairing as follows

(refer to NDT 51-20-009-210):

(a) Visually inspect to make sure that the forward and the aft stops are not

missing from the MLG fairing.

(b) If the forward and/or the aft stops are not missing, visually inspect that

there are no loose or missing fasteners from the forward and aft stops.

(c) Visually inspect along the edge of the MLG fairing adjacent the MLG

door to make sure that there is no damage. Refer to the shaded area

(refer to Figure 1, Sheet 2).

NOTE: For this inspection, damage does not include surface scratches and/or

paint deterioration.

(d) Record the findings on the record sheet of Appendix A.

Refer to Figure 2.

(2) Do a detailed visual inspection of the left MLG inboard door as follows

(refer to NDT 51-20-009-210):

(a) Visually inspect the MLG inboard door to make sure that there is no

missing or broken roller (2) or missing stop (1).

(b) If the stop (1) is not missing, visually inspect that there are no loose or

missing fasteners from the stop (1).

(c) Record the findings on the record sheet of Appendix A.

(d) Visually inspect that the stops (3), (4) and (5) are not damaged.

(e) Visually inspect that there are no loose or missing fasteners from the

stops (3), (4) and (5).

(f) Visually inspect along the edge of the MLG inboard door adjacent to the

MLG fairing to make sure that there is no damage. Refer to the shaded

area (refer to Figure 2, Sheets 3 and 4).

NOTE: For this inspection, damage does not include surface scratches and/or

paint deterioration.

(g) Record the findings on the record sheet of Appendix A.
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Refer to Figure 3.

(3) Do a detailed visual inspection of the stops (1) and (2), and the wedge (3) on

the left side of the forward and the aft spars as follows (refer to NDT

51-20-009-210):

(a) Visually inspect to make sure that the stops (1) and (2) are not missing.

(b) If the stops (1) and/or (2) are not missing, visually inspect that there are

no loose or missing fasteners from the stops (1) and/or (2).

(c) Visually inspect to make sure that the wedge (3) is not missing.

(d) If the wedge (3) is not missing, visually inspect that there are no loose or

missing fasteners from the wedge (3).

(e) Record the findings on the record sheet of Appendix A.

Refer to Figures 1, 2 and 3.

(4) If damage is found and/or there are missing parts and/or fasteners, speak

with a representative of the Customer Response Center (CRC) at phone

number 514-855-8500 for a disposition.

NOTE: Refer to the record sheet of Appendix A for data.

(5) If no damage is found and there is no missing part or fastener, go to the next

step.

NOTE: Refer to the record sheet of Appendix A for data.

Refer to Figure 4.

(6) Remove the roller assembly as follows:

WARNING: WHEN YOU CUT THE COTTER PIN, USE EYE PROTECTION.

PIECES THAT BREAK OFF CAN CAUSE INJURY.

(a) Remove and discard the cotter pin (2) (refer to AMM 20-51-00-000-802).

(b) Remove and discard the nut (3).

(c) Remove and discard the bolt (4), the three washers (5), the bushing (6),

and the roller (1).
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Refer to Figure 5.

(7) Install the new roller assembly as follows:

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(a) Install the drill jig (1) on the aft member of the inboard MLG door as

follows:

1 Make sure that the dowel pin of the drill jig (1) touches the aft

member of the inboard MLG door

(refer to Figure 5, Sheet 1, View B).

2 Make sure that the surface of the drill jig (1) touches the aft

member assembly (refer to Figure 5, Sheet 1, View C).

(b) With the drill bushing (2) and core drill P/N 670BA32040K90-201,

increase the diameter for the holes in the two lugs of the aft member

between 0.2959 in. (7.515 mm) and 0.2969 in. (7.541 mm).

(c) With the reamer bushing (3) and reamer P/N 670BA32040K90-202, ream

the holes of the two lugs in the aft member to a diameter of between

0.3147 in. (7.993 mm) and 0.3149 (7.998 mm).

(d) Remove the drill jig (1) from the inboard MLG door.

(e) Remove burrs and sharp edges from the holes of the lugs in the aft

member of the inboard MLG door.

(f) Make sure that the final diameter of the inboard hole in the aft member is

between 0.3147 and 0.3157 in (7.99 to 8.02 mm).

(g) Make sure that the final diameter of the outboard hole in the aft member

is between 0.3141 and 0.3159 in (7.98 to 8.02 mm).

(h) Apply chemical conversion coating on the bare metal surfaces of the

bores of the two lugs of the aft member (refer to SRM 51-21-11-001-001).
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WARNING: OBEY THE PRECAUTIONS THAT FOLLOW, WHEN YOU

USE DRY ICE:

- USE APPROVED EYE, MOUTH, AND BODY

PROTECTION.

- DO THE WORK IN AN AREA THAT HAS A GOOD FLOW

OF CLEAN AIR.

- DO NOT TOUCH MATERIAL THAT HAS TOUCHED DRY

ICE.

- OBEY THE MANUFACTURER’S INSTRUCTIONS.

- DO NOT LET THE DRY ICE TOUCH YOUR SKIN, EYES,

OR MOUTH.

- ONLY PUT DRY ICE IN AN APPROVED CONTAINER

THAT IS MADE FOR HIGH PRESSURES.

- IF IRRITATION OCCURS, GET MEDICAL AID

IMMEDIATELY.

DRY ICE IS POISONOUS AND CAN CAUSE INJURY TO

PERSONS.

WARNING: OBEY THE PRECAUTIONS THAT FOLLOW WHEN YOU

USE LIQUID NITROGEN:

- USE SAFETY GOGGLES.

- PUT ON PROTECTIVE CLOTHING.

- DO NOT LET THE LIQUID NITROGEN TOUCH YOUR

SKIN, EYES, AND MOUTH.

- WORK IN AN AREA THAT HAS A GOOD FLOW OF

CLEAN AIR.

- OBEY THE MANUFACTURER’S INSTRUCTIONS.

- GET MEDICAL AID IF YOU GET LIQUID NITROGEN ON

YOUR SKIN OR IN YOUR EYES OR MOUTH.

LIQUID NITROGEN IS VERY COLD -195 DEGREES C (77K).

IT WILL FREEZE IMMEDIATELY AND WILL CAUSE

DAMAGE TO SKIN, EYES OR LUNGS. IN SUFFICIENT

QUANTITIES, THE NITROGEN GAS FROM THE LIQUID

NITROGEN CAN ALSO REPLACE THE OXYGEN OF THE

AMBIENT AIR. THIS CAN CAUSE INJURY TO PERSONS.

(i) Use liquid nitrogen or solid carbon dioxide (dry ice) to do a thermal

installation of the flange bushing (7) (refer to AMM-20-31-00-400-801).

(j) With MIL-PRF-81733 type IV corrosion-inhibiting compound, wet-install

the flanged bushing (7) in the inboard lug of the aft member (refer to

Figure 5, Sheet 2, View D and SRM 51-23-00-001-001).
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(k) Do a fillet seal around the flanged bushing (7) (refer to Figure 5, Sheet 2,

View D and SRM 51-23-00-001-001).

(l) Wet-install the bushing (6) with Mastinox 6856K or CA 1000 compound

through the outboard lug (refer to Figure 5, Sheet 3, View G-G and SRM

51-21-11-001-001).

(m) Make sure that no compound is between the bushing (6) and the roller

(5).

(n) Apply Aeroshell 33 grease or equivalent on the shank of the bolt (11).

(o) Install the bolt (11) with the washer (9), through the outboard lug, the

bushing (6), the roller(5), the flanged bushing (7) and the inboard lug of

the aft member.

(p) Install the washer (12) and the nut (8).

NOTE: It is not permitted to replace the washer (12) for a thinner washer.

(q) Torque the nut (8) (refer to AMM 20-21-00-910-801).

(r) Safety the nut (8) with the cotter pin (10)

(refer to AMM 20-51-00-400-801).

(s) Make sure there is a minimum clearance between the aft member and

the roller (5) of 0.030 in. (0.76 mm).

Refer to Figure 6.

(8) Remove and discard the aft fairing seal (4) and the aft retainer seal (5) from

the fairing as follows:

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(a) Remove and discard the three bolts (1), the washers (2) and the nuts

(3).

(b) Remove and discard the seal aft fairing (4) and the aft retainer seal (5)

from the fairing.
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(9) Remove the aft stop-fitting (14) as follows:

(a) Remove the two bolts (6), the washers (10), and the nuts (11).

(b) Remove and discard the stop pad (7), the laminated shim (8) and the

shim (9).

(c) Remove the sealant from the aft stop-fitting (14) and the sealing member

(refer to Figure 6, Sheet 1, View D) (refer to AMM 51-23-00-100-801).

(d) Remove the three solid rivets (17).

(e) Remove and discard the bolts (12) and the nuts (13).

(f) Remove the aft stop-fitting (14) from the sealing member.

(g) Remove the sealant from the MLG fairing, the sealing member and on

the aft stop-fitting (14) (refer to AMM 51-23-00-100-801).

(10) Drill the aft stop-fitting (14) as follows:

(a) Temporarily install the shim fairing (15) on the aft stop-fitting (14). Make

sure that the shim fairing (15) is parallel to the edge of the aft stop-fitting

(14) (refer to Figure 6, Sheet 2, View E).

(b) Attach the shim fairing (15) with the bolt (6), the washer (10) and the nut

(11).

(c) Backdrill one hole to a diameter of 0.190 to 0.194 in (4.83 to 4.93 mm)

from the shim fairing (15) to the aft stop-fitting (14).

(d) Remove and discard the nut (11).

(e) Remove the bolt (6), the washer (10) and the shim fairing (15).

(f) Temporarily install the shim fairing (15) on the laminated shim (16).

(g) Increase the diameter of two holes in the shim fairing (15) and the

laminated shim (16) to 0.213 to 0.217 (5.41 to 5.51 mm).

(h) Disassemble and remove burrs and sharp edges from the holes of the

shim fairing (15), the laminated shim (16), and the aft stop-fitting (14).

(i) Clean the bare metal surfaces of the aft stop-fitting (14) with clean dry

cloths, with no lint, moist with aliphatic naphta or equivalent.
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(j) Dry the bare surfaces with clean dry cloths with no lint.

(k) Apply chemical conversion compound on the bare metal surfaces of the

hole in the aft stop-fitting (14) (refer to SRM 51-21-11-001-001).

(l) Touch-up the hole in the aft stop-fitting (14) with epoxy primer

(refer to SRM 51-25-06-001-001).

(m) Touch-up the hole in the aft stop-fitting (14) with fluid resistant enamel

color grey #16473 (refer to SRM 51-25-16-001-001).

Refer to Figure 7.

(11) Remove 0.53 in. to 0.61 in. (13.4 to 15.5 mm) of material from the aft area of

the MLG fairing (refer to Figure 7, Sheet1, View D and SRM

51-71-00-001-001).

NOTE: An edge distance of 0.57 in (14.50 mm) for the three holes of the aft

stop-fitting (1) is necessary.

(12) Install the aft stop-fitting (1) as follows:

(a) Apply sealant on the mating surface of the aft stop-fitting (1) (refer to

SRM 51-23-00-001-001).

(b) Install the aft stop-fitting (1) on the sealing member of the MLG fairing.

(c) Wet-install the two upper rivets (5) on the aft stop-fitting (1) (refer to

Figure 7, View C) (SRM 51-42-06-001-001and SRM 51-23-00-001-001).

(d) Wet-install one rivet (4) at the bottom of the aft stop-fitting (1) (refer to

Figure 7, View C) (SRM 51-42-06-001-001 and SRM 51-23-00-001-001).

(e) Wet-install the three bolts (2) and the nuts (3)

(refer to SRM 51-42-21-001-001 and SRM 51-23-00-001-001).

NOTE: The installation of the stop pad (7), the laminated shim (8), and the

shim (9) will be incorporated in a subsequent step during the

clearance check.
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Refer to Figure 8.

WARNING: MAKE SURE THAT THE LOCKPINS ARE INSTALLED IN THE NOSE AND

MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN

ACCIDENTALLY RETRACT AND CAUSE INJURY TO PERSONS AND/OR

DAMAGE TO EQUIPMENT.

(13) Disconnect the rod end (13) from the MLG door as follows:

CAUTION: WHEN YOU CUT THE COTTER PIN, USE EYE PROTECTION. PIECES

THAT BREAK OFF CAN CAUSE INJURY.

(a) Remove and discard the cotter pin (7) (refer to AMM 20-51-00-000-801).

CAUTION: MAKE SURE THAT A PERSON HOLDS THE MLG DOOR

ASSEMBLY IN POSITION WHEN YOU DISENGAGE THE DOOR

RODS (13). IT CAN CAUSE INJURY TO PERSONS AND/OR

DAMAGE TO EQUIPMENT.

(b) Remove the nut (8), the washer (9), the bushing (12), the washer (10)

and the pin (11).

(c) Lower the inboard section of the MLG door assembly against the

adjacent tire.

Refer to Figure 9.

(14) Replace the aft seal of the MLG door as follows:

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(a) Remove the three rivets (1) and the two washers (2) from the MLG

inboard door (refer to Figure 9, Sheet 1, View B).

(b) Remove the three rivets (1) and the washers (2) from the MLG inboard

door (refer to Figure 9, Sheet 1, View C).

(c) Remove and discard the aft seal of the MLG door.

(d) Make sure that the holes are not damaged or elongated.
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(e) If the holes are damaged or elongated, increase the diameter of the hole

to a maximum of 0.261 in. ( 6.63 mm)

(refer to Figure 9, Sheet 3, Table 1).

--- 0.176 to 0.180 in. (4.47 to 4.57 mm)

--- 0.192 to 0.196 in. (4.88 to 4.98 mm)

--- 0.205 to 0.209 in. (5.21 to 5.31 mm)

--- 0.256 to 0.261 in. (6.50 to 6.63 mm).

(f) Make sure that there is a minimum of 1.2D of edge distance on the aft

seal (3) and the inboard MLG door before you drill.

(g) If necessary increase the diameter of the hole in the washer (6) and/or

(7) as follows:

DIAMETER OF

FASTENERS HOLE

DIAMETER

WASHER HOLE

WASHER ITEM

NUMBER

0.176 TO 0.180 in.

(4.47 TO 4.57 mm)

N/A (6)

0.192 TO 0.196 in.

(4.88 TO 4.98 mm)

0.214 TO 0.218 in.

(5.44 TO 5.54 mm)

(6)

0.205 TO 0.209 in.

(5.21 TO 5.31 mm)

0.214 TO 0.218 in.

(5.44 TO 5.54 mm)

(6)

0.256 TO 0.261 in.

(6.50 TO 6.63 mm)

N/A (7)

(h) Align and install the aft seal (3) on the MLG door with a constant

clearance of 0.11 in. (2.79 mm) (refer to Figure 9, Sheet 2, View D).

(i) Backdrill six holes from the MLG door through the aft seal (3).

(j) Remove the aft seal (3) from the door and remove burrs and sharp

edges.
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(k) Clean the surfaces of the aft seal (3) and the MLG door with clean dry

cloths, with no lint, moist with aliphatic naphta or equivalent.

(l) Dry the surfaces of the aft seal (3) and the MLG door with clean dry

cloths with no lint.

(m) Install the aft seal (3) on the MLG door.

(n) Wet-install the blind rivets (5) through the MLG door, the aft seal (3) and

the washers (4) (refer to Figure 9, View E and F) (refer to SRM

51-42-13-001-001).

(o) Clean the surfaces of the aft seal (3) and the MLG door with clean dry

cloths, with no lint, moist with aliphatic naphta or equivalent.

(p) Dry the surfaces of the aft seal (3) and the MLG door with clean dry

cloths with no lint.

Refer to Figure 10.

(15) Adjust the aft attachment of the outboard MLG door and the inboard MLG

door as follows:

WARNING: WHEN YOU CUT THE COTTER PIN, USE EYE PROTECTION.

PIECES THAT BREAK OFF CAN CAUSE INJURY.

(a) Remove and discard the cotter pin (9) and the nut (6).

(b) Remove the washer (5).

(c) Remove and discard the washers (7) or (8).

(d) Remove the bolt (1), the washer (10) and the sleeve bushing (4).

(e) Apply Aeroshell No.33 grease on the sleeve bushing (4) and the shank

of the bolt (1).

(f) Install the sleeve bushing (4), the washer (10) and the bolt (1).

(g) Move the door to the aft position until the the bushing (11) touches the

bushing (12).

(h) Measure the clearance between the bushings (2) and (3).

(i) If the clearance is between 0.062 and 0.093 in. (1.57 to 2.36 mm), install

the washer (7).
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(j) If the clearance is between 0.094 and 0.125 in. (2.39 to 3.18 mm), install

the washer (8).

NOTE: If the clearance is more than 0.126 (3.20 mm), speak with a

representative of the Customer Response Center (CRC) at phone

number 514-855-8500 for a disposition.

(k) Make sure that there is a clearance of 0.030 and 0.060 in.

(0.76 to 1.42 mm) after the installation of the new washer.

(l) Install the washer (5) and the nut (6).

(m) Torque the nut (6) (refer to AMM 20-21-00-910-801).

(n) Safety the nut (6) with the cotter pin (9)

(refer to AMM 20-51-00-400-801).

Refer to Figure 8.

(16) Attach the rod end (13) to the MLG door as follows:

(a) Apply Aeroshell No.33 grease on the shank of the pin (11) and the

bushing (12).

(b) Make sure that there is no grease on the threads of the pin (11).

(c) Align the rod end (13) with the attachment of the MLG door assembly.

(d) Install the pin (11) with the washer (10) and the bushing (12) through the

attachment of the MLG door assembly and the rod end (13).

(e) Make sure that the head of the pin (11) points forward.

(f) Install the washer (9), and the nut (8).

(g) Torque the nut (8) from 50 to 70 lb·in (6.65 to 7.91 N·m) plus the running

torque (refer to AMM 20-21-00-910-801).

(h) Safety the nut (8) with the cotter pin (7)

(refer to AMM 20-51-00-400-801).
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Refer to Figure 11.

(17) Remove 11 rivets from the MLG door (refer to Figure 11, Sheet 1, View B).

(18) Remove 5 rivets from the upper inboard aft part of the MLG door (refer to

Figure 11, Sheet 2, View C).

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(19) Do a countersinks in 11 holes on the near side of the forward member for the

installation of the rivets (7). Countersunk depth of the holes on the forward

member must be between 0.030 and 0.045 in. (0.76 to 1.14 mm) or the

countersunk diameter must be between 0.234 and 0.269 in. (5.94 to 6.83

mm).

(20) Do a countersinks in 5 holes on the near side of the upper inboard aft part of

the MLG door for the installation of the rivets (7). Countersunk depth on the

upper part of the MLG door must be between 0.030 and 0.045 in. (0.76 to

1.14 mm) or the countersunk diameter must be between 0.234 and 0.269 in.

(5.94 to 6.83 mm).

(21) Apply chemical conversion compound or equivalent in the 16 countersunk

holes (refer to SRM 51-21-11-001-001).

(22) Wet-install the 11 rivets (7) from the outer skin through the forward member

(refer to SRM 51-42-06-001-001).

(23) Wet-install the 5 rivets (7) from the outer skin through the inboard aft upper

part of the MLG door (refer to SRM 51-42-06-001-001).

(24) Clean the area of the forward member and the outer skin of the MLG door

with clean dry cloths, with no lint, moist with aliphatic naphta or equivalent.

(25) Cut the 11 rivets (7) flush with the forward member

(refer to SRM 51-42-06-001-001).

(26) Cut the 5 rivets (7) flush with the upper inboard aft part of the MLG door

(refer to SRM 51-42-06-001-001).

(27) Clean the area of the forward member, the inboard aft upper part of the MLG

door and the outer skin of the MLG door with clean dry cloths, with no lint,

moist with aliphatic naphta or equivalent.
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(28) Dry the bare surfaces with clean dry cloths with no lint.

(29) Apply chemical conversion compound or equivalent on the cut area of the

forward member and the upper inboard aft part of the MLG door.

(30) Remove material from the stiffener of the MLG inboard-door forward-member

as follows:

(a) At 2.61 in. (66.3 mm) from the web of the forward member, make point A

on the stiffener (refer to Figure 11, Sheet 3, View E-E).

(b) At 0.94 in. (23.8 mm) from the web of the forward member, make a point

on the stiffener.

(c) At the intersection of the point at 0.94 in (23.9 mm), made at the

previous step, and at 0.48 (12.2 mm) from the forward member, make

point B.

(d) At 0.04 in. (1.0 mm) from the web of the forward member make point C

on the stiffener.

(e) With a indelible ink pen, make a line and join points A, B and C, on the

stiffener of the forward member.

(f) Do a radius of .12 in. (3.1 mm) at point A.

(g) Do a radius of 2.0 in. (50.8 mm) at point B.

(h) Do a radius of 0.25 in. (6.3 mm) at point C.

(i) Cut the material outboard of the line on the stiffener of the forward

member (refer to SRM 52-71-00-001-001).

(j) Carefully break sharp edges on the stiffener of the forward member.

(k) Clean the bare surfaces of the forward member of the MLG door with

clean, dry cloths with no lint, moist with aliphatic naphta or equivalent.

(l) Dry the bare surfaces with clean, dry cloths with no lint.

(m) Make sure that the surface finish roughness is 125 in. RHR (3.2 mm

RHR) or more where the material was removed on the stiffener of the

MLG door.
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Refer to Figure 12.

(31) Before the installation of the wheel bin, record the part number of the MLG

fairing.

NOTE: The part number will be necessary in a subsequent step for the

identification.

(32) Install the left MLG wheel bin (refer to AMM 53-83-89-400-801).

(33) Identify locations PT2 to PT6 and PT9 to PT13 on the MLG door as follows:

NOTE: All PT locations must be identified on the outer skin of the MLG door.

NOTE: Make sure that you can see the identification mark---up when the door

is in the closed position.

(a) With a indelible ink pen, identify the PT2 on the forward edge of the

inboard door, at 0.50 in.(12.7 mm) from the outboard edge of the angle,

(refer to Figure 12, Sheet 1,View B).

(b) With a indelible ink pen, identify the PT3 on the forward edge of the

inboard door, aligned with the stiffener of the forward member.

(c) With a indelible ink pen, identify the PT4 on the forward edge of the

inboard door, at 0.50 in.(12.7 mm) from the outboard edge of the

inboard door.

(d) With a indelible ink pen, identify the PT5 on the forward edge of the

outboard door, at 0.50 in.(12.7 mm) from the inboard edge of the

outboard door.

(e) With a indelible ink pen, identify the PT6 on the forward edge of the

outboard door, aligned with the stiffener of the forward member.

(f) With a indelible ink pen, identify the PT9 on the aft edge of the outboard

door, aligned with the stiffener of the forward member.

(g) With a indelible ink pen, identify the PT10 on the aft edge of the

outboard door, at 0.50 in (12.7 mm) from the inboard edge of the

outboard door.

(h) With a indelible ink pen, identify the PT11 on the aft edge of the inboard

door, at 2.50 in (63.5 mm) from the outboard edge of the inboard door.

(i) With a indelible ink pen, identify the PT12 on the aft edge of the inboard

door, aligned with the stiffener of the aft member.

(j) With a indelible ink pen, identify the PT13 on the forward edge of the

inboard door, at 0.50 in.(12.7 mm) from the outboard edge of the angle.
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(34) Do the retraction of the main landing gear

(refer to AMM 32-30-00-865-801).

(35) Identify locations PT1 and PT14 to PT25 on the MLG fairing as follows:

(a) With a indelible ink pen, identify the PT1 on the forward edge of the

inboard door, at 1.50 in.(38.1 mm) from the end of the fairing seal, (refer

to Figure 12, Sheet 2, View E).

(b) With a indelible ink pen, identify the PT14 on the aft edge of the fairing,

aligned with the screw on the fairing.

(c) With a indelible ink pen, identify the PT15 on the aft edge of the inboard

door, at 0.50 in (12.7 mm) from the more down edge of the angle, (refer

to Figure 12, Sheet 2, View D).

(d) With a indelible ink pen, identify the PT16 on the aft edge of the inboard

door, align with the screw on the fairing.

(e) With a indelible ink pen, identify the PT17 on the aft edge of the inboard

door, align with the screw on the fairing.

(f) With a indelible ink pen, identify the PT18 on the aft edge of the inboard

door, align with the screw on the fairing.

(g) With a indelible ink pen, identify the PT19 on the aft edge of the inboard

door, align with the screw on the fairing.

(h) With a indelible ink pen, identify the PT20 on the forward edge of the

inboard door, align with the screw on the fairing.

(i) With a indelible ink pen, identify the PT21 on the forward edge of the

inboard door, align with the screw on the fairing.

(j) With a indelible ink pen, identify the PT22 on the forward edge of the

inboard door, align with the screw on the fairing.

(k) With a indelible ink pen, identify the PT23 on the forward edge of the

inboard door, at 0.50 in (12.7 mm) from the edge of the angle.

(l) With a indelible ink pen, identify the PT24 on the forward edge of the

inboard door, in line with the screw on the fairing.
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(m) With a indelible ink pen, identify the PT25 on the forward edge of the

inboard door, in line with the screw on the fairing.

NOTE: At this point do not remove material on the inboard MLG door or

on the MLG fairing.

Refer to Figure 12.

(36) Measure and record the mismatches in Table 1 of Apppendix B.

NOTE: At this point do not remove material on the inboard MLG door or on the

MLG fairing.

(37) Make sure that the mismatches are within the values shown in Table 1 of

Appendix B.

NOTE: Do not remove the hydraulic test fixture it will be needed in subsequent

steps.

(38) If the mismatches at PT 22 and PT 23 are not within -0.050 to +0.100 in.

(-1.27 to +2.54 mm), speak with a representative of the Customer Response

Center (CRC) at phone number 514-855-8500 for a disposition.

(39) If the mismatched values recorded in Table 1 of Appendix B are not within the

permitted values, do the adjustment of the MLG doors

(refer to AMM 32-12-01-820-801).

(40) If the adjustment of the MLG doors procedure cannot be done with the AMM

task, speak with a representative of the Customer Response Center (CRC) at

phone number 514-855-8500 for a disposition (refer to AMM

32-12-01-820-801).

(41) If the mismatched values recorded in Table 1 of Appendix B are within the

permitted values, record the clearances in Table 2 of Appendix B.

(42) If the recorded clearance values are higher than the acceptable clearance

values given in Table 2 of Appendix B, speak with a representative of the

Customer Response Center (CRC) at phone number 514-855-8500 for a

disposition (refer to AMM 32-12-01-820-801).

Refer to Figure 17.

(43) Record in Table 3 of Appendix B the overlap between the aft stop-fitting (1)

and the MLG door stop fitting (refer to Figure 17, View C-C).

(44) Do the extension of the main landing gear

(refer to AMM 32-30-00-992-801).

NOTE: Do not remove the hydraulic test fixture it will be needed in subsequent

steps.
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Refer to Figure 6 and Figure 17.

(45) Remove material from the aft stop-fitting (14) as follows:

NOTE: The overlap between the aft stop-fitting (14) and the MLG door stop fitting

is recorded in Appendix B Table 3 (refer to Figure 17, Sheet 1, View

C-C).

(a) Remove material from the aft stop-fitting (14) to have a minimum overlap

of 0.600 in. (15.24 mm) between the aft stop-fitting and the MLG door

stop fitting (refer to Figure 6, Sheet 2, View E).

NOTE: The aft stop fitting must be cut as close as possible to the stop pad.

(b) Remove burrs and break sharp edges on the aft stop-fitting (14).

(c) Do a radius of 0.250 in. (6.35 mm) on the aft stop-fitting (14)

(refer to Figure 6, Sheet 2, View E).

(d) Clean the bare surfaces of the aft stop-fitting (14) with clean dry cloths,

with no lint, moist with aliphatic naphta or equivalent.

(e) Dry the bare surfaces with clean dry cloths with no lint.

Refer to Figure 6 and 11.

(46) Do a liquid penetrant inspection or an eddy current inspection on the aft

stop-fitting (14) and on the stiffener of the forward member of the MLG

inboard door as follows:

(a) Do a liquid penetrant inspection or an eddy current inspection on the cut

section of the aft stop-fitting (14) (refer to Figure 6, Sheet 2, View E,

NDT 51-20-008-230, or NDT 51-20-006-250)

(b) Do a liquid penetrant inspection or an eddy current inspection on the cut

section of the stiffener of the inboard MLG door

(refer to Figure 11, Sheet 3, View E-E, NDT 51-20-008-230 or

NDT 51-20-006-250).

(c) If there is no crack on the aft stop-fitting (14) and on the stiffener of the

forward member of the MLG inboard door go to next step

(d) If there is a crack on the cut section of the aft stop-fitting (14), speak with

a representative of the Customer Response Center (CRC) at phone

number 514-855-8500 for a disposition.
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(e) If there is a crack on the cut section of the stiffener of the inboard MLG

door, speak with a representative of the Customer Response Center

(CRC) at phone number 514-855-8500 for a disposition.

(47) If there is no crack on the aft stop-fitting (14) and/or on the MLG door stiffener

do the steps that follow:

(a) Apply chemical conversion compound or equivalent on the bare

surfaces of the aft stop-fitting (14), the forward member stiffener of the

inboard MLG door (refer to SRM 51-21-11-001-001).

(b) Apply epoxy primer on the bare surfaces and the hole of the aft

stop-fitting (14) (refer to SRM 51-25-06-001-001).

(c) Apply epoxy primer on the bare surfaces the forward member stiffener of

the inboard MLG door (refer to SRM 51-25-06-001-001).

(d) Apply fluid resistant enamel color grey #16473 on the aft stop-fitting (14)

and on the stiffener of the MLG inboard door

(refer to SRM 51-25-16-001-001).

