AD 81-11-01
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Nomad TC Pty Ltd | N22B | Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Models N22 and N24 Series Airplanes |
| aircraft | Nomad TC Pty Ltd | N22S | Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Models N22 and N24 Series Airplanes |
| aircraft | Nomad TC Pty Ltd | N24A | Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Models N22 and N24 Series Airplanes |
Unsafe Condition
Improper operation of the emergency exit door handle and door locking mechanism could prevent the emergency exit door from opening, leading to door trim panel fracture or door inoperability during an emergency.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Within 10 hours time-in-service after the effective date, visually inspect the emergency exit door operation by rotating the handle and pushing outward 0.5 inches. If door does not open properly, remove trim panel, inspect door locking mechanism and linkage, correct assembly if needed, free and lubricate corroded or seized pins, reassemble, and reinspect. Record compliance in maintenance records.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within the next 10 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 Models N22B, N22S, N24A, all serial numbers
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Emergency Exit Door
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_81-11-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-11-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Models N22 and N24 Series Airplanes Subject: Emergency Exit Door Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/13/1981 Make: Nomad TC Pty Ltd Model: N22B | N22S | N24A Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 81-11-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4302 AD NUMBER: 81-11-01 SUBJECT HEADING: Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Models N22 and N24 Series Airplanes ACTION: SUMMARY: DATES: Effective May 13, 1981. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 81-11-01 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-4302. Applies to Nomad Models N22 and N24 series airplanes certificated in any category. COMPLIANCE: Required as indicated unless already accomplished. To assure the emergency exit can be opened when the emergency exit door handle is placed in the open position, within the next 10 hours time-in-service after the effective date of this AD, accomplish the following: A) Visually inspect the emergency exit door for proper operation by rotating the emergency exit door handle (interior) to the open position and open the door by physically pushing outward at the bottom of the exit door. It is only necessary to move the door 0.5 inches (12 millimeters) outward to assure proper emergency door operation and that the door latch pins are fully withdrawn. Further movement of the door beyond 0.5 inches could fracture the door trim panel at the lower edge. NOTE: Operation of the door-locking mechanism should not require undue force in complying with this paragraph. B) If the emergency exit door opens properly in accordance with paragraph A) of this AD, secure the door in the closed position and record compliance of this AD with an appropriate entry in the airplane maintenance records. C) If the emergency exit door handle will not rotate or the door will not open in accordance with paragraph A) of this AD, accomplish the following: 1. Remove the inner trim panel from the door in accordance with the manufacturer' s Maintenance Manual No. 25-20-00, page 201, paragraph 1B(3). 2. Visually inspect the door-locking mechanism, including linkage to door locking pins for proper assembly and also assure the door lock pins are free of corrosion and are not seized in the door frame or fuselage by performing the following as applicable: a) Proper assembly of the door lock assembly is assured if the forward door lock pin linkage rod is almost horizontal while the rear rod is angled upwards, thus as viewed from the inside, a clockwise rotation (towards open) of the exit door handle will withdraw the door locking pins. If the linkage is incorrectly assembled, refer to the manufacturer's Illustrated Parts Catalog No. 52-20-01, Figure 1, and: i. Disconnect both operating (linkage) rods (item 8) from the lever assembly (item12), by removing cotter pin, washer and connecting pins (items 9, 10 and 11). ii. Rotate the door lever (handle) assembly (item 12) so that the forward end is sloping upwards at approximately 45 degrees and reconnect the linkage rods using new cotter pins. iii. Rotate the door lever (handle) clockwise (open position) and confirm that the door lock pins can be withdrawn from the door frame and lubricate the locking pins with MIL-G-21164 grease or equivalent. b) If the door locking pins are corroded or seized in the door frame or fuselage, free the pins, remove any corrosion and lubricate the pins with MIL-G-21164 grease or equivalent. c) Reassemble the door and reinstall the trim panels. D) If any part of paragraph C) of this AD was completed, reaccomplish paragraph A) of this AD to assure the emergency exit opens properly and record compliance of this AD with an appropriate entry in the airplane maintenance records. E) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. F) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, P.O. Box 50109, Honolulu, Hawaii 96850. GAF-Nomad Telex Alert Service Bulletin ANMD-52-2 covers the subject matter of this AD. This amendment becomes effective on January 28, 1982, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated May 13, 1981, and identified as AD 81-11-01. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_81-11-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-11-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Models N22 and N24 Series Airplanes Subject: Emergency Exit Door Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/13/1981 Make: Nomad TC Pty Ltd Model: N22B | N22S | 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: 81-11-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4302 AD NUMBER: 81-11-01 SUBJECT HEADING: Airworthiness Directives; GOVERNMENT AIRCRAFT FACTORIES (GAF) Models N22 and N24 Series Airplanes ACTION: SUMMARY: DATES: Effective May 13, 1981. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 81-11-01 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-4302. Applies to Nomad Models N22 and N24 series airplanes certificated in any category. COMPLIANCE: Required as indicated unless already accomplished. To assure the emergency exit can be opened when the emergency exit door handle is placed in the open position, within the next 10 hours time-in-service after the effective date of this AD, accomplish the following: A) Visually inspect the emergency exit door for proper operation by rotating the emergency exit door handle (interior) to the open position and open the door by physically pushing outward at the bottom of the exit door. It is only necessary to move the door 0.5 inches (12 millimeters) outward to assure proper emergency door operation and that the door latch pins are fully withdrawn. Further movement of the door beyond 0.5 inches could fracture the door trim panel at the lower edge. NOTE: Operation of the door-locking mechanism should not require undue force in complying with this paragraph. B) If the emergency exit door opens properly in accordance with paragraph A) of this AD, secure the door in the closed position and record compliance of this AD with an appropriate entry in the airplane maintenance records. C) If the emergency exit door handle will not rotate or the door will not open in accordance with paragraph A) of this AD, accomplish the following: 1. Remove the inner trim panel from the door in accordance with the manufacturer' s Maintenance Manual No. 25-20-00, page 201, paragraph 1B(3). 2. Visually inspect the door-locking mechanism, including linkage to door locking pins for proper assembly and also assure the door lock pins are free of corrosion and are not seized in the door frame or fuselage by performing the following as applicable: a) Proper assembly of the door lock assembly is assured if the forward door lock pin linkage rod is almost horizontal while the rear rod is angled upwards, thus as viewed from the inside, a clockwise rotation (towards open) of the exit door handle will withdraw the door locking pins. If the linkage is incorrectly assembled, refer to the manufacturer's Illustrated Parts Catalog No. 52-20-01, Figure 1, and: i. Disconnect both operating (linkage) rods (item 8) from the lever assembly (item12), by removing cotter pin, washer and connecting pins (items 9, 10 and 11). ii. Rotate the door lever (handle) assembly (item 12) so that the forward end is sloping upwards at approximately 45 degrees and reconnect the linkage rods using new cotter pins. iii. Rotate the door lever (handle) clockwise (open position) and confirm that the door lock pins can be withdrawn from the door frame and lubricate the locking pins with MIL-G-21164 grease or equivalent. b) If the door locking pins are corroded or seized in the door frame or fuselage, free the pins, remove any corrosion and lubricate the pins with MIL-G-21164 grease or equivalent. c) Reassemble the door and reinstall the trim panels. D) If any part of paragraph C) of this AD was completed, reaccomplish paragraph A) of this AD to assure the emergency exit opens properly and record compliance of this AD with an appropriate entry in the airplane maintenance records. E) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. F) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, P.O. Box 50109, Honolulu, Hawaii 96850. GAF-Nomad Telex Alert Service Bulletin ANMD-52-2 covers the subject matter of this AD. This amendment becomes effective on January 28, 1982, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated May 13, 1981, and identified as AD 81-11-01. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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