Results
99-19-39: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes, that requires removal of the insulation blankets surrounding the emergency overwing exit hatches. 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 the freezing of moisture entrapped in the fiberglass/foam insulation installed on the fuselage structure between the overwing exit door and the fuselage door frame and intercostal, which could interfere with the opening of the overwing emergency exit hatches during an emergency evacuation of the airplane.
99-20-01: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires modification of the electrical wiring of the flight warning computer (FWC), and installation of upgraded computer software into the FWC. 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 certain nuisance alerts generated by the FWC and to ensure annunciation of certain flight alerts by the FWC during initial climb. Such nuisance alerts or failures to annunciate certain alerts could result in an improper response by the flight crew and consequent reduced controllability of the airplane.
99-17-17: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-17-17 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (RHC) Model R44 helicopters by individual letters. This AD requires, prior to further flight, replacing certain yoke assemblies with airworthy yoke assemblies. This amendment is prompted by an incident in which, during cruise flight, the pilot heard a loud bang and no tail rotor effectiveness due to a cracked yoke assembly. RHC has identified the manufacturing lots associated with the failed yoke assembly. The actions specified by this AD are intended to prevent failure of the yoke assembly, which could result in loss of main and tail rotor drive and subsequent loss of control of the helicopter.
2022-12-07: The FAA is superseding Airworthiness Directive (AD) 75-23-03 for all Alexander Schleicher GmbH & Co. Segelflugzeugbau (Alexander Schleicher) Model Ka2B, Ka 6, Ka 6 B, Ka 6 BR, Ka 6 C, Ka 6 CR, K 7, K 8, and AS-K 13 gliders. AD 75-23-03 required visually inspecting the glue joint between the elevator nose rib number 1 and the nose plywood skin and replacing the glue joint if insufficient glue adhesion was found. Since the FAA issued AD 75-23-03, the European Union Aviation Safety Agency (EASA) superseded prior EASA ADs for the unsafe condition on these products. This AD adds the Model K 8 B gliders to the applicability and requires repetitively inspecting the glue joint at elevator rib number 1 and repairing any damage found. The FAA is issuing this AD to address the unsafe condition on these products.
72-25-04: 72-25-04 SIKORSKY: Amdt. 39-1571. Applies to all Sikorsky S-61A, S-61B, S-61D, S- 61L Series prior to SS No. 61454, S-61N Series prior to SS No. 61493, S-61R, S-61V helicopters certificated in all categories. Compliance required as indicated. To prevent hazards in flight due to loss of main rotor control as a result of cracked primary servo mounting bracket retaining nuts, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this Airworthiness Directive, remove all MS21042-6 or MS20365-624C retaining nuts from the primary servo mounting brackets, P/N S613520249, and replace with P/N MS21045-6 retaining nuts in accordance with Sikorsky Service Bulletin No. 61B35-18 dated 10 November 1972 or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. (b) Upon request with substantiation data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. (c) Equivalent methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. This amendment becomes effective December 15, 1972.
2022-13-03: The FAA is adopting a new airworthiness directive (AD) for certain Cameron Balloons Ltd. (Cameron) fuel cylinders installed on hot air balloons. 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 identifies the unsafe condition as cracks in the weld between the cylinder valve plate and the upper dished end of Cameron part number (P/N) CB2990 (Alugas) fuel cylinders, which could allow uncontrolled fuel leakage of liquid propane. This AD requires the removal of any installed P/N CB2990 (Alugas) fuel cylinder from service before further flight. The FAA is issuing this AD to address the unsafe condition on these products.
2004-17-02: The FAA adopts a new airworthiness directive (AD) for certain Raytheon Aircraft Company (Raytheon) 65, 90, 99, 100, 200, 300, and 1900 series airplanes. This AD requires you to repetitively inspect the engine controls/cross shaft/pedestal for proper installation and torque, re-torque the cross shaft attach bolt, modify the pedestal, and replace the engine controls cross shaft hardware. Modification of the pedestal and replacement of the engine controls cross shaft hardware is terminating action for the repetitive inspection requirements. This AD is the result of numerous reports of loose bolts on the pedestal attachment of the throttle/prop cross shaft assembly. We are issuing this AD to detect and correct loose bolts not securing the pedestal cross shaft, which could result in limited effectiveness of the control levers. This failure could lead to an aborted takeoff.
2022-12-06: The FAA is adopting a new airworthiness directive (AD) for certain Costruzioni Aeronautiche Tecnam S.P.A. Model P2012 Traveller airplanes. This AD was prompted by 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 free play in the trim tab actuator and trim tab surface. This AD requires repetitively inspecting the trim tab trailing edge to determine if free play exists and taking corrective actions as needed. The FAA is issuing this AD to address the unsafe condition on these products.
