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AD Number: CF-2013-39R2

Issue Date: 12 December 2014

EMERGENCY

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.

Number: CF-2013-39R2 Effective Date: 12 December 2014

ATA: 57 Type Certificate: A-131

Subject: Wings - Inboard Flap Hinge Box – Incorrectly Oriented (Hi-LOK/Hi-LITE) Fastener on 

Forward Attachment Fitting

Revision: Supersedes AD CF-2013-39R1, issued 15 August 2014, for CL-600-1A11 (600), 

CL-600-2A12 (601 Variant) and CL-600-2B16 (601-3A/-3R Variant) aeroplanes

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.

Compliance: As indicated below, unless already accomplished.

Background: There have been three in-service reports on 604 Variant aeroplanes 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 

installation 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.

The original issue of this AD mandated a detailed visual inspection (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. 

Although there have been no reported fractured fastener heads found to date on any 

model CL-600-1A11, -2A12 or -2B16 (601-3A-3R Variant) aeroplanes, incorrectly oriented 

fasteners may also be installed.

After the issuance of the original AD, there has been one reported incident on a 

604 Variant aeroplane where four fasteners were found fractured on the same flap hingebox forward fitting. The investigation determined that the fasteners were incorrectly 

installed.

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. 

For all changes to your mailing address, contact your TC Regional Aircraft Registration Office at 1-800-305-2059,

option 1 for English, 2 for Aircraft Registration and then select the appropriate region.

24-0022 (01-2005)
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Revision 1 of this AD was issued to remove the 604 Variant aeroplanes from the 

Applicability section since they were addressed in AD CF-2014-27 and to clarify 

paragraphs A.2. and C of this AD so that it matched the Bombardier Alert Service 

Bulletins.

After the issuance of Revision 1 of this AD, there have been several reports of incorrectly 

oriented fasteners found on CL-600-1A11, and -2B16 (601-3A Variant) aeroplanes. 

Although there have been no reports of fractured fasteners found to date, incorrectly 

oriented fasteners could result in the premature failure of the forward flap hinge-box 

fitting.

Revision 2 of this AD is issued to reduce the initial and repetitive inspection intervals and 

to impose replacement of the incorrectly oriented fasteners within 24 months. This AD

also corrects various terminology errors which were found in previous French versions of 

this AD.

Corrective Actions:

A. Within 10 flight cycles from the effective date of this AD, or within 100 flight cycles 

from the effective date of the original issue of this AD (20 December 2013), whichever 

occurs first, perform an initial DVI of each inboard flap fastener of the hinge-box 

forward fitting at WS 76.50 and WS 127.25, on both wings, in accordance with the 

Accomplishment Instructions of the applicable Bombardier Alert Service 

Bulletin (ASB) listed below, or later revisions approved by the Chief, Continuing 

Airworthiness, Transport Canada:

Aeroplane Serial Numbers ASB Issue Date

1004 through 1085 A600-0763 Revision 2 9 December 2014

3001 through 3066

5001 through 5194

A601-0627 Revision 2 9 December 2014

1. If all fasteners are found intact and correctly 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 forward and aft fasteners at WS 76.50 & WS 127.25, on 

both wings, in accordance with the applicable above-mentioned ASB. 

Compliance with 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.

Inspection and replacement of the fasteners, as required, in accordance with the 

Accomplishment Instructions in Bombardier ASBs A600-0763, Basic Issue or 

Revision 01, dated 26 September 2013 and 26 February 2014, respectively, or 

ASB A601-0627, Basic Issue or Revision 1, dated 26 September 2013 and 

26 February 2014, respectively, as applicable, prior to the Effective date of this AD, 

also meets the requirements of paragraph A of this AD.

B. Subsequently, repeat the DVI specified in paragraph A of this AD in accordance with 

the following schedule until paragraph C of this AD is accomplished:
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1. Within 10 flight cycles from the effective date of this AD or from the most recent 

inspection, whichever occurs later; and

2. Thereafter, at intervals not to exceed 10 flight cycles.

C. Within 24 months from the effective date of this AD, remove and replace all forward 

and aft fasteners at WS 76.50 & WS 127.25, on both wings, in accordance with the 

applicable above-mentioned ASBs.

Replacement of all forward and aft fasteners at WS 76.50 & WS 127.25, on both 

wings, in accordance with the applicable above-mentioned ASBs, constitutes 

terminating action to this AD.

Replacement of the fasteners in accordance with the Accomplishment Instructions in 

Bombardier ASBs A600-0763, Basic Issue or Revision 01, dated 26 September 2013 

and 26 February 2014, respectively, or ASB A601-0627, Basic Issue or Revision 1, 

dated 26 September 2013 and 26 February 2014, respectively, as applicable, prior to 

the Effective date of this AD, also meets the requirements of paragraph C of this AD.

Authorization: For the Minister of Transport, 

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.