Results
2010-12-02: We are adopting a new airworthiness directive (AD) for the products listed above. 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: The installation of TU250 comparator/selector (CS) boards, however, has resulted in a few occurrences of erratic engine behaviour, in the form of unexpected N1 variations and/or illumination of the "GOV'' warning light. The conclusions from an investigation by Turbom[eacute]ca are that these malfunctions are due to a lapse of quality control in the varnishing process applied to the boards, and that only boards in a specific serial number range, as defined under "Applicability'' and referred to below as the "suspect batch'', are affected. We are issuing this AD to prevent loss of automatic engine control during flight due to an uncommanded engine roll-back, which could result in the inability to continue safe flight.
2004-03-19: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -231 series airplanes, that currently requires repetitive inspections for cracking in the transition and pick-up angles in the lower part of the center fuselage area, and corrective action if necessary. That AD also provides for an optional terminating modification for the repetitive inspection requirements. This amendment reduces the compliance time for the inspections for cracking of the same area. The actions specified by this AD are intended to detect and correct fatigue cracking in the transition and pick-up angles of the lower part of the center fuselage, which could result in reduced structural integrity of the wing-fuselage support and fuselage pressure vessel. This action is intended to address the identified unsafe condition.
2021-03-02: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF6-80C2A1, CF6-80C2A2, CF6- 80C2A3, CF6-80C2A5, CF6-80C2A5F, CF6-80C2A8, CF6-80C2B1, CF6-80C2B1F, CF6-80C2B2, CF6-80C2B2F, CF6-80C2B4, CF6-80C2B4F, CF6-80C2B5F, CF6- 80C2B6, CF6-80C2B6F, CF6-80C2B6FA, CF6-80C2B7F, CF6-80C2B8F, and CF6- 80C2D1F model turbofan engines. This AD was prompted by reports of incidents that resulted in a significant fuel loss during flight and an in-flight shutdown (IFSD) of the engine. This AD requires initial and repetitive shim checks of the hydromechanical unit/main engine control (HMU/MEC) idler adapter on the accessory gearbox (AGB) assembly and, depending on the results of the shim check, possible replacement of the inserts on the HMU/MEC idler adapter. As a terminating action, this AD requires a protrusion check and a pull-out test, and the replacement of inserts on the HMU/MEC idler adapter that fail either test. The FAA is issuing this AD to address the unsafe condition on these products.
95-17-06: This amendment adopts a new airworthiness directive (AD) that applies to Mooney Aircraft Corporation (Mooney) Model M20K airplanes with a Continental TSIO-520-NB engine installed in accordance with Supplemental Type Certificate (STC) SA5691NM. This action requires repetitively inspecting the exhaust transition tube and turbo mount assembly for cracks, and replacing any part found cracked. A report of a cracked exhaust transition tube that connects the exhaust manifolds to the turbocharger inlet on one of the affected airplanes prompted this action. The actions specified by this AD are intended to prevent exhaust gases from entering the cabin heating system because of a cracked exhaust transition tube, which, if not detected and corrected, could result in hazardous levels of carbon monoxide in the airplane cabin.
2004-03-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, -212, and -231 series airplanes. This AD requires repetitive inspections for fatigue cracking around the fasteners attaching the pressure panel to the flexible bracket at frame 36, adjacent to the longitudinal beams on the left and right sides of the airplane; and repair as necessary. This AD would also provide an optional terminating action for the repetitive inspections. This action is necessary to detect and correct fatigue cracking around the fasteners attaching the pressure panel to the flexible bracket at the frame 36 adjacent to the longitudinal beams, which could result in reduced structural integrity and possible rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
96-25-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 series airplanes, that requires a high frequency eddy current inspection to detect cracks of the boundary angle and joint angle of the rear pressure bulkhead, and repair, if necessary. This amendment also requires modification of the rear pressure bulkhead of the fuselage. This amendment is prompted by a report of fatigue cracking in the rear pressure bulkhead of the fuselage. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the fuselage and, consequently, lead to the rapid decompression of the pressurized area of the airplane.
2004-03-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Model 777-200 series airplanes. This action requires a surface high frequency eddy current inspection of the web of the aft pressure bulkhead, repetitive inspections, and corrective action, if necessary. This action is necessary to detect and correct cracks or damage to the web of the aft pressure bulkhead, which could enlarge if undetected, leading to rapid decompression of the airplane and consequent possible loss of flight critical systems. This action is intended to address the identified unsafe condition.
2021-03-12: The FAA is superseding Airworthiness Directive (AD) 2019-03- 27, which applied to all Dassault Aviation Model Falcon 10 airplanes. AD 2019-03-27 required repetitive detailed inspections of certain wing anti-ice outboard flexible hoses, and replacement of certain wing anti- ice outboard flexible hoses. This AD continues to require the actions in AD 2019-03-27, and also adds a new life limit for the improved wing anti-ice flexible hose; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report indicating that certain wing anti-ice outboard flexible hoses were found damaged, likely resulting from the installation process, and the development of an improved wing anti-ice flexible hose. The FAA is issuing this AD to address the unsafe condition on these products.
