AD 2010-09-11

Unless already done, for Model BAe 146-100A, -200A, and -300A series airplanes: Prior to the accumulation of 24,000 landings, or within 60 days after March 2, 1993 (the effective date of AD 93-01-11), whichever occurs later: Perform an X-ray inspection to detect fatigue cracks in the left and right wing upper skins, joint straps, and stringers in the vicinity of rib “0,” in accordance with British Aerospace Inspection Service Bulletin 57-41, dated July 26, 1991. Doing the inspection required by paragraph (g)(1) of this AD terminates the inspection required by this paragraph.

(1) If cracks are found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, Transport Airplane Directorate, FAA; or the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. As of the effective date of this AD, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Thereafter, repeat the inspection required by paragraph (f) of this AD at intervals not to exceed 9,000 landings, in accordance with British Aerospace Inspection Service Bulletin 57-41, dated July 26, 1991, until the initial inspection required by paragraph (g)(1) of this AD is accomplished.

(2) If no cracks are found, repeat the inspection required by paragraph (f) of this AD at intervals not to exceed 9,000 landings, in accordance with British Aerospace Inspection Service Bulletin 57-41, dated July 26, 1991, until the initial inspection required by paragraph (g)(1) of this AD is accomplished.

Unless already done, do the following actions.

Note 1: The instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-070, dated October 15, 2007, which is the subject of this AD, are divided into two parts; consequently, the statement in paragraph 1.C. of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-070, dated October 15, 2007, that there are three parts is incorrect and can be disregarded.

(1) At the applicable compliance time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD: Do an HFEC inspection of the front and rear spar flanges, a detailed visual inspection of the stringers, and a detailed visual inspection of the stringer crown fittings, all at the rib “0” joint strap, for cracking and corrosion, and do all applicable corrective actions, in accordance with “Part 1” of paragraph 2.C., “Inspection,” of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-070, dated October 15, 2007. Repeat the inspections thereafter at intervals not to exceed 4,000 flight cycles. Do all applicable corrective actions before further flight. Accomplishment of these initial inspections terminates the inspections required by paragraphs (f), (f)(1), and (f)(2) of this AD.

(i) For airplanes on which an inspection was not done in accordance with Supplemental Structural Inspection (SSI) 57-10-101 (MPD 571001-DVI-10000-1) as of the effective date of this AD: Prior to the accumulation of 20,000 total flight cycles, or within 4,000 flight cycles after the effective date of this AD, whichever occurs later.

(ii) For airplanes on which an inspection was done in accordance with SSI 57-10-101 (MPD 571001-DVI-10000-1) as of the effective date of this AD: Within 3,000 flight cycles after the effective date of this AD.

(2) At the applicable compliance time specified in paragraph (g)(2)(i) or (g)(2)(ii) of this AD: Do detailed visual and HFEC inspections to detect cracking and corrosion of the rib “0” strap, a radiographic inspection of the rib “0” joint, and an ultrasonic inspection of the skin at the rib “0” joint strap, and do all applicable corrective actions, in accordance with “PART 2” of paragraph 2.C. “Inspection” of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-070, dated October 15, 2007. Do all applicable corrective actions before further flight. Repeat the inspections thereafter at intervals not to exceed 4,000 flight cycles.

(i) For airplanes on which an inspection was not done in accordance with SSI 57-10-102 and 57-10-102A (MPD 571002-SDI-10000-1 and 571002-SDI-10000-2) as of the effective date of this AD: Before the accumulation of 24,000 total flight cycles, or within 4,000 flight cycles after the effective date of this AD, whichever occurs later.

(ii) For airplanes on which an inspection was done in accordance with SSI 57-10-102 or 57-10-102A (MPD 571002-SDI-10000-1 or 571002-SDI-10000-2) as of the effective date of this AD: Within 3,000 flight cycles after the effective date of this AD.

(3) Submit a report of the findings (both positive and negative) of the initial inspections required by paragraphs (g)(1) and (g)(2) of this AD to BAE Systems (Operations) Limited, at the applicable time specified in paragraph (g)(3)(i) or (g)(3)(ii) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. Send reports to Customer Liaison, Customer Support (Building 37), BAE SYSTEMS (Operations) Limited, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland; fax +44 (0) 1292 675432; e-mail raengliaison@baesystems.com.

(i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.

(ii) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.

(4) Accomplishment of any repair does not constitute terminating action for the inspection requirements of this AD.

Note 2: This AD differs from the MCAI and/or service information as follows: No differences.