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MODEL CL-215-1A10
MODEL CL-215-6B11 Page 1 of 2 ATA Ref. 57-30 Rev NC 11-DEC.-2015 Service Bulletin 215-A568 Rev 4 22-JAN.-2019
REVISION TRANSMITTAL SHEET
ALERT SERVICE BULLETIN 215−A568
WINGS
INSPECTION OF WING AND FUSELAGE ATTACHMENT STRUCTURES AT WING ROOT AREA
FOR CRACKS
Service Bulletin No.: 215−A568 Date of Original Issue: 11-Dec-2015 Revision No.: 4 Date of Issue: 22-Jan-2019
NOTES: 1. For aircraft that complied with Revision 3 (or earlier) of this Service Bulletin (SB), it is required to do the following:
a. Inspect additional locations and fastener holes (identified in Revision 4 of this SB, in accordance with applicable instructions in Section II.A);
b. Replace the installed NAS1242AD rivets (on the drag angles specified in previous Revisions of this SB) with Titanium Hi-Lite fasteners in accordance with Section II.B (Revision 4 of this SB, one-time);
c. Report existing standard SRM (Structural Repair Manual) and nonstandard repairs incorporated on wing box structures between WS 355L and WS 355R in accordance with Section II.C (Revision 4 of this SB, onetime). Note that replacement of damaged wing box primary structural member is considered as a “repair”.
2. This Revision supersedes Revision 3 of this SB.
3. Black bars in the left hand (LH) margin of this Service Bulletin and the details on this Revision Transmittal Sheet describe changes made since the previous issue.
Page 2 of 2 ATA Ref. 57-30 Rev NC 11-DEC.-2015 Service Bulletin 215-A568 Rev 4 22-JAN.-2019
This Service Bulletin is re-issued to:
1. Revise Section I.A Compliance to include total Water Drops (WD) and Total Operation Cycles (TOC) in addition to the existing Flight Hours (FH). Note that TOC = WD + water landings (non-water scooping/dropping operations) + Land Landings (LL).
2. Specify initial/repeat inspections, compliance time and additional inspections in Section I.A and II.A.
3. Change the installed NAS1242AD rivets (on the drag angle specified in previous Revisions of this SB) to Titanium Hi-Lite fasteners as specified in Section II.B.
4. Require supporting the entire wing weight before removing fasteners from drag angles and fuselage attachment frames in Section II.A and II.B.
5. Revise Section II.A to specify additional inspections of the drag angles and wing front/rear spar at vertical fuselage attachment frames. Further, the drag angles may be left in situ if no preventative REO or modification is to be installed and if the drag angle flange does not interfere with the hole probe while carrying out the fastener hole eddy current inspection, provided there is no crack found on the wing lower skin.
6. Add Section II.C to identify and report existing standard SRM and non-standard repairs of other than Allowable Damage installed on wing box structures between WS 355L and WS 355R, on aircraft with (or more than) 7500 FH, or 10000 WD, or 12000 TOC, whichever occurs first.
7. Revise Section III (Material Information) to remove Ultrasonic inspection equipment and add new fasteners.
MODEL CL-215-1A10
MODEL CL-215-6B11 Page 1 of 46 ATA Ref. 57-30 Rev NC 11-DEC.-2015 Service Bulletin 215-A568 Rev 4 22-JAN.-2019
ALERT SERVICE BULLETIN 215−A568
WINGS
INSPECTION OF WING AND FUSELAGE ATTACHMENT STRUCTURES AT WING ROOT AREA
FOR CRACKS I. Planning Information A. Compliance
The inspection described in Revision 4 of this Service Bulletin (SB) is mandatory and is applicable to all model CL-215-1A10 (CL-215) and Model CL-215-6B11 (CL-215T).
NOTES:
(1) This Service Bulletin is applicable only 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).
(2) Prior to incorporation of Revision 4 of this SB, 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 inspections or modifications and test procedures (if applicable) detailed in this SB.
