75-24-08 CANADAIR: Amendment 39-2431. Applies to all CL-44D4 and CL-44J airplanes, certificated in all categories, but not altered in accordance with Canadair Service Bulletin 44-478.
Compliance required within the next 25 landings, unless already accomplished within the last 275 landings, and thereafter at subsequent intervals not to exceed 300 landings, after the effective date of this AD.
To detect fretted, pitted or cracked main landing gear actuator attachment bolts, P/N SD300-55880, SD300-65779 or SD300-65779-12S, inspect and, if necessary, replace bolts in accordance with Canadair Service Information Circular 328-CL44D4, Issue 2 or an approved equivalent inspection and part replacement.
Bolts found to be in good condition may be reinstalled provided:
(a) they are of a type specified for replacement in the Canadair SIC 328-CL44D4 or are approved equivalent bolts;
(b) they have not exceeded the life limits specified in Canadair SIC 328-CL44D4; and
(c)they have not been reworked.
Equivalent inspection or parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
Upon request, with substantiating data submitted through an FAA maintenance inspector, the compliance time of this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
This amendment is effective November 25, 1975.