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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Amendment 39-3210; AD 78-10-01

Airworthiness Directives; BEECH Models D18C, D18S, E18S, E18S-9700, G18S, H-18, C-45G, TC-45G, C-45H, TC-45J (SNB-5), JRB-6, 3N, 3M, and 3NM Airplanes


Preamble Information
AGENCY: Federal Aviation Administration, DOT


DATES: Effective May 17, 1978.






Regulatory Information

78-10-01 BEECH: Amendment 39-3210. Applies to Beech Models D18C, D18S, E18S, E18S-9700, G18S, H-18, C-45G, TC-45G, C-45H, TC-45J (SNB-5), JRB-6, 3N, 3M and 3NM modified in accordance with STC SA1243WE, SA1016WE, or SA360WE.

To preclude failure of the lower rudder torque tube, accomplish the following; unless already accomplished:

(a) Within the next 30 days after the effective date of this AD visually inspect the lower rudder torque tube for cracks in the area of the access hole as noted in figure 1 of this AD. (Reference Part Number 452606-7).

(b) If no cracks are found, reinspect at intervals not to exceed 30 days from the prior inspection.

(c) If cracks are found, prior to further flight:

(1) If any crack exceeds 1/2 inch in length, replace with a like serviceable unit, Part Number 452606-7, and reinspect per paragraph (d);

(2) If cracks are 1/2 inch or less in length, repair per a method approved by the Chief, Aircraft Engineering Division, FAA Western Region, and reinspect per paragraph (d);

(d) Reinspect at intervals not to exceed 30 days from repair, replacement, or prior inspection.

(e) The requirements of this AD may be terminated when modifications are incorporated which are approved by the Chief, Aircraft Engineering Division. Submit proposed modifications schemes to:

Chief, Aircraft Engineering Division
FAA Western Region
P.O. Box 92007
Worldway Postal Center
Los Angeles, California 90009

for review and approval.

This amendment becomes effective May 17, 1978.

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