AD 84-23-01

84-23-01 LOCKHEED: Amendment 39-4955. Applies to Lockheed Models 1329-23A, -23D, - 23E, and -25 series airplanes, serial numbers 5001 through 5162 and 5201 through 5240, certificated in all categories.

Compliance is required as indicated, unless already accomplished.

To detect cracks which could lead to failure of the empennage and loss of the airplane, accomplish the following:

A. Within the next 25 hours flying time or within 20 days after the effective date of this airworthiness directive (AD), inspect for cracks, proper hardware, proper installation of hardware, and loose fasteners in the JE24-1 empennage pivot fitting at the point where the fitting attaches to the flange of the JE22-1 rear beam of the vertical stabilizer in accordance with Lockheed Alert Service Bulletins A329II-55-3 and A329-299, dated October 19, 1984. If loose fasteners or cracks are found, before further flight, repair or replace with new or serviceable parts, as necessary, in accordance with a method acceptable to or approved by the FAA.

B. Alternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region.

This amendment becomes effective November 26, 1984.