(3) If standard SRM (Structural Repair Manual) or non-standard repairs were installed on wing lower skin or front/rear spar lower cap/web, or any of these parts were replaced, the structural configuration, fatigue crack prone location and/or the accumulated flight time (FH, WD or TOC) on the concerned components at the inspection areas as specified in Revision 4 of this SB would be changed. This condition may require an Alternative Means of Compliance (AMOC) against applicable ADs associated with Revision 4 of this SB and all other related SBs.
SPECIAL NOTICE CONCERNING COMPLIANCE
A TRANSPORT CANADA AIRWORTHINESS DIRECTIVE
MAY BE IMPOSED REGARDING THE CONTENT OF THIS SERVICE BULLETIN.
OTHER REGULATORY AUTHORITIES MAY TAKE SIMILAR ACTION.
CL-215 CL-215T
Page 2 of 46 ATA Ref. 57-30 Rev NC 11-DEC.-2015 Service Bulletin 215-A568 Rev 4 22-JAN.-2019 MODEL CL-215−1A10 MODEL CL-215-6B11
ALERT SERVICE BULLETIN Contact Viking Air Ltd. (VAL) Technical Support for further inspection instructions to support AMOC application to local airworthiness authority, as required. Provide repair/replacement details, as listed in Section II.C, when contacting VAL Technical Support.
1. Initial inspection threshold (see Table 1): within 7500 Flight Hours (FH), or 10,000 Water Drops (WD), or 12,000 Total Operation Cycles (TOC = water drops + water landings of non-water scooping/dropping operations + land landings), whichever occurs first.
Perform the initial inspection in accordance with Section II.A of this SB (Revision 4).
a. If cracks are found, before next flight, repair/replace damaged part(s) as necessary.
Contact VAL Technical Support for Repair Engineering Order (REO) and/or aircraft specific ICA (Instructions for Continuing Airworthiness) that defines future inspection requirements.
NOTE: The replacement and/or repair of the damaged parts (including wing lower skin, spar lower caps/webs) will change the structural configuration, fatigue crack prone location and/or the accumulated flight time (FH, WD or TOC) on the concerned components in the specified inspection areas. This condition may require an AMOC against applicable Airworthiness Directives (ADs) associated with Revision 4 of this SB and all other related SBs.
Contact VAL Technical Support for aircraft specific ICAs (defining future inspection requirements) to support AMOC application to local airworthiness authority, regardless if the damaged part(s) is (are) replaced or repaired per SRM or REO.
b. If no cracks are found:
(1) perform the repeat inspection in accordance with Para I.A.2 and Table 1 in Revision 4 of this SB; or
(2) alternatively, install preventative REO 215-57-V022 (Revision NC or later), then perform the new initial and repeat inspections of the lower skin and other components (aircraft specific) as specified in that REO, and perform the repeat inspection of locations and fastener holes shown in Figure 1 (Sheet 3 and 4 only), Revision 4 of this SB. Contact VAL Technical Support for REO 215-57-V022.
2. The repeat inspection intervals (see Table 1): thereafter the initial inspection and within every 3750 FH, or 5000 WD, or 6000 TOC, whichever occurs first. Perform the repeat inspection in accordance with Section II.A and Table 1 in Revision 4 of this SB.
a. If cracks are found, before next flight, repair/replace damaged part(s) as necessary.
Contact VAL Technical Support for REO and/or aircraft specific ICA that defines future inspection requirements.
NOTE: The replacement and/or repair of the damaged parts (including wing lower skin, spar lower caps/webs) will change the structural configuration, fatigue crack prone location and/or the accumulated flight time (FH, WD or TOC) on the concerned components in the specified inspection areas. This condition may require an AMOC against applicable ADs associated with Revision 4 of this SB and all other related SBs. Contact VAL Technical Support for aircraft specific ICAs (defining future inspection requirements)
CL-215 CL-215T
Page 3 of 46 ATA Ref. 57-30 Rev NC 11-DEC.-2015 Service Bulletin 215-A568 Rev 4 22-JAN.-2019 MODEL CL-215−1A10 MODEL CL-215-6B11
ALERT SERVICE BULLETIN to support AMOC application to local airworthiness authority, regardless if the damaged part(s) is (are) replaced or repaired per SRM or REO.
b. If no cracks are found:
(1) perform the repeat inspection in accordance with Section I.A.2 and Table 1 in Revision 4 of this SB; or
(2) alternatively install preventative REO 215-57-V022 (Revision NC or later), then, perform the new initial and repeat inspections of the lower skin and other components (aircraft specific) as specified in this REO, and perform the repeat inspection of locations and fastener holes shown in Figure 1 (Sheet 3 and 4 only), Revision 4 of this SB. Contact VAL Technical Support for REO 215-57-V022.