Refer to Figure 13.

(48) If necessary, remove the left MLG wheel bin (refer to AMM 53-83-89-000-801).

(49) Remove of the seals (8), (10), (4), (11), and the seal retainers (5), (7), (9) as

follows:

(a) Remove the bolts (1), (6), (12), and the washers (3).

(b) Remove and discard the nuts (2).

(c) Remove the seal retainers (5), (7) and (9).

(d) Remove the seals (8) and (11).

(e) Remove and discard the seal (4) and (10).
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Refer to Figure 12 and 14.

(50) Remove material from the MLG inboard door, the outboard MLG door and the

MLG fairing as follows (refer to SRM 51-75-00-001-001):

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(a) Calculate the difference between the acceptable clearance values and

the actual clearance values recorded in Table 2 of Appendix B.

NOTE: The removal of the material must be made on the MLG door before

the removal of the material on the MLG fairing.

NOTE: If you do not get the correct clearance after you remove the

maximum permitted material from the MLG door, remove material

from the MLG fairing.

(b) On the forward section of the MLG door from PT A to PT B, remove

material to a maximum of 0.13 (2.5 mm) (refer to Figure 14, Sheet 2,

View G). Make sure that there is a minimum edge distance of 0.23 in.

(6.0 mm) with the fasteners.

(c) On the forward section of the MLG door at the end of PT A, make a

radius of 0.25 in. (6.3 mm) (refer to Figure 14, Sheet 2, View J).

(d) On the forward section of the MLG door, remove the material from PT B

to a maximum of 0.130 in. (2.54 mm) to PT C to a maximum of 0.080 in.

(2.03 mm) (refer to Figure 14, Sheet 2, View K). Make sure that there is a

minimum edge distance of 0.23 in. (6.0 mm) from the fasteners.

(e) On the forward section of the MLG door, remove the material from PT C

to PT D to a maximum of 0.08 in. (2.0 mm) (refer to Figure 14, Sheet 2,

View H). Make sure that there is a minimum edge distance of 0.23 in.

(6.0 mm) from the fasteners.

(f) On the forward section of the MLG door at PT D, make a radius of 0.25

in.(6.35 mm) at the end of the corner

(refer to Figure 14, Sheet 2, View H).

(g) Clean the bare surfaces of the edge of the inboard MLG door with clean

dry cloths, with no lint, moist with aliphatic naphta or equivalent.

(h) Dry the bare surfaces with clean dry cloths with no lint.
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(i) Apply chemical conversion compound or equivalent on the cut area of

the inboard MLG door (refer to SRM 51-21-11-001-001).

(j) On the upper forward section of the MLG fairing, between PTA and PTB,

remove material up to a maximum of 0.23 in. (5.8 mm) (refer to Figure

14, Sheet 1, View C) (refer to SRM 51-75-00-001-001). Make sure that

there is a minimum edge distance of 0.42 in (10.7 mm) from the

fasteners.

(k) On the forward lower section of the MLG fairing between PT B and PT C,

remove material to a maximum of 0.16 in. (4.1 mm) (refer to Figure 14,

Sheet 1, View D) (refer to SRM 51-75-00-001-001). Make sure that there

is a minimum edge distance of 0.57 in (14.5 mm) from the fasteners.

(l) On the aft section of the MLG fairing between PT D and PT E, remove

the material to a maximum of 0.10 in. (2.5 mm) (refer to Figure 14, Sheet

1, View C) (refer to SRM 51-75-00-001-001). Make sure that there is a

minimum edge distance of 0.42 in. (10.7 mm) with the fasteners.

(m) On the aft section of the MLG fairing between PT E and PT F, remove the

material to a maximum of 0.10 in. (2.5 mm). (refer to Figure 14, Sheet 1,

View C) (refer to SRM 51-75-00-001-001). Make sure that there is a

minimum edge distance of 0.57 in. (14.5 mm) with the fasteners.

Refer to Figure 15.

For aircraft that have not had the forward fairing seal (11) incorporated with Service

Bulletin 670BA-32-030

(51) Install the forward fairing seal (11), the upper seal retainer (13), the lower seal

retainer (14) and the fairing safety-guide (12) as follows:

(a) Temporary install and secure the fairing forward seal (11) and the

retainer seal (5) on the MLG fairing (refer to Figure 15, Sheet 1, View B)

(pre-mod).

(b) Backdrill the holes from the MLG fairing through the fairing forward seal

(11) to a diameter of 0.165 to 0.169 in. (4.19 to 4.29 mm).

(c) Remove the fairing forward seal (11) and the seal retainer (5).

(d) Remove the burrs from the forward seal (11).
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For aircraft that had the forward fairing seal (11) incorporated with Service Bulletin

670BA-32-030

(52) Do a detail inspection on the fairing forward seal (11) for signs of cuts or

damages in the material base.

NOTE: For the MLG fairing seal (11) exterior low friction polyester fabric is not

part of the base rubber material rejection criteria.

For all aircraft

(53) Temporary install and secure the aft fairing seal (10) to the seal retainer (9)

(refer to Figure 15, Sheet 2, View D).

(a) Backdrill the holes from the seal retainer (9) through the aft fairing

seal (10) to a diameter of 0.165 to 0.169 in. (4.19 to 4.29 mm).

(b) Remove the aft fairing seal (10) and the seal retainer (9).

(c) Remove the burrs from the aft fairing seal (10).

(54) Temporary install and secure the fairing forward seal (11), the seal retainer (5)

and the fairing safety-guide (12) on the MLG fairing (refer to Figure 15, Sheet

1, View B, (pre-mod).

(a) Make the upper seal retainer (13) and lower seal retainer (14) from the

seal retainer (5) as follows:

1 Make a line on the seal retainer (5) at the two ends of the fairing

safety-guide (12) (refer to Figure 15, Sheet 1, View B, (Pre-Mod).

2 Make sure that the maximum and the minimum clearance between

the seal retainer (5) and the fairing safety-guide (12) is 0.13 to 0.07

in. (2.54 to 1.78 mm).

3 Remove the fairing safety-guide (12), the seal retainer (5) and the

fairing forward-seal (11).

4 Make sure that there is a minimum edge distance of 0.39 in.

(9.9 mm) at the two ends of the seal retainer (5).

5 Cut the seal retainer (5) at the cutting line (refer to SRM

51-71-00-001-001).

6 Do a radius of 0.25 in (6.3 mm) on the upper and lower seals (refer

to Figure 15, Sheet 1, View B) (pre-Mod).
SERVICE BULLETIN 670BA---32---040

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7 Temporarily identify the two seal retainers as follows:

a Identify the upper seal retainer as item (13).

b Identify the lower seal retainer as item (14).

c Discard the middle part of the seal retainer (5).

(55) Temporary install and secure the fairing forward seal (11), the upper seal

retainer (13), the lower seal retainer (14), and the fairing safety-guide (12) on

the MLG fairing.

(56) Make sure that there is a minimum of 0.03 in. (0.76 mm) of protrusion with the

fairing safety-guide (12) and the edge of the MLG fairing (refer to Figure 15,

Sheet 1, View C-C).

(57) Make sure that the distance between the fastener hole of the fairing

safety-guide (12) and the rebate of the MLG fairing is at minimum of 0.340 in.

(1.8 mm).

(58) Drill two holes from the pilot holes of the fairing safety-guide (12) through the

fairing forward seal (11) and the forward fairing to a diameter of 0.097 to 0.100

(2.46 to 2.54 mm).

(59) Increase the diameter of the two holes from the pilot holes of the fairing

safety-guide (12) through the fairing forward seal (11) and the forward fairing

to 0.165 to 0.169 in. (4.19 to 4.29 mm).

(60) Backdrill four holes from the MLG fairing through the fairing forward seal (11)

and the fairing safety-guide (12) to a diameter of 0.165 to 0.169 in. (4.19 to

4.29 mm).

(61) Do a countersink of the two new holes in the MLG fairing to a diameter of

0.331 to 0.342 in. (8.41 to 8.69 mm) for the two bolts (1), (refer to Sheet 1,

View B).

(62) Remove the fairing safety-guide (12), the upper seal retainer (13), the lower

seal retainer (14), and the fairing forward seal (11).

(63) Remove burrs from the fairing safety-guide (12), the fairing forward seal (11)

and the MLG fairing.
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(64) Clean the fairing forward seal (11) and the fairing safety-guide (12), the upper

seal retainer (13), the lower seal retainer (14) and the MLG fairing with clean,

dry cloths with no lint, moist with aliphatic naphta or equivalent.

(65) Dry the outer fairing forward-seal (11) and the fairing safety-guide (12), the

upper seal retainer (13), the lower seal retainer (14) and the MLG fairing with

clean, dry cloths with no lint.

(66) Apply chemical conversion compound or equivalent on the bare metal

surfaces of the upper seal retainer (13), the lower seal retainer (14) and the

fairing safety-guide (12) (refer to SRM 51-21-11-001-001).

(67) Apply epoxy primer on the bare surfaces of the upper seal retainer (13), the

lower seal retainer (14) and the fairing safety-guide (12)

(refer to SRM 51-25-06-001-001).

(68) Apply fluid resistant enamel, color grey No.16473, on the upper seal retainer

(13), the lower seal retainer (14) and the fairing safety-guide (12) (refer to SRM

51-25-16-001-001).

(69) Apply composite-laminate coating on the bare surfaces of the MLG fairing

(refer to SRM 51-25-52-001-001).

(70) Apply epoxy primer in the countersunk holes of the MLG fairing and on the

bare surfaces (refer to SRM 51-25-06-001-001).

(71) Install the fairing forward seal (11), the fairing safety-guide (12), the upper seal

retainer (13) and the lower seal retainer (14) as follows:

(a) Install and secure the fairing forward seal (11), the fairing safety-guide

(12), the upper seal retainer (13) and the lower seal retainer (14) on the

MLG fairing.

(b) With sealant, install the bolt (15) through the MLG fairing and the

MLG fairing seal (refer to SRM 51-41-02-001-001).

(c) Wet-install the bolts (1) through the MLG fairing with the washers (3) and

the nuts (2) (refer to Figure 15, Sheet 1, View B)

(refer to SRM 51-41-02-001-001).

(d) Torque the nuts (2) and the screw (15) (refer to AMM 20-21-00-910-801).

(72) Install the seal (7) and the seal retainer (8) as follows:

(a) Clean the seal retainer (7), the seal (8) and the aft area of the MLG with

clean, dry cloths with no lint moist with aliphatic naphta or equivalent.
SERVICE BULLETIN 670BA---32---040

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(b) With sealant, install the bolts (1) through the MLG fairing, the seal (8),

the seal retainer (7), the washers (3) and the nuts (2)

(refer to SRM 51-23-00-390-810).

(c) Torque the nuts (2) (refer to AMM 20-21-00-910-801).

(73) Install the seal (10) and the seal retainer (9) as follows:

(a) Clean the seal retainer (9), the seal (10) and the aft area of the MLG with

clean, dry cloths with no lint moist with aliphatic naphta or equivalent.

(b) With sealant, wet install the bolts (6) through the MLG fairing, the seal

(10), the seal retainer (9), the washers (3) and the nuts (2)

(refer to SRM 51-23-00-001-001).

(c) Torque the nuts (2) (refer to AMM 20-21-00-910-801).

(d) Clean the area of the forward and the aft MLG fairing with clean, dry

cloths with no lint, moist with aliphatic naphta or equivalent.

(e) Dry the area with clean, dry cloths with no lint.

Refer to Figure 16.

(74) Identify the left inboard MLG door as follows:

(a) Carefully remove the identification plate (1) from the inboard inner skin

with a plastic or phenolic scraper.

(b) Clean the inboard inner skin with clean, dry cloths with no lint, moist with

aliphatic naphta or equivalent.

(c) Dry the forward inboard inner-skin with clean, dry cloths with no lint.

(d) If necessary, apply epoxy primer on the inboard inner skin (refer to SRM

51-25-06-001-001).

(e) If necessary, apply fluid resistant enamel, color grey No.16473, on the

inboard inner skin (refer to SRM 51-25-16-001-001).
SERVICE BULLETIN 670BA---32---040

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(f) Write the data on the new identification plate (1) as follows:

1 On the new identification plate, write with a indelible ink pen or

equivalent in the field DWG.NO: the data that follows:

PRE-SB PART NUMBER POST-SB PART NUMBER

CC670-10520-967 KBA670-10500-23

CC670-10520-2011 KBA670-10500-25

CC670-10520-2013 KBA670-10500-27

CC670-10520-2015 KBA670-10500-29

CC670-10520-13 KBA670-10500-31

KCC670-10900-1 KBA670-10500-33

KCC670-10900-3 KBA670-10500-35

KCC670-10900-5 KBA670-10500-37

KCC670-10901-1 KBA670-10500-51

KCC670-10901-3 KBA670-10500-53

2 With a indelible ink pen or equivalent, write all the other information

(model, serial number, date) from the removed identification plate

(1) to the new identification plate (1).

(g) Discard the removed identification plate (1).

(h) Install the new identification plate (1) on the MLG door as follows:

1 Put the new identification plate (1) in position (refer to Figure 16,

View B).

2 Apply adhesive Magnobond 6380 or equivalent on the mating

surface of new identification plate (1) and inboard inner skin

(refer to SRM 51-22-00-001-001).

3 Install the new identification plate (1) in the correct position on the

inboard inner skin, (refer to Figure 16, View B).

4 Carefully remove unwanted adhesive with a spatula and/or a plastic

or phenolic scraper.

5 Apply a layer clear-gloss fluid resistant enamel on the new

identification plate (1) (refer to SRM 51-25-16-001-001).
SERVICE BULLETIN 670BA---32---040

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Refer to Figure 5.

(75) With a indelible ink pen or equivalent, identify the aft member of the inboard

MLG door (refer to Figure 5, Sheet 3, View F) and AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

CC670-10571-13 KBA670-10500-45

Refer to Figure 7.

(76) With an indelible ink pen or equivalent, identify the aft stop-fitting (1) of the

MLG fairing (refer to AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

CC670-39076-1 KBA670-10500-39

(77) If only PART A is done, with a indelible ink pen or equivalent, identify the left

MLG fairing with the applicable part number listed in the table below (refer to

AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

BA670-00001-2085 KBA670-10500-300

CC670-39005-951 KBA670-10500-500

CC670-39005-3 KBA670-10500-700

CC670-39005-5 KBA670-10500-130

CC670-39019-49 KBA670-10500-190

CC670-39019-963 KBA670-10500-150

CC670-39019-965 KBA670-10500-170

CC670-39019-51 KBA670-10500-210

KBA670-39005-3 KBA670-10500-610

KBA670-39005-5 KBA670-10500-630

KBA670-39005-7 KBA670-10500-650

KBA670-39005-9 KBA670-10500-670
SERVICE BULLETIN 670BA---32---040

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(78) If PART A and PART B are done or PART A and PART D are done, with a

indelible ink pen or equivalent, identify the MLG fairing assembly with the

applicable part number listed in the table below (refer to AMM

20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

BA670-00001-2085 KBA670-10500-3

CC670-39005-951 KBA670-10500-5

CC670-39005-3 KBA670-10500-7

CC670-39005-5 KBA670-10500-13

CC670-39019-49 KBA670-10500-19

CC670-39019-963 KBA670-10500-15

CC670-39019-965 KBA670-10500-17

CC670-39019-51 KBA670-10500-21

KBA670-39005-3 KBA670-10500-61

KBA670-39005-5 KBA670-10500-63

KBA670-39005-7 KBA670-10500-65

KBA670-39005-9 KBA670-10500-67

(79) Apply a bead of sealant on the aft stop-fitting (1) and the sealing member

(refer to Figure 7, Sheet 2, View C) (refer to SRM 51-23-00-001-001).

(80) Apply epoxy primer on the rivets (4) and (5), bolts (2) and nuts (3). (refer to

SRM51-25-06-001-001).

(81) Apply fluid resistant enamel, color grey No.16473, on the bolt (2), the nut (3)

and the rivets (4) and (5) (refer to SRM 51-25-16-001-001).

(82) Apply fluid resistant enamel on the bolts (2). Refer to the external paint

scheme for the color (refer to SRM 51-25-16-001-001).
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Refer to Figure 9.

(83) Apply aerodynamic sealant between the aft seal (3) and the MLG door (refer

to Figure 9, Sheet 2, View E and SRM 51-23-00-001-001).

(84) Apply epoxy primer on the aerodynamic sealant between the aft seal (3) and

the MLG door (refer to SRM 51-25-06-001-001).

(85) Apply fluid resistant enamel, color grey No.16473, on the aerodynamic sealant

between the aft seal (3) and the MLG door

(refer to SRM 51-25-16-001-001).

(86) Apply fluid resistant enamel on the aerodynamic sealant between the aft seal

(3) and the MLG door. Refer to the external paint scheme for the color (refer to

SRM 51-25-16-001-001).

Refer to Figure 11.

(87) With a indelible ink pen or equivalent, identify the forward member of the

inboard MLG door (refer to AMM 20-60-13-930-801).

NOTE: The identification of the forward member must be done with the MLG

door POST-SB number.

MLG DOOR POST-SB

PART NUMBER

FORWARD MEMBER

POST-SB PART NUMBER

KBA670-10500-25

KBA670-10500-27

KBA670-10500-29

KBA670-10500-35

KBA670-10500-37

KBA670-10500-47

MLG DOOR POST-SB

PART NUMBER

FORWARD MEMBER

POST-SB PART NUMBER

KBA670-10500-23

KBA670-10500-31

KBA670-10500-33

KBA670-10500-51

KBA670-10500-53

KBA670-10500-49
SERVICE BULLETIN 670BA---32---040

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(88) If necessary, apply aerodynamic sealant in the area (refer to Figure 11, Sheet

3, View D) (refer to SRM 51-23-00-001-001).

(89) If necessary apply epoxy primer on the aerodynamic sealant on the forward

member (refer to SRM 51-25-06-001-001).

(90) If necessary apply fluid resistant enamel, color grey No.16473, on the

aerodynamic sealant of the forward member

(refer to SRM51-25-16-001-001).

Refer to Figure 15.

(91) Identify the seal retainers (13) and (14) with the applicable part number listed

in the table below (refer to AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

Seal retainer CC670-39245-1 Upper seal retainer

KBA670-10500-41

Lower seal retainer

KBA670-10500-43

Refer to Figure 17.

(92) If removed, do the installation of the left inboard MLG door

(refer to AMM 32-12-01-400-802).

(93) Do a clearance check of the left MLG doors

(refer to AMM 32-12-01-220-801).

NOTE: Use the post service bulletin 670BA-32-040 task to do the clearance

check.

NOTE: If you cannot get the final steps and gaps to agree with AMM TASK

32-12-01-220-801, AFM CDL # 32---12 (Main Landing Gear Door ---

Inboard Door) can be done. This service bulletin can be completed

when the requirements of step 2.B.(93) are met.

(94) Do the extension of the MLG (refer to AMM 32-12-01-220-801).

(95) If it is not possible to complete all the instructions in this service bulletin

because of the configuration of the aircraft, speak with a representative of

Bombardier Customer Response Centre at phone number 514---855---8500 or

send an e-mail at thd.crj@bombardier.com for analysis and to get an

approved disposition to complete this service bulletin.
SERVICE BULLETIN 670BA---32---040

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C. Job Close-Out

(1) Remove all tools, equipment, and unwanted materials from the work area.

(2) Install left MLG door-hinge fairing 542AB

(refer to AMM 57-80-85-400-802).

(3) If removed, install the left MLG wheel bin

(refer to AMM 53-83-89-400-801).

(4) Remove the tags and close the circuit breakers that follow:

CB PANEL CB NO. NAME

CBP-1 A12 HEATERS TAT

CBP-1 A13 HEATERS AOA R

CBP-1 A14 HEATERS PITOT R

CBP-1 C13 ADG HEATER

CBP-1 G1 PSEU CH A

CBP-1 G2 NOSE STEER

CBP-1 G13 HEATERS ADS CONT 2

CBP-1 G14 HEATERS STATIC R

CBP-1 LOWER T7 HEATERS PITOT L

CBP-1 LOWER T8 HEATERS AOA L

CBP-1 LOWER T9 HEATERS PITOT STBY

CBP-1 LOWER U7 ENG IGN A

CBP-2 G1 PSEU CH B

CBP-2 G2 NOSE STEER

CBP-2 N6 ADG DEPLOY AUTO

CBP-2 N9 MLG BAYOVHT DET

CBP-2 P1 PSEU CH A

CBP-2 P2 PSEU CH B

CBP-2 LOWER S1 HEATERS STATIC L
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CB PANEL CB NO. NAME

CBP-2 LOWER S2 HEATERS ADS CONT 1

CBP-2 LOWER S3 HEATERS ADS CONT STBY

CBP-5 B10 ENG IGN B

(5) If the left wheel bin was removed, do the operational test of the MLG overheat

detection and warning system (refer to AMM 26-14-04-710-801).

(6) Do the lubrication of the MLG and the MLG door

(refer to AMM 12-20-32-640-802).

(7) Do the operational test of the landing-gear extension/retraction system

(refer to AMM 32-30-00-710-801).

(8) Remove the aircraft from jacks (refer to AMM 07-11-01-586-801).

(9) Make sure that step 2. B (93) of PART A is completed and meet the

requirements before you do the entry in the applicable logbooks.

(10) When PART A of this service bulletin is completed, add the weight and

balance data shown in paragraph 1.I. of this service bulletin to the Weight and

Balance Manual. Under ‘Description of Change’ enter “Service Bulletin

670BA-32-040 PART A, Revision E, incorporated.”

(11) When PART A of this service bulletin is completed, make this entry in the

applicable logbooks: “Service Bulletin 670BA-32-040, Revision E, Landing

Gear - Main Landing Gear (MLG) and Doors - Increase the Clearances

Between the MLG Fairing and the MLG Doors, PART A , incorporated.”
SERVICE BULLETIN 670BA---32---040

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PART B --- Increase of the Clearance Between the Right MLG Inboard-Door and the MLG

Fairing

D. Job Set-Up

Reference Information

REFERENCE DESIGNATION

AMM 07-11-01-582-801 Jacking of the Aircraft

AMM 07-11-01-586-801 Lowering of the Aircraft

AMM 10-11-00-400-801 Installation of the Nose Landing Gear (NLG)

Lockpin

AMM 10-11-00-400-802 Installation of the Main Landing Gear (MLG)

Lockpins

AMM 12-00-00-867-801 Standard Aircraft Configuration for Maintenance

AMM 12-20-32-640-802 Lubrication of the Main Landing Gear (MLG)

AMM 20-21-00-910-801 Torquing of Threaded Fasteners

AMM 20-31-00-400-801 Thermal Installation of Interference

Fit Bushings

AMM 20-51-00-000-801 Removal of Cotter Pins

AMM 20-51-00-000-802 Removal of Lockwire

AMM 20-51-00-400-801 Installation of Cotter Pins

AMM 20-51-00-400-802 Installation of Lockwire

AMM 20-60-13-930-801 Identification of Aircraft Parts and Assemblies

AMM 32-12-01-000-802 Removal of the Inboard MLG Doors

AMM 32-12-01-220-801 Clearance Check of the MLG Doors

AMM 32-12-01-400-802 Installation of the Inboard MLG Doors

AMM 32-12-01-820-801 Adjustment of the MLG Doors

AMM 32-30-00-710-801 Operational Test of the Landing-Gear Extension/

Retraction System

AMM 51-23-00-100-801 Removal of Sealants
SERVICE BULLETIN 670BA---32---040

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REFERENCE DESIGNATION

AMM 57-80-85-000-802 Removal of the Main Landing Gear Door-Hinge

Fairing (542AB/642AB)

AMM 57-80-85-400-802 Installation of the Main Landing Gear DoorHinge Fairing (542AB/642AB)

NDT 51-20-006-250 Eddy Current - Inspection Procedures

NDT 51-20-008-230 Liquid Penetrant - Inspection Procedures

NDT 51-20-009-210 Visual - Inspection Procedures

SRM 51-21-11-001-001 Corrosion Prevention Procedures

SRM 51-21-16-001-001 Finish Codes

SRM 51-23-00-001-001 Pressure, Environmental, Fuel Tank and Firewall

Sealing

SRM 51-25-06-001-001 Fluid-Resistant (FR) Epoxy Primer

SRM 51-25-16-001-001 Fluid-Resistant (FR) Polyurethane Topcoat

SRM 51-25-52-001-001 Composite-Laminate Coatings

SRM 51-26-00-001-001 Cleaning

SRM 51-40-06-001-001 Fastener Edge Distance and Pitch

SRM 51-40-11-001-001 Preparation of Fastener Holes

SRM 51-41-02-001-001 Bolts, Screws and Related Items

SRM 51-42-06-001-001 Solid Rivets

SRM 51-42-13-001-001 CherryMax and CherryMax A Blind Rivets

SRM 51-42-21-001-001 Hi-Lite Fasteners

SRM 51-71-00-001-001 Typical Structural Repairs

SRM 51-75-00-001-001 Graphite Repairs
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Tolerance Information

Linear Tolerances Angular Tolerance

X.XX in. (X.X mm) X.X in. (X mm)

+/-0 30” +/- 0.03 in. +/- 0.1 in.

+/- 0.8 mm +/- 3 mm

NOTE: The tolerances above apply to the dimensions given in this service

bulletin, except when specified differently.

(1) Make sure that the aircraft is in standard configuration for maintenance

(refer to AMM 12-00-00-867-801).

WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO

MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC

EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS,

INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN

OCCUR.

(2) Open, safety, and tag the circuit breakers that follow:

CB PANEL CB NO. NAME

CBP-1 A12 HEATERS TAT

CBP-1 A13 HEATERS AOA R

CBP-1 A14 HEATERS PITOT R

CBP-1 C13 ADG HEATER

CBP-1 G1 PSEU CH A

CBP-1 G2 NOSE STEER

CBP-1 G13 HEATERS ADS CONT 2

CBP-1 G14 HEATERS STATIC R

CBP-1 LOWER T7 HEATERS PITOT L

CBP-1 LOWER T8 HEATERS AOA L

CBP-1 LOWER T9 HEATERS PITOT STBY

CBP-1 LOWER U7 ENG IGN A

CBP-2 G1 PSEU CH B

CBP-2 G2 NOSE STEER
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CB PANEL CB NO. NAME

CBP-2 N6 ADG DEPLOY AUTO

CBP-2 N9 MLG BAYOVHT DET

CBP-2 P1 PSEU CH A

CBP-2 P2 PSEU CH B

CBP-2 LOWER S1 HEATERS STATIC L

CBP-2 LOWER S2 HEATERS ADS CONT 1

CBP-2 LOWER S3 HEATERS ADS CONT STBY

CBP-5 B10 ENG IGN B

(3) Put the aircraft on jacks (refer to AMM 07-11-01-582-801).

(4) Remove the MLG door-hinge fairing 642AB (refer to AMM 57-80-85-000-802).

(5) If necessary, remove the right MLG wheel bin (refer to AMM

53-83-89-000-801).

(6) If necessary, remove the right inboard MLG door (refer to AMM

32-12-01-000-802).
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E. Procedure

For all aircraft

Refer to Figure 1.

(1) Do a detailed visual inspection of the right section of the MLG fairing as

follows (refer to NDT 51-20-009-210):

(a) Visually inspect to make sure that the forward and the aft stops are not

missing from the MLG fairing.

(b) If the forward and/or the aft stops are not missing, visually inspect that

there are no loose or missing fasteners from the forward and aft stops.

(c) Visually inspect along the edge of the MLG fairing adjacent the MLG

door to make sure that there is no damage. Refer to the shaded area

(refer to Figure 1, Sheet 2).

NOTE: For this inspection, damage does not include surface scratches and/or

paint deterioration.

(d) Record the findings on the record sheet of the Appendix A.

Refer to Figure 2.

(2) Do a detailed visual inspection of the right MLG inboard door as follows

(refer to NDT 51-20-009-210):

(a) Visually inspect the MLG inboard door to make sure that there is no

missing or broken roller (2) or missing stop (1).

(b) If the stop (1) is not missing, visually inspect that there are no loose or

missing fasteners from the stop (1).

(c) Record the findings on the record sheet of Appendix A.

(d) Visually inspect that the stops (3), (4) and (5) are not damaged.

(e) Visually inspect that there are no loose or missing fasteners from the

stops (3), (4) and (5).

(f) Visually inspect along the edge of the MLG inboard door adjacent to the

MLG fairing to make sure that there is no damage. Refer to the shaded

area (refer to Figure 2, Sheets 3 and 4).

NOTE: For this inspection, damage does not include surface scratches and/or

paint deterioration.

(g) Record the findings on the record sheet of Appendix A.
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Refer to Figure 3.

(3) Do a detailed visual inspection of the stops (1) and (2), and the wedge (3) on

the right side of the forward and the aft spars as follows (refer to NDT

51-20-009-210):

(a) Visually inspect to make sure that the stops (1) and (2) are not missing.

(b) If the stops (1) and/or (2) are not missing, visually inspect that there are

no loose or missing fasteners from the stops (1) and/or (2).

(c) Visually inspect to make sure that the wedge (3) is not missing.

(d) If the wedge (3) is not missing, visually inspect that there are no loose or

missing fasteners from the wedge (3).

(e) Record the findings on the record sheet of Appendix A.

Refer to Figures 1, 2 and 3.

(4) If damage is found and/or there are missing parts and/or fasteners, speak

with a representative of the Customer Response Center (CRC) at phone

number 514-855-8500 for a disposition.

NOTE: Refer to the record sheet of Appendix A for data.

(5) If no damage is found and there is no missing part or fastener, go to the next

step.

NOTE: Refer to the record sheet of Appendix A for data.

Refer to Figure 4.

