Results
2022-13-08: 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 of nose wheel steering (NWS) hydraulic motors jamming during pushback or towing. This AD requires doing an inspection to determine the part number and serial number of the NWS hydraulic motor, and re-identifying or replacing the NWS hydraulic motor if necessary. This AD also prohibits the installation of certain NWS hydraulic motors. The FAA is issuing this AD to address the unsafe condition on these products.
68-06-05: 68-06-05 FAIRCHILD-HILLER: Amdt. 39-565. Applies to FH-1100 type helicopters serial numbers 10 thru 76 inclusive and 83. Compliance required as indicated unless already accomplished. To preclude the possibility of failure of the engine-to-transmission coupling shaft due to corrosion resulting from water contamination, accomplish the following: (a) Within the next 100 helicopter hours' time in service following the effective date of this AD, remove Bendix coupling shaft P/N 19E49-3A and inspect for any corrosion and if found, replace with P/N 19E49-3B or if corrosion is absent modify in accordance with accomplishment instructions contained in Fairchild Hiller Service Bulletin No. FH-1100-24-1 dated January 25, 1968, or later FAA approved revision, or an equivalent inspection procedure or modification approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request, with substantiating data submitted through an FAA maintenance inspector, the compliance time may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective March 23, 1968.
2022-14-02: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. LEAP-1A23, LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A (LEAP-1A) model turbofan engines. This AD was prompted by a manufacturer investigation that revealed that certain high-pressure turbine (HPT) rotor stage 1 disks (HPT stage 1 disks) and a stages 6-10 compressor rotor spool were manufactured from material suspected to contain iron inclusion. This AD requires the replacement of certain HPT stage 1 disks and a stages 6-10 compressor rotor spool. The FAA is issuing this AD to address the unsafe condition on these products.
2004-18-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, 737-700, 737-700C, 737-800, and 737-900 series airplanes, that requires measuring the electrical resistance of the support bracket for the fire extinguisher bottle located in the left main landing gear wheel well to ensure that it does not exceed the maximum allowed resistance; and corrective actions, if necessary. This action is necessary to prevent high electrical resistance in the squib firing circuit, which could result in insufficient electrical current to fire the fire extinguisher bottle squib and discharge the fire extinguishing agent, which could lead to an uncontrolled engine fire. This action is intended to address the identified unsafe condition.
2022-13-19: The FAA is superseding Airworthiness Directive (AD) 2022-11- 03, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2022-11-03 required revising the existing airplane flight manual (AFM), and revising the operator's existing FAA-approved minimum equipment list (MEL) by incorporating certain master minimum equipment list (MMEL) provisions, to include limitations and procedures to mitigate the risk of elevator failure during flare. Since the FAA issued AD 2022-11-03, an updated software standard for the PRIMary flight control computers (PRIMs) has been developed to address the unsafe condition. This AD continues to require the actions in AD 2022- 11-03, and also requires installing an updated PRIM software standard, 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.
2013-08-23: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes. This \n\n((Page 24038)) \n\nAD was prompted by fuel system reviews conducted by the manufacturer. This AD requires adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2001-14-08 R1: The FAA is rescinding an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model DC-10 series airplanes, Model MD-10 series airplanes, and Model MD-11 series airplanes. That AD requires repetitive inspections of the numbers 1 and 2 electric motors of the auxiliary hydraulic pump for electrical resistance, continuity, mechanical rotation, and associated wiring resistance/voltage; and corrective actions, if necessary. We issued that AD to prevent various failures of electric motors of the auxiliary hydraulic pump and associated wiring, which could result in fire at the auxiliary hydraulic pump and consequent damage to the adjacent electrical equipment and/or structure. Since we issued that AD, we have determined that the inspection requirements are identical to the inspection requirements of another existing AD.
99-20-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires inspections of the lower engine mount to determine if the tangential link upper bolt and nut are oriented properly, and if the tangential link upper bolt nut is torqued within certain limits. Additionally, that amendment requires replacement of the bolt and nut with serviceable parts, if necessary, and requires certain follow-on actions for airplanes on which the upper bolt is missing. This amendment requires accomplishment of a previously optional terminating action or a new alternative terminating action for the repetitive inspections. This amendment is prompted by development of a new terminating action by the manufacturer. The actions specified by this AD are intended to prevent separation of the engine from the airplane due to migration of the tangential link upper bolt.
