Results
2013-03-10: We are adopting a new airworthiness directive (AD) for certain Lindstrand Hot Air Balloons Ltd female ACME threaded hose connectors, part numbers HS6139 and HS6144, installed on balloons. 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 insufficient tightness of the threaded hose connector in the assembly area that could result in fuel leakage. We are issuing this AD to require actions to address the unsafe condition on these products.
2003-10-02: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-524C2-19 and RB211-524C2-B-19 series turbofan engines. This AD requires replacing the existing low pressure (LP) compressor location bearing assembly, intermediate pressure (IP) compressor location bearing, IP compressor bearing support housing, IP compressor rear stub shaft, LP compressor location bearing support, oil transfer connector assembly, hydraulic oil seal housing, and hydraulic oil seal with improved design parts. This AD is prompted by statistical analysis by the manufacturer of in-service premature bearing failures. The actions specified in this AD are intended to prevent LP compressor failure and uncontained disc failures, resulting in damage to the airplane.
84-19-08: 84-19-08 HILLER HELICOPTERS, a subsidiary of Rogerson Aircraft Corp (formerly Hiller Aviation): Amendment 39-4914. Applies to Model UH-12D and UH-12E series helicopters equipped with engine mount Part No. 63181-5 certificated in any category which have been converted to turbine power by STC SH177WE or SH178WE. Compliance is required as indicated (unless already accomplished). (a) Within the next 20 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 600 hours time in service from the last inspection, remove the paint from the outer gimbal forward attach fitting of the Hiller engine mount Part No. 63181-5 and dye penetrant or magnetic particle inspect the gusset weld beads for cracks on both the front and back sides of the gusset. (b) If cracks are found, replace the engine mount Part No. 63181-5 before further flight. (c) Prior to or immediately following installation or reinstallation of engine mount Part No.63181-5 in any of the Model UH-12 series helicopters listed above, perform the inspection required by paragraph (a) of this AD. (d) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168. This supersedes Amendment 39-3538 (44 FR 50035; August 27, 1979), AD 79-18-01. This amendment becomes effective September 20, 1984.
2018-04-10: We are adopting a new airworthiness directive (AD) for Pilatus Aircraft Limited Model PC-7 airplanes. 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 the brakes remaining activated after release of the brake pedal. We are issuing this AD to require actions to address the unsafe condition on these products.
2003-10-01: This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric (GE) CF6-6 series turbofan engines. This amendment requires a reduction of the cyclic life limit for certain high pressure turbine rotor (HPTR) rear shafts, and requires removing certain HPTR rear shafts from service before exceeding the new, lower cyclic life limit. In addition, this amendment requires removing from service certain HPTR rear shafts that currently exceed, or will exceed, the new, lower cyclic life limit according to the compliance schedule described in this AD. This amendment is prompted by an updated low-cycle-fatigue (LCF) analysis performed by the manufacturer that resulted in a lower cyclic life limit for certain HPTR rear shaft part numbers (PNs) installed in CF6-6 engines. The actions specified by this AD are intended to prevent cracks in HPTR rear shafts that could result in uncontained engine failure and damage to the airplane.