(6) Remove the roller assembly as follows:

WARNING: WHEN YOU CUT THE COTTER PIN, USE EYE PROTECTION.

PIECES THAT BREAK OFF CAN CAUSE INJURY.

(a) Remove and discard the cotter pin (2) (refer to AMM 20-51-00-000-802).

(b) Remove and discard the nut (3).

(c) Remove and discard the bolt (4), the three washers (5), the bushing (6),

and the roller (1).
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Refer to Figure 5.

(7) Install the new roller assembly as follows:

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(a) Install the drill jig (1) on the aft member of the inboard MLG door as

follows:

1 Make sure that the dowel pin of the drill jig (1) touches the aft

member of the inboard MLG door

(refer to Figure 5, Sheet 1, View B).

2 Make sure that the surface of the drill jig (1) touches the aft

member assembly (refer to Figure 5, Sheet 1, View C).

(b) With the drill bushing (2) and core drill P/N 670BA32040K90-201,

increase the diameter for the holes in the two lugs of the aft member to a

diameter of between 0.2959 in. (7.515 mm) and 0.2969 in. (7.541 mm).

(c) With the reamer bushing (3) and reamer P/N 670BA32040K90-202, ream

the holes of the two lugs in the aft member to a diameter of between

0.3147 in. (7.993 mm) and 0.3149 (7.998 mm).

(d) Remove the drill jig (1) from the inboard MLG door.

(e) Remove burrs and sharp edges from the holes of the lugs in the aft

member of the inboard MLG door.

(f) Make sure that the final diameter of the inboard hole in the aft member is

between 0.3147 and 0.3157 in (7.99 to 8.02 mm).

(g) Make sure that the final diameter of the outboard hole in the aft member

is between 0.3141 and 0.3159 in (7.98 to 8.02 mm).

(h) Apply chemical conversion coating on the bare metal surfaces of the

bores of the two lugs of the aft member (refer to SRM 51-21-11-001-001).
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WARNING: OBEY THE PRECAUTIONS THAT FOLLOW, WHEN YOU

USE DRY ICE:

- USE APPROVED EYE, MOUTH, AND BODY

PROTECTION.

- DO THE WORK IN AN AREA THAT HAS A GOOD FLOW

OF CLEAN AIR.

- DO NOT TOUCH MATERIAL THAT HAS TOUCHED DRY

ICE.

- OBEY THE MANUFACTURER’S INSTRUCTIONS.

- DO NOT LET THE DRY ICE TOUCH YOUR SKIN, EYES,

OR MOUTH.

- ONLY PUT DRY ICE IN AN APPROVED CONTAINER

THAT IS MADE FOR HIGH PRESSURES.

- IF IRRITATION OCCURS, GET MEDICAL AID

IMMEDIATELY.

DRY ICE IS POISONOUS AND CAN CAUSE INJURY TO

PERSONS.

WARNING: OBEY THE PRECAUTIONS THAT FOLLOW WHEN YOU

USE LIQUID NITROGEN:

- USE SAFETY GOGGLES.

- PUT ON PROTECTIVE CLOTHING.

- DO NOT LET THE LIQUID NITROGEN TOUCH YOUR

SKIN, EYES, AND MOUTH.

- WORK IN AN AREA THAT HAS A GOOD FLOW OF

CLEAN AIR.

- OBEY THE MANUFACTURER’S INSTRUCTIONS.

- GET MEDICAL AID IF YOU GET LIQUID NITROGEN ON

YOUR SKIN OR IN YOUR EYES OR MOUTH.

LIQUID NITROGEN IS VERY COLD -195 DEGREES C (77K).

IT WILL FREEZE IMMEDIATELY AND WILL CAUSE

DAMAGE TO SKIN, EYES OR LUNGS. IN SUFFICIENT

QUANTITIES, THE NITROGEN GAS FROM THE LIQUID

NITROGEN CAN ALSO REPLACE THE OXYGEN OF THE

AMBIENT AIR. THIS CAN CAUSE INJURY TO PERSONS.

(i) Use liquid nitrogen or solid carbon dioxide (dry ice) to do a thermal

installation of the flange bushing (7) (refer to AMM-20-31-00-400-801).

(j) With MIL-PRF-81733 type IV corrosion-inhibiting compound, wet-install

the flanged bushing (7) in the inboard lug of the aft member (refer to

Figure 5, Sheet 2, View D and SRM 51-23-00-001-001).
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(k) Do a fillet seal around the flanged bushing (7) (refer to Figure 5, Sheet 2,

View D and SRM 51-23-00-001-001).

(l) Wet-install the bushing (6) with Mastinox 6856K or CA 1000 compound

through the outboard lug (refer to Figure 5, Sheet 3, View G-G and SRM

51-21-11-001-001).

(m) Make sure that no compound is between the bushing (6) and the roller

(5).

(n) Apply Aeroshell 33 grease or equivalent on the shank of the bolt (11).

(o) Install the bolt (11) with the washer (9), through the outboard lug, the

bushing (6), the roller(5), the flanged bushing (7) and the inboard lug of

the aft member.

(p) Install the washer (12) and the nut (8).

NOTE: It is not permitted to replace the washer (12) for a thinner washer.

(q) Torque the nut (8) (refer to AMM 20-21-00-910-801).

(r) Safety the nut (8) with the cotter pin (10)

(refer to AMM 20-51-00-400-801).

(s) Make sure there is a minimum clearance between the aft member and

the roller (5) of 0.030 in. (0.76 mm).

Refer to Figure 6.

(8) Remove and discard the aft fairing seal (4) and the aft retainer seal (5) from

the fairing as follows:

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(a) Remove and discard the three bolts (1), the washers (2) and the nuts

(3).

(b) Remove and discard the seal aft fairing (4) and the aft retainer seal (5)

from the fairing.
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(9) Remove the aft stop-fitting (14) as follows:

(a) Remove the two bolts (6), the washers (10), and the nuts (11).

(b) Remove and discard the stop pad (7), the laminated shim (8) and the

shim (9).

(c) Remove the sealant from the aft stop-fitting (14) and the sealing member

(refer to Figure 6, Sheet 1, View D) (refer to AMM 51-23-00-100-801).

(d) Remove the three solid rivets (17).

(e) Remove and discard the bolts (12) and the nuts (13).

(f) Remove the aft stop-fitting (14) from the sealing member.

(g) Remove the sealant from the MLG fairing, the sealing member and on

the aft stop-fitting (14) (refer to AMM 51-23-00-100-801).

(10) Drill the aft stop-fitting (14) as follows:

(a) Temporarily install the shim fairing (15) on the aft stop-fitting (14). Make

sure that the shim fairing (15) is parallel to the edge of the aft stop-fitting

(14) (refer to Figure 6, Sheet 2, View E).

(b) Attach the shim fairing (15) with the bolt (6), the washer (10) and the nut

(11).

(c) Backdrill one hole to a diameter of 0.190 to 0.194 in (4.83 to 4.93 mm)

from the shim fairing (15) to the aft stop-fitting (14).

(d) Remove and discard the nut (11).

(e) Remove the bolt (6), the washer (10) and the shim fairing (15).

(f) Temporarily install the shim fairing (15) on the laminated shim (16).

(g) Increase the diameter of two holes in the shim fairing (15) and the

laminated shim (16) to 0.213 to 0.217 (5.41 to 5.51 mm).

(h) Disassemble and remove burrs and sharp edges from the holes of the

shim fairing (15), the laminated shim (16), and the aft stop-fitting (14).

(i) Clean the bare metal surfaces of the aft stop-fitting (14) with clean dry

cloths, with no lint, moist with aliphatic naphta or equivalent.
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(j) Dry the bare surfaces with clean dry cloths with no lint.

(k) Apply chemical conversion compound on the bare metal surfaces of the

hole in the aft stop-fitting (14) (refer to SRM 51-21-11-001-001).

(l) Touch-up the hole in the aft stop-fitting (14) with epoxy primer

(refer to SRM 51-25-06-001-001).

(m) Touch-up the hole in the aft stop-fitting (14) with fluid resistant enamel

color grey #16473 (refer to SRM 51-25-16-001-001).

Refer to Figure 7.

(11) Remove 0.53 in. to 0.61 in. (13.4 to 15.5 mm) of material from the aft area of

the MLG fairing (refer to Figure 7, Sheet1, View D and SRM

51-71-00-001-001).

NOTE: An edge distance of 0.57 in (14.50 mm) for the three holes of the aft

stop-fitting (1) is necessary.

(12) Install the aft stop-fitting (1) as follows:

(a) Apply sealant on the mating surface of the aft stop-fitting (1) (refer to

SRM 51-23-00-001-001).

(b) Install the aft stop-fitting (1) on the sealing member of the MLG fairing.

(c) Wet-install the two upper rivets (5) on the aft stop-fitting (1) (refer to

Figure 7, View C) (SRM 51-42-06-001-001 and SRM 51-23-00-001-001).

(d) Wet-install one rivet (4) at the bottom of the aft stop-fitting (1) (refer to

Figure 7, View C) (SRM 51-42-06-001-001 and SRM 51-23-00-001-001).

(e) Wet-install the three bolts (2) and the nuts (3)

(refer to SRM 51-42-21-001-001 and SRM 51-23-00-001-001).

NOTE: The installation of the stop pad (7), the laminated shim (8), and the

shim (9) will be incorporated in a subsequent step during the

clearance check.
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Refer to Figure 8.

WARNING: MAKE SURE THAT THE LOCKPINS ARE INSTALLED IN THE NOSE AND

MAIN LANDING GEAR. THE NOSE AND MAIN LANDING GEAR CAN

ACCIDENTALLY RETRACT AND CAUSE INJURY TO PERSONS AND/OR

DAMAGE TO EQUIPMENT.

(13) Disconnect the rod end (13) from the MLG door as follows:

CAUTION: WHEN YOU CUT THE COTTER PIN, USE EYE PROTECTION. PIECES

THAT BREAK OFF CAN CAUSE INJURY.

(a) Remove and discard the cotter pin (7) (refer to AMM 20-51-00-000-801).

CAUTION: MAKE SURE THAT A PERSON HOLDS THE MLG DOOR

ASSEMBLY IN POSITION WHEN YOU DISENGAGE THE DOOR

RODS (13). IT CAN CAUSE INJURY TO PERSONS AND/OR

DAMAGE TO EQUIPMENT.

(b) Remove the nut (8), the washer (9), the bushing (12), the washer (10)

and the pin (11).

(c) Lower the inboard section of the MLG door assembly against the

adjacent tire.

Refer to Figure 9.

(14) Replace the aft seal of the MLG door as follows:

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(a) Remove the three rivets (1) and the two washers (2) from the MLG

inboard door (refer to Figure 9, Sheet 1, View B).

(b) Remove the three rivets (1) and the washers (2) from the MLG inboard

door (refer to Figure 9, Sheet 1, View C).

(c) Remove and discard the aft seal of the MLG door.

(d) Make sure that the holes are not damaged or elongated.
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(e) If the holes are damaged or elongated, increase the diameter of the hole

to a maximum of 0.261 in. ( 6.63 mm)

(refer to Figure 9, Sheet 3, Table 1).

--- 0.176 to 0.180 in. (4.47 to 4.57 mm)

--- 0.192 to 0.196 in. (4.88 to 4.98 mm)

--- 0.205 to 0.209 in. (5.21 to 5.31 mm)

--- 0.256 to 0.261 in. (6.50 to 6.63 mm)

(f) Make sure that there is a minimum of 1.2D of edge distance on the aft

seal (3) and the inboard MLG door before drill.

(g) If necessary increase the diameter of the hole in the washer (6) and/or

(7) as follows:

DIAMETER OF

FASTENER HOLE

DIAMETER OF

WASHER HOLE

WASHER ITEM

NUMBER

0.176 TO 0.180 in.

(4.47 TO 4.57 mm)

N/A (6)

0.192 TO 0.196 in.

(4.88 TO 4.98 mm)

0.214 TO 0.218 in.

(5.44 TO 5.54 mm)

(6)

0.205 TO 0.209 in.

(5.21 TO 5.31 mm)

0.214 TO 0.218 in.

(5.44 TO 5.54 mm)

(6)

0.256 TO 0.261 in.

(6.50 TO 6.63 mm)

N/A (7)

(h) Align and install the aft seal (3) on the MLG door with a constant

clearance of 0.11 in. (2.79 mm) (refer to Figure 9, Sheet 2, View D).

(i) Backdrill six holes from the MLG door through the aft seal (3).

(j) Remove the aft seal (3) from the door and remove burrs and sharp

edges.
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(k) Clean the surfaces of the aft seal (3) and the MLG door with clean dry

cloths, with no lint, moist with aliphatic naphta or equivalent.

(l) Dry the surfaces of the aft seal (3) and the MLG door with clean dry

cloths with no lint.

(m) Install the aft seal (3) on the MLG door.

(n) Wet-install the blind rivets (5) through the MLG door, the aft seal (3) and

the washers (4) (refer to Figure 9, View E and F) (refer to SRM

51-42-13-001-001).

(o) Clean the surfaces of the aft seal (3) and the MLG door with clean dry

cloths, with no lint, moist with aliphatic naphta or equivalent.

(p) Dry the surfaces of the aft seal (3) and the MLG door with clean dry

cloths with no lint.

Refer to Figure 10.

(15) Adjust the aft attachment of the outboard MLG door and the inboard MLG

door as follows:

WARNING: WHEN YOU CUT THE COTTER PIN, USE EYE PROTECTION.

PIECES THAT BREAK OFF CAN CAUSE INJURY.

(a) Remove and discard the cotter pin (9) and the nut (6).

(b) Remove the washer (5).

(c) Remove and discard the washers (7) or (8).

(d) Remove the bolt (1), the washer (10) and the sleeve bushing (4).

(e) Apply Aeroshell No.33 grease on the sleeve bushing (4) and the shank

of the bolt (1).

(f) Install the sleeve bushing (4), the washer (10) and the bolt (1).

(g) Move the door to the aft position until the the bushing (11) touches the

bushing (12).

(h) Measure the clearance between the bushings (2) and (3).

(i) If the clearance is between 0.062 and 0.093 in. (1.57 to 2.36 mm), install

the washer (7).
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(j) If the clearance is between 0.094 and 0.125 in. (2.39 to 3.18 mm), install

the washer (8).

NOTE: If the clearance is more than 0.126 (3.20 mm), speak with a

representative of the Customer Response Center (CRC) at phone

number 514-855-8500 for a disposition.

(k) Make sure that there is a clearance of 0.030 and 0.060 in.

(0.76 to 1.42 mm) after the installation of the new washer.

(l) Install the washer (5) and the nut (6).

(m) Torque the nut (6) (refer to AMM 20-21-00-910-801).

(n) Safety the nut (6) with the cotter pin (9)

(refer to AMM 20-51-00-400-801).

Refer to Figure 8.

(16) Attach the rod end (13) to the MLG door as follows:

(a) Apply Aeroshell No.33 grease on the shank of the pin (11) and the

bushing (12).

(b) Make sure that there is no grease on the threads of the pin (11).

(c) Align the rod end (13) with the attachment of the MLG door assembly.

(d) Install the pin (11) with the washer (10) and the bushing (12) through the

attachment of the MLG door assembly and the rod end (13).

(e) Make sure that the head of the pin (11) points forward.

(f) Install the washer (9), and the nut (8).

(g) Torque the nut (8) from 50 to 70 lb·in (6.65 to 7.91 N·m) plus the running

torque (refer to AMM 20-21-00-910-801).

(h) Safety the nut (8) with the cotter pin (7)

(refer to AMM 20-51-00-400-801).
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Refer to Figure 11.

(17) Remove 11 rivets from the MLG door (refer to Figure 11, Sheet 1, View B).

(18) Remove 5 rivets from the upper inboard aft part of the MLG door (refer to

Figure 11, Sheet 2, View C).

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(19) Do a countersinks in 11 holes on the near side of the forward member for the

installation of the rivets (7). Countersunk depth of the holes on the forward

member must be between 0.030 and 0.045 in. (0.76 to 1.14 mm) or the

countersunk diameter must be between 0.234 and 0.269 in. (5.94 to 6.83

mm).

(20) Do a countersinks in 5 holes on the near side of the upper inboard aft part of

the MLG door for the installation of the rivets (7). Countersunk depth on the

upper part of the MLG door must be between 0.030 and 0.045 in. (0.76 to

1.14 mm) or the countersunk diameter must be between 0.234 and 0.269 in.

(5.94 to 6.83 mm).

(21) Apply chemical conversion compound or equivalent in the 16 countersunk

holes (refer to SRM 51-21-11-001-001).

(22) Wet-install the 11 rivets (7) from the outer skin through the forward member

(refer to SRM 51-42-06-001-001).

(23) Wet-install the 5 rivets (7) from the outer skin through the inboard aft upper

part of the MLG door (refer to SRM 51-42-06-001-001).

(24) Clean the area of the forward member and the outer skin of the MLG door

with clean dry cloths, with no lint, moist with aliphatic naphta or equivalent.

(25) Cut the 11 rivets (7) flush with the forward member

(refer to SRM 51-42-06-001-001).

(26) Cut the 5 rivets (7) flush with the upper inboard aft part of the MLG door

(refer to SRM 51-42-06-001-001).

(27) Clean the area of the forward member, the inboard aft upper part of the MLG

door and the outer skin of the MLG door with clean dry cloths, with no lint,

moist with aliphatic naphta or equivalent.
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(28) Dry the bare surfaces with clean dry cloths with no lint.

(29) Apply chemical conversion compound or equivalent on the cut area of the

forward member and the upper inboard aft part of the MLG door.

(30) Remove material from the stiffener of the MLG inboard-door forward-member

as follows:

(a) At 2.61 in. (66.3 mm) from the web of the forward member, make point A

on the stiffener (refer to Figure 11, Sheet 3, View E-E).

(b) At 0.94 in. (23.8 mm) from the web of the forward member, make a point

on the stiffener.

(c) At the intersection of the point at 0.94 in (23.9 mm), made at the

previous step, and at 0.48 (12.2 mm) from the forward member, make

point B.

(d) At 0.04 in. (1.0 mm) from the web of the forward member make point C

on the stiffener.

(e) With a indelible ink pen, make a line and join points A, B and C, on the

stiffener of the forward member.

(f) Do a radius of .12 in. (3.1 mm) at point A.

(g) Do a radius of 2.0 in. (50.8 mm) at point B.

(h) Do a radius of 0.25 in. (6.3 mm) at point C.

(i) Cut the material outboard of the line on the stiffener of the forward

member (refer to SRM 52-71-00-001-001).

(j) Carefully break sharp edges on the stiffener of the forward member.

(k) Clean the bare surfaces of the forward member of the MLG door with

clean, dry cloths with no lint, moist with aliphatic naphta or equivalent.

(l) Dry the bare surfaces with clean, dry cloths with no lint.

(m) Make sure that the surface finish roughness is 125 in. RHR (3.2 mm

RHR) or more where the material was removed on the stiffener of the

MLG door.
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Refer to Figure 12.

(31) Before the installation of the wheel bin, record the part number of the MLG

fairing.

NOTE: The part number will be necessary in a subsequent step for the

identification.

(32) Install the left MLG wheel bin (refer to AMM 53-83-89-400-801).

(33) Identify locations PT2 to PT6 and PT9 to PT13 on the MLG door as follows:

NOTE: All PT locations must be identified on the outer skin of the MLG door.

NOTE: Make sure that you can see the identification mark---up when the door

is in the closed position.

(a) With a indelible ink pen, identify the PT2 on the forward edge of the

inboard door, at 0.50 in.(12.7 mm) from the outboard edge of the angle,

(refer to Figure 12, Sheet 1,View B).

(b) With a indelible ink pen, identify the PT3 on the forward edge of the

inboard door, aligned with the stiffener of the forward member.

(c) With a indelible ink pen, identify the PT4 on the forward edge of the

inboard door, at 0.50 in.(12.7 mm) from the outboard edge of the

inboard door.

(d) With a indelible ink pen, identify the PT5 on the forward edge of the

outboard door, at 0.50 in.(12.7 mm) from the inboard edge of the

outboard door.

(e) With a indelible ink pen, identify the PT6 on the forward edge of the

outboard door, aligned with the stiffener of the forward member.

(f) With a indelible ink pen, identify the PT9 on the aft edge of the outboard

door, aligned with the stiffener of the forward member.

(g) With a indelible ink pen, identify the PT10 on the aft edge of the

outboard door, at 0.50 in (12.7 mm) from the inboard edge of the

outboard door.

(h) With a indelible ink pen, identify the PT11 on the aft edge of the inboard

door, at 2.50 in (63.5 mm) from the outboard edge of the inboard door.
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(i) With a indelible ink pen, identify the PT12 on the aft edge of the inboard

door, aligned with the stiffener of the aft member.

(j) With a indelible ink pen, identify the PT13 on the forward edge of the

inboard door, at 0.50 in.(12.7 mm) from the outboard edge of the angle.

(34) Do the retraction of the main landing gear

(refer to AMM 32-30-00-865-801).

(35) Identify locations PT1 and PT14 to PT25 on the MLG fairing as follows:

(a) With a indelible ink pen, identify the PT1 on the forward edge of the

inboard door, at 1.50 in.(38.1 mm) from the end of the fairing seal, (refer

to Figure 12, Sheet 2, View E).

(b) With a indelible ink pen, identify the PT14 on the aft edge of the fairing,

aligned with the screw on the fairing.

(c) With a indelible ink pen, identify the PT15 on the aft edge of the inboard

door, at 0.50 in (12.7 mm) from the more down edge of the angle, (refer

to Figure 12, Sheet 2, View D).

(d) With a indelible ink pen, identify the PT16 on the aft edge of the inboard

door, align with the screw on the fairing.

(e) With a indelible ink pen, identify the PT17 on the aft edge of the inboard

door, align with the screw on the fairing.

(f) With a indelible ink pen, identify the PT18 on the aft edge of the inboard

door, align with the screw on the fairing.

(g) With a indelible ink pen, identify the PT19 on the aft edge of the inboard

door, align with the screw on the fairing.

(h) With a indelible ink pen, identify the PT20 on the forward edge of the

inboard door, align with the screw on the fairing.

(i) With a indelible ink pen, identify the PT21 on the forward edge of the

inboard door, align with the screw on the fairing.

(j) With a indelible ink pen, identify the PT22 on the forward edge of the

inboard door, align with the screw on the fairing.

(k) With a indelible ink pen, identify the PT23 on the forward edge of the

inboard door, at 0.50 in (12.7 mm) from the edge of the angle.

(l) With a indelible ink pen, identify the PT24 on the forward edge of the

inboard door, in line with the screw on the fairing.
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(m) With a indelible ink pen, identify the PT25 on the forward edge of the

inboard door, in line with the screw on the fairing.

NOTE: At this point do not remove material on the inboard MLG door or

on the MLG fairing.

Refer to Figure 12.

(36) Measure and record the mismatches in Table 1 of Apppendix B.

NOTE: At this point do not remove material on the inboard MLG door or on the

MLG fairing.

(37) Make sure that the mismatches are within the values shown in Table 1 of

Appendix B.

NOTE: Do not remove the hydraulic test fixture it will be needed in further steps.

(38) If the mismatches at PT 22 and PT 23 are not within -0.050 to +0.100 in.

(-1.27 to +2.54 mm), speak with a representative of the Customer Response

Center (CRC) at phone number 514-855-8500 for a disposition.

(39) If the mismatched values recorded in Table 1 of Appendix B are not within the

permitted values, do the adjustment of the MLG doors

(refer to AMM 32-12-01-820-801).

(40) If the adjustment of the MLG doors procedure cannot be done with the AMM

task, speak with a representative of the Customer Response Center (CRC) at

phone number 514-855-8500 for a disposition

(refer to AMM 32-12-01-820-801).

(41) If the mismatched values recorded in Table 1 of Appendix B are within the

permitted values, record the clearances in Table 2 of Appendix B.

(42) If the recorded clearance values are higher than the acceptable clearance

values given in Table 2 of Appendix B, speak with a representative of the

Customer Response Center (CRC) at phone number 514-855-8500 for a

disposition (refer to AMM 32-12-01-820-801).

Refer to Figure 17.

(43) Record in Table 3 of Appendix B the overlap between the aft stop-fitting (1)

and the MLG door stop fitting (refer to Figure 17, View C-C).

(44) Do the extension of the main landing gear

(refer to AMM 32-30-00-992-801).

NOTE: Do not remove the hydraulic test fixture it will be needed in subsequent

steps.
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Refer to Figure 6 and Figure 17.

(45) Remove material from the aft stop-fitting (14) as follows:

NOTE: The overlap between the aft stop-fitting (14) and the MLG door stop fitting

is recorded in Appendix B Table 3 (refer to Figure 17, Sheet 1, View

C-C).

(a) Remove material from the aft stop-fitting (14) to have a minimum overlap

of 0.600 in. (15.24 mm) between the aft stop-fitting and the MLG door

stop fitting (refer to Figure 6, Sheet 2, View E).

NOTE: The aft stop fitting must be cut as close as possible to the stop pad.

(b) Remove burrs and break sharp edges on the aft stop-fitting (14).

(c) Do a radius of 0.250 in. (6.35 mm) on the aft stop-fitting (14)

(refer to Figure 6, Sheet 2, View E).

(d) Clean the bare surfaces of the aft stop-fitting (14) with clean dry cloths,

with no lint, moist with aliphatic naphta or equivalent.

(e) Dry the bare surfaces with clean dry cloths with no lint.

Refer to Figure 6 and 11.

(46) Do a liquid penetrant inspection or an eddy current inspection on the aft

stop-fitting (14) and on the stiffener of the forward member of the MLG

inboard door as follows:

(a) Do a liquid penetrant inspection or an eddy current inspection on the cut

section of the aft stop-fitting (14) (refer to Figure 6, Sheet 2, View E,

NDT 51-20-008-230, or NDT 51-20-006-250)

(b) Do a liquid penetrant inspection or an eddy current inspection on the cut

section of the stiffener of the inboard MLG door

(refer to Figure 11, Sheet 3, View E-E, NDT 51-20-008-230 or

NDT 51-20-006-250).

(c) If there is no crack on the aft stop-fitting (14) and on the stiffener of the

forward member of the MLG inboard door go to next step

(d) If there is a crack on the cut section of the aft stop-fitting (14), speak with

a representative of the Customer Response Center (CRC) at phone

number 514-855-8500 for a disposition.

(e) If there is a crack on the cut section of the stiffener of the inboard MLG

door, speak with a representative of the Customer Response Center

(CRC) at phone number 514-855-8500 for a disposition.
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(47) If there is no crack on the aft stop-fitting (14) and/or on the MLG door stiffener

do the steps that follow:

(a) Apply chemical conversion compound or equivalent on the bare

surfaces of the aft stop-fitting (14), the forward member stiffener of the

inboard MLG door (refer to SRM 51-21-11-001-001).

(b) Apply epoxy primer on the bare surfaces and the hole of the aft

stop-fitting (14) (refer to SRM 51-25-06-001-001).

(c) Apply epoxy primer on the bare surfaces the forward member stiffener of

the inboard MLG door (refer to SRM 51-25-06-001-001).

(d) Apply fluid resistant enamel color grey #16473 on the aft stop-fitting (14)

and on the stiffener of the MLG inboard door

(refer to SRM 51-25-16-001-001).

Refer to Figure 13.

(48) If necessary, remove the left MLG wheel bin (refer to AMM 53-83-89-000-801).

(49) Remove of the seals (8), (10), (4), (11), and the seal retainers (5), (7), (9) as

follows:

(a) Remove the bolts (1), (6), (12), and the washers (3).

(b) Remove and discard the nuts (2).

(c) Remove the seal retainers (5), (7) and (9).

(d) Remove the seals (8) and (11).

(e) Remove and discard the seal (4) and (10).
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Refer to Figure 12 and 14.

(50) Remove material from the MLG inboard door, the outboard MLG door and the

MLG fairing as follows (refer to SRM 51-75-00-001-001):

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(a) Calculate the difference between the acceptable clearance values and

the actual clearance values recorded in Table 2 of Appendix B.

NOTE: The removal of the material must be made on the MLG door before

the removal of the material on the MLG fairing.

NOTE: If you do not get the correct clearance after you remove the

maximum permitted material from the MLG door, remove material

from the MLG fairing.

(b) On the forward section of the MLG door from PT A to PT B, remove

material to a maximum of 0.13 (2.5 mm) (refer to Figure 14, Sheet 2,

View G). Make sure that there is a minimum edge distance of 0.23 in.

(6.0 mm) with the fasteners.

(c) On the forward section of the MLG door at the end of PT A, make a

radius of 0.25 in. (6.3 mm) (refer to Figure 14, Sheet 2, View J).

(d) On the forward section of the MLG door, remove the material from PT B

to a maximum of 0.130 in. (2.54 mm) to PT C to a maximum of 0.080 in.

(2.03 mm) (refer to Figure 14, Sheet 2, View K). Make sure that there is a

minimum edge distance of 0.23 in. (6.0 mm) from the fasteners.

(e) On the forward section of the MLG door, remove the material from PT C

to PT D to a maximum of 0.08 in. (2.0 mm) (refer to Figure 14, Sheet 2,

View H). Make sure that there is a minimum edge distance of 0.23 in.

(6.0 mm) from the fasteners.

(f) On the forward section of the MLG door at PT D, make a radius of 0.25

in.(6.35 mm) at the end of the corner

(refer to Figure 14, Sheet 2, View H).

(g) Clean the bare surfaces of the edge of the inboard MLG door with clean

dry cloths, with no lint, moist with aliphatic naphta or equivalent.

(h) Dry the bare surfaces with clean dry cloths with no lint.
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(i) Apply chemical conversion compound or equivalent on the cut area of

the inboard MLG door (refer to SRM 51-21-11-001-001).

