Airworthiness Directive · Amendment 39-22317 · Fuselage
BAE Systems (Operations) Limited Airplanes
This AD applies to 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, without modification HCM20011A, HCM20012A, HCM20013A, HCM20313A, HCM20314A, or HMC20315A.
The FAA is superseding Airworthiness Directive (AD) 99-25-11 for certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes. AD 99-25-11 required repetitive inspections for cracks along the face of the retraction attachment boss in the nose landing gear (NLG) sidewall; and corrective action, if necessary. This AD was prompted by a report of a crack found on the left-hand sidewall well on the NLG, and by the determination that additional airplanes are subject to the identified unsafe condition. This AD continues to require the actions in AD 99-25-11, and expands the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (a) of AD 99-25-11, with new terminating action. For airplanes listed in British Aerospace Service Bulletin SB.53-152, dated October 8, 1998: Prior to the accumulation of 8,000 total flight cycles, or within 200 flight cycles after February 1, 2000 (the effective date of AD 99-25-11), whichever occurs later, perform an eddy current inspection to detect cracking along the face of the retraction attachment boss in the NLG sidewall, in accordance with British Aerospace Service Bulletin SB.53-152, dated October 8, 1998. Thereafter, repeat the eddy current inspection at intervals not to exceed 2,600 flight cycles, except as provided in paragraph (j) of this AD.
This paragraph restates the requirements of paragraph (b) of AD 99-25-11, with revised repair approval.
(1) If any crack is detected before the effective date of this AD, during any inspection required by paragraph (g) of this AD, prior to further flight, repair or re-inspect in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Civil Aviation Authority (or its delegated agent). For a repair method to be approved by the Manager, International Branch, as required by this paragraph, the Manager's approval letter must specifically reference this AD.
(2) If any crack is detected on or after the effective date of this AD during any inspection required by paragraph (g) of this AD: Before further flight, either repair using a method approved by the Manager, International Validation Branch, FAA; or the U.K. Civil Aviation Authority (U.K. CAA); or BAE Systems (Operations) Limited's U.K. CAA Design Organization Approval (DOA); or do the replacement specified in paragraph (i) of this AD. If approved by the DOA, the approval must include the DOA-authorized signature.
(1) For all airplanes: Before the accumulation of 7,375 total flight cycles, or within 625 flight cycles after the effective date of this AD, or within 2,600 flight cycles since the most recent inspection required by paragraph (g) of this AD, whichever occurs latest, do an eddy current inspection for cracking in the bore and along the face of the retraction jack attachment boss in the left-hand NLG sidewall, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-152, Revision 8, dated February 19, 2018. Before further flight, repair or replace any cracked sidewall, as applicable, in accordance with BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-152, Revision 8, dated February 19, 2018. Repeat the inspection thereafter at intervals not to exceed 6,700 flight cycles, except as provided in paragraphs (i)(1)(i) and (ii) of this AD.
(i) For airplanes on which a repair identified for Option A, D, or E in Table 1 of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-152, Revision 8, dated February 19, 2018, has been done: Inspect within 20,000 flight cycles after the repair, and repeat thereafter at intervals not to exceed 4,000 flight cycles.
(ii) For airplanes on which the replacement with part number HC537L0002-000, -002, or -004 identified in Option F in Table 1 of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-52, Revision 8, dated February 19, 2018, has been done: Inspect within 20,000 flight cycles after the repair, and repeat thereafter at intervals not to exceed 4,000 flight cycles.
(2) For airplanes on which re-inspection of cracks was allowed as specified in paragraph (h)(1) of this AD: Within 2,600 flight cycles after the most recent inspection required by paragraph (g) of this AD, repair or replace any cracked sidewall, as applicable, in accordance with BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-152, Revision 8, dated February 19, 2018.
(1) Accomplishment of the initial inspection and applicable corrective actions required by paragraph (i) of this AD terminates the repetitive inspection requirements of paragraph (g) of this AD.
(2) Accomplishment of the action identified for Option B or C in Table 1 of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-152, Revision 8, dated February 19, 2018, terminates the repetitive inspection requirements of paragraphs (g) and (i)(1) of this AD.
(3) Accomplishment of the replacement with part number HC537L0002-006 identified for Option F in Table 1 of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-152, Revision 8, dated February 19, 2018, terminates the repetitive inspection requirements of paragraphs (g) and (i)(1) of this AD.
