Results
99-04-13: This amendment adopts a new airworthiness directive (AD) that is applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214ST helicopters. This action requires a reduction of the never-exceed velocity (Vne) limitation until an inspection of the tail rotor yoke (yoke) assembly for fatigue damage and installation of a redesigned yoke flapping stop are accomplished. Recurring periodic and special inspections to detect occurrences of yoke overload are also required. This amendment is prompted by reports of inflight failures of yokes installed on civilian and military helicopters of similar type design. The actions specified in this AD are intended to prevent fatigue failure of the yoke that could result in loss of the tail rotor and subsequent loss of control of the helicopter.
2009-18-19 R1: This amendment rescinds airworthiness directive (AD) 2009-18- 19 for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by EASA, to rescind EASA AD 2010-0083. The MCAI specifies the following: \n\n\n\tIt has been assessed that multiple NRV (non-return valve) failures in combination with certain trapped fuel cases could potentially increase the quantity of unusable fuel on the aeroplane, possibly leading to fuel starvation which could result in engines in-flight shut down and would constitute an unsafe condition. To prevent and detect this condition, EASA issued EASA AD 2010-0083. \n\tBased on in service experience, mainly on the results of the operational test required by \n\n((Page 33987)) \n\nEASA AD 2010-0083, Airbus has performed a safety analysis on the NRV to check if the safety objectives are met. \n\tThis analysis of the Collector Cell motive flow line NRV, taking into account all failure scenarios, concludes thatthe previous non compliance can be alleviated. Consequently, no unsafe condition exists any more on the affected NRV. \n\tFor the reasons described above, EASA AD 2010-0083 is cancelled. \n\n\n\tThis AD rescinds the parallel FAA AD 2009-18-19.
2003-01-03: This amendment adopts a new airworthiness directive (AD) that is applicable to Hartzell Propeller Inc. model ( )HC-( )2Y( )-( ) propellers, with certain serial numbers (SN's) of two-bladed aluminum propeller hubs part numbers (P/N's) D-6522-1, D-6522-2, D-6529-1, and D-6559-3 installed. This action requires removal from service of those certain SN's of two-bladed aluminum propeller hubs and replacement with serviceable hubs. This amendment is prompted by a two-bladed aluminum propeller hub manufacturing quality control problem. The actions specified in this AD are intended to prevent in-flight propeller blade separation resulting in airframe and engine damage, and possible loss of the airplane.
62-24-05: 62-24-05 MARECO SAFETY BELTS: Amdt. 503 Part 507 Federal Register November 3, 1962. Applies to All Aircraft Equipped With Mareco Model 15-1 Safety Belts Which Are Identified on the Manufacturer's Identification Label on the Safety Belt as Being Manufactured in the Third and Fourth Quarters of 1959 and the First and Second Quarters of 1960. Compliance required within the next 100 hours' time in service after the effective date of this AD. Service difficulties with the Mareco Model 15-1 safety belt assemblies have occurred wherein the buckle locking cam became disengaged when tension on the belt assembly was relieved and would not reengage upon application of tension to the belt assembly due to the cam spring slipping from its retention slot. Therefore, the following is required: Replace Mareco Model 15-1 safety belts manufactured in the third and fourth quarters of 1959 and the first and second quarters of 1960, or modify with an FAA approved modification to preventthe slipping of the cam spring from its retaining end slot and to correct the misalignment between the cam and buckle frame. When an FAA approved modification is made after the effective date of this AD, the buckle frame or cam lever shall be permanently marked "MOD." followed by the date of modification. NOTE: Belts which were modified prior to the effective date of this AD in accordance with an FAA approved modification and identified with an embossed "X" are acceptable. This directive effective December 4, 1962.
97-02-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 and 767 series airplanes, that requires replacement of the thrust management computer (TMC) with a new TMC. This amendment is prompted by reports indicating that an uncommanded advancement of the throttle levers occurred; this condition was apparently due to a high impedance connection to the excitation phase of the servo motor. The actions specified by this AD are intended to prevent an uncommanded runaway of the autothrottle during flight or ground operations as a result of problems associated with the TMC, which could distract the crew from normal operation of the airplane or lead to an unintended speed or altitude change.
2011-11-04: This amendment adopts a new airworthiness directive (AD) for the specified fire extinguishers. This action requires replacing each unairworthy portable fire extinguisher with an airworthy portable fire extinguisher. This amendment is prompted by an ongoing investigation that has established that unapproved Halon 1211 has been used to fill L'Hotellier portable fire extinguishers that are likely to be onboard various model helicopters. The actions specified in this AD are intended to prevent using contaminated gas that may reduce fire suppression and release toxic fumes that would endanger the safety of the helicopter and its occupants.
