Results
2024-07-07: The FAA is superseding Airworthiness Directive (AD) 2010-18- 06, which applied to all GA8 Airvan (Pty) Ltd Model GA8 and GA8-TC320 airplanes. AD 2010-18-06 required inspections and a minor design change to the forward slide of the cargo door with corrective action as necessary. Since the FAA issued AD 2010-18-06, the Civil Aviation Safety Authority (CASA), which is the aviation authority for Australia, superseded the previous CASA Australia AD to incorporate more detailed inspections and additional modifications as specified in updated service information published by the manufacturer. This AD was prompted by reports of in-flight cargo door separation. This AD requires inspections and rework (modifications) of the cargo door with corrective action as necessary. The FAA is issuing this AD to address the unsafe condition on these products.
99-19-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model BAe ATP series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
2024-06-13: The FAA is superseding Airworthiness Directive (AD) 2022-21-15 for certain Diamond Aircraft Industries GmbH (DAI) Model DA 42, DA 42 NG, and DA 42 M-NG airplanes. AD 2022-21-15 required replacing the rudder T-yoke axle with an improved rudder T-yoke axle. Since the FAA issued AD 2022-21-15, the European Union Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to correct an unsafe condition on these products. This AD requires, for certain airplanes, inspecting the rudder steering bracket edge distance and depending on the inspection results, inspecting the T-yoke bolt hole for wear and play, and corrective action if necessary. For certain airplanes this AD requires replacing the rudder T-yoke bolt (axle) with a serviceable part, installing a new self-locking nut, and applying torque seal marks on the rudder T-yoke bolt head and self-locking nut. For all airplanes this AD requires repetitively inspecting the torque seal marks on the rudder T-yoke bolt head for proper alignment and the self-locking nut for proper installation and corrective action if necessary. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2005-08-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747 series airplanes. This AD requires repetitive detailed inspections for cracks in the crease beam and adjacent structure of the fuselage, and related investigative and corrective actions if necessary. This AD is prompted by fatigue cracks found in the crease beam during a follow-on inspection of a previously installed modification. We are issuing this AD to find and fix fatigue cracking of the fuselage frame, which could result in reduced structural integrity of the frame and consequent rapid decompression of the airplane.
2024-06-10: The FAA is superseding Airworthiness Directive (AD) 2022-25- 18, which applied to certain BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ series airplanes. AD 2022-25-18 required repetitive inspections for cracking of the main landing gear (MLG) side stay outer link and replacement if necessary. This AD was prompted by additional investigations of the causes of the cracking being conducted. This AD requires a reduction of the repetitive visual inspection interval, provides optional repetitive special detailed inspections, and requires accomplishing a one-off dimensional tolerance check and performing a repetitive lubrication of the MLG side stay outer link pivot, as specified in United Kingdom (U.K.) Civil Aviation Authority (CAA) (U.K. CAA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
77-23-04: 77-23-04 AVIONS MARCEL DASSAULT-BREGUET AVIATION (AMD-BA): Amendment 39-3075. Applies to Model Falcon 10 airplanes, S/N 1 through 56, certificated in all categories, and any other Model Falcon 10 airplane incorporating Badin Crouzet total-pressure probes, P/N 33790-10. Compliance is required as indicated. To prevent failure of total-pressure probe accomplish the following: (a) Prior to the accumulation of 600 total airplane flights or within the next 100 flights after the effective date of this AD, whichever occurs later, replace both total-pressure probes, P/N 33790-10, with new parts of the same part number, or with probes of improved design, P/N 33790-20, in accordance with paragraph 2 of Falcon 10 Service Bulletin No. F10.34.007, dated July 17, 1975, or an equivalent approved by the Chief, Aircraft Certification Staff for Europe, Africa, and Middle East Region, c/o American Embassy, A.P.O. New York, N.Y. 09667. (b) Replacement probes P/N 33790-10 are hereby life limited to 600 flights. (c) For the purpose of this AD, a flight is defined as a single takeoff and landing. If records are not maintained of each takeoff and landing, the number of flights may be determined by dividing each airplane's hours time in service by the operator's fleet average time from takeoff to landing for the airplane type, subject to acceptance by the assigned FAA airworthiness inspector. This amendment becomes effective December 10, 1977.