95-21-13: This amendment adopts a new airworthiness directive (AD) that is applicable to all British Aerospace Model BAe 146 and Model Avro 146-RJ series airplanes. This action requires inspection(s) to detect damaged and missing surface protective finish, corrosion, and cracking on the servo tab brackets and the trim tab drive brackets of the aileron, and corrective actions, if necessary. This amendment is prompted by a report of corrosion on an aileron tab bracket between the two tab drive flanges in the area of the two attachment bolts, which resulted in cracking of the flanges at their base. The actions specified in this AD are intended to prevent the failure of the servo tab brackets and trim tab drive brackets of the aileron due to cracking associated with corrosion, which could result in reduced controllability of the airplane.
95-25-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires various modifications and terminating actions for the passenger door, and repair, if necessary. This amendment requires additional inspections, and replacement of certain parts, if necessary. This amendment also provides for optional terminating action for certain inspections. This amendment is prompted by reports of excessive gaps between lockout cams and crank stops, which resulted in broken power assist triggers. The actions specified by this AD are intended to prevent broken power assist triggers, which could result in an inoperative door opening system during an emergency evacuation.
59-08-01: 59-08-01 BEECH: Applies to Models A35, B35, C35, Serial Numbers D-1501 Through D-2800. Compliance required prior to July 1, 1959. Several cases of landing gear actuation failure have been attributed to malfunctioning of the landing gear limit switches due to oil accumulation in the switch. Inspect the switches in the gear box area and if they are located under the gear box they must be: (1) Cleaned and sealed at the switch case parting surfaces with polyethylene, vinyl or rubber cement and reinstalled in the same location; (use minimum cement to assure that none gets inside switch) or (2) Replaced with new switches installed in a location to preclude oil contamination. Beechcraft Service Bulletin 35-21, A35-14, B35-7, and C35-5, dated June 1, 1953, and Supplement dated August 15, 1953, provide an acceptable procedure for relocation of the switches.
2010-11-07: We are adopting a new airworthiness directive (AD) for all Quartz Mountain Aerospace, Inc. Model 11E airplanes. This AD requires you to clean and lubricate the aileron pushrod bearings. This AD results from reports of the aileron control stick force increasing and of the controls being very noisy. We are issuing this AD to detect and correct insufficient lubrication and residual metallic paint particles in the pushrod end ball joints, which could result in difficulty actuating aileron controls sometime during flight after takeoff. This condition could lead to difficulty controlling the airplane in flight.
2004-03-10: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes; and Model A310 series airplanes. This AD requires revising the Airplane Flight Manual (AFM) to provide the flight crew with procedures to maintain controllability of the airplane in the event of an in-flight deployment of the thrust reverser. This action is necessary to ensure that the flight crew is advised of the potential hazard associated with an in-flight deployment of the thrust reverser, and the procedures necessary to address it. This action is intended to address the identified unsafe condition.
95-25-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech Model 400A airplanes, that requires an inspection to verify if the securing rivet is installed on the rod end of the control push rods of the spoiler flight control system, an inspection to verify if the jam nut is secure on the opposite end of the rod end, and repair of any discrepancy. This amendment is prompted by a report of loss of roll control on the co-pilot's control wheel shortly after takeoff due to a rivet missing from the control push rod. The actions specified by this AD are intended to ensure that the push rod rivets are installed. Missing control push rod rivets could result in the disengagement of the push rod end from the push rod tube; this could lead to loss of roll control and subsequent reduced controllability of the airplane after takeoff.
2021-03-11: The FAA is superseding Airworthiness Directive (AD) 2020-02- 21, which applied to all Dassault Aviation Model FALCON 2000 airplanes. AD 2020-02-21 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD requires revising the existing maintenance or inspection program, as applicable to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2021-04-07: The FAA is adopting a new airworthiness directive (AD) for all Piper Aircraft, Inc., (Piper) Models PA-46-350P (Malibu Mirage), PA- 46R-350T (Malibu Matrix), and PA-46-500TP (Malibu Meridian) airplanes. This AD was prompted by a finding of several airplanes with wing assemblies that did not have the proper stall warning heater modification design. Without the proper stall warning heat control modification kit installed, during flights into icing conditions with the landing gear down, ice can form on the stall vane, which may result in failure of the stall warning system. This AD requires identifying and correcting nonconforming stall warning heat control systems. The FAA is issuing this AD to address the unsafe condition on these products.
