Results
2025-06-05: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X, FALCON 900EX, and FALCON 2000EX airplanes. This AD was prompted by reported occurrences of swelling of the lithium-polymer internal and external batteries of certain electronic display units (EDUs). This AD requires modifying certain EDUs and prohibits the installation of affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
75-08-07: 75-08-07 ROCKWELL INTERNATIONAL CORP., GENERAL AVIATION DIVISION: Amendment 39-2160. Applies to Model 690A airplanes, Serial Numbers 11100 through 11208. Compliance required within 25 hours' time in service after the effective date of this AD, unless otherwise accomplished. To minimize the possibility of bleed air line failure and resultant leakage, accomplish the following: Modify Model 690A airplanes in accordance with Rockwell International, General Aviation Division, Service Bulletin Number 147 dated November 27, 1974, except that the requirements of Paragraphs "s" and "u" may be ignored and the first item under "SUPPLY DATA" may be deleted, or later approved revision, or in accordance with an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. This amendment becomes effective on April 10, 1975.
2013-11-15: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model BO-105A, BO-105C, BO- 105S, BO-105LS A-1, BO-105LS A-3, EC135 P1, EC135 P2, EC135 P2+, EC135 T1, EC135 T2, EC135 T2+, MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A- 4, MBB-BK 117 B-1, MBB-BK 117 B-2, MBB-BK 117 C-1, and MBB-BK 117 C-2 helicopters with certain part-numbered cantilever assemblies, cyclic stick locking devices, or cyclic stick holder assemblies installed. This AD requires modifying and identifying the cyclic stick cantilever or lock. This AD was prompted by pilots inadvertently taking off with the cyclic locked. The actions of this AD are intended to prevent a pilot taking off with the cyclic in the locked position, which could result in loss of control of the helicopter.
2013-11-16: We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation (Type Certificate Previously Held by Raytheon Aircraft Company) Model BAe.125 Series 800A (including C-29A and U-125), and 800B airplanes; and Model Hawker 800 (including variant U-125A) and 800XP airplanes modified in accordance with a certain winglet supplemental type certificate. This AD requires revising the Limitations section of the airplane flight manual (AFM) and installing placards on the instrument panel. This AD was prompted by reports of several instances of severe vibration and wing/aileron oscillations. We are issuing this AD to prevent vibration and wing/aileron oscillations, which could cause structural damage or lead to divergent flutter, and result in loss of integrity of the wing, loss of control of the airplane, and in-flight breakup.
2013-12-02: We are adopting a new airworthiness directive (AD) for certain Engine Alliance GP7270 and GP7277 turbofan engines. This AD was prompted by damage to the high-pressure compressor (HPC) stage 7-9 spool caused by failure of the baffle plate feature on affected HPC stage 6 disks. This AD requires initial and repetitive borescope inspections of the baffle plate feature and removal from service of the HPC stage 6 disk if the plate is missing material. This AD also requires mandatory removal from service of these HPC stage 6 disks at the next HPC module exposure. We are issuing this AD to prevent failure of the HPC stage 7-9 spool, uncontained engine failure, and damage to the airplane.
2013-11-12: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes. This AD was prompted by reports of failure of a screw cap or end cap of the hydraulic system accumulator while on the ground, which resulted in loss of use of that hydraulic system and high-energy impact damage to adjacent systems and structures. This AD would require inspecting for the correct serial number of a certain hydraulic system accumulator, and replacing affected hydraulic system accumulators with new or serviceable accumulators. We are issuing this AD to prevent failure of a screw cap or end cap and loss of the related hydraulic system, which could result in damage to airplane structure and consequent reduced controllability of the airplane.
50-43-01: 50-43-01 DOUGLAS: Applies to All Model DC-6 Aircraft. \n\n\tTo be accomplished on or before the next major inspection where facilities are available and in any event by December 15, 1950, unless already accomplished at last previous tire change, and thereafter at the regular major inspection nearest to 330 hours. This inspection period may be extended to tire replacement periods by the assigned CAA Agent when the airline's service experience indicates that a satisfactory level of safety is being maintained. \n\n\tRemove the tires from all Goodyear main wheels, Model L20HBMF, wheel assemblies 9540049 and 9540332, and thoroughly inspect by Zyglo or equivalent methods the critical areas of the wheel, such as: \n\n\t1.\tBrake drive flange area. \n\n\t2.\tTire bead radius of the fixed flange. \n\n\t3.\tTire bead seat radius of the demountable flange. \n\n\t4.\tRadius of the demountable flange step. \n\n\t5.\tThe flange returning ring groove in the wheel. \n\n\tIf cracks are found in any of the critical areas at one of these inspections, the wheel should be retired from service.
2025-06-09: The FAA is adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190-300 and ERJ 190-400 airplanes. This AD was prompted by a report of a MAU 3B failure which led to brake fault advisory messages followed by loss of normal braking that was undetected until the brakes were pressed by the pilots. This AD requires revising the existing airplane flight manual (AFM) to incorporate procedures associated with the failure of certain modular avionics units (MAUs), as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-11-05: We are adopting a new airworthiness directive (AD) for Bell Model 214B, 214B-1, and 214ST helicopters with a certain tail rotor hanger bearing (bearing) installed. This AD requires inspecting the bearing to determine whether an incorrectly manufactured seal material is installed on the bearing. This AD is prompted by a report that certain bearings were manufactured with an incorrect seal material that does not meet Bell specifications. The actions specified by this AD are intended to prevent loss of bearing grease, failure of the bearing, and subsequent loss of control of the helicopter.
69-13-08: 69-13-08 BRITTEN-NORMAN LTD: Amdt. 39-791 applies to BN-2 and BN-2A Aircraft with fuel line P/N NB-57-439. Compliance required as indicated. (a) To prevent fuel leaks in the engine compartment, before the next flight and before each subsequent flight, inspect fuel line P/N NB-57-439 installed between the engine driven fuel pump and the carburetor for evidence of leakage in accordance with Britten-Norman Ltd. Service Bulletin BN-2/SB.11 Issue 2 dated February 24, 1969, or later ARB approved issue, or an FAA approved equivalent. (b) If during the inspection required by paragraph (a) of this AD evidence of leakage is found, replace P/N NB-57-439 with a serviceable part of the same part number, or with Dunlop P/N 6/W2/121/51/51/24.0 or 6/W2/121/51/51/15.5. (c) The repetitive inspections required by paragraph (a) of this AD may be discontinued when Dunlop P/N 6/W2/121/51/51/24.0 or 6/W2/121/51/51/15.5 has been installed in accordance with Britten-Norman Ltd. Service Bulletin BN-2/SB 11 Issue 2, dated February 24, 1969, or later ARB approved issue, or an FAA approved equivalent. This amendment becomes effective July 2, 1969.