3. One-Time reporting of existing standard SRM and non-standard repairs (other than Allowable Damage) on wing box structures between WS 355L and WS 355R: on aircraft with (or more than) 7500 FH, or 10000 WD, or 12000 TOC, whichever occurs first. Note that replacement of damaged wing box primary structural member is considered as a “repair”.
4. Phase-in schedule of Initial Inspection applicable to aircraft without incorporation of Revision 3 (or earlier) of SB 215-A568 (see Table 2): per one of the following Paragraphs
a. to d. below, as applicable. The shortest compliance time among the following Paragraphs a. to d. shall apply if the accumulated aircraft flight times (FH, WD, TOC) meet multiple criteria:
a. Aircraft with (or more than) 7500 FH, or 22001 WD or 26401 TOC: within 4 months from the issuing date of SB 215-A568 (Revision 4).
b. Aircraft with 7500 FH or more, or 20001-22000 WD or 24001-26,400 TOC: within 8 months from the issuing date of SB 215-A568 (Revision 4).
c. Aircraft with 7500 FH or more, or 10000-20000 WD or 12000-24000 TOC: within 18 months from the issuing date of SB 215-A568 (Revision 4).
d. Aircraft with less than 7500 FH, and 10000 WD and 12000 TOC: at or before the Initial Inspection Threshold specified in Table 1 or within 18 months from the issuing date of SB 215-A568 (Revision 4), whichever occurs later.
5. Phase-in schedule of Initial Inspection applicable to aircraft complied with Revision 3 or earlier of SB 215-A568 (see Table 3): per one of the following Paragraphs a. to c. below, as applicable. The shortest compliance time in Paragraphs a. or b. below shall apply if the accumulated aircraft flight times (FH, WD, TOC) meet both criteria:
a. Aircraft with (or more than) 7500 FH, or 20001 WD or 24001 TOC: within 12 months from the issuing date of SB 215-A568 (Revision 4).
b. Aircraft with 7500 FH or more, or 10000 - 20000 WD or 12000 - 24000 TOC: within 18 months from the issuing date of SB 215-A568 (Revision 4).
c. Aircraft with less than 7500 FH, and 10000 WD and 12000 TOC: at or before the Initial Inspection Threshold specified in Table 1 or within 18 months from the issuing date of SB 215-A568 (Revision 4), whichever occurs later.
CL-215 CL-215T
Page 4 of 46 ATA Ref. 57-30 Rev NC 11-DEC.-2015 Service Bulletin 215-A568 Rev 4 22-JAN.-2019 MODEL CL-215−1A10 MODEL CL-215-6B11
ALERT SERVICE BULLETIN
d. At the “Initial Inspection” time, perform following actions:
(1) Change the installed NAS1242AD rivets on the drag angles (specified in Revision 3 or earlier Revisions of this SB) to Titanium Hi-Lite fasteners in accordance with Section II.B, Revision 4 of this SB. Note that this is a one-time replacement only and all rivet holes common to drag angles are to be re-inspected while changing NAS1242AD rivets.
(2) Perform the rest of the inspections identified in Section II.A, Revision 4 of this SB.
(3) Thereafter, perform future Repeat Inspections per Table 1 schedule.
6. Compliance time for reporting of existing repairs on wing box structure:
a. Within 30 days after accomplishing the Initial Inspection as specified in Paragraph I.A.4 and I.A.5 (Revision 4 of this SB), report existing standard SRM and nonstandard repairs incorporated on wing box structures between WS 355L and WS 355R in accordance with Section II.C, Revision 4 of this SB. Note that replacement of damaged wing box primary structural member is considered as a “repair”.
7. Within 30 days after incorporation of the Initial and each Repeat Inspection per this Revision 4, return the SB 215-A568 Reply Form (attached at the end of this SB) to VAL Technical Support via email to technical.support@vikingair.com or via fax to 1-403-295- 8888.
