Results
2017-08-07: We are adopting a new airworthiness directive (AD) for certain Learjet, Inc., Model 60 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper fuselage skin under the aft oxygen line fairing is subject to multi-site damage (MSD). This AD requires a one-time inspection of the fuselage skin for corrosion, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
76-01-09: 76-01-09 PILATUS AIRCRAFT LTD: Amendment 39-2490. Applies to Pilatus Model PC-6 airplanes (all variants) manufactured by Pilatus Aircraft Ltd. serial numbers 667 and subsequent and serial numbers 2001 through 2047 inclusive manufactured by Fairchild Hiller. Compliance is required as indicated. To prevent a possible fatigue failure of the elevator attachment brackets on the inboard ends of the right and left elevator surfaces, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD unless already accomplished within the last 25 hours' time in service and thereafter at intervals not to exceed 50 hours time in service since the last inspection, visually inspect both the left and right brackets, P/N 6300.0011.00, of the welded attachment assembly for cracks in the flanges using a glass of at least 10 power in accordance with paragraph 2.1 of Pilatus Aircraft Ltd. Service Bulletin No. 107, dated May 1971, or an FAA-approved equivalent. (b) If cracks are found, before further flight, repair in accordance with paragraph 2.1 of Pilatus Aircraft Ltd. Service Bulletin No. 107, dated May 1971, or an FAA-approved equivalent. (c) Within the next 200 hours' time in service after the effective date of this AD, install reinforcement plates, P/Ns 6002.6993.51 and 6002.6993.52, unless already accomplished, in accordance with paragraph 2.2 of Pilatus Aircraft Ltd. Service Bulletin No. 107, dated May 1971, or an FAA-approved equivalent. (d) The repetitive inspections required by paragraph (a) of this AD may be discontinued after all cracks have been repaired and reinforcement plates have been installed in accordance with paragraph (c) of the AD. (Fairchild Hiller Service Bulletin PC-6-55-3 pertains to this same subject.) This amendment becomes effective on February 6, 1976.
2024-16-04: The FAA is superseding Airworthiness Directive (AD) 2009-25- 13, which applied to certain Bombardier, Inc., Model BD-100-1A10 (Challenger 300) airplanes. AD 2009-25-13 required the deactivation of the left-hand (LH) baggage bay heater mat. Since the FAA issued AD 2009-25-13, Bombardier developed a new design solution for the potential uncontrolled heating of the baggage bay sidewall heater mat. This AD retains the requirements of AD 2009-25-13 and requires modifying the baggage bay sidewall interior panel, heater mat, and water tank heater installation, and doing functional testing. Upon the completion of the new actions, the retained requirements of AD 2009-25- 13 will terminate. This AD also revises the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
2024-15-12: The FAA is superseding Airworthiness Directive (AD) 2021-26- 05, which applied to all Saab AB Model SAAB 2000 airplanes. AD 2021-26- 05 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2021-26-05 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.
2024-15-14: The FAA is superseding Airworthiness Directive (AD) 2021-17- 02, which applied to all ATR-GIE Avions de Transport R[eacute]gional Model ATR42-200, -300, and -320 airplanes. AD 2021-17-02 required a one-time inspection for discrepancies of the wire bundles between the left- and right-hand angle of attack (AOA) probes and the crew alerting computer, and, depending on findings, applicable corrective actions. AD 2021-17-02 also required, for certain airplanes, modifying the captain stick shaker wiring, and for all airplanes, revising the existing aircraft flight manual (AFM) and applicable corresponding operational procedures to incorporate procedures for the stick pusher/shaker. Since the FAA issued AD 2021-17-02, additional modification of the affected wiring for certain airplanes was developed. This AD retains all of the requirements of AD 2021-17-02 and requires installing a new AOA power supply unit and removing the AFM amendment; 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.
