AD 61-22-02

61-22-02 CANADAIR: Amdt. 355 Part 507 Federal Register November 1, 1961. Applies to all CL-44D4 aircraft.

Compliance required as indicated.

Failures have occurred on the main landing gear rotation lever P/N 4487528 on Model CL-44D4 aircraft. Failure of the lever can cause the landing gear to remain in "up" position when the lever is operated to lower the gear.

The following must be accomplished pending the development and installation of a Canadian Department of Transport and FAA approved modification of the affected parts after which no further inspection will be required:

(a) Within the next 45 hours' time in service unless already accomplished within the past 180 hours' time in service and at intervals not exceeding 225 hours' time in service thereafter conduct the dye penetrant inspection specified in Canadair Service Information Circular No. 27- CL-44D4 or FAA approved equivalent. Cracked levers must be replaced prior to further flight except for a ferry flightin accordance with the provisions of CAR 1.76.

(b) Subsequent to the effective date of this AD, at intermediate intervals between dye penetrant inspections not exceeding each 45 hours' time in service, conduct a visual inspection of the affected part. Cracked levers must be replaced prior to further flight except for a ferry flight in accordance with the provisions of CAR 1.76.

(c) Upon request of the operator an FAA maintenance inspector subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator.

This directive effective November 1, 1961.