Results
2020-25-01: The FAA is adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. (Textron) (type certificate previously held by Beechcraft Corporation) Models F90, 65-90, 65-A90, B90, C90, H90 (T-44A), E90, 65-A90-1 (JU-21A, U-21A, RU-21A, RU-21D, U-21G, RU- 21H), 65-A90-2 (RU-21B), 65-A90-3 (RU-21C), 65-A90-4 (RU-21E, RU-21H), 99, 99A, 99A (FACH), A99, A99A, B99, C99, 100, A100 (U-21F), and B100 airplanes. This AD was prompted by reports of fatigue cracks in the lower forward wing fitting. This AD requires a one-time inspection for the presence of washer part number (P/N) 90-380058-1 on the left-hand (LH) and right-hand (RH) lower forward wing bolt and, if applicable, removing washer P/N 90-380058-1, inspecting the wing fitting, bolt, and nut, replacing the wing fitting if it is cracked, and replacing the washer with washer P/N 90-380019-1. The FAA is issuing this AD to address the unsafe condition on these products.
95-09-04: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100 and -300 series airplanes, that requires an inspection to verify the integrity of the shield grounds for the cable harness of the electronic engine control (EEC), and correction of any discrepancy. This amendment also requires measurement of the electrical resistance of certain shield grounds, and repair, if necessary. This amendment is prompted by a report of an engine flameout after a lightning strike, due to several shields for the cable harness of the EEC not being properly grounded to the airframe. The actions specified by this AD are intended to prevent engine flameout due to insufficient protection of the EEC.
59-24-03: 59-24-03 BROWN-LINE CORPORATION SAFETY BELT: Applies to All Model WB-2002-2 Safety Belts. Investigation of two recent accidents involving aircraft in which the subject model safety belts were installed, disclosed that the wearer could not free himself from the belt, thereby preventing his escape from the aircraft. The design of this belt buckle is such that it will not enable the wearer to quickly and easily release the belt from the buckle. Thus this belt does not conform with Section 4.1.2 of TSO-C22 (See NOTE) and compliance is considered essential to safety in cases of fire or emergencies involving landings in water. Accordingly, since this model safety belt does not meet the necessary safety requirements, it is not acceptable for installation in civil aircraft. Furthermore, all belts of this model that are in service must be replaced with acceptable safety belts within the next 25 hours of service time or the next periodic inspection whichever occurs first. NOTE: Section 4.1.2 of TSO-C22 states in part: ". . . . shall include an easily operable quick release mechanism which will enable the wearer to release himself easily under a load simulating the wearer hanging in the belt".
2003-24-14: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This action requires one-time inspections to detect discrepancies of electrical wiring installations in various areas of the airplane, and corrective action if necessary. The actions specified by this AD are intended to prevent smoke and fire in various areas of the airplane due to heat damage and/or electrical arcing of improperly installed wiring. This action is intended to address the identified unsafe condition.
2003-24-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell \nDouglas Model MD-11 series airplanes, that currently requires performing a general visual inspection to detect chafing or damage of the parallel power feeder cables of the number 2 integrated drive generator (IDG); repairing any chafed cable and damaged structure; and repositioning the parallel power feeder cables of the number 2 IDG. This amendment revises the applicability of the existing AD by adding certain airplanes and removing certain other airplanes. The actions specified by this AD are intended to prevent chafing and arcing of the parallel feeder cables of the number 2 IDG, which could result in smoke and/or fire in the right aft galley area. This action is intended to address the identified unsafe condition.
95-08-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires replacement of the currently installed door opening actuators of the emergency off-wing escape system with new, improved actuators. This amendment is prompted by reports indicating that the requirements of a previously issued AD do not adequately preclude leakage from these actuators. The actions specified by this AD are intended to prevent failure of the escape slide to deploy due to failure of the door opening/snubbing actuator, which could delay and possibly jeopardize successful emergency evacuation of an airplane.
2008-04-18 R1: We are adopting a new airworthiness directive (AD) for the products listed above that would revise an existing AD. 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 describes the unsafe condition as: It has been found that former revisions of the Maintenance Review Board Report (MRBR) of the EMB-120( ) aircraft do not fully comply with some Critical Design Configuration Control Limitations (CDCCL) and Fuel System Limitations (FSL). These limitations are necessary to preclude ignition sources in the fuel system, as required by RBHA-E88/SFAR-88 (Special Federal Aviation Regulation No. 88). * * * * * The potential of ignition sources, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. This AD requires actions that are intended to address the unsafecondition described in the MCAI.