(j) On the upper forward section of the MLG fairing, between PTA and PTB,

remove material up to a maximum of 0.23 in. (5.8 mm) (refer to Figure

14, Sheet 1, View C) (refer to SRM 51-75-00-001-001). Make sure that

there is a minimum edge distance of 0.42 in (10.7 mm) from the

fasteners.

(k) On the forward lower section of the MLG fairing between PT B and PT C,

remove material to a maximum of 0.16 in. (4.1 mm) (refer to Figure 14,

Sheet 1, View D) (refer to SRM 51-75-00-001-001). Make sure that there

is a minimum edge distance of 0.57 in (14.5 mm) from the fasteners.

(l) On the aft section of the MLG fairing between PT D and PT E, remove

the material to a maximum of 0.10 in. (2.5 mm) (refer to Figure 14, Sheet

1, View C) (refer to SRM 51-75-00-001-001). Make sure that there is a

minimum edge distance of 0.42 in. (10.7 mm) with the fasteners.

(m) On the aft section of the MLG fairing between PT E and PT F, remove the

material to a maximum of 0.10 in. (2.5 mm). (refer to Figure 14, Sheet 1,

View C) (refer to SRM 51-75-00-001-001). Make sure that there is a

minimum edge distance of 0.57 in. (14.5 mm) with the fasteners.

Refer to Figure 15.

For aircraft that have not had the forward fairing seal (11) incorporated with Service

Bulletin 670BA-32-030

(51) Install the forward fairing seal (11), the upper seal retainer (13), the lower seal

retainer (14) and the fairing safety-guide (12) as follows:

(a) Temporary install and secure the fairing forward seal (11) and the

retainer seal (5) on the MLG fairing (refer to Figure 15, Sheet 1, View B)

(pre-mod).

(b) Backdrill the holes from the MLG fairing through the fairing forward seal

(11) to a diameter of 0.165 to 0.169 in. (4.19 to 4.29 mm).

(c) Remove the fairing forward seal (11) and the seal retainer (5).

(d) Remove the burrs from the forward seal (11).
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For aircraft that had the forward fairing seal (11) incorporated with Service Bulletin

670BA-32-030

(52) Do a detail inspection on the fairing forward seal (11) for signs of cuts or

damages in the material base.

NOTE: For the MLG fairing seal (11) exterior low friction polyester fabric is not

part of the base rubber material rejection criteria.

For all aircraft

(53) Temporary install and secure the aft fairing seal (10) to the seal retainer (9)

(refer to Figure 15, Sheet 2, View D).

(a) Backdrill the holes from the seal retainer (9) through the aft fairing seal

(10) to a diameter of 0.165 to 0.169 in. (4.19 to 4.29 mm).

(b) Remove the aft fairing seal (10) and the seal retainer (9).

(c) Remove the burrs from the aft fairing seal (10).

(54) Temporary install and secure the fairing forward seal (11), the seal retainer (5)

and the fairing safety-guide (12) on the MLG fairing (refer to Figure 15, Sheet

1, View B, (pre-mod).

(a) Make the upper seal retainer (13) and lower seal retainer (14) from the

seal retainer (5) as follows:

1 Make a line on the seal retainer (5) at the two ends of the fairing

safety-guide (12) (refer to Figure 15, Sheet 1, View B, (Pre-Mod).

2 Make sure that the maximum and the minimum clearance between

the seal retainer (5) and the fairing safety-guide (12) is 0.13 to 0.07

in. (2.54 to 1.78 mm).

3 Remove the fairing safety-guide (12), the seal retainer (5) and the

fairing forward-seal (11).

4 Make sure that there is a minimum edge distance of 0.39 in.

(9.9 mm) at the two ends of the seal retainer (5).
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5 Cut the seal retainer (5) at the cutting line (refer to SRM

51-71-00-001-001).

6 Do a radius of 0.25 in (6.3 mm) on the upper and lower seals (refer

to Figure 15, Sheet 1, View B) (pre-Mod).

7 Temporarily identify the two seal retainers as follows:

a Identify the upper seal retainer as item (13).

b Identify the lower seal retainer as item (14).

c Discard the middle part of the seal retainer (5).

(55) Temporary install and secure the fairing forward seal (11), the upper seal

retainer (13), the lower seal retainer (14), and the fairing safety-guide (12) on

the MLG fairing.

(56) Make sure that there is a minimum of 0.03 in. (0.76 mm) of protrusion with the

fairing safety-guide (12) and the edge of the MLG fairing (refer to Figure 15,

Sheet 1, View C-C).

(57) Make sure that the distance between the fastener hole of the fairing

safety-guide (12) and the rebate of the MLG fairing is at minimum of 0.340 in.

(1.8 mm).

(58) Drill two holes from the pilot holes of the fairing safety-guide (12) through the

fairing forward seal (11) and the forward fairing to a diameter of 0.097 to 0.100

(2.46 to 2.54 mm).

(59) Increase the diameter of the two holes from the pilot holes of the fairing

safety-guide (12) through the fairing forward seal (11) and the forward fairing

to 0.165 to 0.169 in. (4.19 to 4.29 mm).

(60) Backdrill four holes from the MLG fairing through the fairing forward seal (11)

and the fairing safety-guide (12) to a diameter of 0.165 to 0.169 in. (4.19 to

4.29 mm).

(61) Do a countersink of the two new holes in the MLG fairing to a diameter of

0.331 to 0.342 in. (8.41 to 8.69 mm) for the two bolts (1), (refer to Sheet 1,

View B).

(62) Remove the fairing safety-guide (12), the upper seal retainer (13), the lower

seal retainer (14), and the fairing forward seal (11).
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(63) Remove burrs from the fairing safety-guide (12), the fairing forward seal (11)

and the MLG fairing.

(64) Clean the fairing forward seal (11) and the fairing safety-guide (12), the upper

seal retainer (13), the lower seal retainer (14) and the MLG fairing with clean,

dry cloths with no lint, moist with aliphatic naphta or equivalent.

(65) Dry the outer fairing forward seal (11) and the fairing safety-guide (12), the

upper seal retainer (13), the lower seal retainer (14) and the MLG fairing with

clean, dry cloths with no lint.

(66) Apply chemical conversion compound or equivalent on the bare metal

surfaces of the upper seal retainer (13), the lower seal retainer (14) and the

fairing safety-guide (12) (refer to SRM 51-21-11-001-001).

(67) Apply epoxy primer on the bare surfaces of the upper seal retainer (13), the

lower seal retainer (14) and the fairing safety-guide (12)

(refer to SRM 51-25-06-001-001).

(68) Apply fluid resistant enamel, color grey No.16473, on the upper seal retainer

(13), the lower seal retainer (14) and the fairing safety-guide (12) (refer to SRM

51-25-16-001-001).

(69) Apply composite-laminate coating on the bare surfaces of the MLG fairing

(refer to SRM 51-25-52-001-001).

(70) Apply epoxy primer in the countersunk holes of the MLG fairing and on the

bare surfaces (refer to SRM 51-25-06-001-001).

(71) Install the fairing forward seal (11), the fairing safety-guide (12), the upper seal

retainer (13) and the lower seal retainer (14) as follows:

(a) Install and secure the fairing forward seal (11), the fairing safety-guide

(12), the upper seal retainer (13) and the lower seal retainer (14) on the

MLG fairing.

(b) With sealant, install the bolt (15) through the MLG fairing and the

MLG fairing seal (refer to SRM 51-41-02-001-001).

(c) Wet-install the bolts (1) through the MLG fairing with the washers (3) and

the nuts (2) (refer to Figure 15, Sheet 1, View B and SRM

51-41-02-001-001).

(d) Torque the nuts (2) and the bolt (15) (refer to AMM 20-21-00-910-801).
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(72) Install the seal retainer (7) and the seal (8) as follows:

(a) Clean the seal retainer (7), the seal (8) and the aft area of the MLG with

clean, dry cloths with no lint moist with aliphatic naphta or equivalent.

(b) With sealant, install the bolts (1) through the MLG fairing, the seal (8),

the seal retainer (7), the washers (3) and the nuts (2)

(refer to SRM 51-23-00-390-810).

(c) Torque the nuts (2) (refer to AMM 20-21-00-910-801).

(73) Install the seal (10) and the seal retainer (9) as follows:

(a) Clean the seal retainer (9), the seal (10) and the aft area of the MLG with

clean, dry cloths with no lint moist with aliphatic naphta or equivalent.

(b) With sealant, wet install the bolts (6) through the MLG fairing, the seal

(10), the seal retainer (9), the washers (3) and the nuts (2)

(refer to SRM 51-23-00-001-001).

(c) Torque the nuts (2) (refer to AMM 20-21-00-910-801).

(d) Clean the area of the forward and the aft MLG fairing with clean, dry

cloths with no lint, moist with aliphatic naphta or equivalent.

(e) Dry the area with clean, dry cloths with no lint.

Refer to Figure 16.

(74) Identify the right inboard MLG door as follows

(a) Carefully remove the identification plate (1) from the inboard inner skin

with a plastic or phenolic scraper.

(b) Clean the inboard inner skin with clean, dry cloths with no lint, moist with

aliphatic naphta or equivalent.

(c) Dry the forward inboard inner-skin with clean, dry cloths with no lint.

(d) If necessary, apply epoxy primer on the inboard inner skin

(refer to SRM 51-25-06-001-001).

(e) If necessary, apply fluid resistant enamel, color grey No.16473, on the

inboard inner skin (refer to SRM 51-25-16-001-001).
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(f) Write the data on the new identification plate (1) as follows:

1 On the new identification plate, write with a indelible ink pen or

equivalent in the field DWG.NO: the data that follows:

PRE-SB PART NUMBER POST-SB PART NUMBER

CC670-10520-968 KBA670-10500-24

CC670-10520-2012 KBA670-10500-26

CC670-10520-2014 KBA670-10500-28

CC670-10520-2016 KBA670-10500-30

CC670-10520-14 KBA670-10500-32

KCC670-10900-2 KBA670-10500-34

KCC670-10900-4 KBA670-10500-36

KCC670-10900-6 KBA670-10500-38

KCC670-10901-2 KBA670-10500-52

KCC670-10901-4 KBA670-10500-54

2 With a indelible ink pen or equivalent, write all the other information

(model, serial number, date) from the removed identification plate

(1) to the new identification plate (1).

(g) Discard the removed identification plate (1).

(h) Install the new identification plate (1) on the MLG door as follows:

1 Put the new identification plate (1) in position

(refer to Figure 16, View B).

2 Apply adhesive Magnobond 6380 or equivalent on the mating

surface of new identification plate (1) and inboard inner skin

(refer to SRM 51-22-00-001-001).

3 Install the new identification plate (1) in the correct position on the

inboard inner skin.
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4 Carefully remove unwanted adhesive with a spatula and/or a plastic

or phenolic scraper.

5 Apply a layer clear-gloss fluid resistant enamel CMS 565-02 on the

new identification plate (1) (refer to SRM 51-25-16-001-001).

Refer to Figure 5.

(75) With an indelible ink pen or equivalent, identify the aft member of the inboard

MLG door (refer to Figure 5, Sheet 3, View F)

(refer to AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

CC670-10571-14 KBA670-10500-46

Refer to Figure 7.

(76) With an indelible ink pen or equivalent, identify the aft stop-fitting (1) of the

MLG fairing per (refer to AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

CC670-39076-2 KBA670-10500-40

(77) If only PART B is done, with a indelible ink pen or equivalent, identify the right

MLG fairing with the applicable part number listed in the table below

(refer to AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

BA670-00001-2085 KBA670-10500-350

CC670-39005-951 KBA670-10500-550

CC670-39005-3 KBA670-10500-750

CC670-39005-5 KBA670-10500-135

CC670-39019-49 KBA670-10500-195

CC670-39019-963 KBA670-10500-155
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PRE-SB PART NUMBER POST-SB PART NUMBER

CC670-39019-965 KBA670-10500-175

CC670-39019-51 KBA670-10500-215

KBA670-39005-3 KBA670-10500-615

KBA670-39005-5 KBA670-10500-635

KBA670-39005-7 KBA670-10500-655

KBA670-39005-9 KBA670-10500-675

(78) If PART A and PART B are done or PART B and PART C are done, with an

indelible ink pen or equivalent, identify the MLG fairing with the applicable part

number listed in the table below (refer to AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

BA670-00001-2085 KBA670-10500-3

CC670-39005-951 KBA670-10500-5

CC670-39005-3 KBA670-10500-7

CC670-39005-5 KBA670-10500-13

CC670-39019-49 KBA670-10500-19

CC670-39019-963 KBA670-10500-15

CC670-39019-965 KBA670-10500-17

CC670-39019-51 KBA670-10500-21

KBA670-39005-3 KBA670-10500-61

KBA670-39005-5 KBA670-10500-63

KBA670-39005-7 KBA670-10500-65

KBA670-39005-9 KBA670-10500-67

(79) Apply a bead of sealant on the aft stop-fitting (1) and the sealing member

(refer to Figure 7, View C) (refer to SRM 51-23-00-001-001).

(80) Apply epoxy primer on the rivets (4) and (5), the bolts (2) and the nuts (3)

(refer to SRM51-25-06-001-001).
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(81) Apply fluid resistant enamel, color grey No.16473, on the bolt (2), the nut (3)

and the rivets (4) and (5) (refer to SRM 51-25-16-001-001).

(82) Apply fluid resistant enamel on bolts (2), refer to the external paint scheme for

the color (refer to SRM 51-25-16-001-001).

Refer to Figure 9.

(83) Apply aerodynamic sealant between the aft seal (3) and the MLG door (refer

to Figure 9, Sheet 2, View E) (refer to SRM 51-23-00-001-001).

(84) Apply epoxy primer on the aerodynamic sealant between the aft seal (3) and

on the MLG door (refer to SRM51-25-06-001-001).

(85) Apply fluid resistant enamel, color grey No.16473, on the aerodynamic sealant

between the aft seal (3) and the MLG door (refer to SRM 51-25-16-001-001).

(86) Apply fluid resistant enamel on the aerodynamic sealant between the aft seal

(3) and the MLG door. Refer to the external paint scheme for the color (refer to

SRM 51-25-16-001-001).

Refer to Figure 11.

(87) With a indelible ink pen or equivalent, identify the forward member of the

inboard MLG door (refer to AMM 20-60-13-930-801).

NOTE: The identification of the forward member must be done with the MLG

door POST-SB number.

MLG DOOR - POST-SB

PART NUMBER

FORWARD MEMBER -

POST-SB PART NUMBER

KBA670-10500-26

KBA670-10500-28

KBA670-10500-30

KBA670-10500-36

KBA670-10500-38

KBA670-10500-48
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MLG DOOR - POST-SB

PART NUMBER

FORWARD MEMBER -

POST-SB PART NUMBER

KBA670-10500-24

KBA670-10500-32

KBA670-10500-34

KBA670-10500-52

KBA670-10500-54

KBA670-10500-50

(88) If necessary, apply aerodynamic sealant in the area

(refer to Figure 11,Sheet 3, View D) and AMM 52-23-00-390-813).

(89) If necessary, apply epoxy primer on the aerodynamic sealant on the forward

member (refer to SRM51-25-06-001-001).

(90) If necessary, apply fluid resistant enamel, color grey No.16473, on the

aerodynamic sealant of the forward member (refer to SRM51-25-16-001-001).

Refer to Figure 15.

(91) Identify the seal retainers (13) and (14) with the applicable part number listed

in the table below (refer to AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

Seal retainer CC670-29245-2 Upper seal retainer (13)

KBA670-10500-42

Lower seal retainer (14)

KBA670-10500-44

Refer to Figure 17.

(92) If removed do the installation of the right inboard MLG door

(refer to AMM 32-12-01-400-802).
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(93) Do a clearance check of the right MLG doors

(refer to AMM 32-12-01-220-801).

NOTE: Use the post service bulletin 670BA-32-040 task to do the clearance

check.

NOTE: If you cannot get the final steps and gaps to agree with AMM TASK

32-12-01-220-801, AFM CDL # 32---12 (Main Landing Gear Door ---

Inboard Door) can be done. This service bulletin can be completed

when the requirements of step 2.B.(93) are met.

(94) Do the extension of the MLG (refer to AMM 32-12-01-220-801).

(95) If it is not possible to complete all the instructions in this service bulletin

because of the configuration of the aircraft, speak with a representative of

Bombardier Customer Response Centre at phone number 514---855---8500 or

send an e-mail at thd.crj@bombardier.com for analysis and to get an

approved disposition to complete this service bulletin.
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F. Job Close-Out

(1) Remove all tools, equipment, and unwanted materials from the work area.

(2) Install right MLG door-hinge fairing 642AB (refer to AMM 57-80-85-400-802).

(3) If removed, install the right MLG wheel bin (refer to AMM 53-83-89-400-801).

(4) Remove the tags and close the circuit breakers that follow:

CB PANEL CB NO. NAME

CBP-1 A12 HEATERS TAT

CBP-1 A13 HEATERS AOA R

CBP-1 A14 HEATERS PITOT R

CBP-1 C13 ADG HEATER

CBP-1 G1 PSEU CH A

CBP-1 G2 NOSE STEER

CBP-1 G13 HEATERS ADS CONT 2

CBP-1 G14 HEATERS STATIC R

CBP-1 LOWER T7 HEATERS PITOT L

CBP-1 LOWER T8 HEATERS AOA L

CBP-1 LOWER T9 HEATERS PITOT STBY

CBP-1 LOWER U7 ENG IGN A

CBP-2 G1 PSEU CH B

CBP-2 G2 NOSE STEER

CBP-2 N6 ADG DEPLOY AUTO

CBP-2 N9 MLG BAYOVHT DET

CBP-2 P1 PSEU CH A

CBP-2 P2 PSEU CH B

CBP-2 LOWER S1 HEATERS STATIC L

CBP-2 LOWER S2 HEATERS ADS CONT 1
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CB PANEL CB NO. NAME

CBP-2 LOWER S3 HEATERS ADS CONT STBY

CBP-5 B10 ENG IGN B

(5) If the wheel bin was removed, do the operational test of the MLG overheat

detection and warning system (refer to AMM 26-14-04-710-801).

(6) Do the lubrication of the MLG and the MLG door

(refer to AMM 12-20-32-640-802).

(7) Do the operational test of the landing-gear extension/retraction system

(refer to AMM 32-30-00-710-801).

(8) Remove the aircraft from jacks (refer to AMM 07-11-01-586-801).

(9) Make sure that step 2. B (93) of PART B is completed and meet the

requirements before you do the entry in the applicable logbooks.

(10) When PART B of this service bulletin is completed, add the weight and

balance data shown in paragraph 1.I. of this service bulletin to the Weight and

Balance Manual. Under ‘Description of Change’ enter “Service Bulletin

670BA-32-040, Revision E, incorporated.”

(11) When PART B of this service bulletin is completed, make this entry in the

applicable logbooks: “Service Bulletin 670BA-32-040, Revision E, Landing

Gear - Main Landing Gear (MLG) and Doors - Increase the Clearances

Between the MLG Fairing and MLG Doors, PART B, incorporated.””
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PART C --- Installation of the Inboard MLG Door Part Number CC670-10520-15 and

Increase of the Clearance Between the Left MLG Inboard-Door and the MLG Fairing

G. Job Set-Up

Reference Information

REFERENCE DESIGNATION

AMM 07-11-01-582-801 Jacking of the Aircraft

AMM 07-11-01-586-801 Lowering of the Aircraft

AMM 10-11-00-400-801 Installation of the Nose Landing Gear (NLG)

Lockpin

AMM 10-11-00-400-802 Installation of the Main Landing Gear (MLG)

Lockpins

AMM 12-00-00-867-801 Standard Aircraft Configuration for Maintenance

AMM 12-20-32-640-802 Lubrication of the Main Landing Gear (MLG)

AMM 20-21-00-910-801 Torquing of Threaded Fasteners

AMM 20-51-00-000-801 Removal of Cotter Pins

AMM 20-51-00-000-802 Removal of Lockwire

AMM 20-51-00-400-801 Installation of Cotter Pins

AMM 20-51-00-400-802 Installation of Lockwire

AMM 20-60-13-930-801 Identification of Aircraft Parts and Assemblies

AMM 32-12-01-000-802 Removal of the Inboard MLG Doors

AMM 32-12-01-220-801 Clearance Check of the MLG Doors

AMM 32-12-01-400-802 Installation of the Inboard MLG Doors

AMM 32-12-01-820-801 Adjustment of the MLG Doors

AMM 32-30-00-710-801 Operational Test of the Landing-Gear Extension/

Retraction System

AMM 51-23-00-100-801 Removal of Sealants

NDT 51-20-006-250 Eddy Current- Inspection Procedures

NDT 51-20-008-230 Liquid Penetrant - Inspection Procedures
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REFERENCE DESIGNATION

NDT 51-20-009-210 Visual - Inspection Procedures

SRM 51-21-11-001-001 Corrosion Prevention Procedures

SRM 51-21-16-001-001 Finish Codes

SRM 51-23-00-001-001 Pressure, Environmental, Fuel Tank and Firewall

Sealing

SRM 51-25-06-001-001 Fluid-Resistant (FR) Epoxy Primer

SRM 51-25-16-001-001 Fluid-Resistant (FR) Polyurethane Topcoat

SRM 51-25-52-001-001 Composite-Laminate Coatings

SRM 51-26-00-001-001 Cleaning

SRM 51-40-06-001-001 Fastener Edge Distance and Pitch

SRM 51-40-11-001-001 Preparation of Fastener Holes

SRM 51-41-02-001-001 Bolts, Screws and Related Items

SRM 51-42-06-001-001 Solid Rivets

SRM 51-42-21-001-001 Hi-Lite Fasteners

SRM 51-71-00-001-001 Typical Structural Repairs

SRM 51-75-00-001-001 Graphite Repairs
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Tolerance Information

Linear Tolerances Angular Tolerance

X.XX in. (X.X mm) X.X in. (X mm)

+/-0 30” +/- 0.03 in. +/- 0.1 in.

+/- 0.8 mm +/- 3 mm

NOTE: The tolerances above apply to the dimensions given in this service

bulletin, except when specified differently.

(1) Make sure that the aircraft is in standard configuration for maintenance

(refer to AMM 12-00-00-867-801).

WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO

MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC

EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS,

INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN

OCCUR.

(2) Open, safety, and tag the circuit breakers that follow:

CB PANEL CB NO. NAME

CBP-1 A12 HEATERS TAT

CBP-1 A13 HEATERS AOA R

CBP-1 A14 HEATERS PITOT R

CBP-1 C13 ADG HEATER

CBP-1 G1 PSEU CH A

CBP-1 G2 NOSE STEER

CBP-1 G13 HEATERS ADS CONT 2

CBP-1 G14 HEATERS STATIC R

CBP-1 LOWER T7 HEATERS PITOT L

CBP-1 LOWER T8 HEATERS AOA L

CBP-1 LOWER T9 HEATERS PITOT STBY

CBP-1 LOWER U7 ENG IGN A

CBP-2 G1 PSEU CH B

CBP-2 G2 NOSE STEER
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CB PANEL CB NO. NAME

CBP-2 N6 ADG DEPLOY AUTO

CBP-2 N9 MLG BAYOVHT DET

CBP-2 P1 PSEU CH A

CBP-2 P2 PSEU CH B

CBP-2 LOWER S1 HEATERS STATIC L

CBP-2 LOWER S2 HEATERS ADS CONT 1

CBP-2 LOWER S3 HEATERS ADS CONT STBY

CBP-5 B10 ENG IGN B

(3) Put the aircraft on jacks (refer to AMM 07-11-01-582-801).

(4) If necessary, remove the left MLG wheel bin (refer to AMM 53-83-89-000-801).
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H. Procedure

For all aircraft

Refer to Figure 1.

(1) Do a detailed visual inspection of the left section of the MLG fairing as follows

(refer to NDT 51-20-009-210):

(a) Visually inspect to make sure that the forward and the aft stops are not

missing from the MLG fairing.

(b) If the forward and/or the aft stops are not missing, visually inspect that

there are no loose or missing fasteners from the forward and aft stops.

(c) Visually inspect along the edge of the MLG fairing adjacent the MLG

door to make sure that there is no damage. Refer to the shaded area

(refer to Figure 1, Sheet 2).

NOTE: For this inspection, damage does not include surface scratches and/or

paint deterioration.

(d) Record the findings on the record sheet of Appendix A.

Refer to Figure 3.

(2) Do a detailed visual inspection of the stops (1) and (2), and the wedge (3) on

the left side of the forward and the aft spars as follows (refer to NDT

51-20-009-210):

(a) Visually inspect to make sure that the stops (1) and (2) are not missing.

(b) If the stops (1) and/or (2) are not missing, visually inspect that there are

no loose or missing fasteners from the stops (1) and/or (2).

(c) Visually inspect to make sure that the wedge (3) is not missing.

(d) If the wedge (3) is not missing, visually inspect that there are no loose or

missing fasteners from the wedge (3).

(e) Record the findings on the record sheet of Appendix A.
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Refer to Figures 1 and 3.

(3) If damage is found and/or there are missing parts and/or fasteners, speak

with a representative of the Customer Response Center (CRC) at phone

number 514-855-8500 for a disposition.

NOTE: Refer to the record sheet of Appendix A for data.

(4) If no damage is found and there is no missing part or fastener, go to the next

step.

Refer to Figure 6.

(5) Remove and discard the aft fairing seal (4) and the aft retainer seal (5) from

the fairing as follows:

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(a) Remove and discard the three bolts (1), the washers (2) and the nuts

(3).

(b) Remove and discard the seal aft fairing (4) and the aft retainer seal (5)

from the fairing.

(6) Remove the aft stop-fitting (14) as follows:

(a) Remove the two bolts (6), the washers (10), and the nuts (11).

(b) Remove and discard the stop pad (7), the laminated shim (8) and the

shim (9).

(c) Remove the sealant from the aft stop-fitting (14) and the sealing member

(refer to Figure 6, Sheet 1, View D) (refer to AMM 51-23-00-100-801).

(d) Remove the three solid rivets (17).

(e) Remove and discard the bolts (12) and the nuts (13).

(f) Remove the aft stop-fitting (14) from the sealing member.

(g) Remove the sealant from the MLG fairing, the sealing member and on

the aft stop-fitting (14) (refer to AMM 51-23-00-100-801).
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(7) Drill the aft stop-fitting (14) as follows:

(a) Temporarily install the shim fairing (15) on the aft stop-fitting (14). Make

sure that the shim fairing (15) is parallel to the edge of the aft stop-fitting

(14) (refer to Figure 6, Sheet 2, View E).

(b) Attach the shim fairing (15) with the bolt (6), the washer (10) and the nut

(11).

(c) Backdrill one hole to a diameter of 0.190 to 0.194 in (4.83 to 4.93 mm)

from the shim fairing (15) to the aft stop-fitting (14).

(d) Remove and discard the nut (11).

(e) Remove the bolt (6), the washer (10) and the shim fairing (15).

(f) Temporarily install the shim fairing (15) on the laminated shim (16).

(g) Increase the diameter of two holes in the shim fairing (15) and the

laminated shim (16) to 0.213 to 0.217 (5.41 to 5.51 mm).

(h) Disassemble and remove burrs and sharp edges from the holes of the

shim fairing (15), the laminated shim (16), and the aft stop-fitting (14).

(i) Clean the bare metal surfaces of the aft stop-fitting (14) with clean dry

cloths, with no lint, moist with aliphatic naphta or equivalent.

(j) Dry the bare surfaces with clean dry cloths with no lint.

(k) Apply chemical conversion compound on the bare metal surfaces of the

hole in the aft stop-fitting (14) (refer to SRM 51-21-11-001-001).

(l) Touch-up the hole in the aft stop-fitting (14) with epoxy primer (refer to

SRM 51-25-06-001-001).

(m) Touch-up the hole in the aft stop-fitting (14) with fluid resistant enamel

color grey #16473 (refer to SRM 51-25-16-001-001).

Refer to Figure 7.

(8) Remove 0.53 in. to 0.61 in. (13.4 to 15.5 mm) of material from the aft area of

the MLG fairing (refer to Figure 7, Sheet1, View D and SRM

51-71-00-001-001).

NOTE: An edge distance of 0.57 in (14.50 mm) for the three holes of the aft

stop-fitting (1) is necessary.

(9) Install the aft stop-fitting (1) as follows:

(a) Apply sealant on the mating surface of the aft stop-fitting (1) (refer to

SRM 51-23-00-001-001).
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(b) Install the aft stop-fitting (1) on the sealing member of the MLG fairing.

(c) Wet-install the two upper rivets (5) on the aft stop-fitting (1) (refer to

Figure 7, View C and SRM 51-42-06-001-001 and SRM

51-23-00-001-001).

(d) Wet-install one rivet (4) at the bottom of the aft stop-fitting (1) (refer to

Figure 7, View C and SRM 51-42-06-001-001 and SRM

51-23-00-001-001).

(e) Wet-install the three bolts (2) and the nuts (3) (refer to SRM

51-42-21-001-001 and SRM 51-23-00-001-001).

NOTE: The installation of the stop pad (7), the laminated shim (8), and the

shim (9) will be incorporated in a subsequent step during the

clearance check.

Refer to Figure 18.

(10) If installed, remove the inboard MLG door (1) (refer to AMM 32-12-01-00-802).

For Aircraft 10002 thru 10217, 15002 thru 15043 and 15991 pre-IS Modification

Summary IS670528200033 with inboard MLG door CC670-10520-2013,

CC670-10520-2015, KCC670-10900-3, KCC670-10900-5

(11) Do IS Modification Summary IS670528200033.

NOTE: During the incorporation of the IS Modification Summary

IS670528200033, it is not necessary to remove the outboard MLG door.