75-15-08: 75-15-08 BEECH AND CESSNA: Amendment 39-2266 as amended by Amendment 39- 2361. Applies to Beech Models 35, A35, B35, C35, D35, E35, F35, 35R, 35-33, 35-A33, 35- B33, 35-C33, H35, J35, K35, M35, N35, P35 series airplanes; Cessna Models 150, 150A, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, A150K, 150L, A150L series airplanes certificated in all categories which have been modified in accordance with STC SA2219WE. Compliance required as indicated unless already accomplished. To prevent loss of engine oil, improper engine lubrication or engine oil contamination, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 25 hours' time in service, unless (b) has been accomplished, remove the Beryl Aviation air oil separator Filtrator Assembly and inspect in accordance with the following procedure. (1) Add one quart of clear gasoline to the assembly can and plug or cap the ends of all tubes. (2) Hold the assembly can upright and shake vigorously for about two minutes. (3) Completely drain the gasoline from the 1/8 inch oil return tube through a paint strainer or similar fine mesh strainer and check for the presence of polyester urethane particles that have broken off of the internal screen material. (4) If screen particles are present, accomplish (b). (5) If screen particles are not present, install a 1/8 inch rivet in the top center of the assembly can to fasten the inside center cone to the outside can. Seal the rivet with an oil and fuel resistant type sealant if required. After assuring that cleaning agent has evaporated, reinstall the filtrator assembly. (b) Within the next 100 hours' time in service after the effective date of this AD, unless already accomplished, accomplish (1), (2), or (3). (1) (i) For Beech Models 35, A35, B35, C35, D35, E35, F35, and 35R Series Airplanes, remove the Beryl Aviation filtrator assembly P/N 1000-1 and install P/N B- 1119-M, P/N B-1119-RM, or P/N 1000-1-RM. (ii) For Beech Models H35, J35, K35, M35, N35, P35, 35-33, 35- A33, and 35-B33 and 35-C33 Series Airplanes, remove the Beryl Aviation filtrator assembly P/N 1000-1 and install P/N B-1114-M, P/N B-1114-RM, or P/N 1000-1-RM. (iii) For Cessna Models 150, 150A, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, A150K, 150L, and A150L Series Airplanes, remove the Beryl Aviation filtrator assembly P/N 1000-1 and install P/N B-1119-M, P/N B-1119-RM, or P/N 1000-1-RM. (2) Remove the modification incorporated by STC SA2219WE and return the airplane to the standard unmodified configuration. (3) Provide compliance with an equivalent method approved by Chief, Engineering and Manufacturing Branch, Southern Region. Beryl Aviation Specialties, Route 1, Box 127D, Leesburg, Florida 32748, Service Bulletin B-1-1-75-1 also pertains to this subject. Amendment 39-2266 became effectiveFriday, July 25, 1975. This amendment 39-2361 becomes effective September 10, 1975.
2000-03-11: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires replacement of 10 amp circuit breakers with 5 amp circuit breakers in the left and right windshield anti-ice power controllers; and replacement of the anti-ice control panel with a new or modified panel, or modification and reidentification of the anti-ice control panel. This amendment is prompted by reports of smoke and sparks emanating from the anti-ice control panel in the cockpit. The actions specified by this AD are intended to prevent burnt internal circuit boards caused by a short in either the engine or airfoil anti-ice valve, or the windshield anti-ice controller, which could result in smoke in the cockpit.
73-08-03: 73-08-03 BELL: Amdt. 39-1622. Applies to Bell Models 206A, 206B, 206A-1 and 206B-1 helicopters equipped with pylon support links, P/N 206-031-508-5 or -7, certificated in all categories. Compliance required as indicated. To prevent possible failure of a pylon support link, P/N 206-031-508-5 or -7 accomplish the following: (a) Within the next ten hours time in service after the effective date of this A.D., unless already accomplished, inspect the pylon support link assemblies in accordance with Part II of Bell Helicopter Company Service Bulletin No. 206-01-73-2, Revision A, dated March 27, 1973, or later FAA approved revision or in accordance with an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. If the bearing inner race measures more than 1.255 inches in diameter or there is any crack in the link, the link assembly must be replaced prior to next flight. (b) Within twenty-five hours time in service after compliance with paragraph (a) and thereafter at intervals not to exceed twenty-five hours from the last inspection, inspect the pylon support link assemblies in accordance with Part III of Bell Service Bulletin No. 206-01-73-2, Revision A, dated March 27, 1973, or later FAA approved revision or in accordance with an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. If any crack is found, the link assembly must be removed and replaced prior to next flight. (c) This airworthiness directive is no longer applicable when pylon support links, P/N 206-031-589, are installed. This supersedes Amendment 39-1602 (38 F.R. 6377), A.D. 73-05-04. This amendment becomes effective April 18, 1973.
2021-20-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that during flight tests, the opening of the ram air outlet flaps was found to cause a disturbance of the air flow around the ram air turbine (RAT) when the landing gear (L/G) is extended. This AD requires revising the existing airplane flight manual (AFM) and applicable corresponding operational procedures to provide procedures for all engines failure and L/G gravity extension related to certain software, and installing Airbus temporary quick change (ATQC) V3 for the flight warning system (FWS) software (SW) standard (STD) 6/ 2.0, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-05-22: We are adopting a new airworthiness directive (AD) for all Agusta S.p.A. (Agusta) Model A109, A109A, A109A II, A109C, A109K2, A109E, A109S, and A119 helicopters. This AD was prompted by a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that a Model A109E helicopter experienced a failure of the tail rotor pitch control link assembly caused by a production defect. The actions of this AD are intended to prevent failure of a tail rotor pitch control link and subsequent loss of control of the helicopter.
