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

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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

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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

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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

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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

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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 Washer
MODEL CL-215-6B11

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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

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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

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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/R
MODEL CL-215-6B11

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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 EQUIVALENT
MODEL CL-215-6B11

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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 AREA
MODEL CL-215-6B11

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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

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Service Bulletin 215-A3173

April 11/12

Page 13 of 14

ATA Ref: 54-10

BEFORE TIGHTENING AFTER TIGHTENING

AT HORSE COLLAR AND

AT LOWER LONGERON SLOPING 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 3
MODEL CL-215-6B11

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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.x450

CHAMFER 4 PLACES

1 C415−3902−001 BUSHING 4130 BAR, AMS−S−6758, HEAT TREAT TO 125−145 KSI PER MIL−H−6875

SL. NO NUMBER DESCRIPTION MATERIAL SPECIFICATION

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.
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

Specialized &

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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