72-14-04: 72-14-04 NORTH AMERICAN ROCKWELL: Amdt. 39-1481. Applies to Models NA-265, NA-265-20, NA-265-30, NA-265-40 (Serial Nos. 282-1 thru 282-105), and NA-265-60 (Serial Nos. 306-1 thru 306-63). Compliance required as indicated: To prevent failure of the main landing gear wheel door torque tube assembly, P/N 265- 333338-1, -2, 285-333338-1, -2, -31, -32, as applicable, accomplish the following: (a) Within 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 50 hours' time in service, and at intervals not to exceed 100 hours' time in service thereafter, perform a dye penetrant inspection of the main landing gear wheel door torque tube in the area 3 inches adjacent to the fore and aft weldments for evidence of cracking, until (c), below, is accomplished. (b) If evidence of cracking is discovered as a result of any of the inspections of (a), above, replace the torque tube assembly with a new or serviceable assembly prior to further flight. Mark the rejected part to prevent inadvertent return to service (Note: The manufacturer has recommended that operators return parts for rework by them. If returned, and after rework, the mark may be removed, the part re-identified, and returned to service). (c) Replace main landing gear wheel door torque tube assemblies P/N 265-333338- 1, -2, 285-333338-1, -2, -31, -32 with torque tube assemblies P/N 285-333338-51, -52, 276- 933338-1, -2, -31, -32, -41, -42, -51, -52 as applicable. This amendment becomes effective July 7, 1972.
2022-13-07: The FAA is adopting a new airworthiness directive (AD) for all AutoGyro Certification Limited (type certificate previously held by RotorSport UK Ltd) Model Calidus, Cavalon, and MTOsport 2017 gyroplanes. This AD was prompted by reports of rotor blade longitudinal cracking and rotor blade attachment bolt hole fretting corrosion and cracking. This AD requires reducing the life limits for the rotor systems, repetitively inspecting each rotor blade, and depending on the outcome, removing parts from service. The FAA is issuing this AD to address the unsafe condition on these products.
69-04-01: 69-04-01\tBOEING: Amdt. 39-723. Applies to Model 727 Series airplanes in which the battery switch is located within ten inches of the galley switch. \n\n\tCompliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. \n\n\tAs a result of FAA evaluations of the 727 electrical system sufficient cause has been found to prevent inadvertent operation of the battery switch located on the flight engineer's panel. Inadvertent operation of the battery switch during some operating conditions could result in loss of the standby electrical system. \n\n\tTo prevent inadvertent operation of the battery switch on the flight engineer's panel on those 727 Series airplanes in which the battery switch is located within ten inches of the galley switch, accomplish one of the following: \n\n\t(1)\tInstall a guard (Grimes P/N 11170-1 or equivalent MS type painted black) on the battery switch. The guard must be installed to force the switch to the "on" position and the guard should be mounted with the hinge down. \n\n\t(2)\tReplace the battery switch with a detent lock type switch, P/N MS 25125-E3 or an equivalent MS type, provided the galley switch is a toggle type switch. \n\n\t(3)\tPerform an equivalent installation approved by the Chief, Aircraft Engineering Division, FAA, Western Region. \n\n\tIn each of the above installations, install decals as necessary to retain "bat" and "on-off" switch function and switch position identification. \n\n\tBoeing Service Bulletin No. 24-44 is forthcoming to cover same subject. \n\n\tThis amendment becomes effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated January 31, 1969.
99-20-03: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney (PW) PW2000 series turbofan engines, that requires initial and repetitive inspections of certain High Pressure Turbine (HPT) stage 1 and stage 2 disks utilizing an improved ultrasonic inspection method performed at an approved facility when the disk is exposed during a shop visit, and if a crack indicating a subsurface anomaly is found, removal from service and replacement with a serviceable part. This amendment is prompted by the results of a stage 1 HPT disk fracture investigation, which has identified a population of HPT stage 1 and 2 disks that may have subsurface anomalies formed during a forging process. The actions specified by this AD are intended to prevent HPT disk fracture, which could result in an uncontained engine failure, and damage to the aircraft.
2004-17-04: The FAA supersedes Airworthiness Directive (AD) 2001-26-25, which applies to all Grob-Werke Gmbh & Co KG (Grob) Models G102 CLUB ASTIR III, G102 CLUB ASTIR IIIb, and G102 STANDARD ASTIR III sailplanes. AD 2001-26-25 currently requires you to apply a red mark and install a placard on the airspeed indicator to restrict the Vne airspeed. This AD requires you to install additional mass balance in the elevator and ailerons and determine resultant empty weight and empty weight center of gravity; incorporate a revision in the sailplane maintenance manual; and remove the red mark and the red placard on the airspeed indicator (both required by AD 2001-26-25). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent elevator flutter, which could cause structural damage. Such damage could result in loss of control of the sailplane.
2022-12-12: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney Division (PW) PW4062 model turbofan engines. This AD was prompted by a report of a manufacturing quality escape due to insufficient cooling of the low-pressure turbine (LPT) stage 5 air seal resulting in a reduction of the low-cycle fatigue (LCF) life limit. This AD requires removal and replacement of the LPT stage 5 air seal with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
96-17-11: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney (PW) JT9D-7R4 series turbofan engines, that requires replacement of 3rd, 4th, and 5th stage low pressure turbine (LPT) vane retention bolts and nuts, the removal of the 5th stage vane configuration which includes an electro-discharge machined (EDM) slot and replacement with a cast slot configuration, and prohibits the use of uncured anti-gallant compound on vane retention hardware. This amendment is prompted by reports of LPT failures that resulted in uncontained engine failures. The actions specified by this AD are intended to prevent LPT vane failures, which can result in uncontained engine failure, fire, and possible damage to the aircraft.
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.