2005-08-02: The FAA is superseding an existing airworthiness directive (AD), which applies to all EMBRAER Model EMB-135 and -145 series airplanes. That AD currently requires repetitive inspections of the electrical connectors of the electric fuel pumps to detect discrepancies, and follow-on corrective actions. This new AD extends the repetitive intervals for the inspections; adds new criteria for replacing discrepant fuel pumps; adds a new requirement for applying anti-corrosion spray; adds a requirement to replace all fuel pumps with improved fuel pumps; and adds repetitive inspections after all six fuel pumps are replaced. This AD is prompted by the manufacturer's development of a new modification that addresses the unsafe condition in the existing AD. We are issuing this AD to prevent an ignition source in the fuel tank or adjacent dry bay, which could result in fire or explosion.
2024-05-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a report of a fouling condition (interference) between the gimbal bushing and the airplane horizontal stabilizer trim actuator (HSTA) structural fitting, which prevented engagement of the secondary load path. This AD requires replacing the upper gimbal bushing flanges, 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.
2024-05-12: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent 1000-AE3, Trent 1000-CE3, Trent 1000-D3, Trent 1000-G3, Trent 1000-H3, Trent 1000-J3, Trent 1000-K3, Trent 1000-L3, Trent 1000-M3, Trent 1000-N3, Trent 1000- P3, Trent 1000-Q3, and Trent 1000-R3 engines. This AD is prompted by reports of wear in the combining spill-valve (CSV) assembly of certain hydro-mechanical units (HMUs). This AD requires removing certain HMUs from service and replacing with a serviceable part or modifying the HMU by replacing the CSV assembly, which is an optional terminating action; and prohibits installing certain HMUs unless the HMU is a serviceable part, 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.
2015-17-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a report of several events where pilots experienced difficulty in lateral control of the airplane after doing a climb through heavy rain conditions and a determination that the cause was water ingress in the aileron control pulley assembly. This AD requires, for certain airplanes, inspecting for correct clearance and rework if necessary, and, for certain other airplanes, installing a cover for the aileron pulley assembly. We are issuing this AD to prevent water ingress in the aileron control pulley assembly, which could freeze in cold conditions and result in reduced control of the airplane.
2015-17-10: We are superseding Airworthiness Directive (AD) 2007-04-13 for certain SOCATA Model TBM 700 airplaness (type certificate previously held by EADS SOCATA). 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 cracks found on the main landing gear cylinders. We are issuing this AD to require actions to address the unsafe condition on these products.
60-11-10: 60-11-10 VICKERS: Amdt. 148 Part 507 Federal Register May 10, 1960. Applies to All Viscount Model 745D Aircraft (Pre-modification D.2013 Parts (C), (J), (D), and (K) Standard) and All Viscount 810 Series Aircraft (Pre-modification FG.237 Parts (D) an (K) Standard). Compliance required at next removal of rudder trim tab and/or elevator spring tab, but not later than June 1, 1961. To preclude the possibility of inadvertent interchange of Pre-mod. D.2013 and FG. 237 rudder trim tab and elevator spring tab torque tube assemblies, Vickers Modification D.2918 (700 Series) and FG.1671 (800/810 Series) must be incorporated. This modification insures that the upper rudder trim tab torque tube assembly cannot be connected to the elevator spring tab and the elevator spring tab torque assembly cannot be connected to the rudder trim tab in the upper position. Incorporation of this modification on 700 Series aircraft is accomplished by installation of a nuissance bracket, P/N 70123-359 or equivalent, fitted to the tabs at the point of attachment of the relevant short (Pre-mod. D.2013) skewbars. On Model 810 Series aircraft, the long skewbar introduced by Mod. FG.237 is incorporated in the basic design of the right elevator trim tab. The left elevator anti-balance tab and the spring tab are operated by an external rod system to which Mod. FG.237 is not applicable. Since the rudder tab has a short skewbar, of Pre-mod. FG.237 standard, fitted at the upper position, it is required that installation of the nuissance bracket of Mod. FG.1671 or equivalent be made as a positive safeguard against incorrect assembly. (Vickers-Armstrongs Modification Bulletins D.2918 (700 Series) and FG.1671 (800/810 Series) cover this subject.)
