| AD Number | 83-06-06 | Status | Active |
| Effective Date | April 04, 1983 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-4593 |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | DeHavilland Support Limited |
| Model(s) | Beagle B.121 Series 1 Beagle B.121 Series 2 Beagle B.121 Series 3 |
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.