July 8/11 Service Bulletin 215-A547

Page 1 of 8 ATA Ref: 32-10

MODEL CL-215-1A10

MODEL CL-215-6B11

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SERVICE BULLETIN

LANDING GEAR

INSPECTION OF THE MAIN LANDING GEAR (MLG) UPPER MEMBER FORWARD LUG

USING LIQUID PENETRANT METHOD

1. Planning Information

A. Compliance

The inspection described in this Service Bulletin is Mandatory and must be completed before

November 15, 2011.

NOTE: This Service Bulletin is only applicable to aircraft in the condition as originally

delivered by Canadair and/or Bombardier Aerospace or as subsequently modified by

Canadair and/or Bombardier Aerospace Service Bulletin(s). Prior to incorporation of

this Service Bulletin, the status of any related systems or structural modification(s)

introduced by Supplementary Type Approval (STA) or equivalent action must be

examined for compatibility with the modifications and test procedures (if applicable)

detailed in this Service Bulletin. 

B. Approval

The technical content of this Service Bulletin has been approved under the authority of the

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

C. Effectivity

CL−215−1A10 piston and CL−215−6B11 turboprop aircraft, Serial Nos. 1051 to 1125.

D. Reason

Cracks have been detected on the forward main landing gear lugs in service.

E. Description

This Service Bulletin gives instruction to do a one−time liquid penetrant inspection of the

forward lug part numbers 160−714−3 (LH) and 160−714−4 (RH).
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July 8/11 Service Bulletin 215-A547

Page 2 of 8 ATA Ref: 32-10

F. Manpower

We estimate that it will take 1 technician approximately 16 hours to complete this Service

Bulletin.

G. Material Availability

No kit is necessary for this inspection.

H. Tool Availability

No special tools or equipment are necessary.

I. Weight and Balance

Not affected.

J. Electrical Load Data

Not affected.

K. References

Bombardier Aerospace Restriction and/or Special Instruction (RSI) C-3892, Revision A.

L. Publications Affected

None.

M. Related Service Bulletin

Service Bulletin 215-548, Inspection of the Main Landing Gear Upper Member Forward Lug

Using Eddy Current Inspection Method.
MODEL CL-215-1A10

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SERVICE BULLETIN

July 8/11 Service Bulletin 215-A547

Page 3 of 8 ATA Ref: 32-10

2. Accomplishment Instructions

NOTES: 1. For this modification, it is assumed that standard maintenance and repair practices

will be applied in accordance with applicable Product Support Publications (PSP).

2. For parts location, refer to the illustration page in this Service Bulletin.

3. Bare metal areas must be treated with alodizing solution, MIL-C-81706 Class 1A, and

two coats of fluid resistant epoxy primer, BAMS 565-01. Apply finishing topcoat,

BAMS 565-02, as required. Refer to PSP 297, Chapter 51-52-16, CORROSION

PREVENTIVE TREATMENT − GENERAL PROCEDURES.

4. If any deviation exists, contact your Amphibious Aircraft Technical Representative for

further instructions.

A. Preparation

Refer to Figure 1

The procedure for the left MLG upper member forward lug is described. The procedure for the

right MLG upper member forward lug is similar.

WARNING: ENSURE PERSONNEL AND EQUIPMENT ARE CLEAR OF ALL

HYDRAULICALLY OPERATED SYSTEMS PRIOR TO REMOVING ELECTRICAL

POWER. IF YOU DO NOT DO THIS INJURIES TO PERSONNEL AND

DAMAGE TO EQUIPMENT CAN OCCUR.

(1) Isolate electrical power and observe all safety precautions.

(a) For turboprop aircraft refer to PSP 392, Chapter 24 − ELECTRICAL POWER.

(b) For piston aircraft refer to PSP 292, Chapter 24 − ELECTRICAL POWER.

CAUTION: DO NOT PAINT OR ETCH THE LUG HOLE. APPLY A PROTECTION TO THE

LUG HOLE TO PREVENT UNWANTED MATERIALS OR CONTAMINATION IN

THE LUG HOLE.

(2) Jack the aircraft. Refer to PSP 292, Maintenance Manual, Chapter 7, AIRCRAFT

JACKING.

NOTE: It is necessary to jack the aircraft and remove the upper member pivot pin to

access the inspection area. It is not necessary to remove the MLG upper

member.

