Transport Transports Canada Canada TP 7245E



# AIRWORTHINESS DIRECTIVE

The following airworthiness directive (AD) may be applicable to an aircraft which our records indicate is registered in your na me. ADs are issued pursuant to Canadian Aviation Regulation (CAR) 521 Division X . Pursuant to CAR 605.84 and the further details of CAR Standard 625, Appendix H , the continuing airworthiness of a Canadian registered aircraft is contingent upon compliance with all applicable ADs. Failure to comply with the requirements of an AD may invalidate the flight authorization of the aircraft. Alternative means of compliance shall be applied for in accordance with CAR 605.84 and the above-referenced Standard

. This AD has been issued b y the Continuin g Airworthiness Division ( AARDG ) , National Aircraft Certification Branch, Trans p ort Canada, Ottawa, tele p hone 613 952-4357.

Pursuant to CAR 202.51 the registered owner of a Canadian aircraft shall, within seven days, notify the Minister in writing of any change of his or her name or address. To request a change of address, contact the Civil Aviation Communica tions Centre (AARC) at Place de Ville, Ottawa, Ontario K1A 0N8 , or 1-800-305-2059 , or www.tc.gc.ca/civilaviation/communications/centre/ address.asp
2 4-0022 ( 01-2005 ) 1/2 No

. CF-2013-17R1 Issue Date 27 June 2013

Number: CF-2013-17R1 Subject: Fractured Wing-to-Fuselage Strut Attachment Joint Bolt Effective: 5 July 2013 Revision: Supersedes Airworthiness Directiv e (AD) CF-2013-17, issued 21 June 2013. Applicability: Bombardier Inc. model DHC-8-102, - 103, -106, -201, -202, -301, -311, -314 and -315 aeroplanes, serial numbers 003 through 672. Compliance: As indicated below, unless already accomplished. Background: There have been two in-service reports of a wing-to-fuselage strut attachment joint bolt found fractured during routine maintenance. Laboratory examination of one fractured bolt revealed that the fracture was attr ibuted to stress corrosion cracking. Failure of the bolts could compromise the stru ctural integrity of the wing-to-fuselage strut attachment joint and could lead to a subsequent loss of the wing. This AD mandates the inspection and rectificat ion, as required, of the wing-to-fuselage strut attachment joint bolts and associated hardware. Revision 1 of this AD is issued to correct the Service Bulletin Number, Corrective Actions: A. In accordance with the following schedule:
1. For aeroplanes that have accumulated le ss than 40 000 total flight cycles, or less than 15 years in service since new, as of the effective date of this AD: prior to reaching 42 000 total flight cycles, or 16 years in service since new, whichever occurs first;
2. For aeroplanes that have accumulated 40 000 total flight cycles or more, or 15 years or more in service since new, as of the effective date of this AD: within 2000 flight cycles or 12 months, whichever occurs first, from the effective date of this AD.
B. Perform a torque check of all wing-to-f uselage strut attachment joint bolts in accordance with the Accomplishment Inst ructions in the Bombardier Service Bulletin (SB) 8-57-47, Revision A, dated 29 May 2013, or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada.
1. If all bolts meet the torque check requi rements, proceed to Part C of this AD.No. N ° CF-2013-17R1 2/2

2. If more than one bolt fails the torque check, before further flight, contact the Bombardier Toronto Help Desk for a Transport Canada approved repair. The approved repair must specifically referenc e this AD. Proceed to Part C of this AD.
3. If only one bolt fails the torque check, proceed to Part C of this AD. C. Perform a Detailed Visual Inspection (D VI) of each wing-to-fuselage strut attachment joint bolt, associated hardware and the bolt- hole bore, and rectify as required, in accordance with the accomplishment in structions of the above-mentioned SB. During the DVI, if corrosion or damage is found in a bolt-hole bore, before further flight, contact the Bombardier To ronto Help Desk for a Transport Canada approved repair. The approved repair must specifically refe rence this AD. Compliance in accordance with the Initia l Issue of SB 8-57-47, dated 16 March 2012, prior to the effective date of this AD, al so satisfies the requirements of this AD. Authorization: For the Minister of Transport, Infrastructure and Communities, ORIGINAL SIGNED BY Derek Ferguson Chief, Continuing Airworthiness Contact: Robert Farinas, Continuing Airworthine ss, Ottawa, telephone 613-952-4357, facsimile 613-996-9178 or e-mail AD-CN@tc.gc.ca or any Transport Canada Centre.