2015-17-07: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-603, B4-605R, B4-620, B4-622, B4-622R airplanes; all Airbus Model A300 C4-605R Variant F airplanes; and certain Airbus Model A300 F4-605R airplanes. This AD was prompted by the manufacturer's review of all repairs accomplished using the structural repair manual. This review was done using revised fatigue and damage tolerance calculations. This AD requires an inspection of the surrounding panels of the left and right forward passenger doors, and corrective actions if necessary. We are issuing this AD to detect and correct previous incomplete or inadequate repairs to the surrounding panels of the left and right forward passenger doors and the fail-safe ring, which could negatively affect the structural integrity of the airplane.
76-13-10: 76-13-10 GRUMMAN AMERICAN: Amendment 39-2657 as amended by Amendment 39-2777. Applies to Model G-164 and G-164A Ag-Cat Airplanes, S/N 1 through 1064, certificated in all categories. Compliance required as indicated. To prevent possible hazards associated with main landing gear strut failures, accomplish the following: (a) For airplanes equipped with Grumman American main landing gear struts P/N A1515-11, -12, P/N A1530-11, -12, and Cessna struts P/N 0341109-1, -2: (1) Within the next 100 landings after the effective date of this airworthiness directive, unless accomplished within the last 4400 landings, remove the gear struts and inspect the struts for cracks using dye penetrant or magnetic particle inspection procedures or with an FAA approved equivalent inspection procedure. (2) Repeat the inspections of paragraph (a)(1) at intervals not to exceed 4500 landings. (3) Inspect the struts for cracks and corrosion damage using dye penetrant inspection procedures,at each 1000 landings following the inspections specified in paragraph (a)(1) and (a)(2). This inspection can be conducted without removing the gear struts from the aircraft. (b) Replace cracked or corroded parts prior to further flight with unused struts, Grumman American P/N A1530-33, -34 or with FAA approved equivalent parts. (c) For the purpose of complying with this airworthiness directive, subject to the acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time for takeoff to landing for the airplane type. (d) Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance time in this AD. Grumman American Aviation Corporation Service Note No. 13 covers this same subjects. Amendment 39-2657 was effective July 7, 1976. This Amendment 39-2777 is effective November 30, 1976.
2005-08-04: The FAA is adopting a new airworthiness directive (AD) for GE CF6-45 and CF6-50 series turbofan engines. This AD requires reviewing accumulated cyclic-life records of 10 life-limited rotating parts, correcting those records, and removing from service parts that exceed the low-cycle-fatigue (LCF) life limits published in the Engine Manual Chapter 5, Airworthiness Limitations Section (ALS). This AD results from an error in a tracking database that subtracted flight cycles of certain serial number (SN) parts from the actual accumulated cycles. We are issuing this AD to prevent rotating parts that may have exceeded their LCF life limit from failing, leading to uncontained engine failure.
2024-06-05: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.
2024-05-04: The FAA is superseding Airworthiness Directive (AD) 2020-23- 04, which applied to certain Gulfstream Aerospace Corporation Model GVII-G500 and GVII-G600 airplanes. AD 2020-23-04 required revising the existing airplane flight manual (AFM) and airplane maintenance manual (AMM) to include information pertaining to the fuel boost pump. This AD was prompted by a report of misassembled impellers on the shaft of the fuel boost pump during production. This AD retains the requirements of AD 2020-23-04 and requires inspecting affected fuel boost pumps for proper installation of the impeller shaft key, marking affected fuel boost pumps that pass that inspection, and replacing fuel boost pumps that fail. This AD also limits the installation of affected fuel boost pumps. The FAA is issuing this AD to address the unsafe condition on these products.
2024-05-13: The FAA is adopting a new airworthiness directive (AD) for all Embraer S.A. Model EMB-545 and EMB-550 airplanes. This AD was prompted by a report of a hard landing event with substantial damage to the airplane, in which the angle of attack (AOA) limiter was engaged during the final approach phase in unstable air conditions and remained engaged until the airplane touched down on the runway. This AD requires revising the Limitations and Normal Procedures sections of the existing airplane flight manual (AFM) to incorporate new operational airspeed limitations, and flight control limitations and approach procedures when AOA limiter protection is engaged, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. This AD also requires inspecting records for instances of AOA limiter engagement during a certain phase of flight and reporting findings to the FAA. The FAA is issuing this AD to address the unsafe condition on these products.