Table 1. Initial/Repeat Inspection Intervals and Reporting of Existing Repairs Description Flight Hours Water Drops Total Operation Cycles (1) Note Instruction Initial Inspection Threshold 7500 Or 10000 Or 12000 Whichever occurs first Per Section II.A Repeat Inspection (2) 3750 Or 5000 Or 6000 Whichever occurs first Per Section II.A Reporting of existing repairs on wing box (3) ≥7500 Or ≥10000 Or ≥12000 Whichever occurs first Per Section II.C
(1) Total Operation Cycles = water drops + water landings (non-water scooping/dropping operations) + land landings.
(2) Alternatively, if preventative REO 215-57-V022 (Revision NC or later) is installed, perform the new initial and repeat inspections specified in that REO, and perform the repeat inspection of the locations and fastener holes shown in Figure 1 (Sheet 3 and 4 only).
(3) Note that replacement of damaged wing box primary structural member is considered as a “repair”.
CL-215 CL-215T
Page 5 of 46 ATA Ref. 57-30 Rev NC 11-DEC.-2015 Service Bulletin 215-A568 Rev 4 22-JAN.-2019 MODEL CL-215−1A10 MODEL CL-215-6B11
ALERT SERVICE BULLETIN Table 2. Phase-in Schedule of the Initial Inspection (1) Flight Hours Water Drops Total Operation Cycles (2) Compliance Time Note ≥7500 Or ≥22001 Or ≥26401 Within 4 months (3)(4) Whichever results in the shortest compliance time (5) ≥7500 Or 20001 - 22000 Or 24001 - 26400 Within 8 months (3)(4) ≥7500 Or 10000 - 20000 Or 12000 - 24000 Within 18 months (3)(4) <7500 And <10000 And <12000 At or before Table 1 Initial Inspection Threshold or within 18 months (3)(4), whichever occurs later –
(1) Applicable to aircraft without incorporation of Revision 3 (or earlier) of SB 215-A568.
(2) Total Operation Cycles = water drops + water landings (non-water scooping/dropping operations) + land landings.
(3) From the issuing date of SB 215-A568 Revision 4 (flight hours, water drops, or total operation cycles are the accumulated numbers on the issuing date of SB 215-A568 Revision 4).
(4) If standard SRM or non-standard repairs were installed on wing lower skin or front/rear spar lower cap/web, or any of these parts were replaced in the inspection areas specified in Revision 4 of this SB, the structural configuration, fatigue crack prone location and/or the accumulated flight time (FH, WD, TOC) on the concerned component(s) would be changed. This condition may require an AMOC against applicable ADs associated with Revision 4 of this SB and all other related SBs.
Contact VAL Technical Support for further inspection instructions to support AMOC application to local airworthiness authority as required. Provide repair/replacement details as listed in Section II.C of this SB when contacting VAL Technical Support.
(5) The shortest compliance time shall apply if the accumulated aircraft flight times (FH, WD, TOC) meet multiple criteria.
Table 3. Phase-in Schedule of the Initial Inspection (1) Flight Hours Water Drops Total Operation Cycles (2) Compliance Time Note ≥7500 Or ≥ 20001 Or ≥ 24001 Within 12 months (3)(4)(5) Whichever results in the shortest compliance time (6) ≥7500 Or 10000 - 20000 Or 12000 - 24000 Within 18 months (3)(4)(5) <7500 And <10000 And <12000 At or before Table 1 Initial Inspection Threshold or within 18 months (3)(4)(5), whichever occurs later –
(1) Applicable to aircraft complied with Revision 3 (or earlier) of SB 215-A568.
(2) Total Operation Cycles = water drops + water landings (non-water scooping/dropping operations) + land landings.
(3) From the issuing date of SB 215-A568 Revision 4 (flight hours, water drops, or total operation cycles are the accumulated numbers on the issuing date of SB 215-A568 Revision 4).
