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 Communicat ions 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-2013-39 Issue Date 6 December 2013

Number: CF-2013-39 Subject: Inboard Flap Hinge Box – Missing F astener Head on Forward Attachment Fitting
Effective: 20 December 2013 Applicability: Bombardier Inc.: Model CL-600-1A11 (600) aeroplanes, serial numbers 1004 through 1085; Model CL-600-2A12 (601 Variant) aeroplanes, serial numbers 3001 through 3066; Model CL-600-2B16 (601-3A/3R Variant) aeroplanes, serial numbers 5001 through 5194; Model CL-600-2B16 (604 Variant) aeroplanes, serial numbers 5301 through 5665 and 5701 through 5920. Compliance: As indicated below, unless already accomplished. Background: There have been two in-service reports of a fractured fastener head, on the inboard flap hinge-box forward fitting at Wing Station (WS ) 76.50, found during a routine maintenance inspection. Investigation revealed that the installation of these fasteners on the inboard flap hinge-box forward fittings at WS 76.50 and WS 127.25, on both wings, does not conform to the engineering drawings. Incorrect in stallation may result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting. Failure of the fasteners could lead to the detachment of the flap hinge box and consequently the detachment of the flap surface. The loss of a flap surface could adversely affect the continued safe operation of the aeroplane.
This AD mandates a detailed visual ins pection (DVI) of each inboard flap hinge-box forward fitting, on both wings, and rectification as required. Incorrectly oriented fasteners require repetitive inspections until the terminating action is accomplished.
Corrective Actions: A. Within 100 flight cycles from the effect ive date of this AD, perform a DVI of each inboard flap fastener of the hinge-box forw ard fitting at WS 76.50 and WS 127.25, on both wings, in accordance with the Accomp lishment Instructions of the applicable Bombardier Alert Service Bulletin (ASB) lis ted below, or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada:

Aeroplane Serial Numbers ASB Issue Date 1004 through 1085 A600-0763 26-Sep 2013 3001 through 3066 5001 through 5194 A601-0627 26-Sep 2013
5301 through 5665 A604-57-006 Revision 1 26-Sep 2013 5701 through 5920 A605-57-004 Revision 1 26-Sep 2013No. N ° CF-2013-39 2/2

1. If all fasteners are found intact and co rrectly oriented, no further action is required; compliance with this AD is complete.
2. If a fastener is found fractured, before further flight, remove and replace the fractured fastener and all incorrectly oriented forward and aft fasteners at WS 76.50 & WS 127.25, on both wings, in accordance with the applicable above-mentioned ASB. Compliance wi th this AD is complete.
3. If a fastener is incorrectly oriented but intact, repeat the inspections required in paragraph B of this AD until the terminating action in paragraph C is accomplished.
B. Subsequently, at intervals not to exceed 100 flight cycles, repeat the DVI specified in paragraph A of this AD until paragraph C of this AD is accomplished.
C. Within 48 months from the effective date of this AD, remove and replace all incorrectly oriented forward and aft fa steners at WS 76.50 & WS 127.25, on both wings, in accordance with the applicable above-mentioned ASB. Replacement of all incorrectly orient ed forward and aft fasteners at WS 76.50 & WS 127.25, on both wings, in accordance with the applicable above-mentioned ASB, constitutes terminating action to this AD.
Authorization: For the Minister of Transport,
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.