For all aircraft

Refer to Figure 10 and 18.

(12) Install the left inboard MLG door (2) and adjust the aft attachment of the

outboard MLG door and the inboard MLG door as follows:

(a) Install the left inboard MLG door (2) (refer to AMM 32-12-01-400-802).

NOTE: During the installation of the inboard MLG door (2) refer to the

AMM 32-12-01-400-802 post Service Bulletin 670BA-32-040.

(b) Apply Aeroshell No.33 grease on the sleeve bushing (4) and the shank

of the bolt (1).
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(c) Install the sleeve bushing (4), the washer (10) and the bolt (1).

(d) Move the door to the aft position until the the bushing (11) touches the

bushing (12).

(e) Measure the clearance between the bushings (2) and (3).

(f) If the clearance is between 0.062 and 0.093 in. (1.57 to 2.36 mm), install

the washer (7).

(g) If the clearance is between 0.094 and 0.125 in. (2.39 to 3.18 mm), install

the washer (8).

NOTE: If the clearance is 0.126 (3.20 mm) or higher, speak with a

representative of the Customer Response Center (CRC) at phone

number 514-855-8500 for a disposition.

(h) Make sure to have a clearance of 0.030 and 0.060 in.

(0.76 to 1.42 mm) after the installation of the new washer.

(i) Install the washer (5) and the nut (6).

(j) Torque the nut (6) (refer to AMM 20-21-00-910-801).

(k) Safety the nut (6) with the cotter pin (9) (refer to AMM 20-51-00-400-801).

Refer to Figure 12.

(13) Before the installation of the wheel bin, record the part number of the MLG

fairing.

NOTE: The part number will be necessary in a further step for the identification.

(14) Install the left MLG wheel bin (refer to AMM 53-83-89-400-801).

(15) Identify locations PT2 to PT6 and PT9 to PT13 on the MLG door as follows:

NOTE: All PT locations must be identified on the outer skin of the MLG door.

NOTE: Make sure that you can see the identification mark-up when the door is

in the closed position.

(a) With a indelible ink pen, identify the PT2 on the forward edge of the

inboard door, at 0.50 in.(12.7 mm) from the outboard edge of the angle,

(refer to Figure 12, Sheet 1,View B).
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(b) With a indelible ink pen, identify the PT3 on the forward edge of the

inboard door, aligned with the stiffener of the forward member.

(c) With a indelible ink pen, identify the PT4 on the forward edge of the

inboard door, at 0.50 in.(12.7 mm) from the outboard edge of the

inboard door.

(d) With a indelible ink pen, identify the PT5 on the forward edge of the

outboard door, at 0.50 in.(12.7 mm) from the inboard edge of the

outboard door.

(e) With a indelible ink pen, identify the PT6 on the forward edge of the

outboard door, aligned with the stiffener of the forward member.

(f) With a indelible ink pen, identify the PT9 on the aft edge of the outboard

door, aligned with the stiffener of the forward member.

(g) With a indelible ink pen, identify the PT10 on the aft edge of the

outboard door, at 0.50 in (12.7 mm) from the inboard edge of the

outboard door.

(h) With a indelible ink pen, identify the PT11 on the aft edge of the inboard

door, at 2.50 in (63.5 mm) from the outboard edge of the inboard door.

(i) With a indelible ink pen, identify the PT12 on the aft edge of the inboard

door, aligned with the stiffener of the aft member.

(j) With a indelible ink pen, identify the PT13 on the forward edge of the

inboard door, at 0.50 in.(12.7 mm) from the outboard edge of the angle.

(16) Do the retraction of the main landing gear (refer to AMM 32-30-00-865-801).

(17) Identify locations PT1 and PT14 to PT25 on the MLG fairing as follows:

(a) With a indelible ink pen, identify the PT1 on the forward edge of the

inboard door, at 1.50 in.(38.1 mm) from the end of the fairing seal, (refer

to Figure 12, Sheet 2, View E).

(b) With a indelible ink pen, identify the PT14 on the aft edge of the fairing,

aligned with the screw on the fairing.

(c) With a indelible ink pen, identify the PT15 on the aft edge of the inboard

door, at 0.50 in (12.7 mm) from the more down edge of the angle, (refer

to Figure 12, Sheet 2, View D).
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(d) With a indelible ink pen, identify the PT16 on the aft edge of the inboard

door, align with the screw on the fairing.

(e) With a indelible ink pen, identify the PT17 on the aft edge of the inboard

door, align with the screw on the fairing.

(f) With a indelible ink pen, identify the PT18 on the aft edge of the inboard

door, align with the screw on the fairing.

(g) With a indelible ink pen, identify the PT19 on the aft edge of the inboard

door, align with the screw on the fairing.

(h) With a indelible ink pen, identify the PT20 on the forward edge of the

inboard door, align with the screw on the fairing.

(i) With a indelible ink pen, identify the PT21 on the forward edge of the

inboard door, align with the screw on the fairing.

(j) With a indelible ink pen, identify the PT22 on the forward edge of the

inboard door, align with the screw on the fairing.

(k) With a indelible ink pen, identify the PT23 on the forward edge of the

inboard door, at 0.50 in (12.7 mm) from the edge of the angle.

(l) With a indelible ink pen, identify the PT24 on the forward edge of the

inboard door, in line with the screw on the fairing.

(m) With a indelible ink pen, identify the PT25 on the forward edge of the

inboard door, in line with the screw on the fairing.

NOTE: At this point do not remove material on the inboard MLG door or

on the MLG fairing.

Refer to Figure 12.

(18) Measure and record the mismatches in Table 1 of Apppendix B.

NOTE: At this point do not remove material on the inboard MLG door or on the

MLG fairing.

(19) Make sure that the mismatches are within the values shown in Table 1 of

Appendix B.

NOTE: Do not remove the hydraulic test fixture it will be needed in subsequent

steps.
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(20) If the mismatches at PT 22 and PT 23 are not within -0.050 to +0.100 in.

(-1.27 to +2.54 mm), speak with a representative of the Customer Response

Center (CRC) at phone number 514-855-8500 for a disposition.

(21) If the mismatched values recorded in Table 1 of Appendix B are not within the

permitted values, do the adjustment of the MLG doors

(refer to AMM 32-12-01-820-801).

(22) If the adjustment of the MLG doors procedure cannot be done with the AMM

task, speak with a representative of the Customer Response Center (CRC) at

phone number 514-855-8500 for a disposition

(refer to AMM 32-12-01-820-801).

(23) If the mismatched values recorded in Table 1 of Appendix B are within the

permitted values, record the clearances in Table 2 of Appendix B.

(24) If the recorded clearance values are higher than the acceptable clearance

values given in Table 2 of Appendix B, speak with a representative of the

Customer Response Center (CRC) at phone number 514-855-8500 for a

disposition (refer to AMM 32-12-01-820-801).

Refer to Figure 17.

(25) Record in Table 3 of Appendix B the overlap between the aft stop-fitting (1)

and the MLG door stop fitting (refer to Figure 17, View C-C).

(26) Do the extension of the main landing gear

(refer to AMM 32-30-00-992-801).

NOTE: Do not remove the hydraulic test fixture it will be needed in subsequent

steps.

Refer to Figure 6 and Figure 17.

(27) Remove material from the aft stop-fitting (14) as follows:

NOTE: The overlap between the aft stop-fitting (14) and the MLG door stop fitting

is recorded in Appendix B Table 3 (refer to Figure 17, Sheet 1, View

C-C).

(a) Remove material from the aft stop-fitting (14) to have a minimum overlap

of 0.600 in. (15.24 mm) between the aft stop-fitting and the MLG door

stop fitting (refer to Figure 6, Sheet 2, View E).

NOTE: The aft stop fitting must be cut as close as possible to the stop pad.
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(b) Remove burrs and break sharp edges on the aft stop-fitting (14).

(c) Do a radius of 0.250 in. (6.35 mm) on the aft stop-fitting (14)

(refer to Figure 6, Sheet 2, View E).

(d) Clean the bare surfaces of the aft stop-fitting (14) with clean dry cloths,

with no lint, moist with aliphatic naphta or equivalent.

(e) Dry the bare surfaces with clean dry cloths with no lint.

Refer to Figure 13.

(28) If necessary, remove the left MLG wheel bin (refer to AMM 53-83-89-000-801).

(29) Remove of the seals (8), (10), (4), (11), and the seal retainers (5), (7), (9) as

follows:

(a) Remove the bolts (1), (6), (12), and the washers (3).

(b) Remove and discard the nuts (2).

(c) Remove the seal retainers (5), (7) and (9).

(d) Remove the seals (8) and (11).

(e) Remove and discard the seal (4) and (10).

Refer to Figure 12 and 14.

(30) Remove material from the outboard MLG door and the MLG fairing as follows

(refer to SRM 51-75-00-001-001):

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(a) Calculate the difference between the acceptable clearance values and

the actual clearance values recorded in Table 2 of Appendix B.

NOTE: The removal of the material must be done only on the MLG fairing

and on the outboard MLG door.

(b) On the upper forward section of the MLG fairing, between PTA and PTB,

remove material up to a maximum of 0.23 in. (5.8 mm) (refer to Figure

14, Sheet 1, View C) (refer to SRM 51-75-00-001-001). Make sure that

there is a minimum edge distance of 0.42 in (10.7 mm) from the

fasteners.
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(c) On the forward lower section of the MLG fairing between PT B and PT C,

remove material to a maximum of 0.16 in. (4.1 mm) (refer to Figure 14,

Sheet 1, View D) (refer to SRM 51-75-00-001-001). Make sure that there

is a minimum edge distance of 0.57 in (14.5 mm) from the fasteners.

(d) On the aft section of the MLG fairing between PT D and PT E, remove

the material to a maximum of 0.10 in. (2.5 mm) (refer to Figure 14, Sheet

1, View C) (refer to SRM 51-75-00-001-001). Make sure that there is a

minimum edge distance of 0.42 in. (10.7 mm) with the fasteners.

(e) On the aft section of the MLG fairing between PT E and PT F, remove the

material to a maximum of 0.10 in. (2.5 mm) (refer to Figure 14, Sheet 1,

View C) (refer to SRM 51-75-00-001-001). Make sure that there is a

minimum edge distance of 0.57 in. (14.5 mm) with the fasteners.

Refer to Figure 6.

(31) Do a liquid penetrant inspection or an eddy current inspection of the aft

stop-fitting (14) as follows:

(a) Do a liquid penetrant inspection or an eddy current inspection on the cut

section of the aft stop-fitting (14) (refer to Figure 6, Sheet 2, View E,

NDT 51-20-008-230, or NDT 51-20-006-250)

(b) If there is no crack on the aft stop-fitting (14) go to next step.

(c) If there is a crack on the cut section of the aft stop-fitting (14), speak with

a representative of the Customer Response Center (CRC) at phone

number 514-855-8500 for a disposition.

(32) If there is no crack on the aft stop-fitting (14) do the steps that follow:

(a) Apply chemical conversion compound or equivalent on the bare

surfaces of the aft stop-fitting (14), (refer to SRM 51-21-11-001-001).

(b) Apply epoxy primer on the bare surfaces and the hole of the aft

stop-fitting (14) (refer to SRM 51-25-06-001-001).

(c) Apply fluid resistant enamel color grey #16473 on the aft stop-fitting (14)

(refer to SRM 51-25-16-001-001).
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Refer to Figure 15.

For aircraft that have not had the forward fairing seal (11) incorporated with Service

Bulletin 670BA-32-030

(33) Install the forward fairing seal (11), the upper seal retainer (13), the lower seal

retainer (14) and the fairing safety-guide (12) as follows:

(a) Temporary install and secure the fairing forward seal (11) and the

retainer seal (5) on the MLG fairing (refer to Figure 15, Sheet 1, View B)

(pre-mod).

(b) Backdrill the holes from the MLG fairing through the fairing forward seal

(11) to a diameter of 0.165 to 0.169 in. (4.19 to 4.29 mm).

(c) Remove the fairing forward seal (11) and the seal retainer (5).

(d) Remove the burrs from the forward seal (11).

For aircraft that had the forward fairing seal (11) incorporated with Service Bulletin

670BA-32-030

(34) Do a detail inspection on the fairing forward seal (11) for signs of cuts or

damages in the material base.

NOTE: For the MLG fairing seal (11) exterior low friction polyester fabric is not

part of the base rubber material rejection criteria.

For all aircraft

(35) Temporary install and secure the aft fairing seal (10) to the seal retainer (9)

(refer to Figure 15, Sheet 2, View D).

(a) Backdrill the holes from the seal retainer (9) through the aft fairing

seal (10) to a diameter of 0.165 to 0.169 in. (4.19 to 4.29 mm).

(b) Remove the aft fairing seal (10) and the seal retainer (9).

(c) Remove the burrs from the aft fairing seal (10).

(36) Temporary install and secure the fairing forward seal (11), the seal retainer (5)

and the fairing safety-guide (12) on the MLG fairing (refer to Figure 15, Sheet

1, View B, pre-mod).

(a) Make the upper seal retainer (13) and lower seal retainer (14) from the

seal retainer (5) as follows:
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1 Make a line on the seal retainer (5) at the two ends of the fairing

safety-guide (12) (refer to Figure 15, Sheet 1, View B, (Pre-Mod).

NOTE: The maximum and the minimum clearance between the seal

retainer (5) and the fairing safety-guide (12) is 0.13 to 0.07 in.

(2.54 to 1.78 mm).

2 Remove the fairing safety-guide (12), the seal retainer (5) and the

fairing forward-seal (11).

3 Make sure that there is a minimum edge distance of 0.39 in.

(9.9 mm) at the two ends of the seal retainer (5).

4 Cut the seal retainer (5) at the cutting line (refer to SRM

51-71-00-001-001).

5 Do a radius of 0.25 in (6.3 mm) on the upper and lower seals (refer

to Figure 15, Sheet 1, View B, pre-Mod).

6 Temporarily identify the two seal retainers as follows:

a Identify the upper seal retainer as item (13).

b Identify the lower seal retainer as item (14).

c Discard the middle part of the seal retainer (5).

(37) Temporary install and secure the fairing forward seal (11), the upper seal

retainer (13), the lower seal retainer (14), and the fairing safety-guide (12) on

the MLG fairing.

(38) Make sure that there is a minimum of 0.03 in. (0.76 mm) protrusion with the

fairing safety-guide (12) and the edge of the MLG fairing (refer to Figure 15,

Sheet 1, View C-C).

(39) Make sure that the distance between the fastener hole of the fairing

safety-guide (12) and the rebate of the MLG fairing is at minimum of 0.340 in.

(1.8 mm).

(40) Drill two holes from the pilot holes of the fairing safety-guide (12) through the

fairing forward seal (11) and the forward fairing to a diameter of 0.097 to 0.100

(2.46 to 2.54 mm).
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(41) Increase the diameter of the two holes from the pilot holes of the fairing

safety-guide (12) through the fairing forward seal (11) and the forward fairing

to 0.165 to 0.169 in. (4.19 to 4.29 mm).

(42) Backdrill four holes from the MLG fairing through the fairing forward seal (11)

and the fairing safety-guide (12) to a diameter of 0.165 to 0.169 in. (4.19 to

4.29 mm).

(43) Do a countersink of the two new holes in the MLG fairing to a diameter of

0.331 to 0.342 in. (8.41 to 8.69 mm) for the two bolts (1), (refer to Sheet 1,

View B).

(44) Remove the fairing safety-guide (12), the upper seal retainer (13), the lower

seal retainer (14), and the fairing forward seal (11).

(45) Remove burrs from the fairing safety-guide (12), the fairing forward seal (11)

and the MLG fairing.

(46) Clean the fairing forward seal (11) and the fairing safety-guide (12), the upper

seal retainer (13), the lower seal retainer (14) and the MLG fairing with clean,

dry cloths with no lint, moist with aliphatic naphta or equivalent.

(47) Dry the outer fairing forward-seal (11) and the fairing safety-guide (12), the

upper seal retainer (13), the lower seal retainer (14) and the MLG fairing with

clean, dry cloths with no lint.

(48) Apply chemical conversion compound or equivalent on the bare metal

surfaces of the upper seal retainer (13), the lower seal retainer (14) and the

fairing safety-guide (12) (refer to SRM 51-21-11-001-001).

(49) Apply epoxy primer on the bare surfaces of the upper seal retainer (13), the

lower seal retainer (14) and the fairing safety-guide (12)

(refer to SRM 51-25-06-001-001).

(50) Apply fluid resistant enamel, color grey No.16473, on the upper seal retainer

(13), the lower seal retainer (14) and the fairing safety-guide (12) (refer to SRM

51-25-16-001-001).

(51) Apply composite-laminate coating on the bare surfaces of the MLG fairing

(refer to SRM 51-25-52-001-001).

(52) Apply epoxy primer in the countersunk holes of the MLG fairing and on the

bare surfaces (refer to SRM 51-23-00-001-001).
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(53) Install the fairing forward seal (11), the fairing safety-guide (12), the upper seal

retainer (13) and the lower seal retainer (14) as follows:

(a) Install and secure the fairing forward seal (11), the fairing safety-guide

(12), the upper seal retainer (13) and the lower seal retainer (14) on the

MLG fairing.

(b) With sealant, install the bolt (15) through the MLG fairing and the

MLG faIring seal (refer to SRM 51-41-02-001-001).

(c) Wet-install the bolts (1) through the MLG fairing with the washers (3) and

the nuts (2) (refer to Figure 15, Sheet 1, View B)

(refer to SRM 51-41-02-001-001).

(d) Torque the nuts (2) and the screw (15) (refer to AMM 20-21-00-910-801).

(54) Install the seal (7) and the seal retainer (8) as follows:

(a) Clean the seal retainer (7), the seal (8) and the aft area of the MLG with

clean, dry cloths with no lint moist with aliphatic naphta or equivalent.

(b) With sealant, install the bolts (1) through the MLG fairing, the seal (8),

the seal retainer (7), the washers (3) and the nuts (2)

(refer to SRM 51-23-00-390-810).

(c) Torque the nuts (2) (refer to AMM 20-21-00-910-801).

(55) Installation of the seal (10) and the seal retainer (9) as follows:

(a) Clean the seal retainer (9), the seal (10) and the aft area of the MLG with

clean, dry cloths with no lint moist with aliphatic naphta or equivalent.

(b) With sealant, install the bolts (6) through the MLG fairing, the seal (10),

the seal retainer (9), the washers (3) and the nuts (2)

(refer to SRM 51-23-00-001-001).

(c) Torque the nuts (2) (refer to AMM 20-21-00-910-801).

(d) Clean the area of the forward and the aft MLG fairing with clean, dry

cloths with no lint, moist with aliphatic naphta or equivalent.

(e) Dry the area with clean, dry cloths with no lint.
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Refer to Figure 7.

(56) With an indelible ink pen or equivalent, identify the aft stop-fitting (1) of the

MLG fairing as shown in the table below (refer to AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

CC670-39076-1 KBA670-10500-39

(57) If only PART C is done, with a indelible ink pen or equivalent, identify the left

MLG fairing with the applicable part number listed in the table below (refer to

AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

BA670-00001-2085 KBA670-10500-300

CC670-39005-951 KBA670-10500-500

CC670-39005-3 KBA670-10500-700

CC670-39005-5 KBA670-10500-130

CC670-39019-49 KBA670-10500-190

CC670-39019-963 KBA670-10500-150

CC670-39019-965 KBA670-10500-170

CC670-39019-51 KBA670-10500-210

KBA670-39005-3 KBA670-10500-610

KBA670-39005-5 KBA670-10500-630

KBA670-39005-7 KBA670-10500-650

KBA670-39005-9 KBA670-10500-670
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(58) If PART C and PART D are done or PART B and PART C are done, with a

indelible ink pen or equivalent, identify the MLG fairing assembly with the

applicable part number listed in the table below (refer to AMM

20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

BA670-00001-2085 KBA670-10500-3

CC670-39005-951 KBA670-10500-5

CC670-39005-3 KBA670-10500-7

CC670-39005-5 KBA670-10500-13

CC670-39019-49 KBA670-10500-19

CC670-39019-963 KBA670-10500-15

CC670-39019-965 KBA670-10500-17

CC670-39019-51 KBA670-10500-21

KBA670-39005-3 KBA670-10500-61

KBA670-39005-5 KBA670-10500-63

KBA670-39005-7 KBA670-10500-65

KBA670-39005-9 KBA670-10500-67

(59) Apply a bead of sealant on the aft stop-fitting (1) and the sealing member

(refer to Figure 7, Sheet 2, View C) (refer to SRM 51-23-00-001-001).

(60) Apply epoxy primer on the rivets (4) and (5), bolts (2) and nuts (3). (refer to

SRM51-25-06-001-001).

(61) Apply fluid resistant enamel, color grey No.16473, on the bolt (2), the nut (3)

and the rivets (4) and (5) (refer to SRM 51-25-16-001-001).

(62) Apply fluid resistant enamel on the bolts (2). Refer to the external paint

scheme for the color (refer to SRM 51-25-16-001-001).
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Refer to Figure 15.

(63) Identify the seal retainers (13) and (14) with the applicable part number listed

in the table below (refer to AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

Seal retainer CC670-39245-1 Upper seal retainer

KBA670-10500-41

Lower seal retainer

KBA670-10500-43

Refer to Figure 17.

(64) Do a clearance check of the left MLG doors

(refer to AMM 32-12-01-220-801).

NOTE: Use the post-Service Bulletin 670BA-32-040 task to do the clearance

check.

(65) Do the extension of the MLG (refer to AMM 32-12-01-220-801).

(66) If it is not possible to complete all the instructions in this service bulletin

because of the configuration of the aircraft, speak with a representative of

Bombardier Customer Response Centre at phone number 514-855-8500 or

send an e-mail at thd.crj@bombardier.com for analysis and to get an

approved disposition to complete this service bulletin.
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I. Job Close-Out

(1) Remove all tools, equipment, and unwanted materials from the work area.

(2) If removed, install the left MLG wheel bin (refer to AMM 53-83-89-400-801).

(3) Remove the tags and close the circuit breakers that follow:

CB PANEL CB NO. NAME

CBP-1 A12 HEATERS TAT

CBP-1 A13 HEATERS AOA R

CBP-1 A14 HEATERS PITOT R

CBP-1 C13 ADG HEATER

CBP-1 G1 PSEU CH A

CBP-1 G2 NOSE STEER

CBP-1 G13 HEATERS ADS CONT 2

CBP-1 G14 HEATERS STATIC R

CBP-1 LOWER T7 HEATERS PITOT L

CBP-1 LOWER T8 HEATERS AOA L

CBP-1 LOWER T9 HEATERS PITOT STBY

CBP-1 LOWER U7 ENG IGN A

CBP-2 G1 PSEU CH B

CBP-2 G2 NOSE STEER

CBP-2 N6 ADG DEPLOY AUTO

CBP-2 N9 MLG BAYOVHT DET

CBP-2 P1 PSEU CH A

CBP-2 P2 PSEU CH B

CBP-2 LOWER S1 HEATERS STATIC L

CBP-2 LOWER S2 HEATERS ADS CONT 1

CBP-2 LOWER S3 HEATERS ADS CONT STBY
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CB PANEL CB NO. NAME

CBP-5 B10 ENG IGN B

(4) If the left wheel bin was removed, do the operational test of the MLG overheat

detection and warning system (refer to AMM 26-14-04-710-801).

(5) Do the lubrication of the MLG and the MLG door

(refer to AMM 12-20-32-640-802).

(6) Do the operational test of the landing-gear extension/retraction system

(refer to AMM 32-30-00-710-801).

(7) Remove the aircraft from jacks (refer to AMM 07-11-01-586-801).

(8) Make sure that step 2. B (64) of PART C is completed and meet the

requirements before you do the entry in the applicable logbooks.

(9) When PART C of this service bulletin is completed, add the weight and

balance data shown in paragraph 1.I. of this service bulletin to the Weight and

Balance Manual. Under ‘Description of Change’ enter “Service Bulletin

670BA-32-040 PART C, Revision E, incorporated.”

(10) When PART C of this service bulletin is completed, make this entry in the

applicable logbooks: “Service Bulletin 670BA-32-040, Revision E, Landing

Gear - Main Landing Gear (MLG) and Doors - Increase the Clearances

Between the MLG Fairing and the MLG Doors, PART C , incorporated.”
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PART D --- Installation of the Inboard MLG Door Part Number CC670-10520-16 and

Increase of the Clearance Between the Right MLG Inboard-Door and the MLG Fairing

J. Job Set-Up

Reference Information

REFERENCE DESIGNATION

AMM 07-11-01-582-801 Jacking of the Aircraft

AMM 07-11-01-586-801 Lowering of the Aircraft

AMM 10-11-00-400-801 Installation of the Nose Landing Gear (NLG)

Lockpin

AMM 10-11-00-400-802 Installation of the Main Landing Gear (MLG)

Lockpins

AMM 12-00-00-867-801 Standard Aircraft Configuration for Maintenance

AMM 12-20-32-640-802 Lubrication of the Main Landing Gear (MLG)

AMM 20-21-00-910-801 Torquing of Threaded Fasteners

AMM 20-51-00-000-801 Removal of Cotter Pins

AMM 20-51-00-000-802 Removal of Lockwire

AMM 20-51-00-400-801 Installation of Cotter Pins

AMM 20-51-00-400-802 Installation of Lockwire

AMM 20-60-13-930-801 Identification of Aircraft Parts and Assemblies

AMM 32-12-01-000-802 Removal of the Inboard MLG Doors

AMM 32-12-01-220-801 Clearance Check of the MLG Doors

AMM 32-12-01-400-802 Installation of the Inboard MLG Doors

AMM 32-12-01-820-801 Adjustment of the MLG Doors

AMM 32-30-00-710-801 Operational Test of the Landing-Gear Extension/

Retraction System

AMM 51-23-00-100-801 Removal of Sealants

NDT 51-20-006-250 Eddy Current - Inspection Procedures

NDT 51-20-008-230 Liquid Penetrant - Inspection Procedures
SERVICE BULLETIN 670BA---32---040

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REFERENCE DESIGNATION

NDT 51-20-009-210 Visual - Inspection Procedures

SRM 51-21-11-001-001 Corrosion Prevention Procedures

SRM 51-21-16-001-001 Finish Codes

SRM 51-23-00-001-001 Pressure, Environmental, Fuel Tank and Firewall

Sealing

SRM 51-25-06-001-001 Fluid-Resistant (FR) Epoxy Primer

SRM 51-25-16-001-001 Fluid-Resistant (FR) Polyurethane Topcoat

SRM 51-25-52-001-001 Composite-Laminate Coatings

SRM 51-26-00-001-001 Cleaning

SRM 51-40-06-001-001 Fastener Edge Distance and Pitch

SRM 51-40-11-001-001 Preparation of Fastener Holes

SRM 51-41-02-001-001 Bolts, Screws and Related Items

SRM 51-42-06-001-001 Solid Rivets

SRM 51-42-21-001-001 Hi-Lite Fasteners

SRM 51-71-00-001-001 Typical Structural Repairs

SRM 51-75-00-001-001 Graphite Repairs
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Tolerance Information

Linear Tolerances Angular Tolerance

X.XX in. (X.X mm) X.X in. (X mm)

+/-0 30” +/- 0.03 in. +/- 0.1 in.

+/- 0.8 mm +/- 3 mm

NOTE: The tolerances above apply to the dimensions given in this service

bulletin, except when specified differently.

(1) Make sure that the aircraft is in standard configuration for maintenance

(refer to AMM 12-00-00-867-801).

WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO

MAINTENANCE ON OR NEAR ELECTRICAL/ELECTRONIC

EQUIPMENT. IF YOU DO NOT OBEY THE SAFETY PRECAUTIONS,

INJURIES TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT CAN

OCCUR.

(2) Open, safety, and tag the circuit breakers that follow:

CB PANEL CB NO. NAME

CBP-1 A12 HEATERS TAT

CBP-1 A13 HEATERS AOA R

CBP-1 A14 HEATERS PITOT R

CBP-1 C13 ADG HEATER

CBP-1 G1 PSEU CH A

CBP-1 G2 NOSE STEER

CBP-1 G13 HEATERS ADS CONT 2

CBP-1 G14 HEATERS STATIC R

CBP-1 LOWER T7 HEATERS PITOT L

CBP-1 LOWER T8 HEATERS AOA L

CBP-1 LOWER T9 HEATERS PITOT STBY

CBP-1 LOWER U7 ENG IGN A

CBP-2 G1 PSEU CH B

CBP-2 G2 NOSE STEER
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CB PANEL CB NO. NAME

CBP-2 N6 ADG DEPLOY AUTO

CBP-2 N9 MLG BAYOVHT DET

CBP-2 P1 PSEU CH A

CBP-2 P2 PSEU CH B

CBP-2 LOWER S1 HEATERS STATIC L

CBP-2 LOWER S2 HEATERS ADS CONT 1

CBP-2 LOWER S3 HEATERS ADS CONT STBY

CBP-5 B10 ENG IGN B

(3) Put the aircraft on jacks (refer to AMM 07-11-01-582-801).

(4) If necessary, remove the right MLG wheel bin

(refer to AMM 53-83-89-000-801).
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K. Procedure

For all aircraft

Refer to Figure 1.

(1) Do a detailed visual inspection of the right section of the MLG fairing as

follows (refer to NDT 51-20-009-210):

(a) Visually inspect to make sure that the forward and the aft stops are not

missing from the MLG fairing.

(b) If the forward and/or the aft stops are not missing, visually inspect that

there are no loose or missing fasteners from the forward and aft stops.

(c) Visually inspect along the edge of the MLG fairing adjacent the MLG

door to make sure that there is no damage. Refer to the shaded area

(refer to Figure 1, Sheet 2).

