AD 83-06-06
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | DeHavilland Support Limited | Beagle B.121 Series 1 | Airworthiness Directives; British Aerospace Model B.121, Series 1, 2, and 3 Series Airplanes |
| aircraft | DeHavilland Support Limited | Beagle B.121 Series 2 | Airworthiness Directives; British Aerospace Model B.121, Series 1, 2, and 3 Series Airplanes |
| aircraft | DeHavilland Support Limited | Beagle B.121 Series 3 | Airworthiness Directives; British Aerospace Model B.121, Series 1, 2, and 3 Series Airplanes |
Unsafe Condition
Failure of the Part Number BE.45.10193 Rudder Control Lever Assembly (or Assembly not identified as Part Number BE.45.50107) located at Fuselage Station 217.75.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect the Rudder Control Lever Assembly to determine its part number. If it is BE.45.10193 or cannot be identified, remove and inspect using visual and dye penetrant procedures per Service Bulletin No. B.121/71. Replace if a crack is found with Part No. BE.45.50107. Adjust inspection intervals up to 10% for maintenance scheduling. Use airplane hours time-in-service if records are unavailable.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within 50 hours time-in-service after the effective date of this AD and thereafter at intervals not to exceed 50 hours time-in-service from the last inspection
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
British Aerospace Model B.121, Series 1, 2, and 3 (all serial numbers)
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Rudder Control Lever Assembly
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_83-06-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 83-06-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; British Aerospace Model B.121, Series 1, 2, and 3 Series Airplanes Subject: Rudder Control Lever Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/04/1983 Make: DeHavilland Support Limited Model: Beagle B.121 Series 1 | Beagle B.121 Series 2 | Beagle B.121 Series 3 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: 83-06-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4593 AD NUMBER: 83-06-06 SUBJECT HEADING: Airworthiness Directives; British Aerospace Model B.121, Series 1, 2, and 3 Series Airplanes ACTION: SUMMARY: DATES: Effective April 4, 1983. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 83-06-06 BRITISH AEROSPACE, AIRCRAFT GROUP, SCOTTISH DIVISION: Amendment 39-4593. Applies to Model B.121, Series 1, 2, and 3 (all serial numbers) airplanes certificated in any category. COMPLIANCE: Required as indicated, unless already accomplished. To preclude failure of the Part Number BE.45.10193 Rudder Control Lever Assembly (or Assembly not identified by visual examination as Part Number BE.45.50107) located at Fuselage Station 217.75, within 50 hours time-in-service after the effective date of this AD and thereafter at intervals not to exceed 50 hours time-in-service from the last inspection, accomplish the following: (a) Visually inspect the Rudder Control Lever Assembly at Fuselage Station 217.75, to determine its part number. (b) If Part Number BE.45.50107 is determined to be installed, no further action is required. (c) If the part number cannot be determined, or is found to be number BE.45.10193, remove the Rudder Control Lever Assembly and inspect it using visual and dye penetrant procedures in accordance with Scottish Aviation Ltd., Service Bulletin No. B.121/71 dated December 29, 1976. Particular attention should be paid to areas near welds at the bases of all three levers. (d) If a crack is found in the Rudder Control Lever Assembly, replace it with a Part No. BE.45.50107 Rudder Control Lever Assembly before further flight. (e) The installation of a Part Number BE.45.50107 Rudder Control Lever Assembly constitutes terminating action for this AD. (f) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (g) Operators who have not kept records of hours time-in-service of the rudder control lever must substitute airplane hours time-in-service in lieu thereof. (h) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (i) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on April 4, 1983. FOOTER:
Document Text
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AD Final Rules - DRS_83-06-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 83-06-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; British Aerospace Model B.121, Series 1, 2, and 3 Series Airplanes Subject: Rudder Control Lever Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/04/1983 Make: DeHavilland Support Limited Model: Beagle B.121 Series 1 | Beagle B.121 Series 2 | Beagle B.121 Series 3 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: 83-06-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4593 AD NUMBER: 83-06-06 SUBJECT HEADING: Airworthiness Directives; British Aerospace Model B.121, Series 1, 2, and 3 Series Airplanes ACTION: SUMMARY: DATES: Effective April 4, 1983. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 83-06-06 BRITISH AEROSPACE, AIRCRAFT GROUP, SCOTTISH DIVISION: Amendment 39-4593. Applies to Model B.121, Series 1, 2, and 3 (all serial numbers) airplanes certificated in any category. COMPLIANCE: Required as indicated, unless already accomplished. To preclude failure of the Part Number BE.45.10193 Rudder Control Lever Assembly (or Assembly not identified by visual examination as Part Number BE.45.50107) located at Fuselage Station 217.75, within 50 hours time-in-service after the effective date of this AD and thereafter at intervals not to exceed 50 hours time-in-service from the last inspection, accomplish the following: (a) Visually inspect the Rudder Control Lever Assembly at Fuselage Station 217.75, to determine its part number. (b) If Part Number BE.45.50107 is determined to be installed, no further action is required. (c) If the part number cannot be determined, or is found to be number BE.45.10193, remove the Rudder Control Lever Assembly and inspect it using visual and dye penetrant procedures in accordance with Scottish Aviation Ltd., Service Bulletin No. B.121/71 dated December 29, 1976. Particular attention should be paid to areas near welds at the bases of all three levers. (d) If a crack is found in the Rudder Control Lever Assembly, replace it with a Part No. BE.45.50107 Rudder Control Lever Assembly before further flight. (e) The installation of a Part Number BE.45.50107 Rudder Control Lever Assembly constitutes terminating action for this AD. (f) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (g) Operators who have not kept records of hours time-in-service of the rudder control lever must substitute airplane hours time-in-service in lieu thereof. (h) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (i) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on April 4, 1983. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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