| AD Number | 92-11-03 | Status | Active |
| Effective Date | July 09, 1992 | Issue Date | Not specified |
| Docket Number | 91-NM-280-AD | Amendment | 39-8253 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Textron Aviation Inc. |
| Model(s) | BH.125 Series 400A DH.125 Series 1A DH.125 Series 1A-522 DH.125 Series 1A/R-522 DH.125 Series 1A/S-522 DH.125 Series 3A DH.125 Series 3A/R DH.125 Series 3A/RA DH.125 Series 400A |
92-11-03 BRITISH AEROSPACE: Amendment 39-8253. Docket No. 91-NM-280-AD.
Applicability: British Aerospace Model DH/BH/HS 125 series airplanes, excluding Models 125-600A, 700A, 800A, and 1000A series airplanes; as listed in British Aerospace Service Bulletin S.B. 57-75, dated July 30, 1991; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent reduced structural integrity of the wings, accomplish the following:
(a) Within 3 months after the effective date of this AD, and thereafter at intervals not to exceed 4 years or 2,200 flights, whichever occurs first, perform an eddy current inspection on specified areas of the left and right wing upper skins to detect cracks in countersunk bolt holes in the wing skins and in the internal stringers, in accordance with British Aerospace Service Bulletin S.B. 57-75, dated July 30, 1991.
(b) If cracks are discovered as a result of the eddy current inspection requiredby paragraph (a) of this AD, prior to further flight, perform a dye penetrant inspection, in accordance with British Aerospace Service Bulletin S.B. 57-75, dated July 30, 1991.
(c) If cracks are discovered as a result of either the eddy current inspections required by paragraph (a) of this AD, or the dye penetrant inspection required by paragraph (b) of this AD, prior to further flight, repair the crack(s) as follows:
(1) Cracks that do not exceed the limits specified in British Aerospace Service Bulletin S.B. 57-75, dated July 30, 1991, must be repaired in accordance with the procedures in the Service Bulletin.
(2) Cracks that exceed the limits specified in British Aerospace Service Bulletin S.B. 57-75, dated July 30, 1991, must be repaired in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(d) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113.
(e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(f) The inspections and repairs shall be done in accordance with British Aerospace Service Bulletin S.B. 57-75, dated July 30, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace, PLC. Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.
(g) This amendment becomes effective on July 9, 1992.