Service Bulletin 215-A3173 April 11/12 Page 1 of 14 ATA Ref: 54-10 

# MODEL CL-215-6B11 ALERT SERVICE BULLETIN NACELLES/PYLONS INSPECTION OF THE BUSHINGS IN THE NACELLE UPPER STRUT ASSEMBLIES 1. Planning Information A. Compliance Installation of this Service Bulletin is mandatory. The inspection task described in this Service Bulletin must be performed prior to May 30th, 2013. If bushing 85410265 − 105 is installed and can only be repaired and not replaced at the time of the inspection, then it must be replaced at the next scheduled 5000 hours maintenance check or at the next engine removal, which ever comes first. 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-215-6B11 turboprop aircraft Serial Nos. 1056, 1057, 1061, 1080, 1109, 1113, 1114, 1115, 1116, 1117, 1118, 1119, 1120, 1121, 1122, and 1125. D. Reason It was suspected that bushing 85410265 − 105 could be installed on aircraft in lieu of 85410265 − 103, but bushing 85410265 − 105 is shorter than the − 103 and is not an acceptable replacement and is not intended for use on CL-215T nacelles.MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A3173 April 11/12 Page 2 of 14 ATA Ref: 54-10 E. Description This Service Bulletin gives instructions to do the following:

− Inspect the bushing

− Replace the bushing if necessary

− Repair the bushing if replacement is not possible. F. Manpower We estimate that it will take one technician approximately 4 hours to complete the inspection instructions of this Service Bulletin. We estimate that it will take one technician approximately 4 hours to complete the replacement instructions of this Service Bulletin. We estimate that it will take one technician approximately 4 hours to complete the repair instructions of this Service Bulletin. G. Material Availability Kit No. 215K3173 is necessary to do this Service Bulletin. Information on price and delivery is available from your Bombardier Specialized and Amphibious Spares Representative. Bushing 85410265 − 103 and repair bushing C415 − 3902 − 001 are available through your Bombardier Specialized and Amphibious Spares Representative. H. Tool Availability The following tools (refer to PSP 211) are required to do this inspection:

− Nacelle mounted engine hoist and sling, 08 − 0116 − 5000 (or equivalent) OR

− Engine sling, 08 − 0112 − 4000 (or equivalent)