NOTE: For this inspection, damage does not include surface scratches and/or

paint deterioration.

(d) Record the findings on the record sheet in Appendix A.

Refer to Figure 3.

(2) Do a detailed visual inspection of the stops (1) and (2), and the wedge (3) on

the right side of the forward and the aft spars as follows (refer to NDT

51-20-009-210):

(a) Visually inspect to make sure that the stops (1) and (2) are not missing.

(b) If the stops (1) and/or (2) are not missing, visually inspect that there are

no loose or missing fasteners from the stops (1) and/or (2).

(c) Visually inspect to make sure that the wedge (3) is not missing.

(d) If the wedge (3) is not missing, visually inspect that there are no loose or

missing fasteners from the wedge (3).

(e) Record the findings on the record sheet of Appendix A.
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Refer to Figure 1 and 3.

(3) If damage is found and/or there are missing parts and/or fasteners, speak

with a representative of the Customer Response Center (CRC) at phone

number 514-855-8500 for a disposition.

NOTE: Refer to the record sheet of Appendix A for data.

(4) If no damage is found and there is no missing part or fastener, go to the next

step.

Refer to Figure 6.

(5) Remove and discard the aft fairing seal (4) and the aft retainer seal (5) from

the fairing as follows:

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(a) Remove and discard the three bolts (1), the washers (2), and the nuts

(3).

(b) Remove and discard the seal aft fairing (4) and the aft retainer seal (5)

from the fairing.

(6) Remove the aft stop-fitting (14) as follows:

(a) Remove the two bolts (6), the washers (10), and the nuts (11).

(b) Remove and discard the stop pad (7), the laminated shim (8), and the

shim (9).

(c) Remove the sealant from the aft stop-fitting (14) and the sealing member

(refer to Figure 6, Sheet 1, View D) (refer to AMM 51-23-00-100-801).

(d) Remove the three solid rivets (17).

(e) Remove and discard the bolts (12) and the nuts (13).

(f) Remove the aft stop-fitting (14) from the sealing member.

(g) Remove the sealant from the MLG fairing, the sealing member and on

the aft stop-fitting (14) (refer to AMM 51-23-00-100-801).
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(7) Drill the aft stop-fitting (14) as follows:

(a) Temporarily install the shim fairing (15) on the aft stop-fitting (14). Make

sure that the shim fairing (15) is parallel to the edge of the aft stop-fitting

(14) (refer to Figure 6, Sheet 2, View E).

(b) Attach the shim fairing (15) with the bolt (6), the washer (10), and the nut

(11).

(c) Backdrill one hole to a diameter of 0.190 to 0.194 in (4.83 to 4.93 mm)

from the shim fairing (15) to the aft stop-fitting (14).

(d) Remove and discard the nut (11).

(e) Remove the bolt (6), the washer (10), and the shim fairing (15).

(f) Temporarily install the shim fairing (15) on the laminated shim (16).

(g) Increase the diameter of two holes in the shim fairing (15) and the

laminated shim (16) to 0.213 to 0.217 (5.41 to 5.51 mm).

(h) Disassemble and remove burrs and sharp edges from the holes of the

shim fairing (15), the laminated shim (16), and the aft stop-fitting (14).

(i) Clean the bare metal surfaces of the aft stop-fitting (14) with clean dry

cloths, with no lint, moist with aliphatic naphta or equivalent.

(j) Dry the bare surfaces with clean dry cloths with no lint.

(k) Apply chemical conversion compound on the bare metal surfaces of the

hole in the aft stop-fitting (14) (refer to SRM 51-21-11-001-001).

(l) Touch-up the hole in the aft stop-fitting (14) with epoxy primer (refer to

SRM 51-25-06-001-001).

(m) Touch-up the hole in the aft stop-fitting (14) with fluid resistant enamel

color grey #16473 (refer to SRM 51-25-16-001-001).

Refer to Figure 7.

(8) Remove 0.53 in. to 0.61 in. (13.4 to 15.5 mm) of material from the aft area of

the MLG fairing (refer to Figure 7, Sheet1, View D and SRM

51-71-00-001-001).

NOTE: An edge distance of 0.57 in (14.50 mm) for the three holes of the aft

stop-fitting (1) is necessary.

(9) Install the aft stop-fitting (1) as follows:

(a) Apply sealant on the mating surface of the aft stop-fitting (1) (refer to

SRM 51-23-00-001-001).
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(b) Install the aft stop-fitting (1) on the sealing member of the MLG fairing.

(c) Wet-install the two upper rivets (5) on the aft stop-fitting (1) (refer to

Figure 7, View C and SRM 51-42-06-001-001 and SRM

51-23-00-001-001).

(d) Wet-install one rivet (4) at the bottom of the aft stop-fitting (1) (refer to

Figure 7, View C and SRM 51-42-06-001-001 and SRM

51-23-00-001-001).

(e) Wet-install the three bolts (2) and the nuts (3) (refer to SRM

51-42-21-001-001 and SRM 51-23-00-001-001).

NOTE: The installation of the stop pad (7), the laminated shim (8), and the

shim (9) will be incorporated in a subsequent step during the

clearance check.

Refer to Figure 18.

(10) If installed, remove the inboard MLG door (1) (refer to AMM 32-12-01-00-802).

For Aircraft 10002 thru 10217, 15002 thru 15043 and 15991 pre-IS Modification

Summary IS670528200033 with inboard MLG door CC670-10520-2014,

CC670-10520-2016, KCC670-10900-4, KCC670-10900-6

(11) Do IS Modification Summary IS670528200033.

NOTE: During the incorporation of the IS Modification Summary

IS670528200033, it is not necessary to remove the outboard MLG door.

For all aircraft

Refer to Figure 10 and 18.

(12) Install the right inboard MLG door (2) and adjust the aft attachment of the

outboard MLG door and the inboard MLG door as follows:

(a) Install the right inboard MLG door (2) (refer to AMM 32-12-01-400-802).

NOTE: During the installation of the inboard MLG door (2) refer to AMM

32-12-01-400-802 post-Service Bulletin 670BA-32-040.

(b) Apply Aeroshell No.33 grease on the sleeve bushing (4) and the shank

of the bolt (1).
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(c) Install the sleeve bushing (4), the washer (10) and the bolt (1).

(d) Move the door to the aft position until the the bushing (11) touches the

bushing (12).

(e) Measure the clearance between the bushings (2) and (3).

(f) If the clearance is between 0.062 and 0.093 in. (1.57 to 2.36 mm), install

the washer (7).

(g) If the clearance is between 0.094 and 0.125 in. (2.39 to 3.18 mm), install

the washer (8).

NOTE: If the clearance is 0.126 (3.20 mm) or higher, speak with a

representative of the Customer Response Center (CRC) at phone

number 514-855-8500 for a disposition.

(h) Make sure that there is a clearance of 0.030 and 0.060 in.

(0.76 to 1.42 mm) after the installation of the new washer.

(i) Install the washer (5) and the nut (6).

(j) Torque the nut (6) (refer to AMM 20-21-00-910-801).

(k) Safety the nut (6) with the cotter pin (9) (refer to AMM 20-51-00-400-801).

Refer to Figure 12.

(13) Before the installation of the wheel bin, record the part number of the MLG

fairing.

NOTE: The part number will be necessary in a subsequent step for the

identification.

(14) Install the right MLG wheel bin (refer to AMM 53-83-89-400-801).

(15) Identify locations PT2 to PT6 and PT9 to PT13 on the MLG door as follows:

NOTE: All PT locations must be identified on the outer skin of the MLG door.

NOTE: Make sure that you can see the identification mark-up when the door is

in the closed position.

(a) With a indelible ink pen, identify the PT2 on the forward edge of the

inboard door, at 0.50 in.(12.7 mm) from the outboard edge of the angle,

(refer to Figure 12, Sheet 1,View B).
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(b) With a indelible ink pen, identify the PT3 on the forward edge of the

inboard door, aligned with the stiffener of the forward member.

(c) With a indelible ink pen, identify the PT4 on the forward edge of the

inboard door, at 0.50 in.(12.7 mm) from the outboard edge of the

inboard door.

(d) With a indelible ink pen, identify the PT5 on the forward edge of the

outboard door, at 0.50 in.(12.7 mm) from the inboard edge of the

outboard door.

(e) With a indelible ink pen, identify the PT6 on the forward edge of the

outboard door, aligned with the stiffener of the forward member.

(f) With a indelible ink pen, identify the PT9 on the aft edge of the outboard

door, aligned with the stiffener of the forward member.

(g) With a indelible ink pen, identify the PT10 on the aft edge of the

outboard door, at 0.50 in (12.7 mm) from the inboard edge of the

outboard door.

(h) With a indelible ink pen, identify the PT11 on the aft edge of the inboard

door, at 2.50 in (63.5 mm) from the outboard edge of the inboard door.

(i) With a indelible ink pen, identify the PT12 on the aft edge of the inboard

door, aligned with the stiffener of the aft member.

(j) With a indelible ink pen, identify the PT13 on the forward edge of the

inboard door, at 0.50 in.(12.7 mm) from the outboard edge of the angle.

(16) Do the retraction of the main landing gear (refer to AMM 32-30-00-865-801).

(17) Identify locations PT1 and PT14 to PT25 on the MLG fairing as follows:

(a) With a indelible ink pen, identify the PT1 on the forward edge of the

inboard door, at 1.50 in.(38.1 mm) from the end of the fairing seal, (refer

to Figure 12, Sheet 2, View E).

(b) With a indelible ink pen, identify the PT14 on the aft edge of the fairing,

aligned with the screw on the fairing.
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(c) With a indelible ink pen, identify the PT15 on the aft edge of the inboard

door, at 0.50 in (12.7 mm) from the more down edge of the angle, (refer

to Figure 12, Sheet 2, View D).

(d) With a indelible ink pen, identify the PT16 on the aft edge of the inboard

door, align with the screw on the fairing.

(e) With a indelible ink pen, identify the PT17 on the aft edge of the inboard

door, align with the screw on the fairing.

(f) With a indelible ink pen, identify the PT18 on the aft edge of the inboard

door, align with the screw on the fairing.

(g) With a indelible ink pen, identify the PT19 on the aft edge of the inboard

door, align with the screw on the fairing.

(h) With a indelible ink pen, identify the PT20 on the forward edge of the

inboard door, align with the screw on the fairing.

(i) With a indelible ink pen, identify the PT21 on the forward edge of the

inboard door, align with the screw on the fairing.

(j) With a indelible ink pen, identify the PT22 on the forward edge of the

inboard door, align with the screw on the fairing.

(k) With a indelible ink pen, identify the PT23 on the forward edge of the

inboard door, at 0.50 in (12.7 mm) from the edge of the angle.

(l) With a indelible ink pen, identify the PT24 on the forward edge of the

inboard door, in line with the screw on the fairing.

(m) With a indelible ink pen, identify the PT25 on the forward edge of the

inboard door, in line with the screw on the fairing.

NOTE: At this point do not remove material on the inboard MLG door or

on the MLG fairing.
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Refer to Figure 12.

(18) Measure and record the mismatches in Table 1 of Apppendix B.

NOTE: At this point do not remove material on the inboard MLG door or on the

MLG fairing.

(19) Make sure that the mismatches are within the values shown in Table 1 of

Appendix B.

NOTE: Do not remove the hydraulic test fixture it will be needed in subsequent

steps.

(20) If the mismatches at PT 22 and PT 23 are not within -0.050 to +0.100 in.

(-1.27 to +2.54 mm), speak with a representative of the Customer Response

Center (CRC) at phone number 514-855-8500 for a disposition.

(21) If the mismatched values recorded in Table 1 of Appendix B are not within the

permitted values, do the adjustment of the MLG doors

(refer to AMM 32-12-01-820-801).

(22) If the adjustment of the MLG doors procedure cannot be done with the AMM

task, speak with a representative of the Customer Response Center (CRC) at

phone number 514-855-8500 for a disposition

(refer to AMM 32-12-01-820-801).

(23) If the mismatched values recorded in Table 1 of Appendix B are within the

permitted values, record the clearances in Table 2 of Appendix B.

(24) If the recorded clearance values are higher than the acceptable clearance

values given in Table 2 of Appendix B, speak with a representative of the

Customer Response Center (CRC) at phone number 514-855-8500 for a

disposition (refer to AMM 32-12-01-820-801).

Refer to Figure 17.

(25) Record in Table 3 of Appendix B the overlap between the aft stop-fitting (1)

and the MLG door stop fitting (refer to Figure 17, View C-C).

(26) Do the extension of the main landing gear

(refer to AMM 32-30-00-992-801).

NOTE: Do not remove the hydraulic test fixture it will be needed in subsequent

steps.
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Refer to Figure 6 and Figure 17.

(27) Remove material from the aft stop-fitting (14) as follows:

NOTE: The overlap between the aft stop-fitting (14) and the MLG door stop fitting

is recorded in Appendix B Table 3 (refer to Figure 17, Sheet 1, View

C-C).

(a) Remove material from the aft stop-fitting (14) to have a minimum overlap

of 0.600 in. (15.24 mm) between the aft stop-fitting and the MLG door

stop fitting (refer to Figure 6, Sheet 2, View E).

NOTE: The aft stop fitting must be cut as close as possible to the stop pad.

(b) Remove burrs and break sharp edges on the aft stop-fitting (14).

(c) Do a radius of 0.250 in. (6.35 mm) on the aft stop-fitting (14)

(refer to Figure 6, Sheet 2, View E).

(d) Clean the bare surfaces of the aft stop-fitting (14) with clean dry cloths,

with no lint, moist with aliphatic naphta or equivalent.

(e) Dry the bare surfaces with clean dry cloths with no lint.

Refer to Figure 13.

(28) If necessary, remove the right MLG wheel bin (refer to AMM

53-83-89-000-801).

(29) Remove of the seals (8), (10), (4), (11), and the seal retainers (5), (7), (9) as

follows:

(a) Remove the bolts (1), (6), (12), and the washers (3).

(b) Remove and discard the nuts (2).

(c) Remove the seal retainers (5), (7) and (9).

(d) Remove the seals (8) and (11).

(e) Remove and discard the seal (4) and (10).
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Refer to Figure 12 and 14.

(30) Remove material from the outboard MLG door and the MLG fairing as follows

(refer to SRM 51-75-00-001-001):

CAUTION: DURING THE PROCEDURE PROTECT THE WORK AREA AND THE MLG.

THIS WILL PREVENT DIRT, CHIPS, OR OTHER UNWANTED MATERIAL TO

CAUSE DAMAGE TO THE AIRCRAFT.

(a) Calculate the difference between the acceptable clearance values and

the actual clearance values recorded in Table 2 of Appendix B.

NOTE: The removal of the material must be done only on the MLG fairing

and on the outboard MLG door.

(b) On the upper forward section of the MLG fairing, between PTA and PTB,

remove material up to a maximum of 0.23 in. (5.8 mm) (refer to Figure

14, Sheet 1, View C) (refer to SRM 51-75-00-001-001). Make sure that

there is a minimum edge distance of 0.42 in (10.7 mm) from the

fasteners.

(c) On the forward lower section of the MLG fairing between PT B and PT C,

remove material to a maximum of 0.16 in. (4.1 mm) (refer to Figure 14,

Sheet 1, View D) (refer to SRM 51-75-00-001-001). Make sure that there

is a minimum edge distance of 0.57 in (14.5 mm) from the fasteners.

(d) On the aft section of the MLG fairing between PT D and PT E, remove

the material to a maximum of 0.10 in. (2.5 mm) (refer to Figure 14, Sheet

1, View C) (refer to SRM 51-75-00-001-001). Make sure that there is a

minimum edge distance of 0.42 in. (10.7 mm) with the fasteners.

(e) On the aft section of the MLG fairing between PT E and PT F, remove the

material to a maximum of 0.10 in. (2.5 mm) (refer to Figure 14, Sheet 1,

View C) (refer to SRM 51-75-00-001-001). Make sure that there is a

minimum edge distance of 0.57 in. (14.5 mm) with the fasteners.
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Refer to Figure 6.

(31) Do a liquid penetrant inspection or an eddy current inspection of the aft

stop-fitting (14) as follows:

(a) Do a liquid penetrant inspection or an eddy current inspection on the cut

section of the aft stop-fitting (14) (refer to Figure 6, Sheet 2, View E,

NDT 51-20-008-230, or NDT 51-20-006-250)

(b) If there is no crack on the aft stop-fitting (14) go to next step.

(c) If there is a crack on the cut section of the aft stop-fitting (14), speak with

a representative of the Customer Response Center (CRC) at phone

number 514-855-8500 for a disposition.

(32) If there is no crack on the aft stop-fitting (14) do the steps that follow:

(a) Apply chemical conversion compound or equivalent on the bare

surfaces of the aft stop-fitting (14), (refer to SRM 51-21-11-001-001).

(b) Apply epoxy primer on the bare surfaces and the hole of the aft

stop-fitting (14) (refer to SRM 51-25-06-001-001).

(c) Apply fluid resistant enamel color grey #16473 on the aft stop-fitting (14)

(refer to SRM 51-25-16-001-001).

Refer to Figure 15.

For aircraft that have not had the forward fairing seal (11) incorporated with Service

Bulletin 670BA-32-030

(33) Install the forward fairing seal (11), the upper seal retainer (13), the lower seal

retainer (14) and the fairing safety-guide (12) as follows:

(a) Temporary install and secure the fairing forward seal (11) and the

retainer seal (5) on the MLG fairing (refer to Figure 15, Sheet 1, View B)

(pre-mod).

(b) Backdrill the holes from the MLG fairing through the fairing forward seal

(11) to a diameter of 0.165 to 0.169 in. (4.19 to 4.29 mm).

(c) Remove the fairing forward seal (11) and the seal retainer (5).

(d) Remove the burrs from the forward seal (11).
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For aircraft that had the forward fairing seal (11) incorporated with Service Bulletin

670BA-32-030

(34) Do a detail inspection on the fairing forward seal (11) for signs of cuts or

damages in the material base.

NOTE: For the MLG fairing seal (11) exterior low friction polyester fabric is not

part of the base rubber material rejection criteria.

For all aircraft

(35) Temporary install and secure the aft fairing seal (10) to the seal retainer (9)

(refer to Figure 15, Sheet 2, View D).

(a) Backdrill the holes from the seal retainer (9) through the aft fairing

seal (10) to a diameter of 0.165 to 0.169 in. (4.19 to 4.29 mm).

(b) Remove the aft fairing seal (10) and the seal retainer (9).

(c) Remove the burrs from the aft fairing seal (10).

(36) Temporary install and secure the fairing forward seal (11), the seal retainer (5)

and the fairing safety-guide (12) on the MLG fairing (refer to Figure 15, Sheet

1, View B, pre-mod).

(a) Make the upper seal retainer (13) and lower seal retainer (14) from the

seal retainer (5) as follows:

1 Make a line on the seal retainer (5) at the two ends of the fairing

safety-guide (12) (refer to Figure 15, Sheet 1, View B, (Pre-Mod).

NOTE: The maximum and the minimum clearance between the seal

retainer (5) and the fairing safety-guide (12) is 0.13 to 0.07 in.

(2.54 to 1.78 mm).

2 Remove the fairing safety-guide (12), the seal retainer (5) and the

fairing forward-seal (11).

3 Make sure that there is a minimum edge distance of 0.39 in.

(9.9 mm) at the two ends of the seal retainer (5).

4 Cut the seal retainer (5) at the cutting line (refer to SRM

51-71-00-001-001).

5 Do a radius of 0.25 in (6.3 mm) on the upper and lower seals (refer

to Figure 15, Sheet 1, View B) (pre-Mod).
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6 Temporarily identify the two seal retainers as follows:

a Identify the upper seal retainer as item (13).

b Identify the lower seal retainer as item (14).

c Discard the middle part of the seal retainer (5).

(37) Temporary install and secure the fairing forward seal (11), the upper seal

retainer (13), the lower seal retainer (14), and the fairing safety-guide (12) on

the MLG fairing.

(38) Make sure that there is a minimum of 0.03 in. (0.76 mm) of protrusion with the

fairing safety-guide (12) and the edge of the MLG fairing (refer to Figure 15,

Sheet 1, View C-C).

(39) Make sure that the distance between the fastener hole of the fairing

safety-guide (12) and the rebate of the MLG fairing is at minimum of 0.340 in.

(1.8 mm).

(40) Drill two holes from the pilot holes of the fairing safety-guide (12) through the

fairing forward seal (11) and the forward fairing to a diameter of 0.097 to 0.100

(2.46 to 2.54 mm).

(41) Increase the diameter of the two holes from the pilot holes of the fairing

safety-guide (12) through the fairing forward seal (11) and the forward fairing

to 0.165 to 0.169 in. (4.19 to 4.29 mm).

(42) Backdrill four holes from the MLG fairing through the fairing forward seal (11)

and the fairing safety-guide (12) to a diameter of 0.165 to 0.169 in. (4.19 to

4.29 mm).

(43) Do a countersink of the two new holes in the MLG fairing to a diameter of

0.331 to 0.342 in. (8.41 to 8.69 mm) for the two bolts (1) (refer to Sheet 1,

View B).

(44) Remove the fairing safety-guide (12), the upper seal retainer (13), the lower

seal retainer (14), and the fairing forward seal (11).

(45) Remove burrs from the fairing safety-guide (12), the fairing forward seal (11),

and the MLG fairing.
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(46) Clean the fairing forward seal (11) and the fairing safety-guide (12), the upper

seal retainer (13), the lower seal retainer (14), and the MLG fairing with clean,

dry cloths with no lint, moist with aliphatic naphta or equivalent.

(47) Dry the outer fairing forward-seal (11) and the fairing safety-guide (12), the

upper seal retainer (13), the lower seal retainer (14), and the MLG fairing with

clean, dry cloths with no lint.

(48) Apply chemical conversion compound or equivalent on the bare metal

surfaces of the upper seal retainer (13), the lower seal retainer (14), and the

fairing safety-guide (12) (refer to SRM 51-21-11-001-001).

(49) Apply epoxy primer on the bare surfaces of the upper seal retainer (13), the

lower seal retainer (14) and the fairing safety-guide (12)

(refer to SRM 51-25-06-001-001).

(50) Apply fluid resistant enamel, color grey No.16473, on the upper seal retainer

(13), the lower seal retainer (14), and the fairing safety-guide (12) (refer to

SRM 51-25-16-001-001).

(51) Apply composite-laminate coating on the bare surfaces of the MLG fairing

(refer to SRM 51-25-52-001-001).

(52) Apply epoxy primer in the countersunk holes of the MLG fairing and on the

bare surfaces (refer to SRM 51-23-00-001-001).

(53) Installation of the fairing forward seal (11), the fairing safety-guide (12), the

upper seal retainer (13), and the lower seal retainer (14) as follows:

(a) Install and secure the fairing forward seal (11), the fairing safety-guide

(12), the upper seal retainer (13), and the lower seal retainer (14) on the

MLG fairing.

(b) With sealant, install the bolt (15) through the MLG fairing and the

MLG fairing seal (refer to SRM 51-41-02-001-001).

(c) Wet-install the bolts (1) through the MLG fairing with the washers (3) and

the nuts (2) (refer to Figure 15, Sheet 1, View B)

(refer to SRM 51-41-02-001-001).

(d) Torque the nuts (2) and the screw (15) (refer to AMM 20-21-00-910-801).
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(54) Install the seal (7) and the seal retainer (8) as follows:

(a) Clean the seal retainer (7), the seal (8), and the aft area of the MLG with

clean, dry cloths with no lint moist with aliphatic naphta or equivalent.

(b) With sealant, install the bolts (1) through the MLG fairing, the seal (8),

the seal retainer (7), the washers (3) and the nuts (2)

(refer to SRM 51-23-00-390-810).

(c) Torque the nuts (2) (refer to AMM 20-21-00-910-801).

(55) Installation of the seal (10) and the seal retainer (9) as follows:

(a) Clean the seal retainer (9), the seal (10), and the aft area of the MLG with

clean, dry cloths with no lint, moist with aliphatic naphta or equivalent.

(b) With sealant, install the bolts (6) through the MLG fairing, the seal (10),

the seal retainer (9), the washers (3), and the nuts (2)

(refer to SRM 51-23-00-001-001).

(c) Torque the nuts (2) (refer to AMM 20-21-00-910-801).

(d) Clean the area of the forward and the aft MLG fairing with clean, dry

cloths with no lint, moist with aliphatic naphta or equivalent.

(e) Dry the area with clean, dry cloths with no lint.

Refer to Figure 7.

(56) With an indelible ink pen or equivalent, identify the aft stop-fitting (1) of the

MLG fairing as shown in the table below (refer to AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

CC670-39076-2 KBA670-10500-40
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 134 of 189

Oct 12/2012

Revision E, 13 Nov/2014

(57) If only PART D is done, with a indelible ink pen or equivalent, identify the right

MLG fairing with the applicable part number listed in the table below (refer to

AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

BA670-00001-2085 KBA670-10500-350

CC670-39005-951 KBA670-10500-550

CC670-39005-3 KBA670-10500-750

CC670-39005-5 KBA670-10500-135

CC670-39019-49 KBA670-10500-195

CC670-39019-963 KBA670-10500-155

CC670-39019-965 KBA670-10500-175

CC670-39019-51 KBA670-10500-215

KBA670-39005-3 KBA670-10500-615

KBA670-39005-5 KBA670-10500-635

KBA670-39005-7 KBA670-10500-655

KBA670-39005-9 KBA670-10500-675
SERVICE BULLETIN 670BA---32---040

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Revision E, 13 Nov/2014

(58) If PART C and PART D are done or PART D and PART A are done, with a

indelible ink pen or equivalent, identify the MLG fairing assembly with the

applicable part number listed in the table below (refer to AMM

20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

BA670-00001-2085 KBA670-10500-3

CC670-39005-951 KBA670-10500-5

CC670-39005-3 KBA670-10500-7

CC670-39005-5 KBA670-10500-13

CC670-39019-49 KBA670-10500-19

CC670-39019-963 KBA670-10500-15

CC670-39019-965 KBA670-10500-17

CC670-39019-51 KBA670-10500-21

KBA670-39005-3 KBA670-10500-61

KBA670-39005-5 KBA670-10500-63

KBA670-39005-7 KBA670-10500-65

KBA670-39005-9 KBA670-10500-67

(59) Apply a bead of sealant on the aft stop-fitting (1) and the sealing member

(refer to Figure 7, Sheet 2, View C) (refer to SRM 51-23-00-001-001).

(60) Apply epoxy primer on the rivets (4) and (5), the bolts (2) and the nuts (3)

(refer to SRM51-25-06-001-001).

(61) Apply fluid resistant enamel, color grey No.16473, on the bolt (2), the nut (3),

and the rivets (4) and (5) (refer to SRM 51-25-16-001-001).

(62) Apply fluid resistant enamel on the bolts (2). Refer to the external paint

scheme for the color (refer to SRM 51-25-16-001-001).
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 136 of 189

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Revision E, 13 Nov/2014

Refer to Figure 15.

(63) Identify the seal retainers (13) and (14) with the applicable part number listed

in the table below (refer to AMM 20-60-13-930-801).

PRE-SB PART NUMBER POST-SB PART NUMBER

Seal retainer CC670-39245-2 Upper seal retainer (13)

KBA670-10500-42

Lower seal retainer (14)

KBA670-10500-44

Refer to Figure 17.

(64) Do a clearance check of the right MLG doors

(refer to AMM 32-12-01-220-801).

NOTE: Use the post-Service Bulletin 670BA-32-040 task to do the clearance

check.

(65) Do the extension of the MLG (refer to AMM 32-12-01-220-801).

(66) If it is not possible to complete all the instructions in this service bulletin

because of the configuration of the aircraft, speak with a representative of

Bombardier Customer Response Centre at phone number 514-855-8500 or

send an e-mail at thd.crj@bombardier.com for analysis and to get an

approved disposition to complete this service bulletin.
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 137 of 189

Oct 12/2012

Revision E, 13 Nov/2014

L. Job Close-Out

(1) Remove all tools, equipment, and unwanted materials from the work area.

(2) If removed, install the right MLG wheel bin

(refer to AMM 53-83-89-400-801).

(3) Remove the tags and close the circuit breakers that follow:

CB PANEL CB NO. NAME

CBP-1 A12 HEATERS TAT

CBP-1 A13 HEATERS AOA R

CBP-1 A14 HEATERS PITOT R

CBP-1 C13 ADG HEATER

CBP-1 G1 PSEU CH A

CBP-1 G2 NOSE STEER

CBP-1 G13 HEATERS ADS CONT 2

CBP-1 G14 HEATERS STATIC R

CBP-1 LOWER T7 HEATERS PITOT L

CBP-1 LOWER T8 HEATERS AOA L

CBP-1 LOWER T9 HEATERS PITOT STBY

CBP-1 LOWER U7 ENG IGN A

CBP-2 G1 PSEU CH B

CBP-2 G2 NOSE STEER

CBP-2 N6 ADG DEPLOY AUTO

CBP-2 N9 MLG BAYOVHT DET

CBP-2 P1 PSEU CH A

CBP-2 P2 PSEU CH B

CBP-2 LOWER S1 HEATERS STATIC L

CBP-2 LOWER S2 HEATERS ADS CONT 1

CBP-2 LOWER S3 HEATERS ADS CONT STBY
SERVICE BULLETIN 670BA---32---040

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Page 138 of 189

Oct 12/2012

Revision E, 13 Nov/2014

CB PANEL CB NO. NAME

CBP-5 B10 ENG IGN B

(4) If the right wheel bin was removed, do the operational test of the MLG

overheat detection and warning system (refer to AMM 26-14-04-710-801).

(5) Do the lubrication of the MLG and the MLG door

(refer to AMM 12-20-32-640-802).

