Results
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.
2006-12-16: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, -314, and -315 airplanes. This AD requires certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, -314, and -315 airplanes. This AD results from a report that, during structural testing of the cockpit door, the lower hinge block rotated and caused the mating hinge pin to disengage, and caused excessive door deflection. We are issuing this AD to prevent failure of a door attachment, which could result in uncontrolled release of the cockpit door under certain fuselage decompression conditions, and possible damage to the airplane structure.
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.
2006-12-14: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-120, -120ER, -120FC, -120QC, and -120RT airplanes. This AD requires replacing the shut-off and crossbleed valves of the bleed air system with new valves having hermetically sealed switches. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent a potential source of ignition near a fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2006-12-12: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100 and -200 series airplanes. That AD currently requires repetitive inspections for cracking of the station 800 frame assembly, and repair if necessary. This new AD retains the repetitive inspection requirements of the existing AD, but expands the area to be inspected. This AD also reduces the initial inspection threshold, removes the adjustment of the compliance threshold and repetitive interval based on cabin differential pressure, and adds airplanes to the applicability. This AD results from several reports of cracks of the station 800 frame assembly on airplanes that had accumulated fewer total flight cycles than the initial inspection threshold in the existing AD. We are issuing this AD to detect and correct fatigue cracks that could extend and fully sever the frame, which could result in development of skin cracks that could lead to rapid depressurization of the airplane.
2018-11-12: We are adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a report that Belleville washers installed on the shimmy damper of the main landing gear (MLG) may fail due to fatigue. This AD requires revising the maintenance or inspection program, as applicable, to incorporate a repetitive task specified in the maintenance review board (MRB) report. We are issuing this AD to address the unsafe condition on these products.