2003-09-13: This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) Models PA-23, PA-23-160, PA-23-235, PA-23-250, and PA-E23-250 airplanes that do not incorporate a certain design flap control torque tube or torque tube assembly. This AD requires you to repetitively inspect the flap control torque tube for cracks, corrosion, wear, or elongation of the attachment bolt holes (referred to as damage); and requires you to replace any damaged torque tube with either an improved design flap control torque tube or flap control torque tube assembly. The repetitive inspections will no longer be necessary when the improved design torque tube or torque tube assembly is installed. This AD is the result of several reports of damage found in the flap control torque tube on the affected airplanes. The actions specified by this AD are intended to detect and correct damage to the flap control torque tube, which could result in failure of the flap operating system. If such failure occurred during landing or takeoff, then a split flap condition could occur with potential loss of control of the airplane.
2008-07-11 R1: We are rescinding an airworthiness directive (AD) for all PILATUS AIRCRAFT LTD. Models PC-12, PC-12/45, and PC-12/47 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. We issued that AD to mandate new life limits for the pitch trim actuator and pitch trim actuator attachment parts. If these new limitations were not mandated, the pitch trim actuator and the pitch trim actuator components could fail. This failure could lead to an unsafe flying configuration. Since we issued that AD, we have determined that the unsafe condition addressed in that AD is now addressed in another AD.
2013-05-18: We are superseding an existing airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211 Trent 500 series turbofan engines. That AD currently requires a one-time inspection of the fuel tubes and fuel tube clips for evidence of damage, wear, and fuel leakage. This AD requires the same inspection, and adds additional repetitive inspections. This AD was prompted by additional RR engineering analysis. We are issuing this AD to prevent engine fuel leaks, which could result in engine damage and damage to the airplane.
2003-09-14: This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric (GE) CF34-8C1 turbofan engines. This amendment requires replacing combustion chamber assemblies, part number (P/N) 4126T87G04, before accumulating a new reduced cyclic life limit. This amendment is prompted by stress and life analysis conducted by GE. The actions specified by this AD are intended to prevent rupture of the combustion chamber assembly and possible engine fire.
2013-05-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires doing an inspection to identify the part number of the motor-operated valve (MOV) actuators of the main and center fuel tanks; replacing certain MOV actuators with new MOV actuators; and measuring the electrical resistance of the bond from the adapter plate to the airplane structure, and doing corrective actions if necessary. We are issuing this AD to prevent electrical current from flowing through an MOV actuator into a fuel tank, which could create a potential ignition source inside the fuel tank. This condition, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2013-05-09: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -300, and -200 Freighter series airplanes; and all Airbus Model A340-200 and -300 series airplanes. This AD was prompted by a determination that the bonding lead from a certain isolation valve to a frame was too close to an electrical harness, which might cause chafing between the electrical harness and the associated bonding lead. This chafing could lead to a short circuit of the isolation valve and consequent non-closure of the isolation valve, which would prevent the air flow to be shut off in case of fire. This AD requires modifying the bonding lead installation of the isolation valve. We are issuing this AD to prevent such chafing, which could result in non-closure of the isolation valve in the event of a fire and consequent damage to the airplane and injury to its occupants.
68-19-05: 68-19-05 CESSNA: Amendment 39-652. Applies to Types 172B, 172C, 172D, 172E, 172F, and 172G airplanes equipped with a Franklin Engine Co., Inc. Model 6A-335-B engine installed in accordance with Supplemental Type Certificate No. SA11680. Compliance required as indicated within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible structural damage to the airplane, resulting from conducting Utility Category maneuvers, accomplish the following: Remove any placarded reference to Utility Category specifications and install a placard stating, "Use in Utility Category Prohibited." This amendment effective September 13, 1968.
2013-05-06: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2A12 (CL-601) and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by reports of jamming/malfunctioning of the left-hand engine thrust control mechanism. This AD requires modifying the left-hand engine upper core-cowl. We are issuing this AD to prevent jamming/ malfunctioning of the left-hand engine thrust control mechanism, which could lead to loss of control of the airplane.
