Airworthiness directives › 2018-19-24
AD 2018-19-24 Airworthiness Directives; BAE Systems (Operations) Limited Airplanes
Models named: 4101. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to all BAE Systems (Operations) Limited Model 4101 airplanes, certificated in any category, all manufacturer serial numbers.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
At the compliance times specified in paragraphs (g)(1) and (g)(2) of this AD, as applicable: Do a detailed inspection of fuselage frame 90 for cracking or fatigue damage, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Alert Service Bulletin J41-A53-058, dated December 6, 2016. If any cracking or fatigue damage is found: Before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or BAE Systems (Operations) Limited's EASA Design Organization Approval (DOA). (1) For airplanes with 6,300 flight cycles or fewer since Structural Significant Items (SSI) 53-10-029 (Maintenance Planning Document (MPD) 531029-DVl-10010-1) was last accomplished: Within 6,600 flight cycles after the last accomplishment of SSI 53-10-029 (MPD 531029-DVl-10010-1), or within 6 months after the effective date of this AD, whichever is later. (2) For airplanes with more than 6,300 flight cycles since SSI 53-10-029 (MPD 531029-DVl-10010-1) was last accomplished: Within 300 flight cycles or 4.5 months, whichever is earlier, since the last accomplishment of SSI 53-10-029 (MPD 531029-DVl-10010-1), or within 6 months after the effective date of this AD, whichever is later.
Unsafe condition
This AD was prompted by a determination that it is possible for cracks in fuselage frame 90 to exceed the critical length for failure in less time than the current inspection interval; and a determination that inspection requirements for a number of maintenance tasks involving certain airworthiness limitations are incorrect. We are issuing this AD to address cracking in fuselage frame 90, which could cause it to fail and thereby compromise the structural integrity of the aircraft pressure hull. We are also issuing this AD to address fatigue damage of various airplane structures, which could result in reduced structural integrity of the airplane.
Affected ADs
This AD affects AD 2005-15-11, Amendment 39-14200 (70 FR 43025, July 26, 2005) (“AD 2005-15-11”).
Read the original on the Federal Register →
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1