78-11-06 BEECH: Amendment 39-3226. Applies to Model 65-A90, B90 and C90 (Serial Numbers LJ-114 through LJ-705), and Model E90 (Serial Numbers LW-1 through LW-141) airplanes incorporating Beechcraft H-14 autopilot installations with a 13.5 inch diameter elevator servo bellcrank.
To preclude possible failure of the elevator control cable, unless already accomplished.
A) Before the next flight, except for those airplanes previously modified in accordance with Beech Modification Kit Number 90-9067-1S, open the aft fuselage belly access door and locate the autopilot elevator servo bellcrank at F.S. 319.00, located to the left of centerline. Measure the bellcrank and if it measures 10 inches or less no further action is required. If the bellcrank measures 13.5 inches or larger (groove to groove), visually inspect the primary elevator control cable, the pulley bracket at F.S. 340.00, the autopilot servo cable, and autopilot bellcrank in accordance with Beech Service Instructions No. 0988, or later approved revisions. If there is no evidence of cable rubbing or damage to the airplane, no further immediate action is required.
1. If rubbing of the elevator cable is noted, but no damage has occurred.
a. Disconnect and remove the autopilot servo cable from the airplane.
b. Install a locally fabricated placard in plain view of the pilot indicating "AUTOPILOT INOPERATIVE".
2. If fraying of the elevator cable or other damage is noted:
a. Replace the elevator cable and repair or replace any other damaged parts.
b. Accomplish paragraphs A)1.a. and 1.b.
B) If not previously accomplished, on or before September 1, 1978, modify the servo mount of any Beechcraft H-14 elevator autopilot servo having a 13.5 inch diameter or larger bellcrank in accordance with Beech Modification Kit Number 90-9067-1S, or later approved revisions. Upon the completion of this modification any autopilot made inoperative under paragraphs A)1. orA)2. of this AD may be returned to service and the "AUTOPILOT INOPERATIVE" placard removed.
C) Aircraft may be flown in accordance with 21.197 to a base where the inspection required by this AD can be accomplished, after coordination with the Chief, Engineering and Manufacturing Branch, FAA, Central Region.
D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.
This amendment becomes effective June 8, 1978, to all persons except those to whom it has already been made effective by air mail letter from the FAA dated May 4, 1978.