(3) Install a support and a jack under the shock strut to hold the weight of the shock strut.

(4) Remove the pivot pin from the upper member forward lug and replace it with a temporary

pin. Refer to PSP 292, Maintenance Manual, Chapter 32-11-05, MAIN LANDING GEAR

UPPER-MEMBERS − REMOVAL/INSTALLATION, Paragraph A and do the steps as

necessary.

(5) Remove all grease, sealing compound, paint and primer from the shoulder of the upper

member forward lug 1 in. (2,54 cm) around the inspection area. Refer to PSP 297,

Chapter 51−52−16, Section 6.A. − Removal of Paint and Primer from Metal Surfaces.
MODEL CL-215-1A10

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July 8/11 Service Bulletin 215-A547

Page 4 of 8 ATA Ref: 32-10

(6) Apply masking material to the outer surface around the inspection area to make sure

etchant solution is contained to the inspection area.

(7) Use a brush to apply a thin layer of the etchant solution to the inspection area.

NOTE: Etchant solution is made with 15% sodium hydroxide thickened with 50 grams

per litre of cornstarch.

(8) Continue to apply etchant solution to the inspection area to keep the surface wet.

NOTE: Do not let the solution go outside the masked area.

(9) Let the etchant stay on the inspection area for five to ten minutes.

(10) Use a wet water cloth to clean the inspection area, then apply the neutralizing solution

(nitric acid 2−Normal).

(11) Clean the area again with water, then dry the area with clean cloths.

(12) Remove the masking materials and make sure the surface is clear of all etchant solution.

B. Inspection

(1) Apply penetrant Type 1, Method C as per PSP 296, Part 1 Chapter 51-15-05, LIQUID

PENETRANT, Type 1 Method C.

CAUTION: OVER−REMOVAL OF THE SURFACE PENETRANT SHALL REQUIRE THAT

THE COMPONENT BE CLEANED AND REPROCESSED. A GOOD INDICATOR

OF OVER−WASH OR OVER−REMOVAL OF THE SURFACE PENETRANT IS

INDICATED BY THE TOTAL LACK OF RESIDUE THAT MAY OCCUR ON ALL,

OR A SPECIFIC AREA OF THE PART, WHEN INSPECTED UNDER A BLACK

LIGHT DURING THE REMOVAL CYCLE AND/OR IN THE INSPECTION

STATION AFTER DRYING.

(2) Remove penetrant Type 1, Method Cas per PSP 296, Part 1 Chapter 51-15-05, LIQUID

PENETRANT, Type 1 Method C.

NOTE: Use a black light lamp during the cleaning operation to make sure that all excess

penetrant is removed.

(3) Apply a thin spray of developer (Form d), equally over the inspection surface as per PSP

296, Part 1 Chapter 51−15−05, LIQUID PENETRANT, Developer Application −

Non−aqueous Developers.

NOTE: Developer coverage should be uniform and light enough so that the metallic

surface background is visible through the developer application.

(4) Let the developer stay on the inspection area for a minimum of 10 minutes to a maximum

of 60 minutes.
MODEL CL-215-1A10

MODEL CL-215-6B11

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July 8/11 Service Bulletin 215-A547

Page 5 of 8 ATA Ref: 32-10

(5) Do a fluorescent penetrant inspection of the lug shoulder on the forward lug. Refer to

PSP 296, Part 1 Chapter 51-15-05, LIQUID PENETRANT, Component Examination,

Para A, Type 1 Process.

NOTE: If the inspection is not completed before the maximum time permitted, you must

clean the inspection area and start over (it is not necessary to etch the area

again).

(6) Evaluate all inspection surfaces for evidence of relevant and non−relevant indications.

The black light must not be closer than 6 in. (15,24 cm) to the inspection surface.

(7) Determine the type and size of discontinuities as per PSP 296, Part 1 Chapter 51-15-05,

LIQUID PENETRANT − Discontinuity Interpretation.

Refer to Figure 2 − INSPECTION RESULTS − CRACK TOLERANCES

(8) If there is a crack,

− provide details of findings (crack length, zone affected, aircraft serial number, and

photo) to your Amphibious Aircraft Technical Representative, and

− replace the forward lug (160−714−3 or 160−714−4), as per PSP 298, MAIN LANDING

GEAR UPPER AND LOWER MEMBERS − DISASSEMBLY/ASSEMBLY.

