Results
2003-08-53: This document publishes in the Federal Register an amendment adopting a superseding Airworthiness Directive (AD) 2003-08-53, sent previously to all known U.S. owners and operators of the specified Eurocopter France (Eurocopter) model helicopters by individual letters. This AD requires, in addition to the checks and tapping test inspections required in the existing AD, adding the Eurocopter Model AS 365 N3 to the applicability and correcting tail rotor blade (blade) part numbers. Also, this AD requires doing tapping tests for bonding separation on blades and removing certain blades at specified intervals. The actions specified by this AD are intended to prevent failure of a blade, loss of tail rotor control, and subsequent loss of control of the helicopter. \n\nDATES: Effective June 20, 2003, to all persons except those persons to whom it was made immediately effective by Emergency AD 2003-08-53, issued on April 23, 2003, which contained the requirements of this amendment.
95-03-12: This amendment supersedes an existing airworthiness directive (AD), applicable to Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A series helicopters, that currently requires an initial and repetitive visual inspections of the clutch control spring assembly for component wear and replacement of affected unairworthy parts. This amendment requires the same initial and repetitive visual inspections and replacements required by the existing Priority Letter AD, but references a revised service bulletin and provides replacement procedures for the aluminum spring retainer thermofit tube (plastic sleeve). This amendment is prompted by a recent accident involving a Model 269C helicopter that reportedly lost engine drive power at 100 feet above ground level (AGL) with a resulting unsuccessful autorotative landing, and the manufacturer's issuance of revised service information that provides more detailed instructions for replacementof two components of the belt drive clutch control assembly. The actions specified by this AD are intended to prevent failure of the aluminum spring retainer, loss of power to the rotor drive system, and a subsequent forced landing.
2003-04-10: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes, that requires a one-time general visual inspection to find wire chafing damage and to determine adequate clearance between the disconnect panel structure and the wires above the aft left lavatory; and corrective actions, if necessary. This action is necessary to prevent damage to certain wires due to contact between the wires and the adjacent structure, which could result in electrical arcing and consequent smoke and fire in the cabin. This action is intended to address the identified unsafe condition.
2017-26-09: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR 42-500 airplanes and Model ATR 72-212A airplanes. This AD requires a one-time inspection for damage of the engine fire extinguishing pipes and incorrect pipe installation, and corrective actions if necessary. This AD was prompted by a report of damage to an engine fire extinguishing pipe due to chafing between the pipe and a fastener assembly; the chafing occurred as a result of incorrect installation of the pipe. We are issuing this AD to address the unsafe condition on these products.
2002-16-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain serial numbers (SN's) of Bombardier-Rotax GmbH type 912 F, 912 S and 914 F series reciprocating engines. This action requires replacement of the valve spring retainers, part number (P/N) 854.182, with the new-reinforced valve spring retainers, P/N 854.184. This amendment is prompted by reports of several cracked valve spring retainers discovered in-service. The actions specified in this AD are intended to prevent cracking of the valve spring retainers resulting in possible engine failure while in-flight.
95-03-13: This amendment supersedes an existing airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Company and Hughes Helicopters, Inc. Model 369 and OH-6A series helicopters with certain main rotor (M/R) blade assemblies or certain M/R hub lead-lag assemblies installed, that currently requires repetitive inspections and checks for cracks. This amendment requires the same inspections as the superseded AD, but would eliminate pilot checks, expand the areas of inspection, and require the application of slippage marks on each M/R blade root fitting lug and related bushings. This amendment is prompted by additional reports of cracks in the M/R blade root fittings, lugs, and adjacent blade skin, and movement of the root fitting bushings. The actions specified by this AD are intended to prevent failure of a M/R blade assembly or a M/R hub lead-lag link assembly, loss of a M/R blade, and subsequent loss of control of the helicopter.
47-49-03: 47-49-03 LOCKHEED: (Was Mandatory Note 36 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2080, Except 2033, 2058 and 2071 Through 2075. Compliance required at next engine change period. Inspect all attachments of rudders to torque tube flanges for evidence of stripped threads or elongated holes. (This does not require removal of rudders.) When such evidences are found, redrill holes to next larger size and/or install new nuts as required. (LAC Service Bulletin 49/SB-256 covers this same subject.)
2017-26-08: We are adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R[eacute]gional Model ATR42-500 and ATR72- 212A airplanes. This AD requires revising the airplane flight manual (AFM) to provide procedures to the flight crew for operational restrictions affecting in-flight use of the autopilot (AP) or yaw damper (YD) during dual-engine operation. This AD also provides an optional software modification, which would terminate the AFM requirement. This AD was prompted by flight test evaluations that revealed that after engine failure during AP or YD re-engagement, the YD unit commanded the rudder to return to neutral position, leading to inadequate balancing of the asymmetric power. We are issuing this AD to address the unsafe condition on these products.
2002-16-26: This amendment adopts a new airworthiness directive (AD) that is applicable to certain serial numbers (SN's) of Bombardier-Rotax GmbH type 912 F and 914 F series reciprocating engines. This action requires initial and repetitive visual inspections of the engine crankcase for cracks. This amendment is prompted by reports of several instances of engine crankcases found cracked in service. The actions specified in this AD are intended to prevent oil loss caused by cracks in the engine crankcase, which could lead to in-flight failure of the engine and forced landing.
2002-16-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes that have been converted from a passenger- to a cargo-carrying ("freighter") configuration, that requires require, among other actions, installation of a fail-safe hinge, redesigned main deck cargo door warning and power control systems, and 9g cargo barrier. This amendment is prompted by the FAA's determination that the main deck cargo door hinge is not fail-safe; that certain main deck cargo door control systems do not provide an adequate level of safety; and that the main deck cargo barrier is not structurally adequate during an emergency landing. The actions specified by this AD are intended to prevent structural failure of the main deck cargo door hinge or failure of the cargo door system, which could result in the loss or opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane, including possible loss of flight control or severe structural damage; and to prevent failure of the main deck cargo barrier during an emergency landing, which could injure occupants.