AD 74-24-02 R1

74-24-02 SWEARINGEN: Amendment 39-2012 as amended by Amendment 39-2529. Applies to Models SA226-T, SA226-AT, and SA226-TC airplane.

Compliance required as indicated.

To detect cracks and provide for repair and reinforcement of the horizontal stabilizer rear spar at the outboard elevator hinge bracket attachment accomplish the following inspection and modifications:

(a) After September 2, 1974, conduct the following inspection for the Model SA226-TC before the next flight unless already accomplished and for the Models SA226-T and SA226-AT within the next 10 hours time in service unless already accomplished. Inspect horizontal stabilizer rear spar in the vicinity of the left and right outboard elevator hinge bracket attachment for spanwise cracking above and below the hinge bracket in the bend radii of the spar flanges in accordance with paragraphs II.A.1. through 4. of Swearingen Service Bulletins A27-40-3067, revised October 9, 1974, for the Model SA226-T and A27-40-2064-4067, revised October 9, 1974, for the Models SA226-TC and SA226-AT or later FAA approved revisions.

(b) If cracks are found, before further flight, repair horizontal stabilizer rear spar in accordance with:

(1) Paragraph II.B. of Swearingen Service Bulletin A27-40-3067, revised October 9, 1974 or later FAA approved revision for the Model SA226-T, or

(2) Paragraph II.B. of Swearingen Service Bulletin A27-40-2064-4067 revised October 9, 1974 or later FAA approved revision for the Models SA226-TC and SA226-AT.

(c) If no cracks are found, accomplish the following:

(1) Continue the inspections specified in (a) for the Model SA226-T at intervals not to exceed 200 hours time in service after the effective date of this AD. These periodic inspections may be discontinued after installation of the spar reinforcement specified in paragraph II.C. of Swearingen Service Bulletin A27-40-3067 revised October 9, 1974 or later FAA approved revision.

(2) Within 50 hours timein service after the effective date of this AD, unless already accomplished for the Models SA226-TC and SA226-AT, install the spar reinforcement specified in paragraph II.C. of Swearingen Service Bulletin A27-40-2064-4067 revised October 9, 1974, or later FAA approved revisions.

(3) After the rework specified in (c)(2), continue the inspections specified in (a) for the Models SA226-TC and SA226-AT at intervals not to exceed 500 hours' time in service from the date of rework or from the effective date of this AD if the rework was accomplished before the effective date.

(d) Alternate methods of spar repair and reinforcement must be approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, FAA.

Amendment 39-2012 superseded Amendment 39-1950, AD 74-18-14, and became effective November 18, 1974.

This amendment 39-2529 becomes effective March 8, 1976.