AD 79-25-07

79-25-07 CESSNA: Amendment 39-3633. Applies to: 180 Series (Serial Numbers 18051762 thru 18052981, except 18052975) airplanes; 182/F182 Series (Serial Numbers 18257446 thru 18266590, F18200001 thru F18200094) airplanes; 185 and A185 Series (Serial Numbers 18501096 thru 18503619) airplanes; 188 and A188 Series (Serial Numbers 18800050 thru 18803240) airplanes; P206 Series (Serial Numbers P20600280 thru P20600647) airplanes; U206 and TU206 Series (Serial Numbers 20600634 thru 20604649) airplanes; 207 and T207 Series (Serial Numbers 20700001 thru 20700451) airplanes; 210 and T210 Series (Serial Numbers 21058783 thru 21062649, 21062651 thru 21062661, 21062663 thru 21062666, T210-0001 thru T210-0454) airplanes; Model P210N (Serial Numbers P21000001 thru P21000026) airplanes.

COMPLIANCE: Required within the next 50 hours' time-in-service after the effective date of this AD unless previously accomplished.

To preclude the possibility of electrical orelectronic component damage or an in-flight fire due to a short between an ungrounded alternator and flammable fluid carrying lines, accomplish the following:

A) Perform either 1 or 2 below:

1) Install an additional ground strap, Cessna P/N 1570102-22, between the ground stud on the alternator and the lower left hand mounting stud on the engine auxiliary drive pad in accordance with Cessna Single Engine Service Information Letter SE79-59. An equivalent ground strap fabricated per FAA Advisory Circular 43.13-1A appropriate for the alternator rating is also acceptable.

2) Modify the alternator installation by installing a different engine mount leg per Cessna Service Kit SK210-84 (Reference Cessna Single Engine Customer Care Service Information Letter SE79-5, dated February 26, 1979) or for the 182 Series, Cessna Service Kit SK182-55A (Reference Cessna Single Engine Customer Care Service Information Letter SE79-58 dated November 23, 1979).

NOTE: When accomplishing Paragraph 1) or 2), assure all contact areas are clean and provide good electrical continuity.

B) Visually inspect the alternator installation for, and if necessary, provide at least 1/2 inch clearance between the alternator installation and adjacent flammable fluid carrying lines, powerplant controls and electrical wiring in accordance with FAA Advisory Circular 43.13-1A.

C) Visually inspect the existing alternator to airframe ground for proper installation (Reference View A-A of SE79-59), evidence of looseness at the terminal and adequate length to allow for relative motion between the alternator and airframe. Also, visually verify that the ground straps between the engine and airframe mount are installed and provide continuity between the engine and mount. Correct any unsatisfactory conditions noted per FAA Advisory Circular 43.13-1A.

D) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

E) Any equivalent method of compliance with this Airworthiness Directive must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region, 601 E. 12th Street, Kansas City, Missouri 64106.

Cessna Single Engine Customer Care Service Information Letters SE79-5 dated February 26, 1979, SE79-58 dated November 23, 1979, and SE79-59 dated November 23, 1979, pertain to the subject matter of this AD.

This amendment becomes effective December 13, 1979.