Service Bulletin 215-A548 July 15/11 Page 1 of 13 ATA Ref: 32-10 

# MODEL CL-215-1A10 MODEL CL-215-6B11 ALERT SERVICE BULLETIN LANDING GEAR INSPECTION OF THE MAIN LANDING GEAR (MLG) UPPER MEMBER FORWARD LUG USING EDDY CURRENT METHOD 1. Planning Information A. Compliance The inspection described in this Service Bulletin is Mandatory and must be completed within the next 50 flight hours upon receipt of this Service Bulletin. The inspection described in this Service Bulletin is to be repeated at or before every 165 land landings until a permanent solution is incorporated in the Aircraft Maintenance Manual and/or pending further instruction from your Amphibious Aircraft Technical Representative. 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 to1125. D. Reason Cracks have been detected on the forward main landing gear lugs in service.MODEL CL-215-1A10 MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A548 July 15/11 Page 2 of 13 ATA Ref: 32-10 E. Description This Service Bulletin gives instruction to do an eddy current inspection on the forward lug part numbers 160 − 714 − 3 (LH) and 160 − 714 − 4 (RH), without removing the MLG upper member. F. Manpower We estimate that it will take 1 technician approximately 2 hours to complete this Service Bulletin. NOTE : All NDT inspections must be done by certified level 2 or 3 individuals in an NDT standard approved by the national Airworthiness authority. G. Material Availability No kit is necessary for this inspection. H. Tool Availability REFERENCE1.9 DESIGNATION Hocking Phasec 2200 or equivalent Eddy Current-Instrument-Impedance-Plane Type AL29 − 32 Calibration reference standard made from aluminum alloy (29% IACS), that contains 0.008 in. (0.20 mm), 0.020 in.(0.51 mm), and 0.040 in. (1.02 mm) deep electrical discharge machined (EDM) notches. Commercially available Coaxial cable (microdot to BNC type) Commercially available Surface probe, 45 °tip, 500 kHz frequency, NFe/Fe, absolute, shielded, 0.092 in. (2.34 mm) diameter, 4.50 in. (114.30 mm) length, 0.750 in. (19.5 mm) tip length. (GE P/N 205P4XF or equivalent) Commercially available Explosion Proof Light NOTES : 1. You can use equivalent eddy current equipment if it satisfies the requirements of this procedure and is capable of resolving the reference notch in the calibration reference standard at the required level of resolution and sensitivity. 2 To get access to the inspection area, it is permitted to use a surface probe of different configuration from the one specified. The test frequency can range from 100 kHz to 500 kHz.MODEL CL-215-1A10 MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A548 July 15/11 Page 3 of 13 ATA Ref: 32-10 I. Weight and Balance Not affected. J. Electrical Load Data Not affected. K. References For Bombardier Aerospace Reference only: (Not Supplied with Kit) Bombardier Aerospace Restriction and/or Special Instruction (RSI) C-3892, Revision, A. L. Publications Affected None. M. Related Service Bulletin Service Bulletin 215-547, Inspection of the Main Landing Gear Upper Member Forward Lug Using Liquid Penetrant Inspection Method. 