Results
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.
97-07-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 series airplanes. It requires a one-time template inspection of the rear pressure bulkhead to detect dents; repetitive eddy current inspections of dents greater than a certain depth to detect cracking; and repair, if necessary. This amendment is prompted by a report indicating that cracking has been found in the vicinity of a dent in the rear pressure bulkhead of one airplane. The actions specified by this amendment are intended to prevent fatigue cracking resulting from a dent in the rear pressure bulkhead; that condition, if not corrected, could reduce the structural integrity of the bulkhead and, consequently, lead to rapid depressurization of the airplane.
2011-10-15: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Electrical discontinuity has been detected on terminal modules Part Number (P/N) NSA 937901M1604, manufactured by Deutsch, due to an insufficient crimping of the female contacts on the shunt, caused by a wrong setting of the crimping tool. * * * * * This condition, if not corrected, could potentially result in in-flight failure of the Electrical Flight Control System (EFCS) and consequent loss of control of the aeroplane. In addition, this condition could lead to a non detected passenger oxygen loss, which, in case of emergency, could result in a large number of passenger oxygen masks not being supplied with oxygen, possibly causing personal injuries. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2011-10-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: A specific area, the lower tail plane cut-out located in the tail cone is subject to an inspection programme [for cracking] * * *. * * * * * The unsafe condition is reduced structural integrity of the tail cone. We are issuing this AD to require actions to correct the unsafe condition on these products.
98-20-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires modification of the struts for the stowage box located forward of galley 2. 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 failure of the struts, which could result in displacement of the stowage box, and possible injury to passengers and flight crew.
96-24-11: This amendment adopts a new airworthiness directive (AD), applicable to all IAI, Ltd., Model 1123, 1124, and 1124A series airplanes, that requires repetitive inspections of the aileron push-pull tubes for excessive wear and the guide rollers for smooth rotation; and repair or replacement of worn parts with serviceable parts. This amendment is prompted by reports of excessive wear on the aileron push-pull tube in the area of the guide rollers. The actions specified by this AD are intended to prevent such wear, which could result in uneven movement of the control wheel, perforation of the aileron push-pull tube, and consequent reduced roll control of the airplane.
2011-10-08: We are adopting a new airworthiness directive (AD) for the products listed above that would supersede two existing ADs. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France AD 1992-106-132(B) * * * has been issued in order to mandate a set of inspections/modifications which address JAR/FAR [Joint Aviation Regulation/Federal Aviation Regulation] 25-571 requirements related to damage-tolerance and fatigue evaluation of structure. * * * * * The unsafe condition is reduced structural integrity of the wings, fuselage, and stabilizers. We are issuing this AD to require actions to correct the unsafe condition on these products.