2004-03-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Learjet Model 31, 31A, 35, 35A (C-21A), 36, and 36A airplanes, that requires modification of the drag angles of the fuselage and engine pylons to gain access to the shear webs of the forward engine beams; repetitive inspections of the shear webs of the forward engine beams for cracks; follow-on actions; and modification/repair of the shear webs of the forward engine beams, as necessary, which terminates the repetitive inspections. This action is necessary to prevent significant structural damage to the engine pylons, possible separation of the engines from the fuselage, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
95-18-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech Model 400 and 400A airplanes, that requires modification of the autopilot and rudder boost interlock. This amendment is prompted by a report indicating that the rudder boost system installed on these airplanes does not operate correctly during deployment of a thrust reverser. The actions specified by this AD are intended to prevent incorrect operation of the rudder boost system during deployment of a thrust reverser and to prevent the autopilot from exceeding certain bank angle limits; these conditions could result in reduced controllability of the airplane.
95-24-14: This amendment adopts a new airworthiness directive (AD) that is applicable to certain de Havilland Model DHC-8 series airplanes. This action requires eddy current inspections to detect cracking of the pivot tubes in the drag strut of the nose landing gear (NLG), and repair or replacement of any cracked tube with a serviceable or new tube. This amendment is prompted by reports that the pivot tubes cracked or failed completely due to fatigue. The actions specified in this AD are intended to prevent such fatigue cracking and subsequent failure of the pivot tube, which could result in a nose gear-up landing.
69-15-06: 69-15-06 LEARJET: Amendment 39-802. Applies to Model 23 (Serial Numbers 23-012, 23-019 and 23-030 thru 23-099) equipped with Controlex ball bearing throttle cables; Model 24 (Serial Numbers 24-100 thru 24-139) equipped with Controlex ball bearing throttle cables; and (Serial Numbers 24-140 thru 24-180); and Model 25 (Serial Numbers 25-003 thru 25-024) Airplanes. Compliance: Within 50 hours' time in service after the effective date of this Airworthiness Directive, unless already accomplished: To prevent the possibility of the engine power control cable jamming, accomplish the following: Remove the one-piece Controlex throttle cables and install two-piece quick-disconnect type ball bearing throttle cables in accordance with Lear Service Kit No. 23/24/25-317, dated May 19, 1969, or later Federal Aviation Administration approved revision, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region. This amendment becomes effective August 15, 1969.
2021-01-01: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by evidence that a revised structural life limit of some components of the nose landing gear (NLG) and/or main landing gear (MLG) was not implemented during repair. This AD requires verifying that the affected components are installed on the airplane, revising the structural life limits in the existing structural deviation inspection requirements (SDIR) airplane document, and replacing affected components if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
57-25-02: 57-25-02 HELIO: Applies to Model H-391B Aircraft Serial Numbers 001 Through 055. Compliance required as indicated. Cracks have been found in the fin front spar underneath the steel attachment fittings holding the stabilizer to the fin. Cracks were also discovered in the flanges of the fins nose ribs second and third from the bottom. To preclude possible failure of the fin spar, the following inspections and rework are required: 1. Aircraft with less than 400 hours total time. (a) Inspect visually for cracks the fin front spar and lower nose ribs within the next 100 hours of operation and every 100 hours thereafter until reinforced as described in Helio Service Bulletin No. 17 or equivalent. (b) If cracks are found they must be stopdrilled and the parts reinforced prior to further flight. (c) If no cracks are found reinforcement of the fin front spar and lower nose ribs attachments is required prior to the accumulation of 400 hours total time.2. Aircraft having 400 hours or more total time. (a) Visual inspection and reinforcement are required within the next 25 hours flight time. If any cracks are found, they should be stop-drilled prior to adding the reinforcements. (Helio Service Bulletin No. 17 covers this subject.)
95-15-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T95-15-52 that was sent previously to all known U.S. owners and operators of certain Boeing Model 747-100 and -200 series airplanes by individual telegrams. This AD requires a revision of the Airplane Flight Manual (AFM) and Airplane Weight and Balance Supplement to restrict cargo loading to a certain level. This AD also provides for the removal of the restrictions following accomplishment of a modification of the longitudinal floor beams. This amendment is prompted by a determination that inadequate strength in the floor beams exists on certain airplanes that have been modified for cargo configurations. The actions specified by this AD are intended to prevent failure of the longitudinal floor beams, which may cause the keel beam to fail and result in rupture of the fuselage.
95-23-12: This amendment adopts a new airworthiness directive (AD) that applies to The New Piper Aircraft, Inc. (Piper) Model PA-46-350P airplanes. This action requires installing a placard (to the right of the manifold pressure gauge in full view of the pilot) that specifies manifold pressure limits, and incorporating a revision into the Limitations section of the Pilot's Operating Handbook (POH). The actions specified by this AD are intended to prevent fatigue damage to the propeller caused by operating above certain manifold pressure limits.
2021-02-14: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a report that the necessary sealant was not applied to the side of body (SOB) slot as a result of a production drawing that provided unclear SOB slot sealant application instructions. This AD requires a general visual inspection for insufficient sealant in the SOB slot, and related investigative and corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.