AD 90-09-07

90-09-07 SCHWEIZER AIRCRAFT CORPORATION (HUGHES HELICOPTER INC): Amendment 39-6717. Final Rule of priority letter AD. Docket No. 90-ASW-29-AD.

Applicability: Model 269C series helicopters, serial number (S/N) 0004 through 1456, certificated in any category.

Compliance: Required prior to further flight after the effective date of this AD, unless already accomplished.

To prevent possible loss of longitudinal cyclic control and subsequent loss of the helicopter, accomplish the following:

(a) Inspect the lower longitudinal cyclic control rod assembly, part number (P/N) 269A9940-7, to verify the proper location of the rod spring attachment clamp, P/N AN735-9, and position of the spring attach angles as follows:

(1) Gain access to the lower longitudinal cyclic control rod assembly.

(2) Position the cyclic stick to the full forward position. Verify that the stud in the friction linkage is completely forward in the friction link slot. If not, see paragraph (b).

(3) On the lower longitudinal cyclic control rod assembly, measure the distance between the aft face of the forward jam nut and the forward edge of the clamp, P/N AN735-9. The distance should be between 7.85 and 7.97 inches. If not, see paragraph (b).

(4) Verify that the horizontal legs of the angles attached to the clamp, P/N AN735-9, are parallel to the control rod and aligned with each other. If not, see paragraph (b). If correct, prevent movement of the parts, and torque the clamp nut to 20-25 in-lb.

(b) Adjust the clamp and the attached angles, if necessary, by disconnecting the springs and loosening the screw and nut holding the angles and clamp, P/N AN735-9, together. Set a distance of 7.85 to 7.97 inches between the aft face of the rod forward jam nut and the forward edge of the clamp, P/N AN735-9. Position the horizontal legs of the angles attached to the clamp, P/N AN735-9, parallel to the control rod, and align with each other. Prevent movementof the parts, and torque the nut to 20-25 in-lb. Determine that the clamp is secure. Reconnect the springs to the angles.

(c) Install the new worm type hose clamp, P/N AN737TW22 or AN737TW24, on the control rod, forward of and touching the clamp, P/N AN735-9. Torque the screw to a range of 40-45 in-1b. Determine that the clamp is secure.

(d) Aircraft may be ferried in accordance with the provisions of FAR Sections 21.197 and 21.199 to a base where the requirements of the AD can be accomplished, provided cyclic control displacement is not reduced.

(e) Alternate inspections, modification, or other actions which provide an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, 181 South Franklin Avenue, Room 202, Valley Stream, New York.

NOTE: Schweizer Service Bulletin No. B237 pertains to the requirements of this AD.

This amendment (39-6717, AD 90-09-07) becomes effective October 3, 1990, as to allpersons except those persons to whom it was made immediately effective by Priority Letter AD 90-09-07, issued on April 24, 1990, which contained this amendment.