AD 80-13-07

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AD Number:
80-13-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Models N22B and N24A Airplanes
Subject:
Aileron Control
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/06/1980
Make:
Nomad TC Pty Ltd
Model:
N22B | N24A
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 80-13-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3806

AD NUMBER:   80-13-07

SUBJECT HEADING:   Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Models N22B and N24A Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 6, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-13-07 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-3806. Applies to Models N22B (Serial Nos. N22B-5 and up) and N24A (Serial Nos. N24A-42 and up).

Compliance required as indicated. To prevent possible control obstruction when aileron is applied at the extreme aft stick position, accomplish the following:

(a) Before the first flight of each day, until inspected per paragraph (b) of this AD, check the longitudinal and lateral controls for freedom of movement in the aft stick position by application of full left and right aileron. This check may be performed by the pilot-in-command and shall be recorded in the appropriate aircraft records in accordance with FAR 91.173. If interference is detected, accomplish paragraph (b) before further flight except that the aircraft may be flown in accordance with FAR 21.197 and FAR 21.199 to a base where the repair can be performed.

(b) Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, inspect the gimbal support structure tie rod attachment plates and take corrective action as necessary to ensure that a minimum clearance of 0.125 inches exists between the end of the control wheel attachment bolt and the attachment plates in accordance with Part B of GAF Alert Service Bulletin ANMD-27-14 dated December 3, 1979, or an FAA approved equivalent.

(c) The equivalent means of compliance specified in this AD must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii.

NOTE: All persons affected by this directive who have not already received the applicable service bulletin from the manufacturer, may obtain copies upon request to the Government Aircraft Factories, 226 Lorimer Street, Port Melbourne, 3207 Vic., Australia. This document may be examined at the FAA, Engineering and Manufacturing District Office, 300 Ala Moana Blvd., Room 7321, Honolulu, Hawaii 96850, or Rules Docket, Room 916, FAA, 800 Independence Ave., S.W., Washington, D.C. 20591.

This amendment becomes effective July 6, 1980.

FOOTER: