AD 71-19-05 ACTIVE

71-19-05 BRITISH AIRCRAFT CORPORATION: Amdt. 39-1292. Applies to Model BAC 1- 11 200 series airplanes.

Compliance is required as indicated.

To prevent failure of the saddle bracket structure located at Station 575 in the main landing gear bay, accomplish the following:

(a) For airplanes with saddle bracket assemblies with 9,000 or more landings on the effective date of this AD, within the next 25 landings after the effective date of this AD, unless already accomplished within the last 175 landings, and thereafter at intervals not to exceed 200 landings from the last inspection, inspect the saddle bracket assembly in accordance with paragraph (c).

(b) For airplanes with saddle bracket assemblies with less than 9,000 landings on the effective date of this AD, within the next 25 landings after the effective date of this AD, or before the accumulation of 9,000 landings on the saddle bracket assembly, whichever occurs later, unless already accomplished within the last 175 landings, and thereafter at intervals not to exceed 200 landings from the last inspection, inspect the saddle bracket assembly in accordance with paragraph (c).

(c) Visually inspect the main landing gear door jack attachment saddle bracket assembly for cracks or damage in accordance with BAC 1-11 Alert Service Bulletin No. 53-A- PM3620, Issue 2, dated March 4, 1971, or an FAA-approved equivalent.

(d) If a saddle bracket assembly is found to have cracks only in the top closing plate, P/N AB27-12079, and the cracks do not exceed the acceptable limits defined in BAC 1-11 Alert Service Bulletin No. 53-A- PM3620, Issue 2, dated March 4, 1971, during an inspection required by paragraph (c), before further flight repair the saddle bracket assembly in accordance with paragraph 3.1 of that service bulletin or an FAA-approved equivalent, or comply with paragraph (e).

(e) If a saddle bracket assembly is found to have cracks in the top closing plate, P/N AB27-12079, which exceed theacceptable limits defined in BAC 1-11 Alert Service Bulletin No. 53-A-PM3620, Issue 2, dated March 4, 1971, or is found to have cracks or damage to any other part of the assembly during an inspection required by paragraph (c), before further flight either -

(1) Replace the affected saddle bracket assembly with a serviceable assembly of the same part number; or -

(2) Replace the affected saddle bracket assembly with a serviceable assembly incorporating BAC Modification PM3620.

(f) The repetitive inspections required by paragraphs (a) and (b) may be discontinued after compliance with paragraph (e)(2).

(g) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East Region may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.

This supersedes Amendment 39-687 (33 F.R. 17895), AD 68-25-01, as amended by Amendment 39-910 (35 F.R. 144).

This amendment becomes effective September 20, 1971.