92-22-03 BRITISH AEROSPACE: Amendment 39-8389. Docket No. 91-NM-277-AD.
Applicability: All Viscount Model 744, 745D, and 810 series airplanes, certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent structural failure of the bulkhead and associated decompression of the passenger cabin, accomplish the following:
(a) Within 90 days after the effective date of this AD, using both visual and specified non-destructive test methods, inspect the rear pressure bulkhead for corrosion, cracks, and damage, in accordance with British Aerospace Viscount Alert Preliminary Technical Leaflet 195, Issue 2, dated August 20, 1991 (for Model 810 series airplanes); or British Aerospace Viscount Alert Preliminary Technical Leaflet 325, Issue 2, dated August 22, 1991 (for Model 744 and 745D series airplanes); as applicable.
(b) Repeat the visual and non-destructive test inspections required by paragraph (a) of this AD at the following intervals:
(1) For "Part One: Rear Pressure Bulkhead - Forward Face - Rear Face," as specified in the applicable service bulletin: Repeat the inspections at intervals not to exceed 500 landings or 6 months, whichever occurs first.
(2) For "Part Two: Rear Pressure Bulkhead Web Lap-Joints," as specified in the applicable service bulletin: Repeat the inspections at intervals not to exceed 1,600 landings or 2 years, whichever occurs first.
(3) For "Part Three: Rear Pressure Bulkhead Rear Face, Boundary Member, Adjacent Skin and Structure," as specified in the applicable service bulletin: Repeat the inspections at intervals not to exceed 2,500 landings or 3 years, whichever occurs first.
(c) If corroded, cracked, or damaged parts are found as a result of inspections required by paragraphs (a) or (b) of this AD, prior to further flight, repair in accordance with British Aerospace Viscount Alert Preliminary Technical Leaflet (PTL) 195, Issue 2, dated August 20, 1991; or PTL 325, Issue 2, dated August 22, 1991; as applicable.
(d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.
NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the 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 Viscount Alert Preliminary Technical Leaflet 195,Issue 2, dated August 20, 1991; or British Aerospace Viscount Alert Preliminary Technical Leaflet 325, Issue 2, dated August 22, 1991; as applicable. 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, DC 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, 800 North Capitol Street, NW., suite 700, Washington, DC.
(g) This amendment becomes effective on December 3, 1992.