97-24-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires repetitive inspections of certain flanges and finger strips at rib 5.0 of the vertical stabilizer to detect fatigue cracking, and repairs, if necessary. This amendment also requires modifications that would strengthen the torsion box at rib 5.0 and prevent fatigue cracking; one of these modifications constitutes terminating action for the repetitive inspections. This amendment is prompted by reports indicating that, during full-scale fatigue testing, cracking has been found on the vertical stabilizer of the test article. The actions specified by this AD are intended to detect and prevent fatigue cracking in the subject area, which, if not corrected, could reduce the structural integrity of the vertical stabilizer.
97-02-14: This amendment supersedes an existing airworthiness directive (AD), applicable to Robinson Helicopter Company (Robinson) Model R22 helicopters, that currently requires installation of an improved throttle governor; an adjustment to the low RPM warning unit threshold to increase the revolutions-per-minute (RPM) at which the warning horn and caution light activate; and revisions to the R22 Rotorcraft Flight Manual that prohibit flight with the improved throttle governor selected off, except in certain situations. This amendment requires the same actions required by the existing AD, as well as requires an insertion of procedures for the improved throttle governor into the Normal and Emergency sections of the R22 Rotorcraft Flight Manual and corrects the applicability section of the existing AD. This amendment is prompted by the need to insert normal and emergency procedures for the improved throttle governor into the flight manual, and expand the applicability statement of this AD to include all Robinson Model R22 helicopters. The actions specified by the proposed AD are intended to minimize the possibility of pilot mismanagement of the main rotor (M/R) RPM, which could result in unrecoverable M/R blade stall and subsequent loss of control of the helicopter.
2011-11-07: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Cracks have been reportedly found on DA 42 Main Landing Gear (MLG) Damper-to-Trailing Arm joints during standard maintenance. Depending on environmental-, operating- and runway conditions, the affected MLG joint, Part Number (P/N) D60-3217-23-5x (4 different lengths are available), which is made of aluminum, is susceptible to cracking. This condition, if not detected and corrected, may lead to failure of the joint and subsequent damage or malfunction of the MLG, possibly resulting in damage to the aeroplane during landing and injury to occupants. We are issuing this AD to require actions to correct the unsafe condition on these products.
62-05-01: 62-05-01 AERO COMMANDER: Amdt. 403 Part 507 Federal Register March 6, 1962. Applies to All Model 680F Aircraft, Including Pressurized Versions, With Serial Numbers 871 Through 1170. Compliance required within the next 25 hours' time in service after the effective date of this directive. In order to preclude failure of the alternate induction air valve and shaft assembly resulting in loss of engine power, replace the original air valve and shaft and rig in accordance with instructions outlined in Aero Commander Service Bulletin No. 76A dated February 5, 1962, or FAA approved equivalent. This directive effective March 6, 1962.
99-21-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-301, and Model A340-211, -212, -311, and -312 series airplanes, that requires repetitive detailed visual inspections of the fuselage belly fairing support structure to detect cracks; and corrective action, if necessary. This amendment also provides an optional terminating action for the repetitive inspections. 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 detect and correct fatigue cracking of the fuselage belly fairing support structure, which could result in reduced structural integrity of the fuselage belly fairing support structure.
2011-09-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitive inspections for any damage of the lower surface of the center wing box, and corrective actions if necessary. This AD was prompted by reports of fatigue cracks of the lower surface of the center wing box. We are issuing this AD to detect and correct such cracks, which could result in the structural failure of the wings.
2011-11-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During production quality inspections of the aeroplane fuel motive flow system, it was discovered that some motive flow check valves (MFCV) were manufactured with an outlet fitting containing red anodized threads. These MFCV do not provide adequate electrical bonding between the valve and the adjacent fitting. In the absence of proper electrical bonding within the motive flow system, the aeroplane fuel tank could be exposed to ignition sources in the case of a lightning strike. * * * * * The unsafe condition is the potential for ignition sources inside the fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2002-26-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections to detect evidence of wear damage in the area at the interface between the vertical stabilizer and fuselage skin, and corrective actions, if necessary. This amendment also provides for an optional terminating action for the repetitive inspections. The actions specified by this AD are intended to detect and correct wear damage of the fuselage skin, which could result in thinning and cracking of the fuselage skin, and consequent in-flight depressurization of the airplane. This action is intended to address the identified unsafe condition.
96-25-20: This amendment adopts a new airworthiness directive (AD), applicable to Hamilton Standard 14RF and 14SF series, and Hamilton Standard/British Aerospace Model 6/5500/F propellers, that requires initial and repetitive inspections of critical control components, and removal and replacement with serviceable parts those critical control components that do not meet the return to service criteria. This amendment is prompted by failure modes effects analysis (FMEA), certification test data, engineering analysis, and repair actions performed at overhaul depots. The actions specified by this AD are intended to prevent loss of propeller control due to failure of critical control components, which could result in loss of control of the aircraft.
