Airworthiness Directive · Amendment 39-22118 · Fuselage
BAE Systems (Operations) Limited Airplanes
This AD applies to all BAE Systems (Operations) Limited Model BAe 146-100A, -200A, and -300A airplanes; and Model Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes; certificated in any category.
The FAA is superseding Airworthiness Directive (AD) 2015-07- 05, which applied to all BAE Systems (Operations) Limited Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. AD 2015-07-05 required repetitive external eddy current inspections on the aft skin lap joints of the rear fuselage for cracking, corrosion, and other defects, and repair if necessary. This AD continues to require the actions in AD 2015-07-05, at certain revised compliance times, and also requires repetitive low frequency eddy current (LFEC) inspections for any cracking, corrosion, and other defects in the aft skin lap joints of the rear fuselage and in the fuselage skin panels, and repair if necessary. This AD was prompted by a report of a pressurization problem on an airplane during climb-out; a subsequent investigation showed a crack in the fuselage skin; and that repetitive LFEC inspections in the rear fuselage aft skin lap joints and in the fuselage skin panels are necessary. Certain compliance times must also be revised. The FAA is issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (g) of AD 2015-07-05, with new service information.
(1) Within the compliance times specified in paragraphs (g)(1)(i) and (ii) of this AD, as applicable: Do an external eddy current inspection on the aft skin lap joints of the rear fuselage for cracking, corrosion, and other defects (i.e., surface damage and spot displacement); in accordance with paragraph 2.C. of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin 53-239, including Appendix 2, Revision 3, dated May 7, 2014; or paragraph 2. of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin 53-239, Revision 5, including Appendix 2, Revision 5, and Appendix 3, Revision 1, all dated March 2, 2017. As of the effective date of this AD, use BAE Systems (Operations) Limited Inspection Service Bulletin 53-239, Revision 5, including Appendix 2, Revision 5, and Appendix 3, Revision 1, all dated March 2, 2017, only.
(i) For any airplane which has accumulated 9,000 flight cycles or more since the airplane's first flight as of May 19, 2015 (the effective date of AD 2015-07-05): Do the inspection within 1,000 flight cycles or 6 months after May 19, 2015, whichever occurs first.
(ii) For any airplane which has accumulated less than 9,000 flight cycles since the airplane's first flight as of May 19, 2015 (the effective date of AD 2015-07-05): Do the inspection before accumulating 10,000 flight cycles since the airplane's first flight.
(2) Repeat the inspection required by paragraph (g)(1) of this AD thereafter at intervals not to exceed the times specified in paragraphs (g)(2)(i) and (ii) of this AD, as applicable to the airplane's modification status.
(i) For Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes post modification HCM50070E, or post modification HCM50070F, or post modification HCM50259A, repeat the inspection at intervals not to exceed 4,000 flight cycles.
(ii) For Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes premodification HCM50070E, and premodification HCM50070F, and premodification HCM50259A, repeat the inspection at intervals not to exceed 7,500 flight cycles.
This paragraph restates the requirements of paragraph (h) of AD 2015-07-05, with revised repair approval. If any cracking, corrosion, or other defect is found during any inspection required by AD 2015-07-05: Before further flight as of May 19, 2015 (the effective date of AD 2015-07-05), repair using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or the European Aviation Safety Agency (EASA); or BAE Systems (Operations) Limited's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. Accomplishment of the repair does not constitute a terminating action for the inspections required by paragraph (g) of this AD. As of the effective date of this AD, repair approvals must be obtained through the Manager, Large Aircraft Section, International Validation Branch, FAA; or the Civil Aviation Authority of the United Kingdom (UK CAA); or BAE Systems (Operations) Limited's UK CAA DOA.
After the effective date of this AD, at the applicable times specified in paragraph 1.D. “Compliance” of BAE Systems (Operations) Limited Inspection Service Bulletin 53-239, Revision 5, including Appendix 2, Revision 5, and Appendix 3, Revision 1, all dated March 2, 2017: Do an LFEC inspection for any cracking, corrosion, and other defects in the aft skin lap joints of the rear fuselage and in the fuselage skin panels, in accordance with paragraph “1. Procedure” of Appendix 2 and Appendix 3 of BAE Systems (Operations) Limited Inspection Service Bulletin 53-239, Revision 5, including Appendix 2, Revision 5, and Appendix 3, Revision 1, all dated March 2, 2017. Repeat the LFEC inspection thereafter at intervals not to exceed the times specified in paragraph 1.D. “Compliance” of BAE Systems (Operations) Limited Inspection Service Bulletin 53-239, Revision 5, including Appendix 2, Revision 5, and Appendix 3, Revision 1, all dated March 2, 2017.
If any cracking, corrosion, or other defect is found during any inspection required by this AD: Before further flight, repair using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or the UK CAA; or BAE Systems (Operations) Limited's UK CAA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. Accomplishment of the repair does not constitute a terminating action for the inspections required by paragraph (i) of this AD.
