AD 82-16-11 ACTIVE

82-16-11 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-4435. Applies to Nomad Model N22B land planes only (S/Ns N22B-5 thru N22B-101 having horizontal stabilizer mass balance trim tabs except as noted in paragraphs A)(1) and A)(2) of this AD) certificated in any category. NOTE: Installation of horizontal stabilizer mass balance trim tabs in accordance with GAF Factory Modification No. N439 can be determined by visual inspection and verification that trim tab balance weights are installed on the inboard and outboard ends of each trim tab.

COMPLIANCE: Required as indicated unless previously accomplished. A) To improve airplane controllability in severe turbulence when loaded near the aft C.G. limit, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following:

(1) Assemble and install a new horizontal stabilizer control rod and modified torque shaft in accordance with the instructions contained in GAF Nomad Service BulletinNMD 27-9 Revision 1 dated April 30, 1982. GAF Modification N211 is the same as this Service Bulletin. It has been incorporated by the manufacturer on S/Ns 26, 55, 90, 93, 95, 102 and subsequent and modification of these S/Ns to this paragraph is not required.

(2) Remove the pulley mounting bracket at Station 399 and replace with redesigned bracketry to obtain direct cable/pulley alignment in accordance with GAF Nomad Service Bulletin NMD-27-15 dated December 23, 1981. GAF Modification N63 is the same as this Service Bulletin. It has been incorporated by the manufacturer on S/Ns 82 and subsequent and modification of those S/Ns to this paragraph is not required.

(3) Remark the horizontal stabilizer trim indicator drum assembly by attaching a new label per the procedure as outlined in paragraph 2.Q. of GAF Nomad Service Bulletin NMD-27-9 dated March 10, 1982.

(4) With the modification incorporated, verify that the horizontal stabilizer rigging angle has changed from 3-1/2 degrees plus or minus 1/2 degree stabilizer (not aircraft) nosedown to 3 degrees plus or minus 1/2 degree nosedown. For rigging instructions, see Maintenance Manual (MM) 27-40-00. (Service Bulletin NMD 27-9 Rev. 1 dated April 30, 1982, provides an alternate procedure.)

NOTE: On completion of rigging, check controls for correct sense (direction) or operation and for full and free movement under all trim conditions. In particular, ensure that positive clearance exists between the tab and the horizontal stabilizer trailing edge structure through full range of stabilizer travel with full noseup (aircraft) trim selected.

B) 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 provided the aft C.G. does not exceed 35 percent MAC.

C) An alternate means of compliance with this AD may be used if approved by the Chief, Honolulu Aircraft Certification Field Office, Northwest Mountain Region, Federal Aviation Administration, 300 Ala Moana Boulevard, Honolulu, Hawaii 96850.
This amendment becomes effective on August 12, 1982.