97-01-06: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI)-manufactured restricted category Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P helicopters, that requires a one-time inspection of the tail rotor slider (slider) to verify that it was manufactured with the correct outside diameter. This amendment is prompted by a United States (U.S.) Army Safety of Flight message that reports that some sliders may have been improperly manufactured with an undersized wall thickness by U.S. Army vendors. The actions specified by this AD are intended to prevent fatigue failure of the slider, which could cause loss of tail rotor control and subsequent loss of control of the helicopter.
98-07-22: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model HS 748 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits the positioning of the power levers below the flight idle stop during flight, and to add a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller ground beta range was used improperly during flight. The actions specified in this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
2002-26-12: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330 and A340 series airplanes, that requires a one-time inspection to determine the manufacturer's name, part number, and date code of certain circuit breakers; and replacement of any suspect circuit breaker with a new improved circuit breaker. The actions specified by this AD are intended to ensure that proper circuit breakers are installed for the fire extinguishing system or part of the supplemental oxygen supply. A defective circuit breaker, if not corrected, could trip without the cockpit indication light illuminating. If the flightcrew is unaware of this situation while operating the airplane, this latent failure in combination with other failures could present an immediate hazard to the airplane. This action is intended to address the identified unsafe condition.
96-25-16: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-7 series airplanes, that requires modification of the power control relay installation of the emergency lights. This amendment also requires revising the FAA-approved Airplane Flight Manual to include procedures for turning off and on the emergency lights switch in certain conditions. This amendment is prompted by a report that the emergency lights do not automatically illuminate when all generated electrical power on the airplane is lost and the power to the left essential bus is maintained from the aircraft batteries. The actions specified by this AD are intended to ensure that the emergency lights illuminate when needed in an emergency situation.
97-25-12: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-44 series airplanes, that requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
96-25-18: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes, that requires inspections of the components of the leading edge outboard slat; replacement of the control rod end, if necessary; and various follow-on actions. This amendment is prompted by reports of skewed panels of the outboard leading edge slat due to failure of a corroded rotary actuator or the control rod. The actions specified by this AD are intended to prevent such conditions, which could result in reduced controllability of the airplane and damage to or cracking of the leading edge slats or the fixed leading edge of the wing.
2002-26-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2002-26-51 that was sent previously to all known U.S. owners and operators of certain EMBRAER Model EMB-135 and -145 series airplanes by individual notices. This AD requires revising the Limitations Section of the Airplane Flight Manual to advise the flightcrew of the possibility of locking of the elevator during takeoff and to provide the appropriate procedures to prevent it. This action is prompted by a report indicating that the elevator locked during the takeoff run on a Model EMB-145 series airplane. The actions specified by this AD are intended to prevent locking of the elevator during takeoff, which could result in loss of controllability of the airplane.
98-26-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time inspection to verify correct installation of the lockplates of the roll spoiler actuators, and corrective actions, 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 prevent fatigue cracking of the fork flanges of the roll spoiler actuators due to incorrect installation of the lockplates, which could result in reduced structural integrity of the components of the roll spoiler actuators, and consequent reduced controllability of the airplane.
2011-10-12: We are adopting a new airworthiness directive (AD) for the specified Eurocopter France (ECF) helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the aviation authority of the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The superseding MCAI AD states that several engine flameouts have involved failure of the 41-tooth pinion in the engine accessory gearbox. Each affected helicopter had a starter-generator manufactured by one company. Investigation revealed the torque damping system of the starter-generator was inoperative due to incorrect adjustment that caused bending stresses on the 41-tooth pinion. Failure of the pinion causes the engine fuel pump to stop operating, resulting in an engine flameout. The EASA AD requires a new adjustment procedure to optimize the performance of the specified starter-generator damping assembly. This AD is intended to prevent failure of a pinion and a fuel pump, engine flameout, and subsequent loss of control of the helicopter.
2011-10-11: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 helicopters. This AD results from mandatory continuing airworthiness information (MCAI) originated by the aviation authority of Italy to identify and correct an unsafe condition related to the rescue hoist hook installed on this model helicopter. The aviation authority of Italy, with which we have a bilateral agreement, states in the MCAI that a missing lock pin may cause the loss of the hoist hook and any load. The absence of the lock pin constitutes an unsafe condition, and this AD is intended to detect the presence of an identification plate marked ``BT 412-124,'' which indicates that the hook assembly has the lock pin installed to prevent the loss of a rescue hoist hook and its load.