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 name. 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 by the Continuing Airworthiness Division (AARDG), National Aircraft Certification Branch, Transport Canada, Ottawa, telephone 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 Communications 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 

24-0022 (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 Directive (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 attributed to stress corrosion cracking. 

Failure of the bolts could compromise the structural 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 rectification, 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 less 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-fuselage strut attachment joint bolts in 

accordance with the Accomplishment Instructions 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 requirements, 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 reference 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 (DVI) 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 instructions 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 Toronto Help Desk for a Transport Canada

approved repair. The approved repair must specifically reference this AD. 

Compliance in accordance with the Initial Issue of SB 8-57-47, dated 16 March 2012, 

prior to the effective date of this AD, also 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 Airworthiness, Ottawa, telephone 613-952-4357, facsimile 

613-996-9178 or e-mail AD-CN@tc.gc.ca or any Transport Canada Centre.