(4) “Initial Inspection” includes following actions:
a. Change the NAS1242AD rivets from the drag angles (specified in previous Revisions of this SB) in accordance with Section II.B, Revision 4 of this SB. Note that this is a one-time replacement and the rivet holes common to drag angles are to be re-inspected while changing NAS1242AD rivets.
CL-215 CL-215T
Page 6 of 46 ATA Ref. 57-30 Rev NC 11-DEC.-2015 Service Bulletin 215-A568 Rev 4 22-JAN.-2019 MODEL CL-215−1A10 MODEL CL-215-6B11
ALERT SERVICE BULLETIN
b. Perform the rest of inspections identified in Section II.A (Revision 4 of this SB), then, perform the Repeat Inspection per Table 1 schedule thereafter.
(5) The same as Note (4) in Table 2.
(6) The shortest compliance time shall apply if the accumulated aircraft flight times (FH, WD, TOC) meet both criteria.
B. Approval The technical content of this Service Bulletin has been approved under the authority of the Transport Canada Civil Aviation (TCCA) Design Approval Organization No: DAO 04-V-02.
C. Effectivity Aircraft Validity: This Service Bulletin is valid for CL-215-1A10 (CL-215) Piston and CL-215-6B11 (CL-215T) turboprop Aircraft Serial No. 1001 to 1125.
Service Effectivity: This Service Bulletin is authorized for CL-215-1A10 (CL-215) Piston and CL-215-6B11 (CL-215T) turboprop Aircraft Serial No. 1001 to 1125.
D. Reason Multiple cracks were found in fastener holes in the wing lower skin common to the closing drag angles, located at WS 51.00 on the Left Hand (LH) and Right Hand (RH) sides. New inspection intervals and additional inspections are needed to maintain the continuing airworthiness of the aircraft. Service history indicates that the aircraft structural condition is more related to the total number of water drops and/or total operation cycles than flight hours. This is reflected in initial/repeat inspection intervals, Revision 4 of this SB.
Revision 4 of this SB also expands the scope of the inspections to include the drag angles and the wing front/rear spar to vertical fuselage attachment frame joints at wing root area.
This is to prevent long, and/or multiple cracks hidden on wing lower skin and spar web/cap being possibly missed by existing inspections at the wing root area. Also, if cracks are detected and rectified in earlier stages (on aircraft with less severe usage or less accumulated FH, WD or TOC), the associated repair could be much simpler and subsequent cracks that could occur on the mating components may be eliminated or postponed.
E. Description Within the compliance time and upon reaching the initial/repeat inspection intervals specified in Section I.A of SB 215-A568 Revision 4, perform Eddy Current fastener hole inspection with the drag angles removed (or in place if the drag angle flange does not interfere with the hole probe while carrying out the fastener hole eddy current inspection). A check for a gap condition which may exist between the drag angle and the wing lower skin is also required, before installation of the removed serviceable drag angles (or with serviceable drags in situ, if they are not removed).
Within the compliance time specified in Table 3, the NAS1242AD rivets from the drag angles (installed on aircraft complied to Revision 3 or earlier of this SB) need to be changed to Titanium Hi-Lite fasteners, in accordance with Section II.B, Revision 4 of this SB. The rivet holes common to the drag angles will be re-inspected when changing the rivets. At the same time, perform the rest of the inspection in accordance with applicable instructions in Section II.A, Revision 4 of this SB. Then, perform the Repeat Inspection per Table 1 thereafter.
CL-215 CL-215T
Page 7 of 46 ATA Ref. 57-30 Rev NC 11-DEC.-2015 Service Bulletin 215-A568 Rev 4 22-JAN.-2019 MODEL CL-215−1A10 MODEL CL-215-6B11
ALERT SERVICE BULLETIN To assess the overall wing structural conditions and specify further inspection of the wing box structures, it is needed to identify existing standard SRM and non-standard repairs of other than Allowable Damage (including replacements) installed on wing front/rear spar web, upper/lower caps, upper/lower skins, upper/lower stringer and ribs between WS 355L and WS 355R, with or without initial/repeat inspections specified.
Optional preventative REO is offered for installation on the wing lower skin at the initial or future repeat inspection time.
F. Manpower We estimate that it will take 2 technicians approximately 24 hours to complete the combination of eddy current and visual inspection described in this Service Bulletin.
