53-24-01: Stabilizer Strut Terminal

53-24-01 GRUMMAN AIRCRAFT: Amendment 39-1264. Applies to all G-21A (Converted OA-9, JRF-1 through JRF-5 Under TC 654) Aircraft. Compliance required as indicated. 1. Within the next 50 hours in service after the effective date of the revision to this airworthiness directive, unless already accomplished within the last 50 hours' in service and at intervals thereafter not to exceed 50 hours' in service, accomplish Paragraph (3) for the stabilizer forward attachment fittings (P/N 12548 and P/N 12093). 2. Within the next 100 hours' in service after the effective date of this airworthiness directive, unless already accomplished within the last 100 hours in service and at intervals thereafter not to exceed 100 hours in service, accomplish paragraph (3) for the upper terminal (P/N 12561-1) of stabilizer strut (P/N 12560). 3. Inspect for cracks extending radially from the outside edge of the ears to the inside of the hole into which the shoulder bushings are pressed.Cracked parts must be replaced before further flight with parts inspected in accordance with this Directive or with equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. 4. Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance times specified in this airworthiness directive may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 5. (Grumman Aircraft Engineering Corporation Service Bulletin No. 21 dated March 17, 1948, and Customer Bulletin No. 5 dated October 30, 1953 cover this same subject). AD 53-24-01 which was to have been accomplished by January 15, 1954 supersedes AD 48-18-01. This amendment 39-1264 is effective August 17, 1971.