AD 76-22-03

76-22-03 BEECH: Amendment 39-2756. Applies to Models 99, 99A, A99A, B99 (Serial Numbers U-1 through U-164), Models 100 and A100 (Serial Numbers B-1 through B-230), and Models B100 (Serial Numbers BE-1 through BE-17) airplanes.

Compliance: Required as indicated, unless already accomplished.

To prevent possible loss of elevator control:

A) Within 50 hours' time in service after the effective date of this AD and thereafter at 400 hour intervals, until Beech P/N 100-4005-15 elevator update kits are installed on left and right elevators or new improved left and right replacement elevators are installed in accordance with Beechcraft Service Instructions No. 0799-133, Revision II, or later approved revisions, accomplish the following:

1. If not previously accomplished, install a 1.38 inch inspection access hole, access hole doubler, Tinnerman P/N A6914-1024-1 patch plate and Tinnerman P/N CO D805096-1 split doubler in the leading edge of right and left elevators in accordance with Beechcraft Service Instructions 0799-133, Revision II, or later approved revisions.

2. Remove the Tinnerman patch plate and elevator outboard hinge access door. Working through these openings using a light and mirror, visually inspect the following areas of right and left elevators for cracks:

a. Elevator main spar web and flanges from Station 118.66 to 124.91.

b. Elevator outboard leading edge rib flanges at Stations 115.61, 120.71 and 124.91.

B) If a crack is found during any inspection specified in Paragraph A prior to further flight, accomplish either Paragraphs B(1) or B(2) and Paragraph B(3) if applicable:

1. Obtain from Beech and install on the cracked elevator Beech P/N 100- 4005-1S elevator update kit per instructions provided with the kit.

2. Install a new replacement elevator, in place of the cracked elevator, in accordance with Beechcraft Service Instructions 0799-133, Revision II, or later approved revisions.

3. OnModels 99 and 99A (Serial Numbers U-1 through U-131, U-133 through U-145 and U-147 except aircraft having elevators equipped with boundary layer separation wedge at trailing edge of elevator) flight check for out of trim control forces in accordance with Chapter 27-40 of Beech Maintenance Manual P/N 99-590015-1A3 or later revisions any time an elevator is repaired or replaced.

C) The aircraft may be flown in accordance with FAR 21.197 to a location where Paragraph B may be accomplished, providing elevator damage has not progressed to the point where abnormal elevator flexing exists in the outboard hinge area.

D) Time intervals for repetitive inspections noted in Paragraph "A" of this AD may be adjusted up to 40 hours to a maximum interval of 440 hours to allow inspections required by this AD to be accomplished at previously scheduled maintenance periods.

E) 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 November 4, 1976.