AD 81-07-01 R1
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
Loss of structural rigidity in the horizontal stabilizer which could result in hazardous tail flutter and subsequent loss of airplane control.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Modify the horizontal stabilizer to incorporate mass balance weights, improved riveting, access panels, and structural reinforcements per Service Bulletin NMD-55-10, Rev. 1. Install high strength steel trim tab control brackets, self-aligning control rod ends, and longer control rods per Service Bulletin NMD-55-8, Rev. 3. Modify horizontal stabilizer pivot bracket attachments per Alert Service Bulletin ANMD-55-13, Rev. 1. Replace AGS pop rivets with MS20470AD rivets where removed during modification. Equivalent means require FAA approval.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within the next 25 hours time in service after the effective date of this AD
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Nomad TC Pty Ltd Model N22B (Serial Nos. N22B-5 and up) and N24A (Serial Nos. N24A-42 and up) airplanes
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Horizontal Stabilizer Modification
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_81-07-01_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-07-01 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Model N22B and N24A Airplanes Subject: Horizontal Stabilizer Modification Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/10/1982 Make: Nomad TC Pty Ltd Model: N22B | N24A Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 81-07-01 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4388 AD NUMBER: 81-07-01 R1 SUBJECT HEADING: Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Model N22B and N24A Airplanes ACTION: SUMMARY: DATES: Effective June 10, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 81-07-01 R1 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-4068 as amended by Amendment 39-4388. Applies to Nomad Model N22B (Serial Nos. N22B-5 and up) and N24A (Serial Nos. N24A-42 and up) airplanes, certificated in all categories. Compliance required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To prevent loss of structural rigidity which could result in hazardous tail flutter and subsequent loss of airplane control, accomplish the following (a) Modify the horizontal stabilizer to incorporate mass balance weights, improved riveting, addition of access panels, and structural reinforcements to the horizontal stabilizer in accordance with Part 2, "ACCOMPLISHMENT INSTRUCTIONS," of Government Aircraft Factories Nomad Service Bulletin NMD-55-10, Revision 1, dated May 2, 1980, or an FAA- approved equivalent. All AGS pop rivets removed as a result of this modification must be replaced with MS20470AD rivets. NOTE: AGS 2048-420-BS 1/8 inch pop rivets are acceptable in the access panel door as specified in Service Bulletin NMD-55-10, Rev. 1. (b) Install high strength steel trim tab control brackets, self-aligning control rod ends, and longer control rods in accordance with Part 2, "ACCOMPLISHMENT INSTRUCTIONS," of Government Aircraft Factories Nomad Service Bulletin NMD-55-8, Revision 3, dated September 1, 1980, or an FAA-approved equivalent. (c) Modify the horizontal stabilizer pivot bracket attachments in accordance with Part 2, "ACCOMPLISHMENT INSTRUCTIONS," of Government Aircraft Factories Nomad Alert Service Bulletin ANMD-55-13, Revision 1, dated August 22, 1980, or an FAA-approved equivalent. (d) In accordance with FAR 21.197 and 21.199 the airplane may be flown to a location where these modifications can be accomplished. (e) If an equivalent means of compliance is used in complying with paragraphs (a) through (c) of this AD, that equivalent means must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Government Aircraft Factories, 226 Lorimer Street, Port Melbourne 3207 Vic., Australia. These documents may be examined at FAA, Pacific-Asia Region, Engineering and Manufacturing District Office, 300 Ala Moana Blvd., Room 7321, Honolulu, Hawaii, and at FAA Headquarters, Room 916, 800 Independence Avenue, S.W., Washington, DC. Amendment 39-4068 became effective April 2, 1981. This amendment 39-4388 becomes effective on June 10, 1982. FOOTER:
Document Text
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AD Final Rules - DRS_81-07-01_R.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-07-01 R1 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Model N22B and N24A Airplanes Subject: Horizontal Stabilizer Modification Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/10/1982 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: 81-07-01 R1 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4388 AD NUMBER: 81-07-01 R1 SUBJECT HEADING: Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Model N22B and N24A Airplanes ACTION: SUMMARY: DATES: Effective June 10, 1982. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 81-07-01 R1 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-4068 as amended by Amendment 39-4388. Applies to Nomad Model N22B (Serial Nos. N22B-5 and up) and N24A (Serial Nos. N24A-42 and up) airplanes, certificated in all categories. Compliance required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To prevent loss of structural rigidity which could result in hazardous tail flutter and subsequent loss of airplane control, accomplish the following (a) Modify the horizontal stabilizer to incorporate mass balance weights, improved riveting, addition of access panels, and structural reinforcements to the horizontal stabilizer in accordance with Part 2, "ACCOMPLISHMENT INSTRUCTIONS," of Government Aircraft Factories Nomad Service Bulletin NMD-55-10, Revision 1, dated May 2, 1980, or an FAA- approved equivalent. All AGS pop rivets removed as a result of this modification must be replaced with MS20470AD rivets. NOTE: AGS 2048-420-BS 1/8 inch pop rivets are acceptable in the access panel door as specified in Service Bulletin NMD-55-10, Rev. 1. (b) Install high strength steel trim tab control brackets, self-aligning control rod ends, and longer control rods in accordance with Part 2, "ACCOMPLISHMENT INSTRUCTIONS," of Government Aircraft Factories Nomad Service Bulletin NMD-55-8, Revision 3, dated September 1, 1980, or an FAA-approved equivalent. (c) Modify the horizontal stabilizer pivot bracket attachments in accordance with Part 2, "ACCOMPLISHMENT INSTRUCTIONS," of Government Aircraft Factories Nomad Alert Service Bulletin ANMD-55-13, Revision 1, dated August 22, 1980, or an FAA-approved equivalent. (d) In accordance with FAR 21.197 and 21.199 the airplane may be flown to a location where these modifications can be accomplished. (e) If an equivalent means of compliance is used in complying with paragraphs (a) through (c) of this AD, that equivalent means must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Government Aircraft Factories, 226 Lorimer Street, Port Melbourne 3207 Vic., Australia. These documents may be examined at FAA, Pacific-Asia Region, Engineering and Manufacturing District Office, 300 Ala Moana Blvd., Room 7321, Honolulu, Hawaii, and at FAA Headquarters, Room 916, 800 Independence Avenue, S.W., Washington, DC. Amendment 39-4068 became effective April 2, 1981. This amendment 39-4388 becomes effective on June 10, 1982. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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