AD 2016-16-11 Airworthiness Directives; BAE Systems (Operations) Limited Airplanes

Models named: BAe 146-100A, -200A, -300A series, Avro 146-RJ70A, 146-RJ85A, 146-RJ100A. Read the applicability below — it usually turns on serial or part numbers too.

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.

Comply with this AD within the compliance times specified, unless already done.

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 AD was prompted by revised inspection procedures issued by the Design Approval Holder. 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 AD replaces AD 2010-10-13, Amendment 39-16292 (75 FR 27419, May 17, 2010) (“AD 2010-10-13”).