C. Close−Out

(1) Replace any finish that was removed from the inspection area. Refer to PSP 297,

Stuctural Repair Manual, Chapter 51−52−16, CORROSION PREVENTIVE TREATMENT

− GENERAL PROCEDURES.

(2) Install the pivot pin for the upper member forward lug and remove the temporary pin.

Refer to PSP 292, Maintenance Manual, Chapter 32-11-05, MAIN LANDING GEAR

UPPER-MEMBERS − REMOVAL/INSTALLATION, Paragraph B and do the steps as

necessary.

(3) Remove the support and jack from under the shock strut that was in place to hold the

weight of the shock strut.

(4) Do a functional test of the extension and retraction of the landing gear. Refer to PSP 292,

Chapter 32-30-00-501, Paragragh A.

(5) Remove all tools, equipment, and unwanted materials from the work area.

(6) Lower the aircraft. Refer to PSP 292, Maintenance Manual, Chapter 7, AIRCRAFT

JACKING.

(7) Restore the electrical power. Refer to PSP 392 (turboprop aircraft) or PSP 292 (piston

aircraft), Chapter 24 − ELECTRICAL POWER.

D. Recording

When this Service Bulletin is completed, make the entry in the aircraft technical record and

send back the attached Incorporation Notice to Amphibious Aircraft Technical Publications.
MODEL CL-215-1A10

MODEL CL-215-6B11

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July 8/11 Service Bulletin 215-A547

Page 6 of 8 ATA Ref: 32-10

INSPECTION LOCATION OF THE MAIN LANDING GEAR (MLG) UPPER MEMBER FORWARD LUG

FIGURE 1

REMOVE ALL PAINT AND PRIMER FROM THIS AREA

(DO NOT REMOVE PAINT FROM THE LUG HOLE)

FORWARD LUG

160−714−3

LH MLG

UPPER MEMBER

INSPECT 0.500 in. (12,7 mm)

AROUND THE RADIUS

TYPICAL FOR BOTH ENDS

INSPECTION AREA
MODEL CL-215-1A10

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July 8/11 Service Bulletin 215-A547

Page 7 of 8 ATA Ref: 32-10

INSPECTION RESULTS − CRACK TOLERANCES

FIGURE 2

LH MLG

UPPER MEMBER

ZONE 1

ZONE 2

BOTH SIDES
MODEL CL-215-1A10

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July 8/11 Service Bulletin 215-A547

Page 8 of 8 ATA Ref: 32-10

3. Material Information

This Service Bulletin contains no kit.

A. The following materials, or equivalent, are necessary to do this Service Bulletin. You can buy

them locally:

DESCRIPTION PART NO./NAME SPECIFICATION QUANTITY

Alodizing Solution Alodine 1200S MIL-C-81706 

Class 1A

A/R

Aerodynamic 

Sealant

Pro Seal 870

Class B−2

MIL-S-81733 

Type 2

A/R

Faying Surface

Sealant

Pro Seal 870

Class C

MIL-S-81733 

Type 4

A/R

Humiseal 1B15 A/R

Fluid Resistant Epoxy

Primer

BAMS 565-01 A/R

Fluid Resistant Epoxy

Topcoat

BAMS 565-02 A/R

Etchant solution (50

grams cornstarch per

litre of Sodium hydroxide solution)

15% Sodium hydroxide

solution thickened with

cornstarch

A/R

Nitric acid solution

(2−Normal)

A/R

Plastic masking tape HS8171 Richmond Aircraft or

equivalent

A/R

Aluminium masking

tape

425 3M or equivalent A/R
Upon completion of Service Bulletin(s), please fill in and return by fax to:

Service Bulletin Number(s) Rev.

Aircraft Serial No.

Date of Incorporation

Aircraft Reg. No.

Technical Publication,

Dept. 649-DBF−(9)

Bombardier Aerospace

Amphibious Aircraft

St. Laurent, Quebec

Fax No.: (514) 855−7602

Airframe Hours

Remarks

Name

SERVICE BULLETIN

INCORPORATION NOTICE

REPLY FAX

Customer/Operation

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