G. Material Availability This Service Bulletin includes no kit.
H. Tool Availability The Eddy Current non-destructive testing equipment is commercially available. You will need to obtain the use of the following:
The fastener hole inspection requires the following equipment:
– Hocking Phasec 2200, Eddy Current−Instrument−Impedance−Plane Type, or equivalent – Hocking 33A100 Mini Drive Unit, or equivalent – Hocking 33A103, Cable−Mini Drive Unit, or equivalent – Calibration Reference Standard BH7475−T7351, or equivalent – Techna NDT HRY 0.125 to 0.156, rotating bolt − hole probe, 100 kHz − 2.0 MHz frequency, adjustable, 0.125 to 0.156−inch. adjustable diameter, 2.0−inch length, or equivalent – Techna NDT HRY 0.156 to 0.187, rotating bolt − hole probe, 100 kHz − 2.0 MHz frequency, adjustable, 0.156 to 0.187−inch. adjustable diameter, 2.0−inch length, or equivalent.
The Eddy Current surface scan inspection requires the following equipment:
– Hocking Phasec 2200, Eddy Current−Instrument−Impedance−Plane Type, or equivalent – Coaxial cable, BNC to Microdot – Calibration Reference Standard AL29−32, or equivalent – Techna NDT PEN45−6, 45° Surface probe, 50 kHz to 500 kHz frequency, Fe/NFe, absolute, shielded, 0.125−in. (3.175−mm) diameter, 6.0−in. (152.4−mm) length,
0.500−in (12.7 mm) drop, or equivalent I. Weight and Balance Not affected.
CL-215 CL-215T
Page 8 of 46 ATA Ref. 57-30 Rev NC 11-DEC.-2015 Service Bulletin 215-A568 Rev 4 22-JAN.-2019 MODEL CL-215−1A10 MODEL CL-215-6B11
ALERT SERVICE BULLETIN J. Electrical Load Data Not affected.
K. References None.
L. Publications Affected PSP 296, Non-Destructive Testing Manual, Part 1 General, 51−15−03 Eddy Current.
M. Related Service Bulletin None.
This Service Bulletin is self-contained. No drawings are supplied. For more information please contact:
Viking Air Limited (VAL) FAX: 403-295-8888 Technical Support Telephone Numbers:
7757 8th Street NE Regional: 587-430-0572 Calgary, Alberta North America: 1-800-663-8444 Canada, T2E 8A2 technical.support@vikingair.com
CL-215 CL-215T
Page 9 of 46 ATA Ref. 57-30 Rev NC 11-DEC.-2015 Service Bulletin 215-A568 Rev 4 22-JAN.-2019 MODEL CL-215−1A10 MODEL CL-215-6B11
ALERT SERVICE BULLETIN II. 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 information regarding Hi-Lite fasteners, refer to PSP 297, Structural Repair Manual, Chapter 51−43−19 HI-LITES − GENERAL PROCEDURES.
(3) For information regarding Hi-Lok fasteners, refer to PSP 297, Structural Repair Manual, Chapter 51−43−16 HI-LOKS − GENERAL PROCEDURES.
(4) For information regarding the removal and application of primer and paint, refer to PSP 297, Structural Repair Manual, Chapter 51−52−16 CORROSION PREVENTIVE TREATMENT − GENERAL PROCEDURES.
(5) For information regarding leveling of the aircraft:
For CL-215 aircraft, refer to PSP 292, Aircraft Maintenance Manual, Chapter 8−20−00 LEVELING − MAINTENANCE PRACTICES.
FOR CL-215T aircraft, refer to PSP 392, Aircraft Maintenance Manual, Chapter 8−10−00 LEVELING − MAINTENANCE PRACTICES.
(6) For information regarding the removal and installation of fuel cells:
For CL-215 aircraft, refer to PSP 292, Aircraft Maintenance Manual, Chapter 28−11−01 FUEL CELL − REMOVAL/INSTALLATION.
For CL-215T aircraft, refer to PSP 392, Aircraft Maintenance Manual, Chapter 28−11−01 FUEL CELL − REMOVAL/INSTALLATION.
