92-26-05 BRITISH AEROSPACE: Amendment 39-8432. Docket No. 92-NM-72-AD.
Applicability: Model ATP series airplanes, serial numbers 2001 through 2044, inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent reduced controllability of the airplane, accomplish the following:
(a) Within 30 days after the effective date of this AD, perform a one-time functional inspection to detect tightness or seizure of the nose wheel steering quadrant pivot and the upper steering control toggle link assembly, in accordance with British Aerospace Service Bulletin ATP-32-37, dated February 14, 1992.
(1) If the quadrant pivot/upper toggle link attachment bolt can be turned freely, in accordance with paragraph 2.A.(1) through 2.A.(8) of the Service Bulletin, no further action is necessary.
(2) If the quadrant pivot/upper toggle link attachment bolt is still tight, prior to further flight, if possible, remove and replace the bolt, in accordance with paragraphs 2.A.(9) and 2.A.(8) of the Service Bulletin. After this procedure, if the bolt turns freely, no further action is necessary.
(3) If the quadrant pivot/upper toggle link attachment bolt is found to be seized and cannot be removed, prior to further flight, check to see if the upper toggle link is free to rotate about the bolt, in accordance with paragraphs 2.A.(10) through 2.A.(12) of the Service Bulletin.
(i) If the upper toggle link is free to rotate about the bolt, prior to the accumulation of 50 landings after the functional inspection required by this AD, accomplish paragraph (a)(4) of this AD.
(ii) If the upper toggle link is not free to rotate about the bolt, prior to further flight, accomplish paragraph (a)(4) of this AD.
(4) If the upper toggle link has been checked in accordance with paragraph (a)(3)(i) or (a)(3)(ii) of this AD, repair the quadrant pivot/upper toggle link and bolt assembly, visually inspect the support channels/structure for deformation or cracks, and repair or replace any deformed or cracked structure, in accordance with paragraph 2.B. of the Service Bulletin.
(b) 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. 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.
(c) 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.
(d) The inspections, repair, and replacement shall be done in accordance with British Aerospace Service Bulletin ATP-32-37, dated February 14, 1992. 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.
(e) This amendment becomes effective on February 1, 1993.