Results
2018-12-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 and 787-9 airplanes. This AD was prompted by a report of an in-service reliability issue of a latent flow sensor failure combined with single cabin air compressor (CAC) operation. This condition resulted in reduced airflow which led to a persistent single CAC surge condition that caused overheat damage to the CAC inlet. This AD requires installing new pack control unit (PCU) software for the cabin air conditioning and temperature control system (CACTCS) and new CAC outlet pressure sensor J-tube hardware, and doing related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
69-21-01: 69-21-01 HUGHES: Amdt. 39-859. Applies to Model 269 and 369H series helicopters with Hughes P/N 269A6027 or 369A5400 tail rotor transmission installed. Compliance required prior to further flight unless already accomplished. To prevent loss of tail rotor power due to possible failure of the input pinion shaft (a part of the 369A5425 gear shaft assembly) of certain tail rotor transmissions accomplish the following: Prior to further flight, determine if the serial number of the transmission gearbox installed is one of those listed in Hughes Service Information Notice, No. N-71, dated September 24, 1969 or later FAA approved revisions (all 269 series), or Hughes Service Information Notice No. HN-1, dated September 24, 1969, or later FAA approved revisions (all Model 369H series). If the gearbox is listed, and if the total time in service of the gearbox is in excess of 90 hours, replace the gearbox before the next flight with a gearbox marked with "M" on the tail rotortransmission identification plate or a serial number not listed in the Hughes Notices. For those gearboxes listed with less than 90 hours total time in service, replace the gearbox before 90 hours total time in service. If the tail rotor gearboxes are in spares inventory and within the listed serial numbers, they must not be installed on any aircraft. NOTE: The tail rotor transmission identification plate will be stamped with the letter "M" following the serial number to indicate installation of a satisfactory input pinoin shaft. Hughes Service Information Notice N-71 dated September 24, 1969, or later FAA approved revisions and HN-1 dated September 24, 1969 or later FAA approved revisions cover same subject. This amendment becomes effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated September 26, 1969.
2006-12-17: The FAA is superseding an existing airworthiness directive (AD) which applies to all Boeing Model 737-200C series airplanes. That AD currently requires a one-time external detailed inspection for cracking of the fuselage skin in the lower lobe cargo compartment; repetitive internal detailed inspections for cracking of the frames in the lower lobe cargo compartment; repair of cracked parts; and terminating action for the repetitive internal detailed inspections. This new AD restates the requirements of the existing AD and adds a requirement to perform repetitive detailed inspections of the body station (BS) 360 and BS 500 fuselage frames, after accomplishing the terminating action, and repair if necessary. This AD results from multiple reports that the existing AD is not fully effective in preventing cracks in the BS 360 and BS 500 fuselage frames. We are issuing this AD to detect and correct cracking of the fuselage frames from BS 360 to BS 500B, which could lead to loss of the cargo door during flight and consequent rapid decompression of the airplane.
72-01-02: 72-01-02 BEECH: Amdt. 39-1371. Applies to following airplanes: MODELS SERIAL NUMBERS AFFECTED 95-55 TC-1 thru TC-190 95-A55 TC-191 thru TC-501 (except TC-350 & TC-371) 95-B55 and 95-B55A TC-371, TC-520 thru TC-1409 95-B55B TF-1 thru TF-70 95-C55 and 95-C55A TC-350, TE-1 thru TE-451 D55 and D55A TE-452 thru TE-767 E55 and E55A TE-768 thru TE-846 58 and 58A TH-1 thru TH-173 Compliance: Required as indicated, unless already accomplished. To prevent engine damage from loss of lubricant due to accidental opening of oil sump drains by age stiffened plastic drain hoses, within 25 hours' time in service after the effective date of this AD, accomplish the following: Remove the oil drain tubes from the sump drain valves. Beechcraft Service Instructions No. 0473-241 pertains to this same subject. This amendment becomes effective January 5, 1972.
2000-05-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Rolls-Royce plc RB211-524 series turbofan engines. This action requires initial and repetitive ultrasonic inspections for cracks in fan blade dovetail roots, and, if necessary, replacement with serviceable parts. This action also provides the options of installing improved design fan blades or reworking current fan blades to the improved configuration as terminating action for the inspections. This amendment is prompted by reports of fan blade failures due to dovetail root cracks. The actions specified in this AD are intended to prevent possible multiple fan blade failures, which could result in an uncontained engine failure and damage to the aircraft.
