74-04-04 CANADAIR: Amendment 39-1787. Applies to all CL-44D4 and CL-44J airplanes which have experienced more than 7,000 landings. To detect cracks in the lugs of the rear spar attachment lower fitting, P/N 44-10149, of the main landing gear actuator, accomplish the following:
1. Within the next 100 landings after the effective date of this AD, unless accomplished within the last 900 landings, and at intervals thereafter not to exceed 1,000 landings, inspect the lower lugs of the main landing gear actuator rear spar attachment fitting, P/N 44-10149, for cracks using a dye penetrant method with a glass of at least 10-power or an approved equivalent inspection.
2. If cracks are found, reduce the inspection intervals as noted in the instructions of paragraphs i, ii, iii of the Inspection Data of Canadair Service Information Circular No. 371-CL- 44.
3. The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data, submitted through an FAA maintenance inspector.
4. Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
5. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552 (a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Canadair Limited, Attention: Mr. C. Bloom, P.O. Box 6078, Montreal, Canada. These documents may also be examined at the Engineering and Manufacturing Branch, FAA, Eastern Region, J.F.K. International Airport, Jamaica, New York 11430, and at FAA headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and at the Eastern Region.
This amendment is effective February 18, 1974.