(6) Do the operational test of the landing-gear extension/retraction system

(refer to AMM 32-30-00-710-801).

(7) Remove the aircraft from jacks (refer to AMM 07-11-01-586-801).

(8) Make sure that step 2. B (64) of PART D is completed and meet the

requirements before you do the entry in the applicable logbooks.

(9) When PART D of this service bulletin is completed, add the weight and

balance data shown in paragraph 1.I. of this service bulletin to the Weight and

Balance Manual. Under ‘Description of Change’ enter “Service Bulletin

670BA-32-040 PART D, Revision E, incorporated.”

(10) When PART D of this service bulletin is completed, make this entry in the

applicable logbooks: “Service Bulletin 670BA-32-040, Revision E, Landing

Gear - Main Landing Gear (MLG) and Doors - Increase the Clearances

Between the MLG Fairing and the MLG Doors, PART D, incorporated.”
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 139 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Inspection of the Stops on the MLG Fairing

Figure 1 (Sheet 1 of 2)

ba7472a02.cgm, sd 7juin/2012

MLG FAIRING

(REF)

AFT STOP

(REF)

C

A

MLG FAIRING

(REF)

MLG FAIRING

(REF)

FWD STOP

(REF)

B

Left side shown,

right side opposite.

FASTENER

(REF)

FASTENER

(REF)

A

B C

NOTES
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 140 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Inspection of the MLG Fairing

Figure 1 (Sheet 2 of 2)

ba7472a01.cgm, gb, 09/07/12

A

A

MLG FAIRING

(REF)

1. Inspection area

is shaded.

2. Left side shown,

right side opposite.

NOTES
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 141 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Inspection of the Stops on the MLG Door

Figure 2 (Sheet 1 of 4)

ba7473a01.cgm, sd, 1 juin 2012

B

A

B

1

A

2

LEGEND

1. Stop.

2. Roller.

NOTE

Left side shown,

right side opposite.

MLG INBOARD

DOOR

(REF)
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 142 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Inspection of the Stops on the MLG Inboard Door

Figure 2 (Sheet 2 of 4)

ba7473a02.cgm, sd, 1juin 2012

C

5

NOTE

Left side shown,

right side opposite.

3

D

C

E

D

A

MLG INBOARD

DOOR

(REF)

E

4

LEGEND

3. Stop.

4. Stop.

5. Stop.
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 143 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Inspection of The Forward Edge of The MLG Door

Figure 2 (Sheet 3 of 4)

ba7473a03.cgm, sc, June 2012

MLG INBOARD

DOOR (REF)

1. Left side shown,

right side opposite.

2. Inspection area

is shaded.

G

F

F

G

NOTES
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 144 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Inspection of the aft Edge of The MLG Door

Figure 2 (Sheet 4 of 4)

ba7473a04.cgm, sc/cr, July 2012

1. Left side shown,

right side opposite.

2. Inspection area

is shaded.

H

F

H

NOTES
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 145 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Inspection of the Stops and Wedge

Figure 3 (Sheet 1 of 2)

ba7474a01.cgm, sd 1 juin 2012

B

NOTE

Left side shown,

right side opposite.

LEGEND

1. Stop.

FWD LOWER

SKIN

(REF)

A

B

A

1

FASTENER

(REF)
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 146 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Inspection of the Stops and Wedge

Figure 3 (Sheet 2 of 2)

ba7474a02.cgm, sd, 1 juin 2012

A

C

NOTE

Left side shown,

right side opposite.

3

2

FASTENER

(REF)

FASTENER

(REF)

LEGEND

2. Stop.

C 3. Wedge.

AFT LOWER

SKIN

(REF)
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 147 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Removal of the Roller Assembly

Figure 4 (Sheet 1 of 1)

ba7470a01.cgm, sd 30mai/2012

B

1

5

5

4

3

5

2

6

LEGEND

1. Roller

601R38119--19.

2. Cotter pin

MS24665--153.

3. Nut

MS17826--3.

4. Bolt

NAS6203--17D.

5. Washer

NAS1149D0332J.

6. Bushing

NAS76A3--024P.

A

A

B

INBOARD

MLG DOOR

(REF)

OUTBOARD

MLG DOOR

(REF)

NOTE

Left side shown. Right side opposite.
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 148 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Installation of the New Roller Assembly

Figure 5 (Sheet 1 of 3)

ba7499a01.cgm, sc/kp, February 17, 2014

A

NOTE

1. Left side shown.

Right side opposite.

LEGEND

1. Drill jig

670BA32040K90--101 (LH)

670BA32040K90--102 (RH).

2. Drill bushing

670BA32040K90--112.

3. Reamer bushing

670BA32040K90--113.

AFT MEMBER

ASSEMBLY

(REF)

B

C

1

2

OR

3

DOWEL

PIN

(REF)

POINT WHERE THE DOWEL

PIN TOUCH THE AFT

MEMBER ASSEMBLY

C

SURFACE OF THE TOOL

THAT TOUCH THE AFT

MEMBER ASSEMBLY

(REF)

POINT WHERE THE DOWEL

PIN TOUCH THE AFT

MEMBER ASSEMBLY

C -- C

2

OR

3

B

VIEW LOOKING FORWARD

A
SERVICE BULLETIN 670BA---32---040

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Page 149 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Installation of the New Roller Assembly

Figure 5 (Sheet 2 of 3)

ba7499a02.cgm, mgr, 5 sept 2012

D

A

D

2

4

OUTBOARD

LUG (REF)

INBOARD

LUG (REF) 7

3

OUTBOARD

LUG (REF)

INBOARD

LUG (REF)

D

0.3147 TO 0.3157 in.

(7.99 TO 8.02 mm) 0.3141 TO 0.3159 in.

(7.98 TO 8.02 mm)

LEGEND

7. Flanged bushing

CC670--39165--1.

0.15 in. (3.8 mm)

MINIMUM TYP.

NOTES

1. Left side shown.

Right side opposite.

Liquid nitrogen or solid,

technical, carbon dioxide (dry ice).

Sealant.

Filet of sealant all around.

5. Conversion coating.

2

4

3
SERVICE BULLETIN 670BA---32---040

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Page 150 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Installation of the New Roller Assembly

Figure 5 (Sheet 3 of 3)

ba7499a03.cgm, mg, 1 Aug. 2012

7

1. Left side shown.

Right side opposite.

Greese aeroshell.

Mastinox.

6

7

5. Roller

CC670--10926--1.

6. Bushing

NAS75C3A030.

7. Flanged bushing

CC670--39165--1.

8. Self locking nut

B0203010--3.

9. Washer

MS21299C3K.

10. Cotter pin

MS24665--86.

11. Bolt

NAS6303--20D.

12. Washer

NAS1149E0363P.

E

F

G

G -- G

0.030 in.

(0.76 mm)

6

G

5

9

7

8

12

10

6

11

AFT MEMBER

(REF)

F

E

INBOARD

MLG DOOR

(REF)

OUTBOARD

MLG DOOR

(REF)

NOTES

LEGEND
SERVICE BULLETIN 670BA---32---040

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Page 151 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Aft Stop-Fitting --- Removal

Figure 6 (Sheet 1 of 2)

ba7478a01.cgm, mg, 1 Aug. 2012

A 1

A

1. Bolt.

2. Washer.

3. Nut.

4. Seal aft fairing.

5. Aft retainer seal.

6. Bolt NAS8603--6.

7. Stop pad.

8. Laminated shim.

9. Shim.

10. Washer NAS1149E0363P.

11. Nut MS21043--3.

12. Bolt.

13. Nut.

14. Aft stop--fitting.

17. Solid rivet.

D

D

2

3

4

5

6

7

9 8

11 10

14

12

13

B

MLG FAIRING

(REF)

14

SEALING

MEMBER

MLG (REF)

C

B

2

1. Left side shown.

Right side opposite.

2 Sealant to be removed.

17

C

NOTES

LEGEND

PRE--MOD

PRE--MOD
SERVICE BULLETIN 670BA---32---040

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Page 152 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Aft Stop-Fitting --- Removal

Figure 6 (Sheet 2 of 2)

ba7478a02.cgm, sc, 28 jan 2013

A

MLG FAIRING

(REF)

0.250 in.

(6.35 mm)

RADIUS

14

E

0.190 TO 0.194 in

(4.83 TO 4.93 mm).

DRILL CODE

E POST--MOD

BREAK

SHARP

EDGE

14

6

10

11

15

3

16

NOTES

1. Left side shown.

Right side opposite.

Part to trim.

Material to be removed. 3

LEGEND

6. Bolt

NAS8603--6.

10. Washer

NAS1149EO363P.

11. Nut

MS21043--3.

14. Aft stop--fitting

KBA670--10500--39 (LH)

KBA670--10500--40 (RH).

15. Shim fairing

CC670--39161--1.

16. Laminated shim CC670--39160--1
SERVICE BULLETIN 670BA---32---040

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Page 153 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Removal of Material and Installation of the Aft Stop-Fitting

Figure 7 (Sheet 1 of 2)

ba7513a05.cgm, cr, aug--2012

A

MLG FAIRING

(REF)

D

MLG FAIRING

(REF)

0.53 TO 0.61 in.

(13.4 TO 15.5 mm)

VIEW LOOKING INBOARD

D
SERVICE BULLETIN 670BA---32---040

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Page 154 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Removal of Material and Installation of the Aft Stop-Fitting

Figure 7 (Sheet 2 of 2)

ba7512a01.cgm, sc/cr, 5 sept 2012

A

GAP

SEAL

(REF)

1

C

VIEW LOOKING AFT

A

B

MLG FAIRING

(REF)

1

2

3

B POST--MOD

C

SEALING

MEMBER

(REF).

6 7

8

9

10

11

7. Stop pad

CC670--39159--1 (LH),

CC670--39159--2 (RH).

8. Laminated shim

CC670--39160--1 (LH),

CC670--39160--2 (RH).

9. Shim CC670--39161--1.

10. Washer NAS1149E0363P.

11. Nut MS21043--3.

LEGEND

1. Aft stop-fitting

CC670--39076--1 (Pre--Mod LH),

CC670--39076--2 (Pre--Mod RH),

KBA670--10500--39 (Post--Mod LH),

KBA670--10500--40 (Post--Mod RH).

2. Bolt B0206004AG6--5.

3. Nut B0203014--3.

4. Rivet MS20470AD4--7A.

5. Rivet MS20470AD5--7A.

6. Bolt NAS8703--6.

2

NOTE

1. Left side shown.

Right side opposite.

Rivet heads installed

near side.

2

ITEM NAME PART NUMBER FASTENER

CODE

MS20470AD4--7A

MS20470AD5--7A

Rivet

Rivet

4

5
SERVICE BULLETIN 670BA---32---040

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Page 155 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Rod End --- Removal/Installation

Figure 8 (Sheet 1 of 1)

ba7469a02.cgm,cr,05--july--2012

A

LEGEND

7. Cotter pin.

8. Nut.

9. Washer.

10. Washer.

11. Pin.

12. Bushing.

13. Rod end.

A

B

13

10

12

9

8

7

11

B
SERVICE BULLETIN 670BA---32---040

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Page 156 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Aft Seal MLG Door Removal

Figure 9 (Sheet 1 of 3)

C

ba7513a01.cgm, sc, 03--Aug 2012

MLG INBOARD

DOOR

(REF)

A

A

B

C PRE--MOD

B PRE--MOD

AFT SEAL

MLG DOOR

(REF)

AFT SEAL

MLG DOOR

(REF)

1

2

1

1

2

LEGEND

1.Rivet.

2.Washer.
SERVICE BULLETIN 670BA---32---040

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Page 157 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Table for Aft Seal MLG Door Installation

Figure 9 (Sheet 2 of 3)

ba8187a02.cgm, sc/kp/cr, 24--mar--2014

LEGEND

3. Aft seal

CC670--10893--3 (LH),

CC670--10893--4 (RH).

NOTES

Fastener head far side.

Washer installed between

seal and expanded end of

the fastener.

No washer is necessary.

2

3

4

5 The gap must be between

the door and the seal.

F POST--MOD

3

E POST--MOD

3

F

4

AERODYNAMIC

SEALANT

(REF)

A

D

2

MLG INBOARD

DOOR

(REF)

3

4

6 or 7

5

E

0.110 in. (2.79 mm)

CONSTANT GAP 5

D

3
SERVICE BULLETIN 670BA---32---040

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Revision E, 13 Nov/2014

Aft Seal MLG Door Installation

Figure 9 (Sheet 3 of 3)

ba8187a03.cgm, kp, 24--mar--2014

NAS1149DN832K

NAS9302E--5--03

Washer

Blind Rivet

ITEM NAME PART NUMBER

4

5

SYMBOL HOLE DIAMETER

0.160 TO 0.164 in. (4.06 TO 4.17 mm)

NAS1149D0332K

NAS9305E--5--03

Washer

Blind Rivet

6

5

N/A

NAS1149D0332K

NAS9303E--6--03

Washer

Blind Rivet

6

5

NAS1149D0832K

NAS9305E--6--03

Washer

Blind Rivet

6

5

NAS1149D0432K

CR3224--8--03

Washer

Blind Rivet

7

5

N/A

N/A

OR

OR

OR

OR

FASTENER SYMBOL CHART

0.176 TO 0.180 in. (4.47 TO 4.57 mm)

0.192 TO 0.196 in. (4.88 TO 4.98 mm)

0.214 TO 0.218 in. (5.44 TO 5.54 mm)

0.214 TO 0.218 in. (5.44 TO 5.54 mm)

0.205 TO 0.209 in. (5.21 TO 5.31 mm)

0.256 TO 0.261 in. (6.50 TO 6.63 mm)

NOTES

1. It is permitted to install oversize or next size fasterners in lieu of NAS9302E--5--03.

6 Open washer ID to specified hole diameter.

6

6
SERVICE BULLETIN 670BA---32---040

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Page 159 of 189

Oct 12/2012

Revision E, 13 Nov/2014

MLG Inboard and Outboard Doors Attachments

Figure 10 (Sheet 1 of 1)

C

1

4

7

8

5

6

B

B

0.030 TO 0.060 in.

(0.76 TO 1.52 mm)

0.000

1

4

7

8

9

5

3 2

6

B -- B

ASSEMBLED

9

A

C

A

NOTES

1. MLG not shown for clarity.

2. Left side shown. Right side opposite.

ba7469a01.cgm, sd/cr-- 24--aug--2012

10

10

11 12

LEGEND

1. Bolt.

2. Bushing.

3. Bushing.

4. Sleeve bushing.

5. Washer

NAS1149E0663P.

6. Nut

B0203010L6.

7. Washer

NAS1149C0832R.

8. Washer

NAS1149C0863R.

9. Cotter pin

MS24665--300.

10. Washer.

11. Bushing.

12. Bushing.
SERVICE BULLETIN 670BA---32---040

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Revision E, 13 Nov/2014

Removal and Installation of Fasteners

Figure 11 (Sheet 1 of 3)

ba7513a01.cgm, sc/kp,February 17, 2014

B0205017AD5--5S

NAME PART NUMBER

Rivet

ITEM

7

FASTENER

CODE

NOTES

1. Countersink to be done on

nearside of the forward

member.

Fastener to be removed.

B POST--MOD

FORWARD MEMBER

MLG DOOR

(REF)

B PRE--MOD

B

A

MLG INBOARD

DOOR

(REF)

A
SERVICE BULLETIN 670BA---32---040

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Revision E, 13 Nov/2014

Removal and Installation of Fasteners

Figure 11 (Sheet 2 of 3)

ba7513a02.cgm, cr/kp, February 17, 2014

A

MLG INBOARD

DOOR

(REF)

C PRE--MOD C POST--MOD

NOTES

1. Countersink to be done on

nearside of the forward

member.

Fastener to be removed.

B0205017AD5--5S

NAME PART NUMBER

Rivet

ITEM

7

FASTENER

CODE

C

INBOARD

INNER SKIN

(REF)

INBOARD

INNER SKIN

(REF)
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 162 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Removal and Installation of Fasteners

Figure 11 (Sheet 3 of 3)

ba7513a03.cgm, sc/kp, February 18, 2014

A

MLG INBOARD

DOOR

(REF)

E

E

D

FORWARD MEMBER

MLG DOOR

(REF)

AERODYNAMIC

SEALING AREA

(REF)

END OF

STIFFENER

(REF)

D POST--MOD

2.61 in.

(66.3 mm)

0.48 in.

(12.2 mm)

0.94 in.

(23.9 mm) 0.04 in.

(1.0 mm)

0.12 in.

(3.1 mm)

RADIUS

2.00 in.

(50.8 mm)

RADIUS 0.25 in.

(6.3 mm)

RADIUS

OUTER SKIN

INBOARD

(REF)

FORWARD

MEMBER

(REF)

INNER SKIN

INBOARD

(REF)

POINT A

(REF)

POINT B

(REF)

POINT C

(REF)

WEB (REF)

2

E -- E POST--MOD

NOTE

2 Material to be removed.
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 163 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Clearance And Mismatch Between MLG Fairing and MLG Doors

Figure 12 (Sheet 1 of 2)

ba7515a01.cgm,FP, Oct 21. 2013

DOOR BRUSH

(REF)

B

PT 9

PT 10

0.50 in.

(12.7 mm)

2.50 in.

(63.5 mm)

PT 11

PT 12

0.50 in.

(12.7 mm)

0.50 in. PT 13

(12.7 mm)

PT 2

PT 3

0.50 in.

(12.7 mm)

0.50 in.

(12.7 mm)

PT 5

PT 4

PT 6

2

3

2

2

2

A

VIEW LOOKING DOWN

B

NOTES

Aligned with door stiffener.

From angle edge.

Left side shown,

right side opposite.

2

5.

3

3

A
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 164 of 189

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Revision E, 13 Nov/2014

Clearance And Mismatch Between MLG Fairing and MLG Doors

Figure 12 (Sheet 2 of 2)

0.50 in.

(12.7 mm)

PT 19

0.50 in.

(12.7 mm)

PT 20

PT 25 (REF)

PT 24 (REF)

PT 16

PT 17

PT 15

PT 18

PT 23

PT 22

PT 21

1

1

1

1

1

1

1

1

1

DOOR BRUSH (REF)

PT 14

1.50 in.

(38.1 mm)

PT 1

VIEW LOOKING UP

C

VIEW LOOKING INBOARD

E

D

D

C

E

ba7515a02.cgm,FP, Oct 21. 2013

NOTES

Aligned with screw.

From angle edge.

From end of seal.

Left side shown,

right side opposite.

1

3

5.

4

4

1

3

3
SERVICE BULLETIN 670BA---32---040

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Page 165 of 189

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Revision E, 13 Nov/2014

Seal and Seal Retainer --- Removal

Figure 13 (Sheet 1 of 1)

ba7514a01.cgm, sc, 28 jan 2013

A

B

A

MLG FAIRING

(REF)

B

PRE MOD

NOTES

4

OR

11

5

1

2

3

6

2

3

8

1

2

9 7 3

10

Left side shown,

right side opposite.

LEGEND

1. Bolt NAS7502U4.

2. Nut MS21043--08.

3. Washer NAS1149EN832P.

4. Seal.

5. Seal retainer

CC670--39245--1 (LH),

CC670--39245--2 (RH).

6. Bolt NAS7502U3.

7. Seal retainer.

8. Seal.

9. Seal retainer.

10. Seal.

11. Fairing, forward seal

CC670--38244--5SB (LH),

CC670--38244--6SB (RH).

12. Bolt NAS7502U5.

12
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 166 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Removal of Material on MLG Fairing and MLG Door

Figure 14 (Sheet 1 of 2)

ba7514a01.cgm,cr/kp, February 18, 2014

MLG FAIRING

(REF)

C

0.10 in. (2.5 mm)

(MAXIMUM)

PT A

0.23 in. (5.8 mm)

(MAXIMUM)

EDGE to TRIM

PT A to PT B

PT B

ENSURE MINIMUM ED OF

0.42 in. (10.7 mm)

(12 PLACES)

PT C

PT D

PT F

PT B

PT C

0.10 in. (2.5 mm)

(MAXIMUM)

0.10 in. (2.5 mm)

(MAXIMUM)

0.23 in. (5.8 mm)

(MAXIMUM)

0.16 in. (4.1 mm)

(MAXIMUM)

A

C

B

A

B

NOTES

1. Left side shown, right side opposite.

2. Minimum of edge distance of 0.42 in.

(10.7 mm) PT A to PT B, PT D to PT E.

3. Minimum of edge distance of 0.57 in.

(14.5 mm) PT B to PT C and PT E to PT F.

PT E
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 167 of 189

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Revision E, 13 Nov/2014

Removal of Material on MLG Fairing and MLG Door

Figure 14 (Sheet 2 of 2)

ba7514a03.cgm, sc/kp, 24--mar--2014

PT B

(ALIGNED WITH

SCREW)

PT C

(ALIGNED WITH

SCREW)

H

0.08 in. (2.0 mm)

(MAXIMUM)

0.13 in. (3.3 mm)

(MAXIMUM)

J

PT C

0.08 in. (2.0 mm)

(MAXIMUM)

PT D

0.25 0.010 in.

(6.3 2.5 mm)

RADIUS

PT A

J

G

F

PT B

EDGE TO TRIM

PT A TO PT D

PT C

H

NOTES

1. Left side shown,

right side opposite.

4. Minimum edge distance

between PT A to PT D

is 0.23 in. (6.0 mm).

D

INBOARD MLG

DOOR (REF)

E

F

ANGLE

CC670--10521 (REF)

D

PT A

0.25 in.

(6.3 mm)

0.13 in. (3.3 mm)

(MAXIMUM)

0.25 0.010 in.

(6.3 2.5 mm)

RADIUS

G

E
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 168 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Seal and Seal Retainer --- Installation

Figure 15 (Sheet 1 of 2)

ba7514a04.cgm, sc, 28 jan 2013

DRILL CODE

0.165 to 0.169 in.

(4.19 to 4.29 mm).

11

13

12

14 1

2

3

C

C

A

B

MLG FAIRING

(REF)

VIEW LOOKING OUTBD

POST MOD

B

VIEW LOOKING OUTBD

PRE MOD

B

LEGEND

1. Bolt

NAS7502U4.

2. Nut

MS21043--08.

3. Washer

NAS1149EN832P.

5. Seal retainer

CC670--39245--1 (LH),

CC670--39245--2 (RH).

11. Fairing Forward seal

CC670--39244--5SB (LH),

CC670--39244--6SB (RH).

12. Fairing Safety--guide

CC670--39158--1SB (LH),

CC670--39158--2SB (RH).

13. Upper Seal retainer

KBA670--10500--41 (LH),

KBA670--10500--42 (RH).

14. Lower seal retainer

KBA670--10500--43 (LH),

KBA670--10500--44 (RH).

C -- C

9

8

7

12

11

0.030 in.

(0.76 mm)

0.340 in.

(8.64mm)

MINIMUM

9

8

7

6

NOTES

1. Left side shown, right side opposite.

5. Radius 0.25 in. (6.3 mm) clearance

0.10 in. (2.5 mm).

Countersink far side.

Rebate of the MLG fairing.

The distance between the fastener

hole and the rebate of the MLG fairing.

Minimum clearance between the fairing

safety--guide and the MLG fairing.

12

5

0.25 in.

(6.3 mm)

RADIUS

(2 PLACES)

0.07 TO 0.13 in.

(1.8 TO 2.5 mm)

6

0.07 TO 0.13 in.

(1.8 TO 2.5 mm)

15. Bolt

NAS7502U5.

15
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 169 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Seal and Seal Retainer --- Installation

Figure 15 (Sheet 2 of 2)

ba7514a05.cgm, sc, 28 jan 2013

A

D

MLG FAIRING

(REF)

6

2

3

8

1

2

9 7 3

10

D

VIEW LOOKING OUTBD

POST--MOD

LEGEND

1. Bolt NAS7502U4.

2. Nut MS21043--08.

3. Washer NAS1149EN832P.

6. Bolt NAS7502U3.

7. Seal retainer

CC670--39070--1 (LH),

CC670--39070--2 (RH).

8. Seal

CC670--39067--1 (LH),

CC670--39067--2 (RH).

9. Seal retainer

CC670--39248--1 (LH),

CC670--39248--2 (RH).

10. Aft fairing seal

CC670--39163--1SB (LH),

CC670--39163--2SB (RH).

NOTES

1. Left side shown,

right side opposite.

2. Fastener head far side.
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 170 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Nameplate --- Removal/Installation

Figure 16 (Sheet 1 of 1)

ba2982a01_01.cgm, gb, 5 sept 2012

B

FORWARD

MEMBER

(REF)

AFT

MEMBER

(REF)

B

INBOARD

INNER SKIN

(REF)

7.0 in. (178 mm)

APPROXIMATELY

A

2.0 in. (51 mm)

APPROXIMATELY

1. Identification plate S6472--4.

LEGEND A

1

Bombardier Inc.

Montreal, Canada

DWG.NO.:

MODEL:

DATE:

MODS:

CAGE CODE

88308

QC:

SERIAL:

ISSUE:

88308/S6472--4
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 171 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Aft Stop-Fitting and the Forward Fairing Seal Overlap

Figure 17 (Sheet 1 of 1)

ba7614a01.cgm, sc, 23 jan 2013

ASSY FAIRING MLG

VIEW LOOKING INBOARD

C

INBD MLG DOOR ASSY

SEAL

OVERLAP

DOOR STOP FITTING

(REF)

B

D

A

C C

D

C

B

A

VIEW LOOKING DOWN ON LHS

D D

VIEW LOOKING UP ON LHS

1

2 0.600 in.

(15.24. mm)

MINIMUM.

LEGEND

1. Aft stop--fitting

KBA670--10500--39 (LH)

KBA670--10500--40 (RH).

2. Fairing, forward seal

CC670--38244--5SB (LH),

CC670--38244--6SB (RH).
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 172 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Removal of the Inboard MLG Door

Figure 18 (Sheet 1 of 2)

ba8186a01.cgm, kp/kl, July 23, 2014

B

A

A

B

1

PRE--MOD

NOTE

1. Left side shown,

right side opposite.

LEGEND

1. Inboard MLG door
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 173 of 189

Oct 12/2012

Revision E, 13 Nov/2014

Installation of the Inboard MLG Door

Figure 18 (Sheet 2 of 2)

ba8158a02.cgm, kp, January 30, 2014

B

A

B

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

2

LEGEND

2. Inboard MLG door

CC670--10520--15 (LH)

CC670--10520--16 (RH)

POST--MOD
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 174 of 189

Oct 12/2012

Revision E, 13 Nov/2014

3. MATERIAL INFORMATION

A. Kit Information

Kit Contents:

KIT 670BA32040K1A

PART NUMBER QTY NAME ALTERNATE

PARTS NOTES

600-10213-41 1 Laminated Shim

CC670-10893-3 1 Seal MLG Door L/H

CC670-10926-1 1 Roller MLG Door L/H

and R/H

CC670-39158-1SB 1 Safety Guide MLG

Door L/H

CC670-39158-1-01

CC670-39159-1 1 Stop Pad MLG Door

L/H

CC670-39160-1 1 Laminated Shim MLG

Door

CC670-39161-1SB 1 Shim MLG CC670-39161-1-01

CC670-39163-1SB 1 Seal AFT MLG Fairing

L/H

CC670-39161-1-01

CC670-39165-1 1 Bushing MLG Door
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 175 of 189

Oct 12/2012

Revision E, 13 Nov/2014

KIT 670BA32040K2A

PART NUMBER QTY NAME ALTERNATE

PARTS NOTES

600-10213-41 1 Laminated Shim

CC670-10893-4 1 Seal MLG Door R/H

CC670-10926-1 1 Roller MLG Door L/H

& R/H

CC670-39158-2SB 1 Safety Guide MLG

Door R/H

CC670-39158-2-01

CC670-39159-2 1 Stop Pad MLG Door

R/H

CC670-39160-1 1 Laminated Shim MLG

Door

CC670-39161-1SB 1 Shim MLG CC670-39161-1-01

CC670-39163-2SB 1 Seal AFT MLG Fairing

R/H

CC670-39161-1-01

CC670-39165-1 1 Bushing MLG Door

KIT 670BA32040K3A ¡

PART NUMBER QTY NAME ALTERNATE

PARTS NOTES

B0203010-3 2 Nut, Self-Locking

B0203010L6 2 Nut

B0203014-3 3 Nut Self-Locking

B0205017AD5-5S 13 Solid Rivet

B0206004AG6-5 3 Bolt

MS20470AD4-7A 2 Solid Rivet

MS20470AD5-7A 3 Solid Rivet

MS21043-08 32 Nut

MS21043-3 2 Nut
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 176 of 189

Oct 12/2012

Revision E, 13 Nov/2014

PART NUMBER NOTES ALTERNATE

PARTS QTY NAME

MS21299C3K 1 Washer

MS24665-300 2 Cotter Pin

MS24665-86 2 Cotter Pin

NAS1149CO832R 1 Washer

NAS1149CO863R 1 Washer

NAS1149DN832K 6 Washer

NAS1149EN832P 2 Washer

NAS1149EO363P 1 Washer

NAS6303-20D 1 Bolt

NAS7502U4 2 Bolt

NAS75C3A030 1 Bushing

NAS8703-6 2 Bolt

NAS9302E-5-03 6 Blind Rivet

NAS9305E-5-03 6 Blind Rivet 1st oversize

S6472-4 1 NamePlate

¡ The kit can contain more hardware and/or material than necessary.