2020-25-04: The FAA is superseding Airworthiness Directive (AD) 2016-24-08 for all Rolls-Royce Deutschland Ltd. & Co KG (RRD) RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211- Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 model turbofan engines. AD 2016-24-08 required repetitive inspections of the engine upper bifurcation nose fairing assembly and repair or replacement of any fairing assembly that fails inspection. This AD retains the requirements to perform repetitive inspections of the engine upper bifurcation nose fairing assembly and repair or replacement of any fairing assembly that fails inspection. As a terminating action to these inspections, this AD also requires the modification of the engine upper bifurcation nose fairing assembly. The FAA is issuing this AD to address the unsafe condition on these products.
57-06-01: 57-06-01 COLONIAL: Applies to Model C1 Aircraft Serial Numbers 2 Through 10 Inclusive, and Serial Number 13. Compliance required by May 1, 1957. To prevent unwanted extension of the landing gear, a more positive lock must be installed for the landing gear selector valve lever in accordance with Colonial Service Bulletin No. 1 dated January 25, 1957.
95-08-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that currently requires repetitive inspections of the attachment bolts and nuts in the rear spar root joint attachment fittings at wing rib 2 for integrity of nuts, tightness of bolts, and/or fuel leaks; and repair, if necessary. That AD was prompted by fuel leaks from bolt positions on the rear spar attachment fitting at wing rib 2. This amendment provides for an optional terminating modification for the repetitive inspections, and expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent fuel leaks and a subsequent fire.
69-08-10: 69-08-10 AERO COMMANDER DIVISION, NORTH AMERICAN ROCKWELL CORPORATION: Amdt. 39-754. Applies to all Aero Commander Model 1121 series airplanes. Compliance required within the next 100 hours' time in service after the effective date of this A.D., unless already accomplished. To assure required trim capability at the approved aft center of gravity limit, accomplish the following: Modify the horizontal stabilizer trim system in accordance with Part II of Aero Commander Service Bulletin No. J-4B dated February 28, 1969, or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southwest Region, Fort Worth, Texas. This amendment becomes effective May 24, 1969.
2009-22-09: We are adopting a new airworthiness directive (AD) for the products listed above. 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 describes the unsafe condition as: A change in dimensions of the fuse blocks in the Auxiliary Power Unit (APU) Start Contactor Assembly (ASCA) box assembly can cause an incorrect interface between the bus bars and fuses. This condition can result in an increase in temperature, which could damage the ASCA box and/or compromise the availability of battery bus supply. The unsafe condition could result in the ignition of a fire in the ASCA box. We are issuing this AD to require actions to correct the unsafe condition on these products.
96-12-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires inspections to detect missing fasteners, cracked fitting angles, and elongated fastener holes in certain frames, and correction of discrepancies. It also provides an optional terminating action. This amendment is prompted by discrepancies found at the fitting angles on the frame at which a certain electronic rack is attached. The actions specified by this AD are intended to prevent damage propagation that could lead to failure of the rack-to-structure attachment points, and subsequently could result in loss of airplane systems, structural damage, and possible electrical arcing.
2003-24-12: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7F, -7H, -7AH, and -7J turbofan engines, with gearbox pressure tube, part number (P/N) 697896, and No. 4 bearing front pressure manifold, P/N 670663, installed. This AD requires a one-time visual inspection of the gearbox pressure tube and No. 4 bearing front pressure manifold and the attaching clamp assemblies for correct positioning and for wear and damage, and replacement if necessary. This AD is prompted by a report of a failed gearbox pressure tube that resulted in an engine fire. We are issuing this AD to prevent engine fires caused by failed gearbox pressure tubes or failed No. 4 bearing front pressure manifolds.