(7) For information regarding the removal and installation of solid rivets, refer to PSP 297 Structural Repair Manual, Chapter 51−42−11 SOLID RIVETS − GENERAL PROCEDURES.
(8) For information regarding the application of sealants, refer to PSP 297 Structural Repair Manual, Chapter 51−55−00 SEALING − GENERAL PROCEDURES.
(9) For information regarding the application of repair reference markings to the aircraft, refer to PSP 297, Structural Repair Manual, Chapter 51−59−00 IDENTIFICATION OF REPAIR PARTS AND ASSEMBLIES.
(10) If standard SRM or non-standard repairs were installed on wing lower skin or front/rear spar lower cap/web, or any of these parts were replaced in the inspection areas specified in Revision 4 of this SB, the structural configuration, fatigue crack prone location and/or the accumulated flight time (FH, WD, TOC) on the concerned component(s) would be changed. This condition may require an AMOC against applicable ADs associated with Revision 4 of this SB and all other related SBs. Contact VAL Technical Support for further inspection instructions to support AMOC application to local airworthiness authority as required. Provide repair/replacement details as listed in Section II.C of this SB when contacting VAL Technical Support.
CL-215 CL-215T
Page 10 of 46 ATA Ref. 57-30 Rev NC 11-DEC.-2015 Service Bulletin 215-A568 Rev 4 22-JAN.-2019 MODEL CL-215−1A10 MODEL CL-215-6B11
ALERT SERVICE BULLETIN A. Combination Visual and Eddy Current Inspection Refer to Figure 1.
1. Prepare the aircraft for the visual and the eddy current inspection as follows. Support the entire wing weight (including engines, accessory components and fluid) by jacking up the wing with suitable cradles positioned at WS 91.2L/R and/or 212L/R under the ribs. This is to “zero-load” the wing to fuselage joints. Refer to applicable maintenance manuals for the wing weight (depending on the wing condition, it may be in the order of 22,500 lbs. with zero fuel).
a. Remove the LH and RH side No. 2 fuel cell.
For CL-215 Aircraft, refer to PSP 292 Chapter 28.
For CL-215T Aircraft, refer to PSP 392 Chapter 28.
b. B efore removing fasteners identified in Figure 1, check the fastener installation for abnormal conditions (missed, sheared, distorted, deformed or loose fastener heads/collar/nuts and corrosion).
U sing the inspection Reply Form provided with this Service Bulletin, record the results, taking note of the type and location of any damage indication. Submit all your findings to VAL Technical Support.
NOTE: A photographic record of the damage attached to the inspection Reply Form is highly recommended.
c. See Notes (1) to (3) below. Remove identified fasteners and the front and rear drag angles 215−30031 from both the LH and RH sides as shown in Figure 1 Sheet 1 and Sheet 2. Remove identified fasteners from the wing front and rear spar (on both the LH and RH sides) as shown in Figure 1 Sheet 3 and Sheet 4. Take care to avoid damaging the fastener holes prior to inspection. Refer to PSP 297, Chapter 51.
NOTES:
(1) On wings with Standard SRM or Non-Standard repairs (including REO) installed on wing lower skin or front/rear spar lower cap/web, or any of these parts were replaced in the inspection areas specified in Revision 4 of this SB, the structural configuration, fatigue crack prone location and/or the accumulated flight time (FH, WD or TOC) on the concerned components at the inspection areas as specified in Revision 4 of this SB would be changed. This condition may require an AMOC against applicable ADs associated with Revision 4 of this SB and all other related SBs. Contact Viking Air Ltd. (VAL) Technical Support for further inspection instructions to support AMOC application to local airworthiness authority, as required. Provide repair/replacement details as listed in Section II.C when contacting VAL Technical Support.
(2) If no preventative modification (or REO 215-57-V022) is to be installed and if the drag angle flange does not interfere with the hole probe while carrying out the fastener hole eddy current inspection, the drag angle may not need to be removed. I.e.: the fasteners on the vertical flange of the drag angles do not need to be removed between FS 388.86 and 434.836 (see Figure 1 Sheet 1), but the fasteners identified forward of FS 388.86 and aft of FS 434.836 still need to be removed to inspect the fastener holes.