2000-05-17: This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter France Model EC 120B helicopters, that currently requires, at specified time intervals, inspecting the engine coupling tube for cracks and replacing any cracked engine coupling tube with an airworthy engine coupling tube. This amendment requires, at specified time intervals, visually inspecting and dye-penetrant inspecting the coupling tube for any crack and replacing any cracked coupling tube with a reinforced, airworthy coupling tube. Replacing all coupling tubes and certain engine support fitting components is required on or before March 31, 2000. This amendment is prompted by the discovery of cracks in several coupling tubes. The actions specified by this AD are intended to prevent coupling failure, loss of engine drive, and a subsequent forced landing.
72-02-01: 72-02-01 CESSNA: Amendment 39-1379. Applies to Models 411, 411A, 421, 421A and 421B (up to and including Serial Number 421B0147) airplanes. Compliance: Required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished: To prevent possible propeller separation in flight as a result of rough engine operation, accomplish the following: A) Check the torque on the propeller attachment nuts by applying 80 to 85 ft. lbs. torque. Nuts which do not move when the proper torque is applied should not be further tightened. If any nuts are found loose (70 Ft. lbs. torque or less), complete the detailed inspection required by Cessna Service Letter ME71-16 Supplement No. 2, dated January 7, 1972. (See Note) NOTE: A special adapter, Cessna P/N 5090006-5 for Hartzell propellers or P/N 5090006-9 for McCauley propellers, or equivalent, is required to accomplish the above torque check. B) Modify the engine tachometer by incorporating a yellow arc restricting continuous engine operation for Models 411 and 411A airplanes between 2100 and 2350 rpm, and for Models 421, 421A and 421B airplanes between 1950 and 2225 rpm. C) Install appropriate operational placard on the engine tachometer with the following wording: "AVOID CONTINUOUS OPERATION IN YELLOW ARC" D) Replace existing Airplane Flight Manual pages with the following FAA/DOA approved revised Airplane Flight Manual pages, or later FAA/DOA approved revision, as appropriate: 1. Model 411 - Revision No. 12 dated December 7, 1971. 2. Model 411A - Revision No. 4 dated December 7, 1971. 3. Model 421 - Revision No. 8 dated December 8, 1971. 4. Model 421A - Revision No. 4 dated December 8, 1971. 5. Model 421B (Serial Numbers 421B001 through 421B0147) - Revision No. 4 dated December 1, 1971. E) Equivalent methods of compliance with this AD must be approved by Chief, Engineering and Manufacturing Branch, FAA, CentralRegion. Cessna Service Letter ME71-16 Supplement No. 2 dated January 7, 1972, pertains to this subject. NOTE: This does not preclude continued recheck of propeller attach bolt as required by FAR 91 and specified for each 100 hours' time in service per Cessna Service Instructions. This amendment becomes effective January 18, 1972.
2020-24-01: The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. Model PC-24 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as overheating of the electrical wiring splices close to the right-hand pitot-static connector on frame 10. The FAA is issuing this AD to address the unsafe condition on these products.
2020-24-02: The FAA is superseding Airworthiness Directive (AD) 2018-23- 51, which applied to all The Boeing Company Model 737-8 and 737-9 (737 MAX) airplanes. AD 2018-23-51 required revising certificate limitations and operating procedures of the Airplane Flight Manual (AFM) to provide the flightcrew with runaway horizontal stabilizer trim procedures to follow under certain conditions. This AD requires installing new flight control computer (FCC) software, revising the existing AFM to incorporate new and revised flightcrew procedures, installing new MAX display system (MDS) software, changing the horizontal stabilizer trim wire routing installations, completing an angle of attack (AOA) sensor system test, and performing an operational readiness flight. This AD also applies to a narrower set of airplanes than the superseded AD, and only allows operation (dispatch) of an airplane with certain inoperative systems if specific, more restrictive, provisions are incorporated into the operator'sexisting FAA-approved minimum equipment list (MEL). This AD was prompted by the potential for a single erroneously high AOA sensor input received by the flight control system to result in repeated airplane nose-down trim of the horizontal stabilizer. The FAA is issuing this AD to address the unsafe condition on these products.
2006-12-15: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires repetitive inspections for cracks of the first fuel access panel outboard of the nacelle on the left- and right-hand wings, and related investigative/corrective actions if necessary. This AD also requires eventual replacement of each access panel with a new access panel having a new part number. The replacement terminates the repetitive inspection requirements. This AD results from reports of cracks of the fuel access panels. We are issuing this AD to detect and correct cracked fuel access panels, which could lead to arcing and ignition of fuel vapor during a lightning strike, and result in fuel tank explosions and consequent loss of the airplane.