Results
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.
75-27-06: 75-27-06 PILATUS AIRCRAFT LTD: Amendment 39-2478. Applies To Pilatus Model PC-6 airplanes, serial numbers 685 and below (all variants) manufactured by Pilatus Aircraft Ltd., powered by Lycoming GSO-480-B1A6 engines. NOTE: This AD does not apply to Pilatus PC-6 airplanes manufactured by Fairchild Hiller. Compliance is required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To prevent hazardous fuel leaks from developing at the elbow fittings connecting the fuel line to the fuel pump and carburetor and to prevent a broken fuel line, accomplish the following: (a) Replace aluminum fittings (AN 822-8D and AN 823-8D) with stainless steel fittings (MS 20822-8C and MS 20823-8C), or FAA-approved equivalents. (b) Replace aluminum fuel line P/N 6238.0094.80 with a stainless steel fuel line P/N 6238.0094.80C, or an FAA-approved equivalent. This amendment becomes effective on January 19, 1976.
58-22-01: 58-22-01 HAMILTON STANDARD: Applies to All 6800, 6900, and 7000 Series Externally Surface-Treated Aluminum Alloy Blades (Airfoil Shotpeened and/or Shank Rolled, Including Nickel-Plated Blades). Compliance required at first blade overhaul after January 1, 1959, and at every overhaul thereafter. Two surface-treated aluminum alloy blades have fractured during operation. Blade bending may have, depending on the circumstances surrounding the incident, a serious detrimental effect on the fatigue strength of a blade. Therefore, it is considered necessary to establish a means to detect and evaluate instances of unrecognized blade bending by systematically comparing at overhaul measured face alinement values with previously established values. To establish such a means, follow the detailed instructions contained in Hamilton Standard Service Bulletin No. 546. This procedure requires that face alinement measurements be made prior to any overhaul, and then again following all operationsthat would affect face alinement. (Hamilton Standard Service Bulletins Nos. 546 and 546A cover this same subject.)
53-09-02: 53-09-02\tde HAVILLAND: Applies to All Model DHC-2 Beaver Aircraft. \n\n\tCompliance required as indicated. \n\n\tInspect as soon as practical but not later than the next 100-hour flying time and at 100- hour intervals thereafter for skin cracks on the fuselage side panel at front door step. (See Figure 2 for typical cracks and methods of repairing.) Any cracks found should be stop drilled at each end and repaired in accordance with directions in sketch. 100-hour inspection may be discontinued upon incorporation of recommended repair. \n\n\n\n\n\n\t(de Havilland Technical News Sheet, Series B, No. 59 - Issue 2, dated January 15, 1953, covers this same subject.)
2017-06-04: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 B4- 605R and A300 B4-622R airplanes; and Model A300 C4-605R Variant F airplanes. This AD was prompted by an in-service detection of cracks in the fuselage skin lap joints. This AD requires an ultrasonic inspection of certain skin lap joints, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
2024-16-02: The FAA is superseding Airworthiness Directive (AD) 2018-01- 07, AD 2018-19-33, AD 2019-21-01, AD 2021-26-20, AD 2022-13-09, AD 2022-14-06, AD 2023-09-05, and AD 2023-26-06, which applied to all Airbus SAS 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); and AD 2020-23-11, which applied to all Airbus SAS Model A300 and A300-600 series airplanes. AD 2018-01-07, AD 2018-19-33, AD 2019-21-01, AD 2021-26-20, AD 2022-13-09, AD 2022-14-06, AD 2023-09-05, and AD 2023-26-06 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. AD 2020-23-11 required repetitive inspections for discrepancies of certain areas in and around the fuselage and repair if necessary. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions specified in the superseded ADs, 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. This AD also removes the Model A300 series airplanes from the applicability. The FAA is issuing this AD to address the unsafe condition on these products.