Airworthiness Directive · Amendment 39-18609 · Wings
BAE Systems (Operations) Limited Airplanes
This AD applies to BAE Systems (Operations) Limited Model BAe 146-100A, -200A, and -300A series airplanes; and Model Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes; certificated in any category, all serial numbers.
We are superseding Airworthiness Directive (AD) 2010-10-13, for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146 series airplanes. AD 2010-10-13 required repetitive inspections of the wing fixed leading edge and front spar structure for corrosion and cracking, and repair if necessary. This new AD requires revised inspection procedures that terminate a previously approved inspection procedure. This AD was prompted by revised inspection procedures issued by the Design Approval Holder (DAH). We are issuing this AD to detect and correct corrosion and cracking of the wing fixed leading edge and front spar structure, which could result in reduced structural integrity of the airplane.
This paragraph restates the requirements of paragraph (f) of AD 2010-10-13, with an added provision for terminating action. Accomplishing the initial inspection required by paragraph (j) of this AD terminates the requirements of paragraph (g) of this AD.
(1) At the applicable time identified in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of this AD: Perform a detailed visual inspection and visual inspection (Method 1) or a detailed visual inspection (Method 2) for cracking and corrosion of the wing fixed leading edge and front spar structure, in accordance with paragraph 2.C. or 2.D., as applicable, of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008.
(i) For airplanes with less than 9 years since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of the effective date of this AD: Within 18 months after June 21, 2010 (the effective date of AD 2010-10-13).
(ii) For airplanes with 9 years or more, but less than 15 years, since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of June 21, 2010 (the effective date of AD 2010-10-13): Within 18 months after June 21, 2010, or within 16 years since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness, whichever occurs first.
(iii) For airplanes with 15 years or more since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of June 21, 2010 (the effective date of AD 2010-10-13): Within 6 months after June 21, 2010.
(2) After doing the initial inspection required by paragraph (g)(1) of this AD, at the applicable intervals specified in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, accomplish the repetitive inspections of the wing fixed leading edge and front spar structure for cracking and corrosion in the “area of inspection” specified in table 1 of paragraph 1.D., “Compliance,” of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. Do the inspections in accordance with paragraph 2.C. (Method 1) or paragraph 2.D. (Method 2) of the Accomplishment Instructions of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. Where previously applied, enhanced corrosion protection may then be re-applied, as an option, in accordance with paragraph 2.E. of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. Perform the repetitive inspections at the times specified in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, as applicable.
(i) For airplanes having enhanced corrosion protection that was applied during the previous inspection: Inspect at intervals not to exceed 144 months.
(ii) For airplanes not having enhanced corrosion protection that was applied during the previous inspection: Inspect at intervals not to exceed 72 months.
(3) After doing the initial inspection required by paragraph (g)(1) of this AD, at intervals not to exceed 36,000 flight cycles, accomplish fatigue inspections in accordance with paragraph 2.C. (Method 1) or paragraph 2.D. (Method 2) of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008.
(4) If any cracking or corrosion is found during any inspection required by paragraph (g) of this AD, before further flight, repair in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008.
(5) No repair terminates the inspection requirements of this AD.
(6) Actions done before June 21, 2010 (the effective date of AD 2010-10-13), in accordance with BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, dated February 22, 2008, are considered acceptable for compliance with the corresponding actions specified in this AD.
(7) Submit a report of the findings (both positive and negative) of the inspection required by paragraph (f)(1) of this AD to Customer Liaison, Customer Support (Building 37), BAE Systems (Operations) Limited, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland; fax +44 (0) 1292 675432; email raengliaison@baesystems.com, at the applicable time specified in paragraphs (g)(7)(i) and (g)(7)(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.
(i) If the inspection was done on or after June 21, 2010 (the effective date of AD 2010-10-13): Submit the report within 30 days after the inspection.
(ii) If the inspection was done before June 21, 2010 (the effective date of AD 2010-10-13): Submit the report within 30 days after June 21, 2010.
This paragraph restates the corrosion protection information in Note 2 of AD 2010-10-13, with no changes. At the discretion of the airplane owner/operator, corrosion protection may be embodied on those areas subject to a detailed visual inspection, in accordance with paragraph 2.E. or paragraph 2.F. of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008. Embodiment of enhanced corrosion protection in accordance with paragraph 2.E. of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008, allows the interval of the repetitive inspections (as required by paragraph (g)(2) of this AD) to be extended in the area(s) of application in accordance with paragraph (g)(2)(i) or (g)(2)(ii) of this AD, as applicable.
This paragraph restates the inspection information in Note 3 of AD 2010-10-13, with no changes. The inspections required by this AD prevail over the Maintenance Review Board Report (MRBR), Maintenance Planning Document (MPD), Corrosion Prevention and Control Program (CPCP), and Supplemental Structural Inspection Document (SSID) inspections defined in paragraph 1.C.(3) of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008.
At the applicable time identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD; or within 6 months after the effective date of this AD; whichever occurs later: Perform a detailed visual inspection for cracking and corrosion of the wing fixed leading edge and front spar structure, in accordance with paragraph 2.C. of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 3, dated August 31, 2010. Repeat the inspection thereafter at the applicable intervals specified in paragraph 1.D.2. of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, Revision 3, dated August 31, 2010. Accomplishing the initial inspection required by this paragraph terminates the requirements of paragraph (g) of this AD.
(1) For airplanes with less than 9 years since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of June 21, 2010 (the effective date of AD 2010-10-13): Within 18 months after June 21, 2010, or within 9 years since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness, whichever occurs later.
(2) For airplanes with 9 years or more, but less than 15 years, since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of June 21, 2010 (the effective date of AD 2010-10-13): Within 18 months after June 21, 2010, or within 16 years since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness, whichever occurs first.
(3) For airplanes with 15 years or more since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness as of June 21, 2010 (the effective date of AD 2010-10-13): Within 6 months after June 21, 2010.
If any crack or corrosion is found during any inspection required by paragraph (j) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or BAE Systems (Operations) Limited's EASA Design Organization Approval (DOA).
Accomplishment of any repair, as required by paragraph (k) of this AD, does not constitute terminating action for inspections required by this AD.