71-20-06: 71-20-06 CANADAIR: Amendment 39-1300 as amended by Amendment 39-3699. Applies to all Canadair Model CL-44D4 and CL-44J aircraft. Compliance required as indicated. Within the next 300 hours time in service after the effective date of this AD, unless already accomplished within the last 4500 hours time in service and at intervals not exceeding 4800 hours time in service, accomplish the following: (a) Inspect horizontal stabilizer front spar web, spar cap, and local structure at all stations from station 22 left to station 22 right for cracks in accordance with the inspection procedure defined in paragraphs 3, 3.1, and 3.2 of Canadair Service Information Circular No. 377-CL-44 dated May 20, 1971, as amended by amendment A, dated May 15, 1979, or in accordance with an FAA approved, equivalent inspection. (b) If cracks are found in the spar web, spar caps, or local structure, repair or replace damaged parts before further flight with unused parts or with equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed. (c) Repair procedures required by paragraph (b) must be in accordance with Canadair CL-44D4 Structural Repair Manual or an equivalent repair procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (d) The repetitive inspection time may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region upon receipt of substantiating data submitted through an FAA Maintenance Inspector. Amendment 39-1300 was effective October 5, 1971. This Amendment 39-3699 is effective February 21, 1980.
99-19-32: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires inspecting all flap actuator internal gear systems to assure that correct end-play and backlash measurements exist, and accomplishing any corrective adjustments as necessary. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent premature wear of the internal gear system caused by excessive backlash in the flight control flap actuators, which could eventually result in loss of actuator output with possible reduced or loss of airplane control.
2004-17-03: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney Canada (PWC) PW206A and PW206E turboshaft engines. That AD currently requires: Initial and repetitive borescope inspections of compressor turbine and power turbine blades for blade axial shift. Replacement of blade retaining rivets and certain rotor air seals as terminating action for the repetitive borescope inspections. This ad requires the same actions as AD 2003-NE-25-AD but the extent of engine disassembly that triggers the required part replacements needs clarification. This AD results from reports of engine shutdowns and emergency landings due to severe vibration, resulting in exhaust gases escaping from the engine-to-exhaust nozzle interface, thereby triggering in-flight engine fire warnings. We are issuing this AD to prevent turbine blade axial shift, which could cause high levels of vibration, loss of engine torque, in-flight engine shutdown, and loss of the airframe exhaust duct. DATES: This AD becomes effective September 24, 2004. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of August 29, 2003. The incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of August 29, 2003 (68 FR 48544; August 14, 2003).
96-19-02: This amendment adopts a new airworthiness directive (AD) that applies to Industrie Aeronautiche E Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This action requires modifying the passenger seat cushion next to the emergency exit door handle. Reports of interference between the passenger seat cushion and the emergency exit door handle, preventing the door from opening from the outside, prompted this AD action. The actions specified by the AD are intended to prevent the possibility of not being able to open the emergency exit door during an emergency evacuation of the airplane, which could result in injury to the passengers.
2022-11-14: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by reports that following a main landing gear (MLG) extension, one of the MLGs could not be locked in the gear down position due to deterioration of greasing effectiveness over time. This AD requires repetitive lubrication of the MLG assembly. The FAA is issuing this AD to address the unsafe condition on these products.
2004-14-12: The FAA is adopting a new airworthiness directive (AD) for certain The New Piper Aircraft, Inc. (Piper), Models PA-28-161, PA-28-181, PA-28R-201, PA-32R-301 (HP), PA-32R-301T, PA-32-301FT, PA-32-301XTC, PA-34-220T, PA-44-180, PA-46-350P, and PA-46-500TP airplanes. This AD requires you to inspect the control wheel attaching hardware for proper installation, replace if required, add Loctite thread- locking compound to the screw installation, and install a retainer clip to the control wheel attachment. This AD is the result of inadequate control wheel attachment design. The screw used to attach the control wheel to the control column is too short in some installations, and the nut-plate does not have adequate locking features. In addition, the screw is installed from the bottom of the control wheel and will depart quickly after thread disengagement. We are issuing this AD to detect and correct inadequate control wheel attachment design features, which could result in loss of control of the ailerons and elevator. This failure could lead to loss of control of the aircraft.
99-19-27: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires a one-time inspection of the main landing gear (MLG) wheel assemblies to determine whether certain parts are installed, and follow-on corrective actions, if necessary. For certain airplanes, this amendment also requires eventual modification of MLG wheel assemblies, which terminates the requirements of this AD. This amendment is prompted by incidents of multiple tie bolt failures on certain BFGoodrich wheel assemblies. The actions specified by this AD are intended to prevent failure of multiple tie bolts of MLG wheel assemblies, which could result in failure of the wheel rim, rapid release of tire pressure, and possible consequent damage to the airplane and injury to passengers and flightcrew.
2012-14-08: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires inspecting the main gearbox (MGB) for a crack. This AD is prompted by a crack in the cored passage of the MGB housing, which may be indicated by oil on the housing. These actions are intended to detect a crack in the MGB housing, which could result in loss of oil, failure of the MGB, and subsequent loss of control of the helicopter.
2022-12-02: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report of multiple in-service events where, following a STAB TRIM FAULT advisory message and auto-pilot disconnect, flightcrew commands for a nose-up trim resulted in nose-down trim movement of the horizontal stabilizer instead. This AD requires revising the existing airplane flight manual (AFM) to provide the flightcrew with instructions for an expanded pre-flight check of the pitch trim, trim malfunction procedures, and revised ''AP STAB TRIM FAIL'' caution and ''STAB TRIM FAULT'' advisory procedures. The FAA is issuing this AD to address the unsafe condition on these products.