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. If any deviation exists, contact your Amphibious Aircraft Technical Representative for further instructions.MODEL CL-215-1A10 MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A548 July 15/11 Page 4 of 13 ATA Ref: 32-10 A. Preparation For piston aircraft refer to PSP 296, Nondestructive Testing Manual, PART 1 GENERAL − EDDY CURRENT, and Figure 2. For turboprop aircraft refer to PSP 396, Nondestructive Testing Manual, PART 6 GENERAL − EDDY CURRENT, and Figure 2. 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. NOTE : It is not necessary to remove the MLG upper member to do this inspection. (2) Make sure the inspection surface is clearly visible. Refer to Figure 3. WARNING : WEAR RUBBER GLOVES, EYE PROTECTION, AND A RESPIRATOR WHEN HANDLING SOLVENTS, SEALING COMPOUNDS, OR ADHESIVES. CONTACT WITH SOLVENTS, SEALING COMPOUNDS, OR ADHESIVES AND THEIR VAPOURS MAY CAUSE IRRITATION TO THE SKIN, THE EYES, AND THE LUNGS. FAILURE TO WEAR PROPER PROTECTION MAY CAUSE INJURIES TO PERSONNEL. (3) Clean the areas to be inspected thoroughly with aliphatic naphtha using a nylon bristled brush and clean cloths in accordance with PSP 297, Chapter 51. Allow the surfaces to dry completely. NOTE : If the paint or primer is in good condition, it does not need to be stripped. If the finish is damaged, the bare metal must be exposed and refinished in accordance with PSP 297, Chapter 51.MODEL CL-215-1A10 MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A548 July 15/11 Page 5 of 13 ATA Ref: 32-10 B. Equipment Calibration Refer to Figures 1 and 2 NOTES : 1. Make sure that you follow the manufacturer’s instrument instructions when you operate the test equipment. 2. The values listed in Figure 1 may vary between instruments. (1) Connect the probe 205P4XF with the coaxial cable to the eddy current instrument. (2) Turn the instrument ON and adjust and set the instrument controls as shown in Figure 1. (3) Put the probe (coil) tip perpendicular to the surface of the AL29 − 32 calibration reference standard (CRS), away from the 0.040 in. (1,02 mm) deep EDM notch and the edge. (4) Balance (BAL) the eddy current instrument. (a) Adjust the instrument (PHASE) control to obtain a horizontal lift − off signal moving from right − to − left (with increasing lift − off) across the screen display. (b) Use the (X − POS) and (Y − POS) controls to position the dot in the lower right quadrant of the screen display. (5) Move the probe (coil) tip across the 0.040 in. (1,02 mm) deep EDM notch, and adjust the instrument sensitivity (gain) to obtain an amplitude signal as shown in Figure 1, Screen Display. (6) Differentiate between the EDM notch and the edge signals by moving the probe over the edge of the reference standard. (a) Make sure the signal obtained from the edge slants − off towards the upper left quadrant as shown in Figure 1.MODEL CL-215-1A10 MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A548 July 15/11 Page 6 of 13 ATA Ref: 32-10 C. Lift − Off Compensation Verification Refer to Figures 1 and 2 (1) Put the probe (coil) tip perpendicular to the inspection surface. NOTE : DO NOT balance the instrument. (2) Compare the screen displays between the operating point on the inspection surface and the balance point on the CRS for the following conditions: (a) If the operating point on the inspection surface matchesthe balance point on the CRS, no compensation for paint thickness is required: 1 Proceed to the Inspection Procedure section.

