AD 86-16-12 ACTIVE

86-16-12 DeHAVILLAND: Amendment 39-5389. Applies to Model DHC-3 (all serial numbers) airplanes certificated in any category.

Compliance: Required as indicated, after the effective date of this AD, unless already accomplished.

To preclude loss of elevator control and to ensure proper operation of the control system, accomplish the following inspections and parts replacement:

(a) Within 25 hours time-in-service (TIS), after the effective date of this AD, visually inspect the following parts:

(1) The elevator pushrod, and the elevator pushrod to rear quadrant attachment bolt, for bending, in accordance with "ACCOMPLISHMENT INSTRUCTIONS" in DeHavilland Service Bulletins (S/B) No. 3/35, Revision A, dated April 11, 1980, and S/B No. 3/43, dated January 18, 1985.

(2) The threaded shank of the elevator pushrod rod ends, for cracks.

(3) All elevator control system cables and pulleys for damage or distortion.

(b) Replace unserviceable parts, prior to further flight, with serviceable pacts follows:

(1) Elevator pushrod with new pushrod Part Number (P/N) C3-CF-633-1, in accordance with "ACCOMPLISHMENT INSTRUCTIONS" in DeHavilland S/B No. 3/35, Revision A, dated April 11, 1980.

(2) Elevator pushrod to rear quadrant attachment bolt with a new NAS1954- 24D bolt, in accordance with paragraph (c) of this AD.

(3) Elevator control system cables and pulleys in accordance with the applicable section of the aircraft maintenance manual.

NOTE: When a parked DHC-3 airplane has been subjected to wind gusts of 60 mph or greater (including helicopter or jet blasts) damage may occur to the elevator control system, and the requirements specified in paragraphs (a) and (b) of this AD should be accomplished again.

(c) If the elevator pushrod to rear quadrant attachment bolt is replaced with a NAS1954-24D bolt, replace the associated hardware and in addition, replace the rudder pushrod to rear quadrant attachment bolt with a NAS1954-24D bolt and the associated hardware in accordance with "ACCOMPLISHMENT INSTRUCTIONS" in DeHavilland S/B No. 3/43 dated January 18, 1985. Torque nuts to 65 in-pounds prior to installation of cotter pins.

(d) If no damage is found during the inspection as required by paragraph (a) of this AD, within 60 days after the effective date of this AD, unless already accomplished:

(1) Replace the elevator pushrod in accordance with paragraph (b)(1) of this AD, and

(2) Replace the elevator and rudder pushrod to rear quadrant attachment bolts in accordance with paragraph (c) of this AD.

(e) The airplane may be flown in accordance with Federal Aviation Regulations (FAR) 21.197 to a location where the requirements of this AD may be accomplished.

(f) An equivalent method of compliance with this AD, if used, must be approved by the Manager, New York Aircraft Certification Office, ANE-170, FAA, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, NewYork 11581.

(g) Upon submission of substantiating data by an owner or operator, through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office, FAA, New- England Region, may adjust the compliance intervals specified in this AD.

All persons affected by this directive may obtain copies of the documents referred to herein upon request to DeHavilland Aircraft of Canada, Ltd., Downsview, Ontario, Canada, M3K 1Y5 or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment becomes effective on August 15, 1986.