71-25-08: 71-25-08 FAIRCHILD HILLER ROTORCRAFT: Amdt. 39-1356. Applies to Fairchild Hiller UH-12 helicopters certificated in all categories. Compliance required as indicated. Following an immediate visual inspection and within 10 hours time in service after the effective date of this airworthiness directive inspect main rotor blade P/N 53100 for cracks, using dye penetrant. Any blades found defective are to be removed from service prior to further flight and S/Ns reported to Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region, JFK International Airport, Jamaica, New York 11430. Approval of this reporting procedure has been obtained from the Bureau of Budget in accordance with Federal Reports Act. Reporting approved by Bureau of Budget under BOB Number 04-R0174. This amendment is effective December 14, 1971 and was effective upon receipt by owners and operators of the letter dated November 9, 1971 which contained this amendment.
99-18-23: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas MD-90-30 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness (MD-90-30 Airworthiness Limitations Instructions (ALI)) to incorporate certain replacement times for safe-life limited parts. This amendment is prompted by analysis of data that identified reduced replacement times for certain safe-life limited parts. The actions specified by this AD are intended to prevent fatigue cracking of various safe-life limited parts; such fatigue cracking could adversely affect the structural integrity of these airplanes.
2013-05-16: We are adopting a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 369D, 369E, 369F, and 369FF helicopters with certain serial-numbered tailboom assemblies. This AD requires measuring the distance between aft longeron rivets and the outboard edge of frame rings. If the distance is too short to ensure a safe flight, the AD requires installing a doubler. This AD was prompted by the discovery of short-edge margin conditions on two tailboom assemblies. The actions are intended to detect a short-edge margin condition, prevent failure of the tailboom and loss of control of the helicopter.
2012-12-06: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by a design review which revealed the absence of electrical insulation material between a wing or integral center wing tank (ICWT) fuel quantity indication system (FQIS) probe and the bottom of the tank structure. This AD requires for all airplanes, applying sealant below the FQIS probes in the wing tanks; and for certain airplanes, applying sealant below the FQIS probes in the ICWT. This AD also requires revising the aircraft maintenance program by revising the fuel airworthiness limitations and incorporating critical design configuration control limitations (CDCCLs). We are issuing this AD to prevent an ignition source in the tank vapor space, which could result in a fuel tank explosion and consequent loss of the airplane.
2022-11-11: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited (type certificate previously held by Bombardier, Inc.) Model DHC-8-401 and -402 airplanes. This AD was prompted by reports of a certain bolt at the pivot pin link being found missing or having stress corrosion cracking. This AD requires a modification to the nose landing gear (NLG) shock strut assembly. The FAA is issuing this AD to address the unsafe condition on these products.
96-18-13: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Garrett Engine Division) TFE731 series turbofan engines, that requires removing certain fan rotor disks from service in accordance with a drawdown schedule, and would establish new fan rotor disk life limits. This amendment is prompted after additional analyses revealed that stress levels in the fan rotor disk dovetail slots for the applicable engine models are higher than initially calculated. The actions specified by this AD are intended to prevent uncontained failure of the fan rotor disk due to fatigue cracking in the dovetail slots, which can result in inflight engine shutdowns, severe secondary damage, and fan rotor assembly separation from the engine.
99-18-16: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-400, 757-200, 767-200, and 767-300 series airplanes. This action requires repetitive checks to detect certain failures in the warning electronic unit (WEU) or modular avionic warning electronic assembly (MAWEA); repetitive tests to detect any failure of tactile, visual, or aural alert generated by the WEU or MAWEA; and corrective action, if necessary. This AD also provides for an optional terminating action for the repetitive checks and tests. This amendment is prompted by a report of a MAWEA power supply failure due to inadequate over-voltage protection. The actions specified in this AD are intended to detect and correct such a failure, which could result in loss of visual, aural, and tactile alerts to the flightcrew. Absence of such alerts could result in the flightcrew being unaware that an immediate or appropriate action should be taken in the event of an unsafecondition.
2012-08-12: We are adopting a new airworthiness directive (AD) for all Airbus Model A310 series airplanes. This AD was prompted by a report of an electrical arc and hydraulic haze in the wheel bay of the left-hand main landing gear (MLG) possibly resulting from chafing between the hydraulic high pressure hose and electrical wiring of the green electrical motor pump (EMP). This AD requires temporarily prohibiting in-flight use of the green EMPs; temporarily revising the airplane flight manual (AFM) limitations section; temporarily installing a placard in the cockpit overhead panel; doing a one-time general visual inspection for correct condition and installation of hydraulic pressure hoses, electrical conduits, feeder cables, and associated clamping devices; and corrective action if necessary. We are issuing this AD to detect and correct chafing of hydraulic pressure hoses and electrical wiring of the green EMPs, which in combination with a system failure, could cause an uncontrolled and undetected fire in the MLG bay.