AD 77-08-04

77-08-04 BEECH: Amendment 39-2875. Applies to Models 58P and 58PA (Serial Numbers TJ-46 thru TJ-74, TJ-76, TJ-78 thru TJ-80, TJ-82 thru TJ-85, TJ-88 and TJ-89) and Models 58TC and 58TCA (Serial Numbers TK-7 thru TK-18, TK-20, TK-21, TK-25, TK-27, TK-30, TK-32, TK-34, TK-37 and TK-38) airplanes certified in all categories.

Compliance: Required as indicated, unless already accomplished.

To assure that the correct bolts are installed in the engine mount fittings, within the next 100 hours' time in service after the effective date of this AD, accomplish the following:

A. Inspect, and if necessary, replace the engine mount fitting bolts in accordance with the following procedures:

1. Remove the access covers just aft of the engine firewall on the upper and lower inboard and outboard sides of both right and left engine nacelles to gain access to the engine mount fittings (four per engine).

2. Visually inspect the two attach bolts in each fitting (eight bolts for each engine) to determine that NAS bolts are installed. NAS bolts may be identified by a concave indentation on the bolt head and NAS stamped on the bolt head.

3. If NAS bolts are installed, reinstall the access covers and proceed to Paragraph A.6. below. If NAS bolts are not installed, proceed with Paragraphs A.4. thru A.6. below.

4. Using engine hoist and sling as noted in the engine removal section of the applicable Beech Maintenance Manual, lift the engine weight off of the engine mount fittings.

5. Remove any of the engine mount fitting bolts that are not NAS bolts (remove and replace one bolt at a time). Discard the bolts and self-locking nuts removed and install new NAS1104-7 or NAS1104-7M bolts using new AN960-416L washers and new MS21042-4 self-locking nuts. Torque bolts to 50 to 70 inch pounds. Reinstall access covers and proceed to Paragraph A.6.

6. Make proper entry in the aircraft maintenance records that are to be transferred with the aircraft showing compliance with this AD.

B. Compliance time for this AD may be extended up to 10 hours to a maximum of 110 hours to allow compliance with this AD at previously scheduled maintenance periods.

C. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.

D. Beechcraft Service Instructions No. 0875-038 covers the subject matter of this AD.

This amendment becomes effective May 26, 1977.