KIT 670BA32040K4A ¡

PART NUMBER QTY NAME ALTERNATE

PARTS NOTES

B0203010-3 2 Nut, Self-Locking

B0203010L6 2 Nut

B0203014-3 3 Nut, Self-Locking

B0205017AD5-5S 13 Solid Rivet

B0206004AG6-5 3 Bolt

MS20470AD4-7A 2 Solid Rivet
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 177 of 189

Oct 12/2012

Revision E, 13 Nov/2014

PART NUMBER NOTES ALTERNATE

PARTS QTY NAME

MS20470AD5-7A 2 Solid Rivet

MS21043-08 32 Nut

MS21043-3 2 Nut

MS21299C3K 1 Washer

MS24665-300 2 Cotter Pin

MS24665-86 2 Cotter Pin

NAS1149CO832R 1 Washer

NAS1149CO863R 1 Washer

NAS1149DN832K 6 Washer

NAS1149EN832P 2 Washer

NAS1149EO363P 1 Washer

NAS6303-20D 1 Bolt

NAS7502U4 2 Bolt

NAS75C3A030 1 Bushing

NAS8703-6 2 Bolt

NAS9302E-5-03 6 Blind Rivet

NAS9305E-5-03 6 Blind Rivet 1st oversize

S6472-4 1 NamePlate

¡ The kit can contain more hardware and/or material than necessary.

KIT 670BA32040K5

PART NUMBER QTY NAME ALTERNATE

PARTS NOTES

CC670-39244-5SB 1 Seal MLG Door L/H CC670-39244-5-01
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 178 of 189

Oct 12/2012

Revision E, 13 Nov/2014

KIT 670BA32040K6

PART NUMBER QTY NAME ALTERNATE

PARTS NOTES

CC670-39244-6SB 1 Seal MLG Door R/H CC670-39244-6-01

KIT 670BA32040K7

PART NUMBER QTY NAME ALTERNATE

PARTS NOTES

600-10213-41 1 Laminated Shim

B0203010L6 2 Nut

B0203014-3 3 Nut Self---Locking

B0206004AG6---5 3 Bolt

CC670-39158-1SB 1 Safety Guide MLG

Door L/H

CC670-39158-1-01

CC670-39159-1 1 Stop Pad MLG Door

L/H

CC670-39160-1 1 Laminated Shim MLG

Door

CC670-39161-1SB 1 Shim MLG CC670-39161-1-01

CC670-39163-1SB 1 Seal AFT MLG Fairing

L/H

CC670-39161-1-01

MS20470AD4-7A 2 Solid Rivet

MS20470AD5-7A 3 Solid Rivet

MS21043-08 32 Nut

MS21043-3 2 Nut

MS24665-300 2 Cotter Pin

NAS1149CO832R 1 Washer

NAS1149CO863R 1 Washer

NAS1149EN832P 2 Washer
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 179 of 189

Oct 12/2012

Revision E, 13 Nov/2014

PART NUMBER NOTES ALTERNATE

PARTS QTY NAME

NAS7502U4 2 Bolt

NAS8703-6 2 Bolt

KIT 670BA32040K8

PART NUMBER QTY NAME ALTERNATE

PARTS NOTES

600-10213-41 1 Laminated Shim

B0203010L6 2 Nut

B0203014-3 3 Nut Self---Locking

B0206004AG6-5 3 Bolt

CC670-39158-2SB 1 Safety Guide MLG

Door L/H

CC670-39158-1-01

CC670-39159-2 1 Stop Pad MLG Door

L/H

CC670-39160-1 1 Laminated Shim MLG

Door

CC670-39161-1SB 1 Shim MLG CC670-39161-1-01

CC670-39163-2SB 1 Seal AFT MLG Fairing

L/H

CC670-39161-2-01

MS20470AD4-7A 2 Solid Rivet

MS20470AD5-7A 3 Solid Rivet

MS21043-08 32 Nut

MS21043-3 2 Nut

MS24665-300 2 Cotter Pin

NAS1149CO832R 1 Washer

NAS1149CO863R 1 Washer

NAS1149EN832P 2 Washer
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 180 of 189

Oct 12/2012

Revision E, 13 Nov/2014

PART NUMBER NOTES ALTERNATE

PARTS QTY NAME

NAS7502U4 2 Bolt

NAS8703-6 2 Bolt

KIT 670BA32040K9

PART NUMBER QTY NAME ALTERNATE

PARTS NOTES

CR3224-8-03 12 Rivet, Blind

NAS9303E-6-03 12 Rivet, Blind

NAS9305E-6-03 12 Rivet, Blind

NAS1149D0332K 12 Washer

NAS1149D0432K 12 Washer

KIT 670BA32-040K90 ¡

PART NUMBER QTY NAME ALTERNATE

PARTS NOTES

670BA32040K90-1 1 Drill Jig MLG Door

Roller

¡ Refer to paragraph 1.H. for special terms and conditions.

NOTE: For permitted superseded parts, refer to the Parts Supersession Cross

References Lists at www.iflybombardier.com under Resources ---

Engineering Documents.

NOTE: Some parts listed in the kit content of this service bulletin are supplied in

a temporary condition of supply configuration. These parts are identified

with a ---SB, /SB, SB or other suffix after the Bombardier engineering part

number. When the parts are installed, with the instructions given in the

Accomplishment Instructions of this service bulletin, the parts agree with

the requirements of the engineering configuration. Refer to the SB

Introduction document for more explanation.
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 181 of 189

Oct 12/2012

Revision E, 13 Nov/2014

B. Consumable Information

The materials that follow are necessary to do this service bulletin. You can order

them from Bombardier or purchase them directly from industry sources. If the

material is ordered from Bombardier, there can be some lead time because of the

shelf life of the material.

CONSUMABLES

SPECIFICATION QUANTITY NAME REFERENCE

MIL-PRF-23827 As

necessary

Grease, Aeroshell #33 04-004 [1]

Not Specified As

necessary

Liquid nitrogen 05-351 [1]

MIL-PRF-81733

Type IV

As

necessary

Compound, sealing and

coating, corrosion inhibitive

faying surface sealing

09-020 [2]

BAMS 565-001

(CMS 565-01)

As

necessary

Fluid resistant Epoxy Primer 13-006 [2]

BAMS 565-002

As

necessary

Fluid resistant enamel for

aircraft interior Color clear

gloss

07-019 [2]

BAMS 565-002

As

necessary

Fluid resistant enamel for

aircraft interior Color grey

No.16473 per FED-STD-595

07-019 [2]

BAMS 565-002

As

necessary

Fluid resistant enamel for

aircraft interior (Refer to

aircraft paint scheme for

color)

07-019 [2]

NASM20995C As

necessary

Lockwire,corrosion-resistant

steel MS20995C32

05-004 [1]

AMS 2644 As

necessary

Developer, Form A - dry

powder

05-051 [1]

[1] Refer to AMM 51-31-00-992-801

[2] Refer to SRM 51-31-00-001-001.

NOTE: To complete this list of consumables, refer to the different tasks given as

references in this service bulletin
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 182 of 189

Oct 12/2012

Revision E, 13 Nov/2014

C. Special Tools and Equipment

SPECIAL TOOLS AND EQUIPMENT

PART NUMBER QUANTITY NAME ALTERNATE PARTS

34 gpm and

3000 PSI

1 Hydraulic Power

Unit

¡ Refer to the Illustrated Tool and Equipment Manual

NOTE: To complete this list of special tools and equipment, refer to the different

tasks, the service bulletin and the Appendix that are given as references

in this service bulletin.

D. Disposition of Parts

The table that follows shows the disposition of parts on the aircraft (or spares), and

the relationship between these parts to the new parts to be installed through the

incorporation of this service bulletin.

PRE-SB PART NUMBER NAME QTY DC POST-SB PART

NUMBER

CC670-10520-967

Inboard MLG

Door Assembly,

L/H

1 RWK KBA670-10500-23

CC670-10520-968

Inboard MLG

Door Assembly,

R/H

1 RWK KBA670-10500-24

CC670-10520-967

CC670-10520-2011

CC670-10520-2013

CC670-10520-2015

CC670-10520-13

KCC670-10900-1

KCC670-10900-3

KCC670-10900-5

KCC670-10901-1

KCC670-10901-3

Inboard MLG

Door Assembly,

L/H

1

SAL

[3] CC670-10520-15 [1]
SERVICE BULLETIN 670BA---32---040

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Page 183 of 189

Oct 12/2012

Revision E, 13 Nov/2014

PRE-SB PART NUMBER POST-SB PART

NUMBER

NAME QTY DC

CC670-10520-968

CC670-10520-2012

CC670-10520-2014

CC670-10520-2016

CC670-10520-14

KCC670-10900-2

KCC670-10900-4

KCC670-10900-6

KCC670-10901-2

KCC670-10901-4

Inboard MLG

Door Assembly,

R/H

1

SAL

[4] CC670-10520-16 [2]

CC670-10520-2011

Inboard MLG

Door Assembly,

L/H

1 RWK KBA670-10500-25

CC670-10520-2012

Inboard MLG

Door Assembly,

R/H

1 RWK KBA670-10500-26

CC670-10520-2013

Inboard MLG

Door Assembly,

L/H

1 RWK KBA670-10500-27

CC670-10520-2014

Inboard MLG

Door Assembly,

R/H

1 RWK KBA670-10500-28

CC670-10520-2015

Inboard MLG

Door Assembly,

L/H

1 RWK KBA670-10500-29

CC670-10520-2016

Inboard MLG

Door Assembly,

R/H

1 RWK KBA670-10500-30

CC670-10520-13

Inboard MLG

Door Assembly,

L/H

1 RWK KBA670-10500-31

CC670-10520-14

Inboard MLG

Door Assembly,

R/H

1 RWK KBA670-10500-32
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 184 of 189

Oct 12/2012

Revision E, 13 Nov/2014

PRE-SB PART NUMBER POST-SB PART

NUMBER

NAME QTY DC

KCC670-10900-1

Inboard MLG

Door Assembly,

L/H

1 RWK KBA670-10500-33

KCC670-10900-2

Inboard MLG

Door Assembly,

R/H

1 RWK KBA670-10500-34

KCC670-10900-3

Inboard MLG

Door Assembly,

L/H

1 RWK KBA670-10500-35

KCC670-10900-4

Inboard MLG

Door Assembly,

R/H

1 RWK KBA670-10500-36

KCC670-10900-5

Inboard MLG

Door Assembly,

L/H

1 RWK KBA670-10500-37

KCC670-10900-6

Inboard MLG

Door Assembly,

R/H

1 RWK KBA670-10500-38

KCC670-10901-1

Inboard MLG

Door Assembly,

L/H

1 RWK KBA670-10500-51

KCC670-10901-2

Inboard MLG

Door Assembly,

R/H

1 RWK KBA670-10500-52

KCC670-10901-3

Inboard MLG

Door Assembly,

L/H

1 RWK KBA670-10500-53

KCC670-10901-4

Inboard MLG

Door Assembly,

R/H

1 RWK KBA670-10500-54

CC670-10571-13 aft Member L/H 1 RWK KBA670-10500-45

CC670-10571-14 aft Member R/H 1 RWK KBA670-10500-46

CC670-10570-1 Forward Member

L/H 1 RWK KBA670-10500-47
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 185 of 189

Oct 12/2012

Revision E, 13 Nov/2014

PRE-SB PART NUMBER POST-SB PART

NUMBER

NAME QTY DC

CC670-10570-2 Forward Member

R/H 1 RWK KBA670-10500-48

CC670-10570-5 Forward Member

L/H 1 RWK KBA670-10500-49

CC670-10570-6 Forward Member

R/H 1 RWK KBA670-10500-50

BA670-00001-2085 MLG Fairing

Assembly L/H 1 RWK KBA670-10500-300

BA670-00001-2085 MLG Fairing

Assembly R/H 1 RWK KBA670-10500-350

BA670-00001-2085

MLG Fairing

Assembly L/H and

R/H

1 RWK KBA670-10500-3

CC670-39005-951 MLG Fairing

Assembly L/H 1 RWK KBA670-10500-500

CC670-39005-951 MLG Fairing

Assembly R/H 1 RWK KBA670-10500-550

CC670-39005-951

MLG Fairing

Assembly L/H and

R/H

1 RWK KBA670-10500-5

CC670-39005-3 MLG Fairing

Assembly L/H 1 RWK KBA670-10500-700

CC670-39005-3 MLG Fairing

Assembly R/H 1 RWK KBA670-10500-750

CC670-39005-3

MLG Fairing

Assembly L/H and

R/H

1 RWK KBA670-10500-7

CC670-39005-5 MLG Fairing

Assembly L/H 1 RWK KBA670-10500-130

CC670-39005-5 MLG Fairing

Assembly R/H 1 RWK KBA670-10500-135
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 186 of 189

Oct 12/2012

Revision E, 13 Nov/2014

PRE-SB PART NUMBER POST-SB PART

NUMBER

NAME QTY DC

CC670-39005-5

MLG Fairing

Assembly L/H and

R/H

1 RWK KBA670-10500-13

CC670-39019-49 MLG Fairing

Assembly L/H 1 RWK KBA670-10500-190

CC670-39019-49 MLG Fairing

Assembly R/H 1 RWK KBA670-10500-195

CC670-39019-49

MLG Fairing

Assembly L/H and

R/H

1 RWK KBA670-10500-19

CC670-39019-963 MLG Fairing

Assembly L/H 1 RWK KBA670-10500-150

CC670-39019-963 MLG Fairing

Assembly R/H 1 RWK KBA670-10500-155

CC670-39019-963

MLG Fairing

Assembly L/H and

R/H

1 RWK KBA670-10500-15

CC670-39019-965 MLG Fairing

Assembly L/H 1 RWK KBA670-10500-170

CC670-39019-965 MLG Fairing

Assembly R/H 1 RWK KBA670-10500-175

CC670-39019-965

MLG Fairing

Assembly L/H and

R/H

1 RWK KBA670-10500-17

CC670-39019-51 MLG Fairing

Assembly L/H 1 RWK KBA670-10500-210

CC670-39019-51 MLG Fairing

Assembly R/H 1 RWK KBA670-10500-215

CC670-39019-51

MLG Fairing

Assembly L/H and

R/H

1 RWK KBA670-10500-21

KBA670-39005-3 MLG Fairing

Assembly L/H 1 RWK KBA670-10500-610
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 187 of 189

Oct 12/2012

Revision E, 13 Nov/2014

PRE-SB PART NUMBER POST-SB PART

NUMBER

NAME QTY DC

KBA670-39005-3 MLG Fairing

Assembly R/H 1 RWK KBA670-10500-615

KBA670-39005-3

MLG Fairing

Assembly L/H and

R/H

1 RWK KBA670-10500-61

KBA670-39005-5 MLG Fairing

Assembly L/H 1 RWK KBA670-10500-630

KBA670-39005-5 MLG Fairing

Assembly R/H 1 RWK KBA670-10500-635

KBA670-39005-5

MLG Fairing

Assembly L/H and

R/H

1 RWK KBA670-10500-63

KBA670-39005-7 MLG Fairing

Assembly L/H 1 RWK KBA670-10500-650

KBA670-39005-7 MLG Fairing

Assembly R/H 1 RWK KBA670-10500-655

KBA670-39005-7

MLG Fairing

Assembly L/H and

R/H

1 RWK KBA670-10500-65

KBA670-39005-9 MLG Fairing

Assembly L/H 1 RWK KBA670-10500-670

KBA670-39005-9 MLG Fairing

Assembly R/H 1 RWK KBA670-10500-675

KBA670-39005-9

MLG Fairing

Assembly L/H and

R/H

1 RWK KBA670-10500-67

CC670-39076-1 aft Stop-Fitting

L/H 1 RWK KBA670-10500-39

CC670-39076-2 aft Stop-Fitting

R/H 1 RWK KBA670-10500-40
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 188 of 189

Oct 12/2012

Revision E, 13 Nov/2014

PRE-SB PART NUMBER POST-SB PART

NUMBER

NAME QTY DC

CC670-39245-1 Seal Retainer

Forward 1 RWK

Forward Upper

Retainer-Seal

KBA670-10500-41

And

Forward Lower

Retainer-Seal

KBA670-10500-43

CC670-39245-2 Seal Retainer

Forward 1 RWK

Forward Upper

Retainer-Seal

KBA670-10500-42

And

Forward Lower

Retainer-Seal

KBA670-10500-44

601R38119-19 Roller L/H and

R/H 2 DIS CC670-10926-1

CC670-10897-1 OR

CC670-10520-961

aft Seal MLG Door

L/H 1 DIS CC670-10893-3

CC670-10897-2 OR

CC670-10520-962

aft Seal MLG Door

R/H 1 DIS CC670-10893-4

CC670-39068-1 aft Seal Fairing

L/H 1 DIS

CC670-39068-2 aft Seal Fairing

R/H 1 DIS

CC670-39072-1 aft Seal

Retainer-Fairing

L/H

1 DIS

CC670-39072-2

aft Seal

Retainer-Fairing

R/H

1 DIS

CC670-39078-1 OR

CC670-39079-1 Shim L/H 1 DIS
SERVICE BULLETIN 670BA---32---040

SB 670BA---32---040

Page 189 of 189

Oct 12/2012

Revision E, 13 Nov/2014

PRE-SB PART NUMBER POST-SB PART

NUMBER

NAME QTY DC

CC670-39077-1 aft Stop Pad MLG

Fairing 2 DIS

CC670-39244-1 Seal Forward MLG

Fairing L/H 1 DIS CC670-39244-5

CC670-39244-2 Seal Forward MLG

Fairing R/H 1 DIS CC670-39244-6

CC670-39247-1 Seal AFT MLG

Fairing L/H 1 DIS CC670-39163-1

CC670-39247-2 Seal AFT MLG

Fairing R/H 1 DIS CC670-39163-2

[1] When PART C is done.

[2] When PART D is done.

[3] Door can be rework per PART A.

[4] Door can be rework per PART B.

Disposition code (DC):

DIS: Discard Part.

RWK: Rework part refer to this service bulletin.

SAL: Salvage.

1
Page A1 of A3

Oct 12/2012

1

App

A

670BA---32---040 APPENDIX A

Revision A, Jul 02/2014

DATA SHEET

The data sheets in this appendix are given as references in the

ACCOMPLISHMENT INSTRUCTIONS of Service Bulletin 670BA---32---040.
APPENDIX A

Page A2 of A3

Oct 12/2012

1

App

A

670BA---32---040 APPENDIX A

Revision A, Jul 02/2014

OPERATOR NAME: ___________________________________________________

AIRCRAFT SERIAL NUMBER: __________________________________________

DATE (OF INSPECTION): _____________________________________________

AIRCRAFT FLIGHT CYCLES: ___________________________________________

DETAILED VISUAL INSPECTION

INSPECTION AREA

LEFT SIDE RIGHT SIDE

MLG FAIRING:

Forward stop missing Yes____ No____ Yes____ No____

Aft stop missing Yes____ No____ Yes____ No____

Forward Stop Fasteners

Loose Or Missing

N/A______Yes____ No____ N/A_____Yes____ No____

Aft Stop Fasteners

Loose Or Missing

N/A______Yes____ No____ N/A_____Yes____ No____

Edge Of The Fairing

Adjacent The MLG Door

Damage

Yes____ No____

If Yes, Details:

_________________________

_________________________

_________________________

_________________________

_________________________

Yes____ No____

If Yes, Details:

_________________________

_________________________

_________________________

_________________________

_________________________
APPENDIX A

Page A3 of A3

Oct 12/2012

1

App

A

670BA---32---040 APPENDIX A

Revision A, Jul 02/2014

DETAILED VISUAL INSPECTION

INSPECTION AREA

LEFT SIDE RIGHT SIDE

MLG INBOARD DOOR:

Roller (2) broken or missing Broken____Missing____ Broken____Missing____

Stop (1) Missing Yes____ No____ Yes____ No____

Stop (1) Fasteners

Loose Or Missing

N/A____ Yes____ No____ N/A____ Yes____ No____

Stop (3) Damage Yes____ No____ Yes____ No____

Stop (4) Damage Yes____ No____ Yes____ No____

Stop (5) Damage Yes____ No____ Yes____ No____

Edge Of The MLG Door

Adjacent The Fairing

Damage

Yes____ No____

If Yes, Details:

_________________________

_________________________

_________________________

_________________________

_________________________

Yes____ No____

If Yes, Details:

_________________________

_________________________

_________________________

_________________________

_________________________

FORWARD AND AFT SPAR AREAS:

Stop (1) missing Yes____ No____ Yes____ No____

Stop (1) Fasteners

Loose Or Missing

N/A____ Yes____ No____ N/A____ Yes____ No____

Stop (2) missing Yes____ No____ Yes____ No____

Stop (2) Fasteners

Loose Or Missing

N/A____ Yes____ No____ N/A____ Yes____ No____

Wedge (3) missing Yes____ No____ Yes____ No____

Wedge (3) Fasteners

Loose Or Missing

N/A____ Yes____ No____ N/A____ Yes____ No____

1
Page B1 of B7

Oct 12/2012

1

A

670BA---32---040 APPENDIX B

Revision B, Jul 02/2014

DATA SHEET

The data sheets in this appendix are given as references in the

ACCOMPLISHMENT INSTRUCTIONS of Service Bulletin 670BA---32---040.
APPENDIX B

Page B2 of B7

Oct 12/2012

1

A

670BA---32---040 APPENDIX B

Revision B, Jul 02/2014

LEFT SIDE

AIRCRAFT SERIAL NUMBER: ___________________

TABLE 1

RECORD SHEET --- MISMATCHES

LOCATION MISMATCHES BETWEEN THE LEFT MLG INBOARD DOOR AND THE FAIRING

POINT ACCEPTABLE MISMATCHES MEASURED MISMATCHES

PT1 ---0.200 in. (5.08 mm) to

+0.120 in. (3.05 mm)

PT2

+/---0.030 in. (0.76 mm)

NOTE:---0.050 in. (1.27 mm) to

+0.080 (2.03 mm) for two of the

five locations acceptable.

PT3

PT4

PT5

PT6

PT9

---0.030 in. (0.76 mm) to

+0.080 (2.03 mm)

NOTE: ---0.050 in. (1.27 mm) to

+0.100 (2.54 mm) for two of the

five locations is acceptable.

PT10

PT11

PT12

PT13

PT14 +/---0.120 in. (3.05 mm)

PT15 ---0.070 in. (1.78 mm) to

+0.100 in. (2.54 mm)

NOTE: Up to +0.150 in. (3.81

mm) for two of the five locations

is acceptable.

PT16

PT17

PT18

PT19

PT20

--- 0.050 in. (1.27 mm) to

+0.100 in. (2.54 mm)

PT21

PT22

PT23

PT24

PT25 No measurement is necessay N/A
APPENDIX B

Page B3 of B7

Oct 12/2012

1

A

670BA---32---040 APPENDIX B

Revision B, Jul 02/2014

LEFT SIDE

AIRCRAFT SERIAL NUMBER: ___________________

TABLE 2

RECORD SHEET --- CLEARANCES CHECK

LOCATION CLEARANCE BETWEEN THE LEFT MLG INBOARD DOOR AND THE FAIRING

POINT ACCEPTABLE

CLEARANCE

MEASURED

CLEARANCE

MATERIAL

TO BE REMOVED

PT1 0.275 to 0.425 in.

(6.99 to 10.80 mm)

PT2 0.050 to 0.200 in.

(1.27 to 5.08 mm)

NOTE: Up to 0.250 in. (6.35

mm) for one of the five location is acceptable

PT3

PT4

PT5

PT6

PT7

PT8

PT9

0.050 to 0.200 in.

(1.27 to 5.08 mm)

PT10

PT11

PT12

PT13

PT14 0.100 to 0.200 in.

(2.54 to 5.08 mm)

PT15 0.100 to 0.200 in.

(2.54 to 5.08 mm)

NOTE: Up to 0.250 in. (6.35

mm) for one of the five location is acceptable

PT16

PT17

PT18

PT19

PT20 0.650 to 0.800 in.

(16.51 to 20.32 mm)

PT21 0.850 to 1.000 in.

(21.59 to 25.4 mm)

PT22 0.440 to 0.590 in.

PT23 (11.18 to 14.99 mm)

PT24 0.750 to 0.900 in.

(19.05 to 22.86 mm)

PT25 0.550 to 0.700 in.

(13.97 to 17.78 mm)
APPENDIX B

Page B4 of B7

Oct 12/2012

1

A

670BA---32---040 APPENDIX B

Revision B, Jul 02/2014

LEFT SIDE

AIRCRAFT SERIAL NUMBER: ___________________

TABLE 3

RECORD SHEET --- OVERLAP CHECK

LOCATION SEAL OVERLAP ON THE LEFT MLG INBOARD DOOR

POINT MINIMUM OVERLAP FOR THE

FORWARD SEAL SEAL OVERLAP MEASUREMENT

PT20 0.250 in. (6.3 mm)

PT21 0.250 in. (6.3 mm)

PT22 0.250 in. (6.3 mm)

PT23 0.250 in. (6.3 mm)

RECORD SHEET --- OVERLAP CHECK

LOCATION OVERLAP ON THE LEFT MLG INBOARD DOOR

Figure

17 View

C---C

MINIMUM OVERLAP BETWEEN

THE AFT STOP FITTING AND

THE MLG DOOR STOP FITTING

OVERLAP MEASUREMENT OF THE STOP

FITTING

0.600 in. (15.2 mm)
APPENDIX B

Page B5 of B7

Oct 12/2012

1

A

670BA---32---040 APPENDIX B

Revision B, Jul 02/2014

RIGHT SIDE

AIRCRAFT SERIAL NUMBER: ___________________

TABLE 1

RECORD SHEET --- MISMATCHES

LOCATION MISMATCHES BETWEEN THE RIGHT MLG INBOARD DOOR AND THE FAIRING

POINT ACCEPTABLE MISMATCHES MEASURED MISMATCHES

PT1 ---0.200 in. (5.08 mm) to

+0.120 in. (3.05 mm)

PT2

+/---0.030 in. (0.76 mm)

NOTE:---0.050 in. (1.27 mm)

+0.080 (2.03 mm) for two of the

five locations acceptable.

PT3

PT4

PT5

PT6

PT9

---0.030 in. (0.76 mm) to

+0.080 (2.03 mm)

NOTE: ---0.050 in. (1.27 mm) to

+0.100 (2.54 mm) for two of the

five locations is acceptable.

PT10

PT11

PT12

PT13

PT14 +/---0.120 in. (3.05 mm)

PT15 ---0.070 in. (1.78 mm) to

+0.100 in. (2.54 mm)

NOTE: Up to +0.150 in. (3.81

mm) for two of the five locations

is acceptable.

PT16

PT17

PT18

PT19

PT20

--- 0.050 in. (1.27 mm) to

+0.100 in. (2.54 mm)

PT21

PT22

PT23

PT24

PT25 No measurement is necessay N/A
APPENDIX B

Page B6 of B7

Oct 12/2012

1

A

670BA---32---040 APPENDIX B

Revision B, Jul 02/2014

RIGHT SIDE

AIRCRAFT SERIAL NUMBER: ___________________

TABLE 2

RECORD SHEET --- CLEARANCES CHECK

LOCATION CLEARANCE BETWEEN THE RIGHT MLG INBOARD DOOR AND THE FAIRING

POINT ACCEPTABLE

CLEARANCE

MEASURED

CLEARANCE

MATERIAL

TO BE REMOVED

PT1 0.275 to 0.425 in.

(6.99 to 10.80 mm)

PT2 0.050 to 0.200 in.

(1.27 to 5.08 mm)

NOTE: Up to 0.250 in. (6.35

mm) for one of the five location is acceptable

PT3

PT4

PT5

PT6

PT7

PT8

PT9

0.050 to 0.200 in.

(1.27 to 5.08 mm)

PT10

PT11

PT12

PT13

PT14 0.100 to 0.200 in.

(2.54 to 5.08 mm)

PT15 0.100 to 0.200 in.

(2.54 to 5.08 mm)

NOTE: Up to 0.250 in. (6.35

mm) for one of the five location is acceptable

PT16

PT17

PT18

PT19

PT20 0.650 to 0.800 in.

(16.51 to 20.32 mm)

PT21 0.850 to 1.000 in.

(21.59 to 25.4 mm)

PT22 0.440 to 0.590 in.

PT23 (11.18 to 14.99 mm)

PT24 0.750 to 0.900 in.

(19.05 to 22.86 mm)

PT25 0.550 to 0.700 in.

(13.97 to 17.78 mm)
APPENDIX B

Page B7 of B7

Oct 12/2012

1

A

670BA---32---040 APPENDIX B

Revision B, Jul 02/2014

RIGHT SIDE

AIRCRAFT SERIAL NUMBER: ___________________

TABLE 3

RECORD SHEET --- OVERLAP CHECK

LOCATION SEAL OVERLAP ON THE RIGHT MLG INBOARD DOOR

POINT MINIMUM OVERLAP FOR THE

FORWARD SEAL SEAL OVERLAP MEASURMENT

PT20 0.250 in. (6.3 mm)

PT21 0.250 in. (6.3 mm)

PT22 0.250 in. (6.3 mm)

PT23 0.250 in. (6.3 mm)

RECORD SHEET --- OVERLAP CHECK

LOCATION OVERLAP ON THE RIGHT MLG INBOARD DOOR

Figure

17 View

C---C

MINIMUM OVERLAP BETWEEN

THE AFT STOP FITTING AND

THE MLG DOOR STOP FITTING

OVERLAP MEASURMENT OF THE STOP

FITTING

0.600 in. (15.2 mm)

1
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Service Bulletin No.: Revision: 

Aircraft Serial Number: Date:

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accurate.

Comments:

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were helpful to do the service bulletin.

Comments:

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Part(s) or kit(s) agreed with the service

bulletin requirement.

Comments:

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within the estimated time given.

Comments:

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bulletin.

Comments:

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Name: Telephone or Fax:

FAX your comments or feedback to (450) 476---7300

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