2017-08-03: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320-211, -212, -214, -231, -232, and -233 airplanes, and A321 series airplanes. This AD was prompted by the discovery of corroded circlips in fuel vent protectors (FVP) having a certain part number. This AD requires an inspection to determine the part number and serial number of the FVP, and replacement if necessary; and application of sealant on certain nuts and bolts of the National Advisory Committee for Aeronautics (NACA) duct assembly. We are issuing this AD to address the unsafe condition on these products.
2024-16-08: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2D15 (Regional Jet Series 705), and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by a report that the electrical harnesses in the overhead bin above the class divider may have insufficient or no separation with the class divider mounting plate. This AD requires inspecting the overhead bin electrical harnesses at the class dividers and modifying the class divider mounting plate assembly or accomplishing a temporary repair if necessary; and, eventually modifying the class divider mounting plate assembly if a modification was not done after accomplishing the inspection, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2017-08-01: We are superseding Airworthiness Directive (AD) 2013-22-19 for all Gulfstream Aerospace Corporation Model GV and GV-SP airplanes. AD 2013-22-19 required inspecting to determine if fuel boost pumps having a certain part number were installed, replacing the fuel boost pumps having a certain part number, and revising the airplane maintenance program to include revised Instructions for Continued Airworthiness. This new AD reduces the compliance time for revising the airplane maintenance or inspection program. This AD was prompted by reports of two independent types of failure of the fuel boost pump with overheat damage found on the internal components and external housing on one of the failure types, and fuel leakage on the other. We are issuing this AD to address the unsafe condition on these products.
2024-16-11: The FAA is adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by reports of excessive thickness of the trailing edge of certain ailerons, which may affect the assembly of the rear spar with the lower and upper skins. This AD requires a one-time ultrasonic or visual inspection of the aileron rear spar and trailing edge areas, and applicable corrective actions, 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.
74-24-11: 74-24-11 LOCKHEED-CALIFORNIA CO: Amendment 39-2024. Applies to Lockheed- California Model L-1011-385-1 Series airplanes certificated in all categories. To prevent possible failure of the main landing gear retract actuator rod due to stress corrosion, accomplish the following: 1. On those airplanes with 2000 or more landings in service on the effective date of this AD, perform an ultrasonic inspection described at 4, below, of the main landing gear retract actuator rod assembly P/N 1523206-101 within the next 130 cycles additional time in service, and at intervals not to exceed 130 cycles thereafter, until an actuator piston rod P/N 1523206-109 is installed. 2. On those airplanes with 1500 to 1999 landings in service on the effective date of this AD, perform an ultrasonic inspection described at 4, below, of the main landing gear retract actuator rod assembly P/N 1523206-101 within the next 260 additional cycles in service, and at intervals not to exceed 130 cycles thereafter, until an actuator piston rod P/N 1523206-109 is installed. 3. On those airplanes with less than 1500 landings in service on the effective date of this AD, perform an ultrasonic inspection described at 4, below, of the main landing gear retract actuator rod assembly P/N 1523206-101 within the next 390 additional cycles in service, and at intervals not to exceed 130 cycles thereafter, until an actuator piston rod P/N 1523206-109 is installed. 4. The ultrasonic inspection required by 1, 2, 3, above, is for surface discrepancies and/or cracks in the main landing gear retract actuator piston rod of the rod assembly P/N 1523206-101, in the area three and one-half inches from the grease fitting. The inspection is to be accomplished per instructions and procedures outlined in Lockheed Service Bulletin 093-32-083, dated November 5, 1974, or later FAA-approved revisions. The rod assembly is part of the P/N 1523122-107 main landing gear actuator assembly. 5. If, as a result of any of the inspections performed per 1, 2, or 3, above, a surface discrepancy and/or crack is discovered, replace the defective P/N 1523206-101 rod with either a P/N 1523206-109 rod or a P/N 1523206-101 rod as may be available in kits, as spares, or in existing spare cylinder assemblies prior to further flight. If a replacement P/N 1523206-101 rod is used, it must be ultrasonically inspected prior to installation, and at intervals not to exceed 130 cycles in service thereafter. Mark defective rods in a conspicuous manner to prevent inadvertent return to service. Installation of P/N 1523206-109 rod constitutes a terminating action for those inspections required by this AD, and operators may return to normal maintenance practices with respect thereto. 6. Definitions. Prior to the effective date of this AD, one landing is considered to be equivalent to one main landing gear cycle. After the effective date of this AD, one cycle consists of the retraction/extension of the gear. An added"Up Cycle" prior to gear extension counts as an additional cycle. Note: Lockheed Service Bulletin 093-32-083 defines cycles in the same manner. 7. After the effective date of this AD, all main landing gear retract actuator rod assemblies, P/N 1523206-101 must be replaced with P/N 1523206-109 rod assemblies prior to accumulation of 7,600 total cycles in service. 8. Equivalent inspections and replacements may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. 9. Airplanes may be flown to a base for the accomplishment of the inspections and replacements required by this AD, per FAR's 21.197 and 21.199. This amendment becomes effective December 2, 1974.
