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Page 1 of 2 ATA Ref. 57-51 09-Dec-2019 Service Bulletin V6/0066
REVISION TRANSMITTAL SHEET
AILERON STRUCTURE INSPECTION Service Bulletin No.: V6/0066 Date of Original Issue: 29 August 2019 Revision No: A Date of Issue: 09 December 2019 This Service Bulletin is issued for a one time visual inspection of all the aileron internal structure using a borescope.
NOTE 1: NO ACTION IS REQUIRED ON AIRCRAFT INSPECTED TO THE PREVIOUS ISSUE OF THIS SERVICE BULLETIN.
NOTE 2: This revision introduces threshold flight hours/cycles/calendar time for the Service Bulletin effectivity.
NOTE 3: This revision supersedes the previous revision of this Service Bulletin.
NOTE 4: Revision bars in the left margin of this Service Bulletin indicate changes from the previous revision.
This page transmits Revision ‘A’ of Service Bulletin V6/0066, pages 1 thru 8, dated 09 December 2019.
This Service Bulletin is re-issued to:
1. Establish threshold flight hours or cycles or calendar time for inspection.
2. Clarification that all aileron ribs are to be inspected, including end ribs.
3. Add inspection of all the aileron internal structure.
Remove Service Bulletin V6/0066 Revision ‘NC’ dated 29 August 2019 and replace with attached.
Previous issues of Service Bulletin V6/0066:
Initial Issue – Pages 1 thru 6 dated 29 August 2019
Page 2 of 2 ATA Ref. 57-51 09-Dec-2019 Service Bulletin V6/0066
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1959 de Havilland Way Sidney, B.C.
Canada V8L 5V5 Tel: (250) 656 - 7227 09-Dec-2019 S.B. V6/0066 Revision ‘A’ Page 1 of 8 DHC-6
TWIN OTTER
SERVICE BULLETIN ATA SYSTEM: 57-51 NUMBER: V6/0066 I. PLANNING INFORMATION A. Effectivity Aircraft Affected: All DHC-6 Twin Otters, All Series.
NOTE: This Service Bulletin is only applicable to ailerons having accumulated 16,000 flight hours or more, or 32,000 flight cycles or more, or 10 calendar years or more (whichever occurs first).
B. Reason Cracks and corrosion have been found on the internal aileron structure. This Service Bulletin is issued for a one time visual inspection of the entire aileron internal structure using a borescope.
C. Description Aileron structure is inspected via borescope through existing drain holes in the lower skin.
D. Compliance NOTE: If Service Bulletin V6/0066 Revision ‘NC’ has already been accomplished, Revision ‘A’ of Service Bulletin V6/0066 is considered to be complied with.
Operators shall accomplish the required inspections of this Service Bulletin within six (6) months from the issue date of this Service Bulletin.
If any part is found cracked, damaged or discrepant, it shall be repaired or replaced before next flight.
E. Approval The technical content of this Service Bulletin has been approved under the authority of Transport Canada Civil Aviation (TCCA) Design Approval Organization (DAO) 04-V-02.
F. Labour Requirements Estimated time to accomplish this Service Bulletin is 3 hours.
G. Weight and Balance Not affected.
SUBJECT: AILERON STRUCTURE INSPECTION
SERVICE BULLETIN V6/0066 09-Dec-2019 S.B. V6/0066 Revision ‘A’ Page 2 of 8 H. Electrical Load Data Not affected.
I. Publications Affected None J. References PSM 1-6-3 Structural Repair Manual PSM 1-6-3RS Structural Repair Schemes Manual For more information please contact:
Viking Air Limited 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 dh_technical.support@vikingair.com II. ACCOMPLISHMENT INSTRUCTIONS A. Aileron Structure Inspection Visual inspection of the entire aileron internal structure, including front and rear spars, all aileron ribs (including end ribs and both sides of hinge arms), and upper and lower skins.