− Dynamometer or Load cell of a 2500 lbs capacity. I. Weight and Balance Not affected. J. Electrical Load Data Not affected.MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A3173 April 11/12 Page 3 of 14 ATA Ref: 54-10 K. References For Bombardier Aerospace Reference only: (Not Supplied with Kit) Bombardier Aerospace Restriction and/or Special Instruction (RSI) C-3902, Revision NC. Related document: All Operator Message 54 − 40 − 00 − 007, dated Dec 13/11. L. Publications Affected None. M. Related Service Bulletins None. 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 illustrations in this Service Bulletin. 3. If any deviation exists, contact your Amphibious Aircraft Technical Representative for further instructions. 4. This inspection is for both the LH and RH nacelle, and there are two bushings in each nacelle. A. Preparation WARNING : ENSURE PERSONNEL AND EQUIPMENT ARE CLEAR OF ALL HYDRAULICALLY OPERATED SYSTEMS PRIOR TO REMOVING AIRCRAFT ELECTRICAL POWER. Isolate electrical power and observe all safety precautions (refer to PSP 392, Maintenance Manual, Chapter 24, ELECTRICAL POWER −MAINTENANCE PRACTICES). B. Access (1) Remove lower cowl panel assembly and forward upper cowl panel assembly, as per PSP 392, Maintenance Manual, Chapter 71, POWER PLANT −ENGINE COWLING − MAINTENANCE PRACTICES. (2) On LH nacelle, remove access panels 120 − 1, 120 − 2, 120 − 3, 120 − 4, 120 − 5 and 140 − 1 as per PSP 392, Maintenance Manual, Chapter 6, ENGINE NACELLES −ACCESS PANELS. (3) On RH nacelle, remove access panels 220 − 1, 220 − 2, 220 − 3, 220 − 4, 220 − 5 and 240 − 1 as per PSP 392, Maintenance Manual, Chapter 6, ENGINE NACELLES −ACCESS PANELS.MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A3173 April 11/12 Page 4 of 14 ATA Ref: 54-10 C. Engine Support The nacelle must be in the zero weight condition either by removing the engine from the nacelle (option 1) or by supporting the engine in the nacelle (option 2) as described below. CAUTION : ENSURE ENGINE SLING LIFT POINT IS POSITIONED TO BALANCE THE ENGINE AS CONFIGURED. USE EXTREME CAUTION WHEN SLINGING THE ENGINE TO AVOID DAMAGE TO THE HBV ELECTRICAL CONNECTOR AND FIRE/OVERHEAT SENSING ELEMENTS LOCATED IN NACELLE. OPTION 1 −Engine is removed from Aircraft. Refer to Figure 1.1 NOTE : Use this option only if the engine is scheduled to be removed from the aircraft, if the engine is not scheduled to be removed from the aircraft, then use option 2 for the bushing inspection. (1) Attach sling to reduction gear box lifting brackets and to engine F flange lifting bracket, and remove the engine as shown in PSP 392, Maintenance Manual, Chapter 71, POWER PLANT −TEAR DOWN/BUILD − UP −MAINTENANCE PRACTICES. OPTION 2 −Engine is NOT removed from Aircraft. Refer to Figure 1.2 (2) Calculate total weight to be lifted by adding engine weight (1500 lbs) to weight of lifting equipment located under dynamometer or load cell. (3) Attach sling to reduction gear box lifting brackets and to engine F flange lifting bracket, as shown in PSP 392, Maintenance Manual, Chapter 71, POWER PLANT −TEAR DOWN/BUILD − UP −MAINTENANCE PRACTICES. (4) Slowly raise hoist until reading on dynamometer or load cell indicates total lifted weight to be +50 lbs of calculated weight to be lifted. (5) Make sure the lifting equipment is locked in place and apply appropriate safety tags.MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A3173 April 11/12 Page 5 of 14 ATA Ref: 54-10 PART A −Inspection of the Bushing D. Inspection of the Nacelle Upper Strut Bushing Refer to Figure 2 Do the complete inspection on one strut assembly bushing before starting the other. (1) Remove the cotter pin and nut. (2) Remove and discard the PLI washer, and retain any washer that is installed between the PLI washer and the nut. NOTE : PLI (pre-load indicating) washers cannot be re − used and must be discarded once removed. (3) Remove the bolt 81812 − 8 − 30 and the countersunk washer. NOTES : 1. Make sure that the strut does not move when the bolt is removed. 2. If the engine is in the zero weight condition, the bolt should remove with minimum resistance. (4) Measure the distance “A” as shown in the table on Figure 2 to determine the part number of the bushing installed. (5) If bushing 85410265 − 103 is installed, do the section PART A −cont’d, Installation of Bolt and PLI Washer, then continue with the inspection of the remaining bushings (both upper strut assemblies in both nacelles).

− or − (6) If bushing 85410265 − 105 is installed, do one of the following:

− PART B −Replacement of the Bushing

− PART C −Repair of the Bushing PART B −Replacement of the Bushing E. If bushing 85410265 − 105 is installed and bushing 85410265 − 103 is readily available, then replace the bushing, as follows: (1) Remove the bushing 85410265 − 105 and discard. (2) Check the bushing housing for wear limits, refer to PSP 392, Chapter 54, STRUT MOUNTS −INSPECTION/CHECK. (3) Install the new bushing 85410265 − 103, refer to PSP 298, Chapter 20.MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A3173 April 11/12 Page 6 of 14 ATA Ref: 54-10 (4) If necessary, apply a brush nickel plate coating to bare metal of machined area at each end of the strut. Refer to PSP 298, Chapter 20. (5) Coat the bushing with Mastinox 6856H. (6) Continue with PART A −cont’d, Installation of Bolt and PLI Washer PART C −Repair of the Bushing F. If bushing 85410265 − 105 is installed and bushing 85410265 − 103 is not readily available, then do the repair, as follows: Refer to Figure 4 (1) Fabricate the bushing C415 − 3902 − 001 and rework as per PSP 297, Chapter 51, REPAIR MATERIALS −STANDARD PRACTICES. (a) Material is 4130 BAR, AMS − S − 6758, heat treat to 125 − 145 KSI per MIL− H − 6875. (b) Finish is cadmium plate per QQ − P − 416 Class 1, Type II. (c) Required Dimension is .220 ±.010. (d) The inside diameter is to be parallel and concentric with the outside diameter within .0005 total indicator reading. (e) Break sharp edges .005” to .015”. (f) Do a magnetic particle inspection as per ASTM − E1444, PSP 296 Part 7. (g) The surface texture to be 125RHR per ANSI/ASME B46.1. (h) Identify (ink stamp) as per PSP 297, Chapter 51, IDENTIFICATION OF REPAIR PARTS AND ASSEMBLIES. (2) Install bushing C415 − 3902 − 001 wet and transition fit per PSP 298, Chapter 20 − 53 − 00, PLAIN BUSHING −ASSEMBLY. (3) Continue with PART A −cont’d, Installation of Bolt and PLI WasherMODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A3173 April 11/12 Page 7 of 14 ATA Ref: 54-10 PART A −cont’d G. Installation of Bolt and PLI Washer Refer to Figure 2 and PSP 392, Maintenance Manual, Chapter 54, STRUT MOUNTS − REMOVAL/INSTALLATION, Upper Strut −Installation. (1) Coat the bolt 81812 − 8 − 30 with Mastinox 6856H. (2) Install the countersunk washer and the bolt. (3) Before fitting the PLI washers, determine the necessary gap for the correct pre-load for each PLI washer as follows: NOTE : If the bolt and bushing have not been replaced or repaired, then use the retained washer, if applicable, that was removed as part of the PLI washer assembly. (a) For PLI washer, measure and establish the required gap as follows: 1 Measure the protrusion of the shank of bolt 81812 − 8 − 30. 2 If protrusion is more than 0.21 inch (5,33 millimetres), add an MS 20002-8 washer between the PLI washer and the nut. (4) Install the PLI washer assembly and nut, then do as follows: Refer to Figure 3 (a) Tighten the nut until the outer washer of the PLI washer is against the inner centre ring with the outer center ring remaining loose. (b) Insert the shank of a drill into one of the test holes in the outer centre ring. (c) Rotate the outer center ring back and forth while tightening the nut or the bolt. (d) When the outer centre ring binds between the outer washers and can no longer rotate, stop tightening. Do not over tighten. The bolt has reached its required pre-load. (e) Check for gaps between the outer centre ring and both outer washers. A gap of 0.010 inch (0,25 millimetre) maximum at one of the outer washers or a combined total of 0.010 inch (0,25 millimetre) for both sides is acceptable. (f) If the slots in the castellated nut do not align sufficiently with either of the holes in the bolt to install the cotter pin, tighten the nut to align with the nearest hole. Do not tighten more than this. (g) Check at nuts that bolt threads are in safety. Refer to PSP 292, Maintenance Manual, Chapter 20. NOTE : If for any reason, the nut is backed off after the PLI washer assembly has been compressed, replace the PLI washer assembly. The PLI washer assembly is not re-usable.MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A3173 April 11/12 Page 8 of 14 ATA Ref: 54-10 (5) Safety the nut with the cotter pin. (6) Torque stripe the heads and tails of bolts, nuts, and washers with a 1/8 inch witness mark which extends onto the adjacent structure. Refer to PSP 292, Maintenance Manual, Chapter 20. (7) Apply a coat of Mastinox 6856H to heads and tails of bolt assemblies. H. Completion (1) Gently release hoist and remove engine lifting brackets. (2) On LH nacelle, install access panels 120 − 1, 120 − 2, 120 − 3, 120 − 4, 120 − 5 and 140 − 1 as per PSP 392, Maintenance Manual, Chapter 6, ENGINE NACELLES −ACCESS PANELS. (3) On RH nacelle, install access panels 220 − 1, 220 − 2, 220 − 3, 220 − 4, 220 − 5 and 240 − 1 as per PSP 392, Maintenance Manual, Chapter 6, ENGINE NACELLES −ACCESS PANELS. (4) Install lower cowl panel assembly and forward upper cowl panel assembly, as per PSP 392, Maintenance Manual, Chapter 71, POWER PLANT −ENGINE COWLING − MAINTENANCE PRACTICES. WARNING : ENSURE PERSONNEL AND EQUIPMENT ARE CLEAR OF ALL HYDRAULICALLY OPERATED SYSTEMS PRIOR TO RESTORING AIRCRAFT ELECTRICAL POWER. (5) Restore electrical power and observe all safety precautions (refer to PSP 392, Maintenance Manual, Chapter 24, ELECTRICAL POWER −MAINTENANCE PRACTICES). I. Recording When this Service Bulletin is completed, make the entry in the aircraft log book and send back the attached Incorporation Notice to Amphibious Aircraft Technical Publications.MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A3173 April 11/12 Page 9 of 14 ATA Ref: 54-10 3. Material Information A. Kit No. 215K3173 −Parts List PART NO. QUANTITY DESCRIPTION PLI − 8 − 19.6 4 PLI washer B. The following materials, or equivalent, are necessary to do this Service Bulletin. You can buy them locally: DESCRIPTION PART NO./NAME SPECIFICATION QUANTITY High Temp. Grease MIL − G − 25013 A/R White lacquer TT − L − 32 Fed. Std 595 Colour 17875 A/R Sealing Compound Mastinox 6856H A/R Scotchbrite No. 400 A/RMODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A3173 April 11/12 Page 10 of 14 ATA Ref: 54-10 ZERO WEIGHT CONDITION OF NACELLE FIGURE 1.2 ENGINE HOISTING POINTS ENGINE HOISTING POINTS OVERHEAD HOIST DYNAMOMETER OR LOAD CELL

