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95-22-05 SAAB AIRCRAFT AB: Amendment 39-9412. Docket 95-NM-187-AD.
Applicability: Model SAAB SF340A series airplanes having serial numbers 004 through 159, inclusive; and Model SAAB 340B series airplanes having serial numbers 160 and subsequent; equipped with brake assemblies having part number 5012589, 5007219-1, 5008541, 5008541-1, or 5008541-2; certificated in any category.
NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (d) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished previously.
To prevent failure of the brake assembly and wheel assembly, which could result in the potential for a brake fire, accomplish the following:
(a) Within 10 days after the effective date of this AD, perform a visual inspection to detect damage of the brake assembly and wheel assembly in accordance with Saab Service Bulletin 340-32-105, dated September 5, 1995.
(1) If no damage is detected, repeat the inspection thereafter at intervals not to exceed 225 hours time-in-service.
(2) If any damage is detected, prior to further flight, repair the damaged brake assembly and/or wheel assembly in accordance with the service bulletin. Repeat the inspection thereafter at intervals not to exceed 225 hours time-in-service.
(b) Within 225 hours time-in-service after accomplishing the inspection required by paragraph (a) of this AD, install a heat shield in the torque tube in accordance with Saab Service Bulletin 340-32-105, dated September 5, 1995.
(c) Installation of a redesigned stator clip in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, constitutes terminating action for the repetitive inspections required by paragraph (a) of this AD.
(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 2: 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 sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.
(f) The inspections, repair, and installation of a heat shield shall be done in accordance with Saab Service Bulletin 340-32-105, dated September 5, 1995. 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 SAAB Aircraft AB, SAAB Aircraft Product Support, S- 581.88, Link ping, Sweden. 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 November 8, 1995.
