Airworthiness Directive · Amendment 39-22274 · Landing gear
BAE Systems (Operations) Limited Airplanes
Superseded. A later AD replaced this one: AD 2024-06-10. Comply with the one in force.
This AD applies to BAE Systems (Operations) Limited Model BAe 146-100A, -200A, and -300A airplanes and Model Avro 146-RJ-RJ70A, 146-RJ85A, and 146-RJ100A airplanes, certificated in any category, with main landing gear (MLG) side stay outer links having Safran Landing Systems part number 200884304, 200884305, 200884346, 200884347, 201105300, 201105301, 201105308, 201105309, 201299300, 201299301, 201299305, or 201299306.
The FAA is superseding Airworthiness Directive (AD) 2005-06- 14, which applied to certain British Aerospace Model BAe 146 and Model Avro 146-RJ series airplanes. AD 2005-06-14 required repetitive inspections for cracking of the outer links on the main landing gear (MLG) side stays, and corrective actions if necessary. AD 2005-06-14 also provided an optional terminating action for the repetitive inspections. Since the FAA issued AD 2005-06-14, there has been a report of additional cracking on a MLG side stay on which the terminating action has been done. This AD continues to require the actions specified in AD 2005-06-14 and requires new repetitive inspections for cracking of the MLG side stay outer link and replacement if necessary as specified in a United Kingdom (U.K.) Civil Aviation Authority (CAA) (U.K. CAA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (f) of AD 2005-06-14, with new terminating action. For airplanes having any side stay identified in Messier-Dowty Service Bulletin 146-32-147, dated May 29, 2001: At the applicable time specified in paragraph (g)(1) or (2) of this AD, perform a detailed inspection for cracks of the outer links on the MLG side stays, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.32-156, Revision 1, dated July 3, 2001. Repair cracks before further flight in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.32-156, Revision 1, dated July 3, 2001. Thereafter, repeat the inspection at intervals not to exceed 2,000 flight cycles, until the actions specified in paragraph (h) of this AD have been done or the initial inspection required by paragraph (i) of this AD has been done. Although BAE Systems (Operations) Limited Inspection Service Bulletin ISB.32-156, Revision 1, dated July 3, 2001, specifies to report certain information to the manufacturer, this AD does not require a report.
(1) If the number of flight cycles accumulated on the side stay can be positively determined: Inspect before the accumulation of 2,000 total flight cycles on the side stay, or within 500 flight cycles after May 2, 2005 (the effective date of AD 2005-06-14), whichever occurs later.
(2) If the number of flight cycles accumulated on the side stay cannot be positively determined: Inspect within 500 flight cycles after May 2, 2005 (the effective date of AD 2005-06-14).
This paragraph restates the optional terminating action of paragraph (g) of AD 2005-06-14, with no changes. Relocation of each affected grease nipple to the upper surface of the outer link of the MLG side stays terminates the repetitive inspections required by paragraph (g) of this AD, if the relocation action is done in accordance with paragraph 2.C. of the Accomplishment Instructions of BAE Systems (Operations) Limited Inspection Service Bulletin ISB.32-156, Revision 1, dated July 3, 2001.
Except as specified in paragraph (j) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, United Kingdom Civil Aviation Authority AD G-2022-0018, dated October 18, 2022 (U.K. CAA AD G-2022-0018).
(1) Where U.K. CAA AD G-2022-0018 refers to its effective date, this AD requires using the effective date of this AD.
(2) The “Remarks” section of U.K. CAA AD G-2022-0018 does not apply to this AD.
(3) Where paragraph (2) of U.K. CAA AD G-2022-0018 refers to “discrepancies (i.e. cracks or other adverse findings),” replace the text “discrepancies (i.e. cracks or other adverse findings),” with “any cracking.”
(4) Where U.K. CAA AD G-2022-0018 refers to ASB.32-A189, this AD requires using BAE Systems (Operations) Limited Alert Service Bulletin ASB.32-A189, dated September 16, 2022.
Although BAE Systems (Operations) Limited Alert Service Bulletin ASB.32-A189, dated September 16, 2022, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the International Validation Branch, send it to the attention of the person identified in paragraph (n) of this AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.
(2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, International Validation Branch, FAA; or the United Kingdom Civil Aviation Authority (U.K. CAA); or BAE Systems (Operations) Limited's U.K. CAA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
For more information about this AD, contact Todd Thompson, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone 206-231-3228; email todd.thompson@faa.gov.