ZERO WEIGHT CONDITION IS WHEN INDICATED READING (in LBS)=W+X 50 (in LBS) +

− Where, ”W” is approximate weight of the engine (in lbs). = 1500 ”X” is weight of the engine sling assembly before setup (in lbs). NOTE Use this method if engine is not to be removed. ENGINE HOISTING POINTS ENGINE HOISTING POINTS NOTE Use this method if removing the engine is required. ENGINE REMOVAL FIGURE 1.1 TRONAIR ENGINE HOIST AND SLING 08 − 0116 − 5000 OR EQUIVALENT

TRONAIR ENGINE SLING 08 − 0112 − 4000 OR EQUIVALENTMODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A3173 April 11/12 Page 11 of 14 ATA Ref: 54-10 INSPECTION OF THE BUSHINGS IN THE NACELLE STRUT ASSEMBLIES FIGURE 2 OUTBOARD ON LH NACELLE SHOWN INBOARD ON LH NACELLE OPPOSITE 215T16534 − 2 (SUPPORT STRUT) (REF) ACCESS BOLT AND BUSHING THROUGH THIS AREAMODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A3173 April 11/12 Page 12 of 14 ATA Ref: 54-10 INSPECTION OF THE BUSHINGS IN THE NACELLE STRUT ASSEMBLIES FIGURE 2 NOTE Disassembled view of Bushing is shown for clarity, do not remove from assembly.

A

A (in.) PART NUMBER 0.040 +/−0.010 85410265 − 103 0.260 +/−0.010 85410265 − 105 215T16533 (SLOPING LONGERON) (REF) 215T16534 − 12 (FORK END) (REF)

GAP ”A” −PART NUMBER CORRESPONDENCE 1

85410265 − 103/85410265 − 105 (SHEAR BUSHING) 81812 − 8 − 30 (BOLT) MS20002C8 (WASHER)

MS24665 − 306 (COTTER PIN) 85410265 − 103/85410265 − 105 (SHEAR BUSHING) 1

DSC 370/881811 − 820 (NUT)

PLI − 8 − 19.6 (WASHER)MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A3173 April 11/12 Page 13 of 14 ATA Ref: 54-10 BEFORE TIGHTENING AFTER TIGHTENING

AT HORSE COLLAR AND SLOPING LONGERON AT LOWER LONGERON PRELOAD INDICATING WASHERS Washer assembly comprises two concentric steel rings sandwiched between two close tolerance plain steel washers. The PLI − 8 − 19.6 washer has its center ring coloured blue (180 KSI), a 1/2 − inch internal diameter, and 19,600 LBS nominal preload.

GAP MEASUREMENT NOTE 1 2 OUTER WASHERS INNER CENTRE RING OUTER CENTRE RING BOLT NUT TEST HOLE (3 PLACES)

STRUT BOLT COUNTERSUNK WASHER BUSHING 0.25 INCH (6,3 MM) MAXIMUM BUSHING

0.21 INCH (5,3 MM) MAXIMUM STRUT

FIGURE 3MODEL CL-215-6B11 ALERT SERVICE BULLETIN

Service Bulletin 215-A3173 April 11/12 Page 14 of 14 ATA Ref: 54-10 BUSHING C415 − 3901 − 001 DETAILS USED IN REPAIR FIGURE 4 0.220 in.

DIA 0.500 in. DIA 0.505 in. DIA 0.6875 in. DIA 0.6885 in.

0.015 in.x45 0 CHAMFER 4 PLACES

4130 BAR, AMS − S − 6758, HEAT TREAT TO 125 − 145 KSI PER MIL− H − 6875 BUSHING C415 − 3902 − 001 1 MATERIAL SPECIFICATION DESCRIPTION NUMBER SL. NO REPAIR MATERIAL TABLE

215T16533 (SLOPING LONGERON) (REF) 215T16534 − 12 (FORK END) (REF) C415 − 3902 − 001 (BUSHING)

85410265 − 105 (SHEAR BUSHING) AFTER REPAIR NOTE 1 Use bushing C415 − 3902 − 001 with shear bushing 85410265 − 105 to maintain the gap of 0.040 +/−0.010 in. 1 BUSHING C415 − 3902 − 001 +/−0.010 in.

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