2017-08-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-102, -103, and -106 airplanes; and Model DHC-8-200 and DHC-8-300 series airplanes. This AD was prompted by reports of incorrect installation of the auto-ignition system due to crossed wires at one of the splices in the auto-relight system. This AD requires inspecting the auto-ignition system for correct wiring, and doing corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2024-15-09: The FAA is adopting a new airworthiness directive (AD) for Textron Aviation Inc. (Textron) (type certificate previously held by Cessna Aircraft Company) Model 525, 525A, and 525B airplanes with Tamarack active technology load alleviation system (ATLAS) winglets installed per Supplemental Type Certificate (STC) No. SA03842NY. This AD was prompted by a report of the potential for a failure of the ATLAS system in which a loss of load alleviation would be un-annunciated. This AD requires installing placards on the left-hand inboard edge of the Tamarack active camber surface (TACS) and revising the existing airplane flight manual (AFM) for your airplane. The FAA is issuing this AD to address the unsafe condition on these products.
2017-08-04: We are superseding Airworthiness Directive (AD) 2015-03-01, for all Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2015-03-01 required installing additional attaching hardware on the left and right engine fan cowl access panels and the nacelle attaching structures. This new AD requires weight and balance data to be included in the Weight and Balance Manual for certain modified airplanes. This new AD also requires the weight and balance data to be used in order to calculate the center of gravity for affected airplanes. This AD was prompted by updates to the weight and balance data needed to calculate the center of gravity for affected airplanes. We are issuing this AD to address the unsafe condition on these products.
67-08-03: 67-08-03 FAIRCHILD-HILLER: Amdt. 39-361 Part 39 Federal Register March 4, 1967. Applies to Models UH-12D and UH-12E Helicopters. Compliance required as indicated. To prevent failure of the attachment of cyclic control bracket P/N 3301-5 to the transmission housing P/N 23542, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, inspect the cyclic control bracket attachment bolts for a torque of less than 50 inch-pounds and visually inspect the Rosan inserts in the transmission housing for cracks or any other damage. Replace damaged inserts and inserts where a bolt torque of less than 50 inch-pounds is encountered prior to further flight in accordance with Fairchild-Hiller Service Information Letter No. 3054 of November 4, 1966, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (b) Within the next 100 hours' time in service afterthe effective date of this AD, unless already accomplished, remove the Rosan R206SB-8 inserts and install Roson RD206SB-8 inserts in their place and install MS20073-04-10 bolts in accordance with Fairchild-Hiller Service Information Letter No. 3054 of November 4, 1966, or later revisions approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This directive effective March 9, 1967.
2017-05-51: We are publishing a new airworthiness directive (AD) for Bell Helicopter Textron Canada (Bell) Model 429 helicopters. This AD requires inspecting the condenser blower motor (motor) and condenser blower (blower) to determine if the motor is securely attached to the blower support (shroud). This AD is prompted by a report that the motor detached from the blower. The actions of this AD are intended to prevent an unsafe condition on these products.
2024-16-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model SA330J helicopters. This AD was prompted by a report of a main rotor gearbox (MGB) flange assembly coupling (coupling) that was incorrectly assembled. This AD requires a one-time visual inspection to determine correct assembly of each sliding flange installed on each MGB coupling, and if necessary, further corrective actions. This AD also prohibits installing certain MGB couplings or any MGB equipped with certain MGB couplings on any helicopter. These requirements 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.
2017-06-07: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, -200, and -300 series airplanes; and Airbus Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports that nonconforming aluminum alloy was used to manufacture several structural parts on the inboard flap. This AD requires identification of the potentially affected inboard flap parts, a one-time eddy current inspection to identify which material the parts are made of, and, depending on findings, replacement with serviceable parts. We are issuing this AD to address the unsafe condition on these products.
73-11-04: 73-11-04 SIAI-MARCHETTI: Amdt. 39-1644. Applies to SIAI Marchetti Models S.205-18R, -20R, and -22R airplanes. Serial Numbers 001 through 003, and 101 through 399. Compliance is required within the next 100 hours' time in service after the effective date of this AD unless already accomplished. To provide a means for periodic lubrication to prevent seizing of the eye bolts, P/N 205- 9-047-11, connecting the articulated drag braces to the main landing gear cross members, install grease fittings and washers, P/N MS15720-1 and P/N 205-9-012-15, respectively, in the attachments for the eye bolts, P/N 205-9-047-11, to the main landing gear cross members in accordance with SIAI Marchetti Service Bulletin No. 205B32 dated November 19, 1971, or an FAA-approved equivalent. This amendment becomes effective June 20, 1973.
2017-07-09: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires removing from service the tail gearbox center housing (housing) when it has 12,200 or more hours time-in-service (TIS). This AD was prompted by fatigue analysis conducted by Sikorsky that determined the housing required a retirement life. The actions are intended to prevent an unsafe condition on these products.
2017-07-04: We are superseding Airworthiness Directive (AD) 2013-24-17 for General Electric Company (GE) GE90-110B1 and GE90-115B turbofan engines with certain high-pressure compressor (HPC) rotor stage 2-5 spools installed. AD 2013-24-17 required removing these spools from service at times determined by a drawdown plan. This AD retains the same requirements as AD 2013-24-17. This AD also adds additional part number (P/N) HPC spools to the applicability. This AD was prompted by reports of cracking on these additional spools. We are issuing this AD to correct the unsafe condition on these products.
2024-16-03: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400F series airplanes. This AD was prompted by a report that cap seals were not applied to certain fasteners in the fuel tanks during production. This AD requires applying cap seals to certain fastener collars inside the fuel tanks. The FAA is issuing this AD to address the unsafe condition on these products.
2017-07-05: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by reports of cracks in main landing gear (MLG) leg components. This AD requires detailed visual inspections of these MLG leg components and replacement of the MLG leg if cracked components are found. We are issuing this AD to address the unsafe condition on these products.
2024-15-10: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 505 helicopters. This AD was prompted by a fuel leakage discovered during fuel system crash impact testing activity. This AD requires installing a grommet around the sump drain port fitting airframe hole, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2017-06-12: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319 and A320 series airplanes. This AD was prompted by a report that fatigue cracking could appear at certain fastener locations in the longeron area below the emergency exit cut-outs. This AD requires the modification of certain fastener locations in the longeron area below the emergency exit cut-outs. We are issuing this AD to address the unsafe condition on these products.
2017-07-02: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model 269D and Model 269D Configuration A helicopters. This AD requires reducing the life limit of and inspecting certain drive shafts. This AD is prompted by four incidents involving failure of a drive shaft. The actions specified by this AD are intended to prevent the unsafe condition on these products.