Transport Transports 

Canada Canada

 TP 7245E

 

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.

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-2013-04

Issue Date 

 14 February 2013 

Number: CF-2013-04 

Subject: Cracking of Wing Lower Skin 

Effective: 14 February 2013 

Applicability: Kelowna Flightcraft Ltd. Convair models 340 and 440 aeroplanes, all serial 

numbers, including aeroplanes commonly referred to as models 580, 600, 640 and 

5800 powered by turboprop engines 

Compliance: As indicated below, unless already accomplished. 

Background: While performing a corrosion inspection of the wing internal structures, an operator 

discovered a crack of significant length between Wing Station (WS) 5 and 6, on the right 

hand wing lower skin of a Convair 580 aeroplane. Although an investigation is still 

ongoing to determine the cause, the crack appears to originate from a fastener located at 

the wing skin to wing access door doubler attachment. 

Previous repetitive external inspections of the wing lower skin in accordance with 

Structurally Significant Detail (SSD) 57-1-4, that was mandated by FAA AD 92-06-06, did 

not detect the crack because the location of the crack is covered by the nacelle drag 

angle. 

Cracking of the wing lower skin at a fatigue critical area, if not detected, could 

compromise the structural integrity of the wing. This AD mandates internal visual and 

eddy current inspections to detect cracking of the wing lower skin to mitigate this unsafe 

condition. Transport Canada may mandate additional corrective actions pending the 

outcome of the failure investigation and fleet findings. 

The visual and eddy current inspections mandated by this AD are considered as 

Alternative Means of Compliance (AMOC) to the SSD 57-1-4 inspection that was 

mandated by FAA AD 92-06-06, for the locations addressed by the visual and eddy 

current inspections. 

Corrective 

Actions: 

Part A – Visual Inspection 

1. Within 20 hours air time from the effective date of this AD, carry out a detailed visual 

inspection of the left hand (LH) and right hand (RH) wing lower skin for cracking 

around the inboard side of WS 6-7 access panel doubler fingers and between 

Stringers 5 and 11, in accordance with the Accomplishment Instructions of 

Kelowna Flightcraft Ltd. Convair Division Service Bulletin (SB) 340-57-001, 

dated 12 February 2013, or later revisions approved by the Chief, Continuing 

Airworthiness, Transport Canada. 
No.

N° CF-2013-04 2/2 

2. If any crack is found, contact Kelowna Flightcraft Ltd. Convair Division for a 

Transport Canada approved repair and carry out the repair prior to further flight. 

Part B – Eddy Current Inspection 

1. Within 100 hours air time from the effective date of this AD, carry out an eddy current 

inspection of the LH and RH wing lower skin for cracking around Stringers 6, 8 and 

10 and around the WS 6-7 access panel doubler fingers, in accordance with the 

Accomplishment Instructions of Kelowna Flightcraft Ltd. Convair Division SB 340-57-

001, dated 12 February 2013, or later revisions approved by the Chief, Continuing 

Airworthiness, Transport Canada. 

2. If any crack is found, contact Kelowna Flightcraft Ltd. Convair Division for a 

Transport Canada approved repair and carry out the repair prior to further flight. 

Part C – Repetitive Inspection 

Repeat the inspections of Part A and Part B above at intervals not exceeding 1000 hours 

air time. For operators with a Damage Rate Factor (DRF), a repetitive inspection interval 

not exceeding 1000 hours air time divided by the DRF must be used. 

Part D – Defect Reporting 

No later than 30 days after each inspection in accordance with Part A, Part B or Part C 

above, report all crack findings (positive or negative) to Kelowna Flightcraft 

Convair Division, in accordance with the Accomplishment Instructions of Kelowna 

Flightcraft Ltd. Convair Division SB 340-57-001, dated 12 February 2013, or later 

revisions approved by the Chief, Continuing Airworthiness, Transport Canada. 

Part E – Alternative Means of Compliance (AMOC) to FAA AD 92-06-06 

The inspections mandated by this AD are approved as an AMOC to the SSD 57-1-4 

inspection that was mandated by FAA AD 92-06-06, only for the location addressed by 

the visual and eddy current inspections. Inspections at all other locations addressed by 

SSD 57-1-4 remain applicable. 

Authorization: For the Minister of Transport, Infrastructure and Communities, 

ORIGINAL SIGNED BY

Derek Ferguson 

Chief, Continuing Airworthiness 

Contact: Philip Tang, Continuing Airworthiness, Ottawa, telephone 613-952-4357, facsimile 

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