AD 81-08-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Nomad TC Pty Ltd | N22B | Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Model N22B and N24A Airplanes |
| aircraft | Nomad TC Pty Ltd | N24A | Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Model N22B and N24A Airplanes |
Unsafe Condition
Wear in the horizontal stabilizer trim tab control linkages and excessive free play causing instability.
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Required Actions
Modify the horizontal stabilizer structure to accept balanced trim tabs per GAF Service Bulletin NMD-55-12, Part A within 50 hours time in service. Install balanced trim tabs per Part B of the same Service Bulletin within 100 hours time in service. Equivalent FAA-approved methods are acceptable.
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Compliance Time
Within the next 50 hours time in service after the effective date of this AD for paragraph (a), and within the next 100 hours time in service after the effective date for paragraph (b).
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Affected Aircraft
Nomad TC Pty Ltd Model N22B (Serial Nos. N22B-5 and up) and Model N24A (Serial Nos. N24A-42 and up)
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Federal Register Abstract
Horizontal Stabilizer Structure
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_81-08-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-08-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Model N22B and N24A Airplanes Subject: Horizontal Stabilizer Structure Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/23/1981 Make: Nomad TC Pty Ltd Model: N22B | N24A Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 81-08-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4084 AD NUMBER: 81-08-03 SUBJECT HEADING: Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Model N22B and N24A Airplanes ACTION: SUMMARY: DATES: Effective April 23, 1981. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 81-08-03 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-4084. Applies to Nomad Model N22B (Serial Nos. N22B-5 and up) and Model N24A (Serial Nos. N24A-42 and up), airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To reduce the rate of wear experienced in the horizontal stabilizer trim tab control linkages and prevent instability due to excessive free play, accomplish the following: (a) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished, modify the horizontal stabilizer structure to accept the balanced trim tabs in accordance with Part A, "ACCOMPLISHMENT INSTRUCTIONS," of GAF Nomad Service Bulletin NMD-55-12, dated August 29, 1980, (hereinafter referred to as the Service Bulletin), or an FAA-approved equivalent. The trim tabs previously modified in accordance with Service Bulletin NMD-55-8 may be reinstalled until paragraph (b) is accomplished. (b) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, install the balanced trim tabs in accordance with Part B of the Service Bulletin, or an FAA-approved equivalent. (c) If an equivalent means of compliance is used in complying with paragraphs (a) and (b) of this AD, that equivalent means must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii. This amendment becomes effective April 23, 1981. FOOTER:
Document Text
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AD Final Rules - DRS_81-08-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-08-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Model N22B and N24A Airplanes Subject: Horizontal Stabilizer Structure Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/23/1981 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: 81-08-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4084 AD NUMBER: 81-08-03 SUBJECT HEADING: Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Model N22B and N24A Airplanes ACTION: SUMMARY: DATES: Effective April 23, 1981. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 81-08-03 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-4084. Applies to Nomad Model N22B (Serial Nos. N22B-5 and up) and Model N24A (Serial Nos. N24A-42 and up), airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To reduce the rate of wear experienced in the horizontal stabilizer trim tab control linkages and prevent instability due to excessive free play, accomplish the following: (a) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished, modify the horizontal stabilizer structure to accept the balanced trim tabs in accordance with Part A, "ACCOMPLISHMENT INSTRUCTIONS," of GAF Nomad Service Bulletin NMD-55-12, dated August 29, 1980, (hereinafter referred to as the Service Bulletin), or an FAA-approved equivalent. The trim tabs previously modified in accordance with Service Bulletin NMD-55-8 may be reinstalled until paragraph (b) is accomplished. (b) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, install the balanced trim tabs in accordance with Part B of the Service Bulletin, or an FAA-approved equivalent. (c) If an equivalent means of compliance is used in complying with paragraphs (a) and (b) of this AD, that equivalent means must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii. This amendment becomes effective April 23, 1981. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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