Results
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.