−or − (b) If the operating point on the inspection area does not match the balance point on the CRS, but has moved to the LEFT, compensation for the paint thickness is required. Do as follows: 1 Attach a strip of nonconductive tape or shim to cover the CRS surface and the EDM notches. 2 Put the probe (coil) tip perpendicular to the surface of the CRS. DO NOT balance the instrument. 3 Compare the operating point on the inspection surface to the balance point on the CRS for the conditions that follow:

− If the operating point on the inspection surface is still to the left of the balance point on the CRS, add an additional strip of tape or shim until the balance point on the CRS matches the inspection area.

− If the operating point on the CRS over the tape is to the right of the balance point, remove a strip of tape or shim until the balance point on the CRS matches the inspection area.

− If lift − off compensation and calibration requirements cannot be met, remove the paint or coating prior to inspection. (3) Slide the probe across the 0.040 in. (1,02 mm) EDM deep notch covered with tape on the CRS. (a) Adjust the GAIN to obtain an eddy current amplitude signal from the 0.040 in. (1,02 mm) deep EDM notch as shown in Figure 1, Screen Display. (b) Proceed to the Inspection Procedure section.MODEL CL-215-1A10 MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A548 July 15/11 Page 7 of 13 ATA Ref: 32-10 D. Inspection Procedure Refer to Figure 3 NOTES : 1. Monitor the screen display carefully at all times and make a note of all distinct relevant indications. Include the screen height of each signal and the related location on the part being inspected. 2. A relevant crack indication is as follows:

− A fast up dot movement signal that stays at the up position for more than a longer probe scan distance (more than one probe diameter) when a crack length is parallel to the scan direction,

− a fast vertical deflection signal with a short probe scan distance (one probe diameter or less) when the crack length is perpendicular to the scan direction. 3. After balancing the inspection area, if the balance point drops below the screen display from the original balance point, it could indicate the original balance location contains a defect. If this is true, rebalance on an adjacent area and scan the original balance point for possible defects before continuing the inspection. 4. Instrument calibration verification intervals are as follows:

− Every 30 minutes of continuous operation,

− a change to set − up parameters, and/or equipment (i.e. a different probe),

− when the inspection is completed,

− when there is any variation in the amplitude of the calibration signal, calibrate the instrument again and repeat the inspection at all locations from the last valid calibration point. 5. Make sure the operation point is on the screen display at all times. 6. The maximum inspection scan speed shall be equivalent or less than the calibration probe speed. Refer to Figure 1 for typical screen responses and Figure 3 for inspection areas and scan paths. (1) Put the probe (coil) tip perpendicular to the inspection area as close as possible to the shoulder of the initial machined fillet radius on the left MLG upper member forward lug without getting an edge signal. (2) Balance (BAL) the instrument. (a) If necessary, adjust the instrument (PHASE) control to obtain a horizontal lift − off signal moving from right − to − left across the screen display.MODEL CL-215-1A10 MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A548 July 15/11 Page 8 of 13 ATA Ref: 32-10 (3) Make a series of contour scans parallel to the shoulder adjacent to the machined fillet radius extending for 0.250 in. (6,35 mm) from the machined fillet radius juncture. (a) Make sure you maintain a constant edge distance for the initial scan on the shoulder adjacent to the machined fillet radius. (b) Make sure the probe tip stays perpendicular to the inspection surface at all times during the scan. (c) Index one probe diameter or less from the previous scan. Refer to Figure 3 for inspection location and for typical scan path. (4) Repeat the inspection procedure for the opposite shoulder of the MLG upper member forward lug. (5) Repeat the inspection procedure for the right-hand (RH) MLG upper member forward lug. E. Evaluation of Indications (1) Further investigation is required if: (a) there is a distinct vertical deflection signal that occurs over a short scan distance (one probe tip diameter), or (b) there is a rapid up dot movement signal that stays at the up position over a longer scan distance. (2) If you have a suspect indication, make sure it is not caused by non-relevant factors, as follows:

− edge effect,

− an abrupt change in geometry,

− localized variations in conductivity,

− permeability, or

− other non − relevant factors. (3) Evaluate all suspect crack indications by comparing their phase angle, amplitude and shape to the calibration standard EDM notch signal. (4) If a crack is detected, determine the length and location of the crack.MODEL CL-215-1A10 MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A548 July 15/11 Page 9 of 13 ATA Ref: 32-10 F. Acceptance or Rejection Criteria Refer to Figures 1 and 3 (1) Indications of a crack are as follows: (a) A distinct vertical deflection signal that occurs over a short scan distance (one probe tip diameter), (b) a distinct vertical deflection signal which equals to 50% or greater than the response from the 0.040 in. (1,02 mm) deep EDM notch as shown in Figure 1, (c) a rapid upward dot movement signal which equals to 50% or greater than the response from the 0.040 in. (1,02 mm) deep EDM notch as shown in Figure 1 and remains at the upward position momentarily (or over a longer period of time). (2) If there areno cracks ,

− repeat the Eddy Current Inspection every 165 Land Landings. (3) If there is acrack ,

− provide details of findings to your Amphibious Aircraft Technical Representative,

− replace the forward lug (160 − 714 − 3 or 160 − 714 − 4), as per PSP 298, MAIN LANDING GEAR UPPER AND LOWER MEMBERS − DISASSEMBLY/ASSEMBLY.

