Results
98-20-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time inspection of direct current (DC) power unit 1VE to determine whether electrical connections are correctly installed and stud nuts are correctly torqued, and corrective actions, if necessary. For certain airplanes, this amendment also requires replacement of the existing DC power unit 1VE with a modified DC power unit. 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 overheating of electrical connections, which could result in electrical arcing and consequent fire.
2002-22-09: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters. This action requires, before further flight, inserting statements into the Limitations section of the Rotorcraft Flight Manual (RFM) prohibiting flight under certain atmospheric conditions. Also, this AD requires inspecting the bullet seal on the multi-purpose air intake (MPAI) to determine the pressure and, if the pressure is less than 3 bars on one or both of the sides, replacing the P2 pipe with an airworthy P2 pipe within a specified time interval. This amendment is prompted by the discovery of unairworthy P2 pipes, which might cause insufficient inflation of the bullet seal on the MPAI. This condition, if not detected, could restrict airflow into the engine inlet during flight in icing conditions, resulting in loss of engine power and subsequent loss of control of the helicopter.
2018-02-07: We are adopting a new airworthiness directive (AD) for Model TH-1F, UH-1B, UH-1F, UH-1H, and UH-1P helicopters with a Helicopter Technology Company (HTC) main rotor (M/R) blade installed. This AD requires cleaning and visually inspecting the M/R blades and, depending on the outcome of the inspection, repairing or replacing the M/R blades. This AD is prompted by a report of an M/R blade with a fatigue crack in the grip plate and doublers at the blade retention bolt hole. The actions of this AD are intended to correct an unsafe condition on these products.
85-08-06: 85-08-06 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39- 5042. Applies to all Models P 68, P 68B, P 68C, P 68C-TC, and P 68 OBSERVER (Serial Numbers (S/N) 001 thru 335, XXX-01TC thru XXX-23TC, and XXX-26TC) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent the loss of aileron control, accomplish the following: (a) On all P 68 models from S/N 001 through S/N 335, safety lockwire the aileron cable chain safety lock, Part Number (P/N) 68-5.2017-3, as described in PARTENAVIA Service Bulletin (S/B) No. 64, Revision 1, dated September 10, 1984. (b) On all P 68, P 68B, P 68C, P 68C-TC, and P 68 OBSERVER Models from S/Ns 001 to and including 293, 305 and 312, except 261, 279, 284, 286, 290, 291, and 292 visually inspect the aileron control cable behind the engine compartment firewall for wear caused by rubbing against the cable guardplates as described in the Instructions of PARTENAVIA S/B No. 59, Revision 1, dated November 30, 1983, and replace any cables that exhibit wear damage as defined in this S/B. (c) On all P 68C-TC Models from S/N XXX-01TC to and including XXX-23TC, and XXX-26TC, replace aileron cable guard plates (P/Ns 1.2091B-1 and 1.2091B-2) as described in PARTENAVIA S/B No. 59, Revision 2, dated June 27, 1984. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent means of compliance may be used, if 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 May 28, 1985.
95-24-03: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10, -30, and -40 series airplanes, and KC-10 (military) airplanes, that requires inspections to detect corrosion or cracking of the lower front spar cap and the skin panel of the horizontal stabilizer, and repair of corroded or cracked parts. This amendment also requires eventual modification of the horizontal stabilizer, which terminates the inspection requirements. This action is prompted by reports indicating that corrosion, caused by water entrapment, was found on the horizontal stabilizer. The actions specified by this AD are intended to prevent water entrapment and subsequent damage to the horizontal stabilizer, which could result in reduced controllability of the airplane.
2002-22-10: This amendment supersedes an existing airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (BHTCL) Model 407 helicopters that requires visually inspecting the brackets that attach the horizontal stabilizer slat (slat) to the stabilizer for a crack. If a crack is found, that AD also requires replacing the slat assembly before further flight. Also, that AD requires installing airworthy, segmented slat assemblies by a specified date. Installing segmented slat assemblies was considered terminating action for the requirements of that AD. This amendment requires, initially and at certain time intervals, checking each slat assembly for a cracked bracket and, if a crack is found, replacing any unairworthy slat assembly with an improved, airworthy slat assembly. This amendment also requires replacing, modifying, and installing identification plates on slats on certain helicopters at specified time intervals. This amendment is prompted by two additional reports of cracked brackets. The actions specified by this AD are intended to prevent a slat from separating, contacting a rotor blade, and resulting in subsequent loss of control of the helicopter.
2024-04-09: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, 777-200LR, 777-300, 777- 300ER, and 777F series airplanes. This AD was prompted by reports of wing anti-ice (WAI) valve failure that can result in undetected structural damage to leading edge (LE) slat assemblies, and separately a failure of the autothrottle (A/T) to disconnect after the pilot manually advanced the throttle levers, which caused a low-speed condition during a go-around. This AD was also prompted by a determination that insufficient low-speed protection exists in the 777 fleet and a determination that the flightcrew may not recognize and properly respond to a multi-channel unreliable airspeed event. This AD requires installing certain new software and doing a software configuration check. The FAA is issuing this AD to address the unsafe condition on these products.
2002-22-13: This amendment adopts a new airworthiness directive (AD) that applies to certain Rockwell Collins, Inc. (Rockwell Collins) FMC-4200, FMC-5000, and FMC-6000 flight management computers (FMC) that are installed on airplanes. This AD requires you to remove the affected FMC unit and replace it with a new FMC unit or an FMC unit that has been modified to correct a problem with the flight management system (FMS) accepting new information when an existing procedure or flight plan is changed. This AD is the result of a report that an aircraft proceeded beyond the published altitude constraint on an arrival procedure. The actions specified by this AD are intended to prevent the FMC from retaining and displaying original altitude constraints when an edit or a replacement is made to a procedure or flight plan that shares a waypoint with another procedure or an airway, and there is an altitude constraint on the shared waypoint. Such a condition could cause the pilot to fly the airplane out of the range of the correct altitude constraint. This condition could result in air traffic control or the pilot making flight decisions that put the airplane in unsafe flight conditions.
95-18-10: This amendment supersedes Airworthiness Directive (AD) 81-10-11, which currently requires repetitively inspecting the elevator root ribs for cracks on de Havilland DHC-6 series airplanes, and replacing any cracked part. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate, or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. This action requires modifying the elevator root rib as terminating action for the repetitive inspections currently required by AD 81-10-11. The actions specified by this AD are intended to prevent failure of the elevator root rib, which could result in loss of control of the airplane.
2018-02-01: We are superseding Airworthiness Directive (AD) 2015-08-51 for the Enstrom Helicopter Corporation (Enstrom) Model F-28A, 280, F-28C, F-28C-2, F-28C-2R, 280C, F-28F, F-28F-R, 280F, 280FX, and 480 helicopters. AD 2015-08-51 required an inspection of the main rotor spindle (spindle) and reporting the inspection results to the FAA. This new AD was prompted by additional reports of cracked spindles and requires establishing a life limit and a recurring inspection. The actions of this AD are intended to prevent the unsafe condition on these products.