89-08-02 GROB WERKE GMBH & COMPANY KG (BURKHART GROB): Amendment 39-6174.
Applicability: Models G103 TWIN II and G103 A TWIN II ACRO (serial numbers 3501 through 3878, and 33879 through 34078) gliders.
Compliance: As indicated in the body of the AD.
To preclude failure of the flight control systems, accomplish the following:
(a) Within the next 10 hours time-in-service after the effective date of this AD, inspect the control systems for weld cracks in accordance with the instructions contained in Grob Service Bulletin (S/B) TM315-37, dated July 22, 1988.
(b) If weld cracks are found per the inspection specified in paragraph (a) of this AD, prior to further flight repair the cracks and modify the glider in accordance with the instructions in the above referenced S/B.
(c) If weld cracks are not found per the inspection specified in paragraph (a) of this AD, within the next 100 hours time-in-service after the effective date of this AD, modify the gliderin accordance with the instructions in the above referenced S/B.
(d) An equivalent means of compliance with this AD may be used if approved by the Manager, Brussels Aircraft Certification Staff, AEU-100, FAA, c/o American Embassy, 15 Rue de la Loi B1040, Brussels, Belgium.
All persons affected by this directive may obtain copies of the documents referred to herein upon request to Grob Systems, Incorporated, Aircraft Division, I-75 and Airport Drive, Bluffton, Ohio 45817; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.
This amendment (39-6174, AD 89-08-02) becomes effective on April 27, 1989.