− repeat the Eddy Current Inspection every 165 Land Landings. G. 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) Remove all tools, equipment, and unwanted materials from the work area. (3) Restore the electrical power. (a) For turboprop aircraft refer to PSP 392, Chapter 24 − ELECTRICAL POWER. (b) For piston aircraft refer to PSP 292, Chapter 24 − ELECTRICAL POWER. H. 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 ALERT SERVICE BULLETIN

Service Bulletin 215-A548 July 15/11 Page 10 of 13 ATA Ref: 32-10 AND PROBE 205P4XF) FIGURE 1 

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. . . . . .. . . .

.

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. ... . . . . . .

. . . . . .. . . .

. . . . . .. . . . . . . . . . .

. . .

. SCREEN DISPLAY
EDGE SIGNAL INSTRUMENT SETTINGS SIGNAL FROM 0.040 − in. (1,02 − mm) DEEP EDM NOTCH

LIFT − OFF SIGNAL BALANCE POINT 100%

0% 80 % FSH MODE DISPLAY VIEW CH 1 FREQ CH 1 PHASE GAIN X:Y HI − PASS LO − PASS BAL. LOAD X − POS Y − POS ABS CH1 XY CH 1 500 kHz 342.0 44.5 dB X − 8 dB DC 200 Hz 47 H 40

− 40 

### . 

## . ... .

CALIBRATION DATA (HOCKING PHASEC 2200 EDDY CURRENT INSTRUMENT μMODEL CL-215-1A10 MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A548 July 15/11 Page 11 of 13 ATA Ref: 32-10 3.75 in. 0.75 1.00
1.50 in.

(1,02 mm)

NOTES 4
2. 0.005 in. +0.000/− 0.002 in. (0,127 mm +0,000/− 0,051 mm) (0,51 mm) (0,20 mm) 0.040 0.020 0.008AL 29.324 0.75

0.25 in. Material: 2024 − T3, QQ − A− 250/4 1. Finish surface 125 RMS or better. (19,05 mm)(19,05 mm) (25,40 mm) (95,25 mm)

WIDE X 1.50 in. (38,10 mm) LONG EDM NOTCH (38,10 mm)

(TYPICAL) 0.040 in. 0.020 in. 0.008 in. (6,35 mm)
3. Penetrant inspect as per BAPS 176 − 002. 4. Identification sticker, 0.125 in (3,175 mm) letters black colour. 5. Conductivity test as per BAPS 168 − 013. 6. EDM notches shall have a tolerance of 0.001 in. ( 0.025 mm) for depth and +0.000/0.002 in. (+0,000/− 0,051 mm) for width. − +
− +

CALIBRATION REFERENCE STANDARD AL 29 − 32 FIGURE 2MODEL CL-215-1A10 MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A548 July 15/11 Page 12 of 13 ATA Ref: 32-10 INSPECTION LOCATION OF THE MAIN LANDING GEAR (MLG) FORWARD LUG SHOULDERS FIGURE 3 LH MLG UPPER MEMBER

Inspect 0.250 in. (6,35 mm) from the Machined Filet Radius Juncture 0.250 in. 0.250 in. 0.250 in. Reference: Machined Filet Radius

Typical for Both Sides Typical Inspection Area for Both Shoulders adjacent to the Machined Filet Radius NOTES Dash Lines Represent Typical Scan Paths Typical Crack Location

0.250 in.MODEL CL-215-1A10 MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A548 July 15/11 Page 13 of 13 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 Aliphatic Naphtha TT-N-95 Type 2 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

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