75-14-04 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 2252 as amended by Amendment 39-2769 is further amended by Amendment 39-2948. Applies to Grumman G-164 S/N 101 through 400, G-164A S/N 401 through 1719, G-164B S/N 1B through 206B, and 208B through 277B, certificated in all categories.
1. Compliance required within 20 hours' time in service after the effective date of this AD, unless already accomplished within the last 80 hours' time in service, and thereafter within 100 hours' time in service from the last inspection.
2. a. For the models G-164 and G-164A inspect the rudder cable P/N A1860- 35, -36 within the cockpit floorboard and chafe strip area for fraying.
b. For the Model G-164B inspect the rudder cables P/N A3860-1, -3, within the cockpit floorboard and chafe strip area for fraying.
c. Replace any cables that show broken strands. Defective components must be replaced with the same part number or with approved equivalent parts.
3. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection interval in this AD.
4. Equivalent parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
5. Aircraft altered to incorporate the pulley and bracket P/N AN220-1 and A1839- 11 and -12, respectively, or altered in accordance with Grumman American Drawing A3371-1, and -3 "Foot Rail Assembly" are considered to have complied with the AD.
(Service Bulletin No. 56B dated October 4, 1976, is concerned with this subject).
Amendment 39-2252 was effective July 8, 1975.
Amendment 39-2769 was effective November 17, 1976.
This amendment 39-2948 is effective July 7, 1977.