82-12-06 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-4399. Applies to Nomad Models N22B and N24A (Serial Nos. N22B/N24A-5 through 111, 114, 115, 117, 119 and 120) airplanes, certificated in any category which do not incorporate GAF Modification No. 567.
COMPLIANCE: Required as indicated unless previously accomplished.
To preclude failure of the rudder control system, accomplish the following:
A) Within the next 25 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours time-in-service from the last inspection:
1) Visually inspect, using at least a 5 power magnifier and supplemental lighting as necessary, all rudder control lever shafts, Part Nos. 1/N-45-1102, 1/N-45-1103, and 1/N-45-1104 (ref. items 6, 10, and 11, respectively GAF Illustrated Parts Catalogue (IPC) 27-20- 02, Figure 4) for cracking in the area of the welded joints between the levers and the tubular shaft. Pay particular attention tothe ends of the welds at the lever flanges. (To gain access to the rudder control lever shafts, remove rudder pedal and control column guards in the flight compartment.)
CAUTION: Do not operate flight controls with components disconnected or when personnel area working in the area concerned. Injury to personnel or damage to components and structure could occur.
2) If cracks are found, before further flight, replace with new or serviceable rudder control shafts verified to be free from cracks and installed in accordance with paragraph C) of this AD.
B) Within the next 100 hours time-in-service after the effective date of this AD, check the axial fit of all rod end bearings in lever shafts Part Nos. 1/N-45-1102, 1/N-45-1103 and 1/N- 45-1104. The maximum allowable clearance between rod end bearing and lever before tightening bearing bolt is .010 inch (.25 mm). Add shims or washers and change bolt length in accordance with GAF Alert Service Bulletin ANMD 27-23 dated February 17, 1982, and Revision 1 dated February 19, 1982, to achieve this.
C) Discontinue the inspection per paragraph A when lever shafts Part Nos. 1/N-45- 1102, 1/N-45-1103 and 1/N-45-1104 are removed from aircraft and verified that they are free from cracks by magnetic particle inspection or dye penetrant methods. Serviceable removed or new parts should be installed in accordance with the instructions contained in Part B of GAF Alert Service Bulletin ANMD 27-23 dated February 17, 1982, and Revision 1 dated February 19, 1982.
D) A special flight permit may be issued in accordance with FAR 21.197 to allow flight of the airplane to a location where this AD may be accomplished.
E) The intervals between repetitive inspections required by this AD may be adjusted up to plus or minus 10 percent of the specified intervals to allow accomplishing these inspections during an established inspection.
F) An alternate means of compliance with this AD may be used when approved bythe Chief, Honolulu Aircraft Certification Field Office, Northwest Mountain Region, Federal Aviation Administration, 300 Ala Moana Boulevard, Honolulu, Hawaii.
This amendment becomes effective on June 17, 1982.