Results
2000-05-15: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS355N helicopters. This action requires inspecting the: 4 engine exhaust pipe ejector attachment lugs (lugs) for cracks; starter-generator (S-G) shaft for radial play; S-G attachment flange for cracks; and S-G attachment half- clamps for cracks. This amendment is prompted by 9 reports of S-G damage; 3 reports of the discovery of cracks in the lugs; and 1 report of an in-flight loss of the exhaust pipe ejector. The actions specified in this AD are intended to prevent separation of an engine exhaust pipe ejector from the helicopter, which could result in a tail rotor strike and subsequent loss of control of the helicopter.
2021-05-07: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model BO-105A, BO-105C, BO-105S, MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4, MBB- BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters. This AD was prompted by a report of a loss of electrical ground between the starter-generator and the generator voltage regulator (regulator). This AD requires inspecting the starter-generator electrical ground connection, retrofitting the starter-generator wire harness, and depending on model, revising the existing Rotorcraft Flight Manual (RFM) for your helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
2003-10-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Dassault Model Mystere-Falcon 50 series airplanes. This action requires a detailed inspection for clearance and chafing of the entire length of the hydraulic lines located within the engine pylons, and follow-on/corrective actions, as applicable. This action also requires a revision of the maintenance manual to ensure that the clamps that hold the hydraulic lines are in their initial position during normal maintenance, and that the position is identified with a yellow paint line. This action is necessary to prevent chafing and consequent leakage of the hydraulic lines located within the No. 1 and No. 3 engine pylons, which can result in failure of the No. 1 and No. 2 hydraulic systems, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2000-05-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Fan Jet Falcon series airplanes; Model Mystere-Falcon 20, 50, 200, and 900 series airplanes; and Model Falcon 10, 900EX, and 2000 series airplanes, that requires a functional test of the passenger oxygen masks, determination of the part number of the installed oxygen mask bags; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to ensure that proper plastic bags of the passenger oxygen masks are installed, and that the masks are functioning properly. Improper plastic bags that have cracks or improperly functioning masks could result in insufficient oxygen to passengers in the event of rapid depressurization of the airplane.
2003-08-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2003-08-52 that was sent previously to all known U.S. owners and operators of GE Aircraft Engines (GEAE) CT7-9B turboprop engines. This AD requires rigging the compressor variable geometry (VG) to VG schedule N. This AD is prompted by reports of 12 compressor stall events that occurred over a six-month period. The actions specified in this AD are intended to prevent a dual-engine in-flight shutdown or power loss due to a compressor stall during deceleration from takeoff power to climb power.
2013-08-03: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-300, A340-200 and A340-300 series airplanes. This AD was prompted by a report that revealed the wheel axles of the main landing gear (MLG) were machined with a radius as small as 0.4 millimeters. This AD requires replacing the wheel axle of the MLG with a serviceable part. We are issuing this AD to prevent fatigue of the wheel axle of the MLG, which could adversely affect the structural integrity of the airplane.
74-26-06: 74-26-06 LOCKHEED-CALIFORNIA: Amendment 39-2049 as amended by Amendment 39-2104. Applies to all L-1011-385-1 Series Airplanes certificated in all categories, incorporating Engine Shutoff Control Panel Assemblies, P/N 1520324 or P/N 1580810, all configurations. Compliance required as indicated, unless already accomplished. To provide protection in the event of an unknown incipient failure condition in the housing of the fire pull handle assembly, P/N 1520324 or P/N 1580810, accomplish the following: (1) Within 600 hours time in service after the effective date of this AD, as amended, (a) Modify the Control Panel Assembly, P/N 1520324 or P/N 1580810, in accordance with Part 2 of Lockheed Service Bulletin 093-26-010, dated November 21, 1974, revised February 11, 1975 or later FAA-approved revisions. (b) Re-identify all modified Control Panel Assemblies in accordance with Part 3B of Lockheed Service Bulletin 093-26-010, dated November 21, 1974, revised February 11,1975, or later FAA-approved revisions. (2) Equivalent repairs or modifications may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiating data. Note: Those engine shutoff control panel assemblies marked as P/N 1604009 or P/N 1605009 are in compliance with this AD. Amendment 39-2049 was effective December 23, 1974. This amendment 39-2104 to AD 74-26-06 becomes effective March 4, 1975.
2013-08-06: We are adopting a new airworthiness directive (AD) for Bell Model 430 helicopters, which requires replacing certain components of the air data system. This AD was prompted by the discovery of incorrect indicated airspeed when the helicopter was tested to the cold temperature limits (-40 degrees centigrade) required for Category A operations. The actions of this AD are intended to correct the published Vne and to correct the indicated airspeed.
93-02-12: 93-02-12 BEECH AIRCRAFT CORPORATION: Amendment 39-8495. Docket 92-NM-183-AD. Applicability: Model 400A airplanes; serial numbers RK-2 through RK-29, inclusive, RK-31, and RK-32; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the loss of standby power and the possibility of an electrical fire, accomplish the following: (a) Within 100 hours time-in-service after the effective date of this AD, inspect the left-hand interstage turbine temperature (LH ITT) circuit breaker wiring, in accordance with Beechcraft Service Bulletin No. 2458 (ATA Code 39-10), dated August 1992. Prior to further flight, correct any discrepancies found, in accordance with the service bulletin. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Wichita Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspection shall be done in accordance with Beechcraft Service Bulletin No. 2458 (ATA Code 39-10), dated August 1992. (NOTE: The issue date of Beechcraft Service Bulletin No. 2458 is indicated only on "page 1 of 5"; no other page is dated.) This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085.Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on March 26, 1993.
74-25-05: 74-25-05 SIKORSKY: Amendment 39-2030. Applies to S-61L, S-61N, S-61NM and S- 61R helicopters certificated in all categories including Military Type CH-3C helicopters equipped with S6115-20501 series, S6115-20601 series, S6117-20101 series, and S6188-15001 series main rotor blades except for blades with serial numbers subsequent to 61M-6350-6105 and blades which have had all main rotor blade pockets replaced by Sikorsky Aircraft after October 30, 1972. Compliance required within 5 hours time in service after the effective date of this AD. The maximum never exceed speed is hereby reduced to 110 knots. Install placards as close as practicable to the airspeed indicators reading as follows: "Never exceed speed 110 knots." This supersedes telegram dated October 8, 1974 and supersedes the maximum never exceed speed established by Airworthiness Directive 74-20-7, Amendment 39-1989. This amendment becomes effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated November 6, 1974.