80-12-10 R1 BRITISH AEROSPACE (Formerly Hawker Siddeley Aviation, Ltd.): Amendment 39- 3797 as amended by Amendment 39-4524. Applies to Model DH/BH/HS 125 series airplanes except 700 series airplanes above Serial Number NA-0245, certificated in all categories.
Compliance is required as indicated.
To prevent the possible loss of flaps, accomplish the following:
(a) For those airplanes to which AD 78-03-03 did not apply, before further flight, except that the airplane may be flown in accordance with FAR 21.197 and FAR 21.199 to a base where the work can be accomplished, and for those airplanes to which AD 78-03-03 applies, within the next 3 months after the last inspection performed in accordance with AD 78-03-03, unless already accomplished-
(1) Incorporate British Aerospace Modification No. 252670 or an FAA-approved equivalent in accordance with all items set forth in paragraph 2, "Accomplishment Instructions," British Aerospace Service Bulletin SB. 57-54-(2670), dated March 10, 1978, or an FAA-approved equivalent; and
(2) Concurrently with incorporation of the modification, inspect the aft lug of the hinge arm brackets and, except for 700 series airplanes, trim, blend, and de-burr the reinforcing on the flap lower skin, in accordance with "Additional Action to be Carried Out Concurrently with SB. 57-54 paras. 2.A(4) to (7)," page 8, British Aerospace Service Bulletin SB. 57-54-(2670), dated March 10, 1978, or an FAA-approved equivalent. However, if before the effective date of this AD, an airplane had incorporated Modification 252670 or an FAA-approved equivalent, but any of the actions specified in paragraph (a)(2) of this AD, if applicable, had not been accomplished, comply with paragraph (c) of this AD.
(b) For those airplanes which before the effective date of this AD had not incorporated British Aerospace Modification 252670 or an FAA-approved equivalent and had not performed the lug inspection and the trimming, etc., of the reinforcing specified in paragraph (a)(2) of this AD, within the next 12 months after concurrently accomplishing this work in accordance with paragraph (a) of this AD, inspect in accordance with paragraph (e) of this AD.
(c) For those airplanes which before the effective date of this AD had already incorporated British Aerospace Modification 252670 or an FAA-approved equivalent
(1) Except for 700 series airplanes -
(i) Within the next 3 months after the effective date of this AD, unless already accomplished, trim, blend, and de-burr the reinforcing on the flap lower skin in accordance with paragraph 1, "Additional Action to be Carried Out Concurrently With SB. 57-54 para. 2A(4) to (7)," page 8, British Aerospace Service Bulletins 57-54-(2670), dated March 10, 1978, or an FAA-approved equivalent; and
(ii) Within the next 3 months after the effective date of this AD but not before paragraph (c)(1) of this AD has been accomplished, inspect in accordance with paragraph (e) of this AD.
However, for an airplane on which before the effective date of this AD, British Aerospace Service Bulletin SB. 57-55 dated May 5, 1978, (hereinafter Service Bulletin SB. 57-55) had been accomplished and either before such accomplishment or concurrently with such accomplishment the trimming, etc., of the reinforcing on the flap lower skin specified in paragraph (c)(1) of this AD had been accomplished, within the next 3 months after the effective date of this AD or within the next 12 months after the last accomplishment of Service Bulletin SB. 57-55, whichever occurs later, inspect in accordance with paragraph (e) of this AD.
(2) For 700 series airplanes, within the next 3 months after the effective date of this AD or within the next 12 months after the last accomplishment of Service Bulletin SB. 57-55 of this AD, whichever occurs later, inspect in accordance with paragraph (e) of this AD.
(d) Within the next 12 months after the inspection requiredby paragraph (b) or (c) of this AD, and thereafter at intervals not to exceed 12 months from the last inspection, inspect in accordance with paragraph (e) of this AD.
(e) Inspect the flap outer hinge assemblies using the dye penetrant method in accordance with paragraph 2, "Accomplishment Instructions" of Service Bulletin SB. 57-55 or an FAA-approved equivalent. This inspection requires full compliance with Items 1 through 7 of paragraph 2 of the Service Bulletin.
(f) If, during any inspection required by this AD, any cracks are found:
(1) Before further flight -
(i) Replace the cracked part with a new part in accordance with Service Bulletin SB. 57-55, or an FAA-approved equivalent. In addition, if the rear lug of a hinge arm is found to be cracked, also replace the associated steel strap with a new strap in accordance with Service Bulletin S.B. 57-55 or an FAA-approved equivalent;
(ii) Re-protect and reassemble the assemblies, complying fully with Items 9 through 13, paragraph 2, "Accomplishment Instructions" of Service Bulletin SB. 57-55 or an FAA- approved equivalent.
(2) Continue the repetitive inspection required by this AD.
(g) If, during any inspection required by this AD, no cracks are found, re-protect and reassemble the assemblies complying fully with Items 9 through 13, paragraph 2, "Accomplishment Instructions" of Service Bulletin SB. 57-55 or an FAA-approved equivalent, and continue the repetitive inspections required by this AD.
(h) For purposes of this AD, an FAA-approved equivalent must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium.
(i) Accomplishment of BAe Modification 252659 constitutes terminating action for this AD.
The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1).AD 78-03-03, Amendment 39-3133 was superseded by AD 80-12-10, Amendment 39-3797.
Amendment 39-3797 became effective June 23, 1980.
This Amendment 39-4524 becomes effective January 3, 1983.