Airworthiness Directive · Amendment 39-14280 · BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes
BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes
Superseded. A later AD replaced this one: AD 2009-10-02. Comply with the one in force.
This AD applies to all BAE Systems (Operations) Limited Model Jetstream 4101 airplanes, certificated in any category.
Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (m) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25-1529.
The FAA is superseding an existing airworthiness directive (AD), which applies to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes. That AD currently requires operators to determine the number of flight cycles accumulated on each component of the main landing gear (MLG) and the nose landing gear (NLG), and to replace each component that reaches its life limit with a serviceable component. The existing AD also requires operators to revise the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness in the aircraft maintenance manual to reflect the new life limits. This new AD requires revising the ALS to incorporate extended and more restrictive life limits for structurally significant items. This AD is prompted by engineering analysis of fleet operations which resulted in more restrictive life limits. We are issuing this AD to prevent failure of certain structurally significant items, including the MLG and the NLG, which could result in reduced structural integrity of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 90 days after August 3, 2004 (the effective date of AD 2004-13-07): Determine the number of flight cycles accumulated on each landing gear component listed in Table 1 and Table 2 of the Accomplishment Instructions of BAE Systems (Operations) Limited Service Bulletin J41-32-078, dated April 12, 2002. If there are no records or incomplete records for any component, establish the number of flight cycles in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Service Bulletin J41-05-001, Revision 2, dated March 15, 2002; or Revision 3, dated January 9, 2004.
Note 2: BAE Systems (Operations) Limited Service Bulletin J41-32-078 refers to BAE Systems (Operations) J41 Service Information Leaflet 32-15, Issue 1, dated February 15, 2002, as an additional source of service information for establishing the life limits of landing gear components and for tracking the accumulated life of each component.
Except as provided by paragraph (h) of this AD, within 60 days after establishing the flight cycles per paragraph (f) of this AD: Replace any landing gear component that has reached the life limit determined by paragraph (f) of this AD, with a serviceable component per a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Civil Aviation Authority (CAA) (or its delegated agent). Doing the actions in chapter 32 of the Jetstream 4100 airplane maintenance manual (AMM) is one approved method. Thereafter, replace any component that reaches its life limit prior to the accumulation of the applicable number of flight cycles shown in Table 1 and Table 2 of the Accomplishment Instructions of BAE Systems (Operations) Limited Service Bulletin J41-32-078, dated April 12, 2002.
(h) Any component for which the total accumulated life cycles has not been established, or that has exceeded its life limit, but has not yet been replaced per paragraph (g) of this AD, must be replaced within 72 months after August 3, 2004, in accordance with BAE Systems (Operations) Limited Service Bulletin J41-32-078, dated April 12, 2002.
(i) Within 30 days after August 3, 2004: Revise the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness of the Jetstream 4100 AMM to include the life limits of the components listed in Table 1 and Table 2 of the Accomplishment Instructions of BAE Systems (Operations) Limited Service Bulletin J41-32-078, dated April 12, 2002. This may be accomplished by inserting a copy of the service bulletin into the ALS of the Instructions for Continued Airworthiness until such time as a revision is issued. Thereafter, except as provided in paragraphs (m) and (l) of this AD, no alternative replacement times may be approved for any affected component. Once the AMM revision required by paragraph (l) of this AD is accomplished, the AMM revision required by this paragraph must be removed from the AMM.
As of August 3, 2004, no landing gear unit may be installed on any airplane unless the accumulated flight cycles of all components of that landing gear have been established per paragraph (f) of this AD, and any component that has exceeded its life limit has been replaced per paragraph (g) of this AD.
Calculations of total accumulated flight cycles accomplished per BAE Systems (Operations) Limited Service Bulletin J41-05-001, Revision 1, dated April 10, 2001; or BAE Systems (Operations) Limited Service Bulletin J41-05-001, Revision 2, dated March 15, 2002; are considered acceptable for compliance with the corresponding action specified in this AD.
Within 30 days after the effective date of this AD: Revise the ALS of the Instructions for Continued Airworthiness of the BAE Systems (Operations) Limited J41 AMM to include the life limits of the components listed in Chapter 05-10-10, Airworthiness Limitations—Description and Operation Section, Revision 23, dated February 15, 2005, of the AMM. This may be accomplished by inserting a copy into the ALS of the Instructions for Continued Airworthiness. Thereafter, except as provided in paragraph (m) of this AD, no alternative replacement times may be approved for any affected component. Once this AMM revision is included, the AMM revision required by paragraph (i) of this AD must be removed from the AMM.