Visual inspection to be done with a borescope, inserted through existing drain holes in the lower skin. Refer to Figure 2 for example of cracks in the rib radius; and Figure 3 for example of crack in the forward spar.
1. Equipment Flexible borescope with:
x Suitable size borescope head;
x 10X Magnification;
x Illumination;
x Optional: capability to record digital images.
2. Inspection Procedure
a) Using a flexible borescope through existing drain holes, visually inspect the entire LH aileron internal structure, and upper and lower skins, for cracks, creases or buckling, corrosion, missing/smoking/working/broken fasteners, or other defects, along the length of the LH aileron assembly from aileron inboard end to outboard end.
b) Visually inspect between the leading edge and the front spar, between the front spar and rear spar, and between the rear spar and the trailing edge.
c) Pay attention to the following areas for corrosion and cracks:
x Fastener holes at all joints (e.g., skin to spar/rib flange joints, aileron hinge to spar/rib joints, trim tab hinge flange to skin/rear spar joints, joints on stiffeners, clips, brackets, straps, doublers, etc.);
SERVICE BULLETIN V6/0066 09-Dec-2019 S.B. V6/0066 Revision ‘A’ Page 3 of 8 x Spar/rib/stiffener flanges at edge of fastener heads or edge of washers/nuts (including anchor nuts); Refer to Figure 3 for example crack at a fastener hole in the aileron forward spar flange;
x Open holes, tooling holes, drain holes, access cut-outs, and lightening holes;
x Aileron lower skin at rib/spar attachments (both forward and aft of spars) for corrosion;
x Spar/rib/stiffener along bending/joggle radius. Refer to Figure 2 for example of cracks in the aileron rib radius.
d) Repeat inspection for the RH Aileron Assembly.
e) If any part is found damaged, replace or repair in accordance with an approved repair scheme.
3. Operate ailerons and check for full and free range of movement.
4. Complete attached Inspection Reply Form on Page 7 and return to Viking Technical Support within 30 days from date of the inspection.
B. Recording After completion of this Service Bulletin, make the following entry in the aircraft log book:
“Service Bulletin No. V6/0066 Revision ‘A’ – AILERON STRUCTURE INSPECTION has been incorporated”.
III. MATERIAL INFORMATION AND TOOLING A. Material Information (Parts Required Per Aircraft) As required (On Condition) B. Tooling – Price and Availability Refer to Section II.A.1.
SERVICE BULLETIN V6/0066 Figure 1: Aileron Structure Inspection 09-Dec-2019 S.B. V6/0066 Revision 'A' Page 4 of 8
SERVICE BULLETIN V6/0066 09-Dec-2019 S.B. V6/0066 Revision ‘A’ Page 5 of 8 Figure 2: Example of Crack in Aileron Rib Radius
SERVICE BULLETIN V6/0066 09-Dec-2019 S.B. V6/0066 Revision ‘A’ Page 6 of 8 Figure 3: Example of Crack in Aileron Forward Spar Crack (visible from other side using borescope) VIEW LOOKING OUTBOARD (end rib removed for repairs) Vertical Flange of Inboard Aileron Forward Spar
SERVICE BULLETIN V6/0066 09-Dec-2019 S.B. V6/0066 Revision ‘A’ Page 7 of 8 Service Bulletin V6/0066 Revision A – Inspection Reply Form Operator: Date of Inspection:
Contact Person:
Contact Phone/Email:
A/C Registration # A/C Serial #
A/C TTSN A/C TCSN L/H Aileron Part # L/H Aileron Serial # Any previous repairs to L/H Aileron structure? YES / NO R/H Aileron Part # R/H Aileron Serial # Any previous repairs to R/H Aileron structure? YES / NO Details of Previous Repairs (if any):
Inspection Findings (Prior to Corrective Actions):
Corrective Actions:
Please return form via email to dh_technical.support@vikingair.comor via fax to 403-295-8888
SERVICE BULLETIN V6/0066 09-Dec-2019 S.B. V6/0066 Revision ‘A’ Page 8 of 8
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