76-22-09: 76-22-09 GRUMMAN AMERICAN: Amendment 39-2761. Applies to Model AA-5A serial numbers AA5A-001 through AA5A-0227 and Model AA-5B serial numbers AA5B-0111 through AA5B-0359 airplanes certificated in all categories. Compliance required before further flight. To prevent continued use of certain Stewart Warner oil coolers which may be defective, accomplish the following: (a) Remove the cowl assembly as necessary to gain access to the oil cooler. (b) Check the oil cooler model number and serial number. Oil cooler model and serial numbers are ink stamped on the side of the cooler with the serial number following the model number. 1. If the oil cooler is either model number 10568B with serial number 101 through 579 or model number 10578B with serial number 101 through 634, or if the model or serial number is illegible, remove and replace it with an oil cooler not of the above model and serial numbers. 2. If the oil cooler is neither model number 10568B with serial number 101 through 579 nor model number 10578B with serial number 101 through 634, make the record entry required in paragraph (c). (c) The inspection and maintenance record entry in paragraph (b)2. may be accomplished by holder of a pilot's certificate issued under Part 61 of the Federal Aviation Regulations on any aircraft owned or operated by him. (d) Any equivalent methods of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. NOTE: A ferry flight to accomplish a needed oil cooler replacement may be issued under the provision of FAR 21.197 by FAA Flight Standards District Offices. Grumman American Service Bulletin Number 156 pertains to this subject. This amendment becomes effective November 10, 1976, to all persons except those to whom it was made effective earlier by airmail letters issued on October 18, 1976.
2005-07-23: The FAA is adopting a new airworthiness directive (AD) for all Dassault Model Falcon 10 series airplanes. This AD requires revising the Limitations section of the airplane flight manual (AFM) to include a statement prohibiting flight into known or forecasted icing conditions, and installing a placard in the flight deck. In lieu of the AFM revision and placard installation, this AD allows identifying the part number of each flexible hose in the wing anti-icing system, performing repetitive detailed inspections of each hose for delamination, and performing corrective actions if necessary. This AD is prompted by a report of delamination of the internal wall of a flexible hose in the wing anti-icing system. We are issuing this AD to prevent collapse of the flexible hoses in the wing anti-icing system, which could lead to insufficient anti-icing capability and, if icing is encountered in this situation, could result in reduced controllability of the airplane.
2001-06-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 series airplanes. This action requires a one-time inspection to find chafing or damage of the integrated drive generator cables of the cable harness assembly of the engines, and follow-on actions. This action is necessary to prevent such chafing or damage, which could result in electrical arcing between the cable and an engine cowl door, creating a possible ignition source and consequent fire and/or loss of electrical power on the airplane. This action is intended to address the identified unsafe condition.
2024-04-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a report of possible chafing of a power harness at fuselage frame (FR) 65. This AD requires rerouting the power harness, 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.
2024-05-51: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) Model CT7-2E1, CT7-2F1, CT7-8A, CT7-8E, CT7-8F5 engines, and various restricted category helicopters with GE Model T700-GE-700,-701A, -701C, -701D/CC, -701D, -401, -401C, CT7-2D or CT7-2D1 engines installed. This AD was prompted by at least four reports of failures of the torque reference tube magnetic insert braze joint of the power turbine drive shaft assembly within the last several months. This AD requires a phase array ultrasonic inspection of the torque reference tube magnetic insert braze joint of the power turbine drive shaft assembly for inadequate braze coverage, and repair or replacement of the power turbine drive shaft assembly if necessary. The FAA previously sent an emergency AD to all known U.S. owners and operators of these engines and helicopters and is now issuing this AD to address the unsafe condition on these products.
2000-25-08: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France (ECF) Model AS-350B, BA, B1, B2, and D; and AS-355E, F, F1, F2, and N helicopters. That AD currently requires inspecting the main gearbox suspension bi-directional cross beam (cross beam) for cracks, replacing the cross beam if a crack is found, and adding time intervals for repetitive dye-penetrant inspections on cross beams with 5,000 or more hours time-in-service (TIS). This amendment requires the same inspections as the existing AD but would delete repetitive dye-penetrant inspections on cross beams with 5,000 or more hours TIS. This amendment is prompted by the discovery that repetitive dye-penetrant inspections were erroneously required in the existing AD. The actions specified by this AD are intended to prevent failure of the cross beam that could lead to rotation of the main gearbox, severe vibrations, and a subsequent forced landing.
2024-04-05: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB412 and AB412 EP helicopters. This AD was prompted by reports of cracks in the lateral mounts of the main transmission support case. This AD requires repetitive visual inspections and fluorescent penetrant inspections (FPI) and, depending on the results, corrective action, 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.