2013-05-23: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332C, L, and L1 helicopters to require a one-time inspection of the main rotor head (MRH) swash-plate upper bearing (bearing) for a non-smooth point (friction point). This AD was prompted by a report of the premature deterioration of the MRH bearing of the rotating star installed on a Model AS332L1 helicopter. The actions of this AD are intended to detect deterioration of the MRH bearing and to prevent overloading the scissor links which drive the main rotor system, failure of the scissors links, and subsequent loss of control of the helicopter.
2013-05-19: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611-8 turbofan engines. This AD requires inspection and replacement, if necessary, of affected bolts. This AD was prompted by a quality review determination that bolts with reduced material properties may have been installed in some engines. We are issuing this AD to prevent uncontained turbine disc fracture and damage to the airplane.
2013-03-22: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports that airplanes with a Class C cargo (baggage) compartment have liners that do not meet flammability requirements. This AD requires replacing the existing cargo compartment liners with liners that comply. We are issuing this AD to prevent inadequate fire protection in the cargo compartment and consequent uncontrolled fire.
2025-05-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model SA341G and SA342J helicopters. This AD was prompted by a report of a pilot collective pitch stick handle grip that broke when pulled. This AD requires replacing certain pilot collective pitch stick handle grips and prohibits installing those pilot collective pitch stick handle grips. These actions are specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
95-12-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes. This action requires repetitive inspections to detect cracking in the hinge fittings of the nose landing gear (NLG) aft doors, and replacement of cracked fittings. This amendment is prompted by several reports of loss of an NLG aft door during landing, due to failure of the door's hinge fittings. The actions specified in this AD are intended to prevent the loss of an NLG aft door due to the failure of the hinge fittings; such loss of a door can result in damage to the surrounding aircraft structure or injury to persons on the ground.
93-17-01: 93-17-01 BEECH AIRCRAFT CORPORATION: Amendment 39-8671. Docket No. 93-CE- 23-AD. Applicability: Models B90, C90, and C90A airplanes (serial numbers LJ-489 through LJ-1318), certificated in any category. Compliance: Required within the next 150 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent failure of the leading edge fuel cell nipples caused by cracking and fuel leaks, which, if not detected and corrected, could result in an airplane fire, accomplish the following: (a) Inspect the inboard nipple on the leading edge fuel cell for cracks or fuel leaks in accordance with Part I of the ACCOMPLISHMENT INSTRUCTIONS section of Beech Service Bulletin (SB) No. 2475, dated February 1993. If cracks or fuel leaks are found, prior to further flight, repair the fuel cells in accordance with procedures specified in the applicable maintenance manual. (b) Replace the fuel interconnect tube assembly in accordance with Part II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2475, dated February 1993. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (e) The inspection and replacement required by this AD shall be done in accordance with Beech Service Bulletin No. 2475, dated February 1993. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on October 12, 1993.
92-25-12: 92-25-12 AIRBUS INDUSTRIE: Amendment 39-8426. Docket No. 92-NM-150-AD. Applicability: Model A300 B2, A300 B4, A310, and A300-600 series airplanes; equipped with Messier Bugatti carbon brakes; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent overrunning the available runway length during a rejected takeoff (RTO), accomplish the following: (a) Within 30 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to change the data concerning the accelerate stop distance to be used during a RTO, in accordance with either Model A300 AFM Temporary Revision 5.02.00/1, dated December 4, 1991; Model A310 AFM Temporary Revision 5.04.00/3, dated February 13, 1992; Model A310 AFM Temporary Revision 5.04.00/1, dated October 22, 1991; Model A310 AFM Temporary Revision 5.04.00/4, dated March 6, 1992; Model A300-600 AFM Temporary Revision 5.04.00/1, datedNovember 4, 1991; or Model A300-600 AFM Temporary Revision 5.04.00/2, dated December 4, 1991; as applicable. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The AFM revision shall be done in accordance with Model A300 AFM Temporary Revision 5.02.00/1, dated December 4, 1991; Model A310 AFM Temporary Revision 5.04.00/3, dated February 13, 1992; Model A310 AFM Temporary Revision 5.04.00/1, dated October 22, 1991; Model A310 AFM Temporary Revision 5.04.00/4, dated March 6, 1992; Model A300-600 AFM Temporary Revision 5.04.00/1, dated November 4, 1991; or Model A300-600 AFM Temporary Revision 5.04.00/2, dated December 4, 1991; as applicable. (NOTE: The issue date of the AFM Temporary Revisions are indicated only on "page 1"; no other pages of these documents are dated.) This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700, Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e)This amendment becomes effective on January 12, 1993.