AD 92-15-01

92-15-01 BEECH: Amendment 39-8294. Docket No. 92-CE-18-AD.

Applicability: The following model and serial numbered airplanes, certificated in any category:

Models Serial Numbers T-34C GP-1 through GP-50, GL-1 through GL-353, and GM-2 through GM-98 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, F90, and H90 LJ-1 through LJ-1285, LW-1 through LW-347, LA-2 through LA-236, LM-1 through LM-141, LS-1, LS-2, LS-3, LT-1, LT-2, LU-1 through LU-15, and LL-1 through LL-61 99, 99A, A99A, B99, and C99 U-1 through U-239 100, A100, and B100 B-1 through B-247 and BE-1 through BE-137 200, 200C, 200CT, 200T, A200, A100-1, A200CT, B200, B200C, B200CT, and B200T BB-2 through BB-1405, BC-1 through BC-75, BD-1 through BD-30, BJ-1 through BJ-66, BL-1 through BL-137, BN-1 through BN-4, BP-1 through BP-71, BT-1 through BT-33, BU-1 through BU-12, BV-1 through BV-12, FC-1, FC-2, FC-3, FE-1 through FE-9, FG-1, and FG-2 300, 300C, B300, and B300C FA-1 through FA-217, FF-1 through FF-19, FL-1 through FL-60, and FM-1

Compliance: Required as indicated, unless already accomplished.

To prevent undetected failure of engine truss-to-firewall bolts, which could eventually lead to separation of the engine mount from the airplane, accomplish the following:

(a) Within the next 150 hours time-in-service after the effective date of this AD, accomplish the following:

(1) Individually remove each engine truss-to-firewall bolt and determine whether the bolt is manufactured by Dumont Aviation as specified by Figure 2 of, and in accordance with paragraphs 1 and 2 of the ACCOMPLISHMENT INSTRUCTIONS section of, Beech Service Bulletin (SB) No. 2432, dated February 1992. Only one engine truss-to-firewall bolt shall be removed at any given time.

(2) Prior to further flight, replace any bolt manufactured by Dumont Aviation as identified in paragraph (a)(1) of this AD with a new bolt part number (P/N) MS20006-20 /M/.

NOTE 1: The inspection of the engine truss-to-firewall bolts and associated hardware for corrosion that is referenced in Beech SB No. 2432, dated February 1992, is recommended but is not required by this AD.

(b) 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.

(c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office.

(d) The inspection required by this AD shall be done in accordance with Beech Service Bulletin No. 2432, dated February 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 the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC.

(e) This amendment becomes effective on August 21, 1992.