2009-22-03: The FAA is superseding an existing airworthiness directive (AD) for Hartzell Propeller Inc. ()HC-()2Y()-() series propellers with non-suffix serial number (SN) propeller hubs installed on Lycoming O-, IO-, LO-, and AEIO-360 series reciprocating engines. That AD currently requires initial and repetitive eddy current inspections (ECIs) of the front cylinder half of the propeller hub for cracks and removing cracked hubs from service before further flight. In addition, that AD allows installation of an improved design propeller hub (suffix SN "A'' or "B'') as terminating action to the repetitive ECI. This ad requires the same actions but changes the affected propeller series designation to ()HC-()2Y(K,R)-() series propellers with non-suffix SN propeller hubs and suffix SN letter "E'' propeller hubs. This AD also expands the engine eligibility to include Lycoming LIO-, TO-, LTO-, AIO-, and TIO-360-series engines. This AD results from the need to make changes to the affected seriesdesignation of propellers, to expand the engine applicability, and to respond to comments received on AD 2006- 18-15. We are issuing this AD to prevent failure of the propeller hub causing blade separation and subsequent loss of airplane control.
95-06-53: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T95-06-53 that was sent previously to all known U.S. owners and operators of Boeing Model 737 series airplanes by individual telegrams. This AD requires identification of the part and serial numbers of the main rudder power control unit (PCU), and replacement of certain PCU's with serviceable parts, if necessary. This amendment is prompted by reports indicating that certain modified rudder PCU's malfunctioned and failed functional retesting. The actions specified by this AD are intended to prevent the rudder actuator piston and the rudder from operating with reduced force capability or moving in a direction opposite the intended direction due to malfunctioning of the rudder PCU; these conditions could result in reduced controllability of the airplane.
2009-22-04: We are adopting a new airworthiness directive (AD) for the specified ECF model helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that freezing of the route display on the navigation display (ND) in the Sector mode occurs for flight plans that include procedures in the terminal zone (departure or arrival). The MCAI AD prohibits the use of the UNS-1D navigation system (also known as the Flight Management System (FMS)) for Standard Instrument Departure (SID), Standard Instrument Terminal Arrival Route (STAR), and instrument approach procedures. The actions are intended to prevent the flight crew from relying on a frozen route ND, unanticipated increases in flight crew workload, pilot confusion in the terminal airspace environment, and subsequent loss of control of the helicopter.
2003-24-05: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-31 and DC-9-32 airplanes. This action requires installation of ceiling panels and a protective pad in the tailcone emergency exit passageway. The actions specified by this AD are intended to prevent people on board the airplane from striking their heads on exposed metal frames in the tailcone area, which could cause injury and delay or impede their evacuation during an emergency. This action is intended to address the identified unsafe condition.
2020-24-09: The FAA is adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc., Model PA-34-220T airplanes. This AD was prompted by a report of damage to the rudder flight control cables and the emergency power supply (EPS) system wiring due to inadequate clearance from the EPS wiring harness. This AD requires inspecting the rudder flight control cables and the EPS wiring for damage, replacing damaged cables and wires if necessary, and re-routing the EPS wiring harness to ensure proper clearance between the EPS and the rudder flight control cables. The FAA is issuing this AD to address the unsafe condition on these products.
2003-24-06: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dassault Model Mystere-Falcon 200 series airplanes. This action requires a one-time inspection of the fire extinguishing pipe for each engine to determine whether holes for dispersal of fire-extinguishing agent are present, and corrective action if necessary. This action is necessary to ensure that the flightcrew is able to extinguish an engine fire, should one occur. Inability to extinguish an engine fire could result in loss of control of the airplane. This action is intended to address the identified unsafe condition.
56-05-01: 56-05-01 BELL: Applies to Model 47 Helicopters: Model 47D1 Serial Number 477 and Subsequent, Model 47G Serial Numbers 667 Through 692, 694 Through 1511, Model 47G2 Serial Numbers 1342 Through 1418, Model 47H1 Serial Numbers 1347, 1349 Through 1356, 1358, and 1360, All Model 47 Modified to Include 47-644-172-3 Tail Rotor Extension Drive Shaft and All 47-644-172-3 Shafts in Stock. Compliance required by March 1, 1956. As a result of manufacturing error some Bell Model 47 tail rotor extension drive shafts P/N 47-644-172-3 were bored too deep resulting in a weakened wall section. Bell has issued Service Bulletin No. 106 requiring an immediate mandatory inspection by X-ray or by method described in the Service Bulletin. This supersedes telegraph AD of February 3, 1956.
2009-21-12: We are adopting a new airworthiness directive (AD) for the products listed above. 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 describes the unsafe condition as: Further to initial qualification tests of the spoiler actuators currently installed in position No. 3 to 7 on A300-600 and A300- 600ST aircraft fleet, a life limit [of 55,750 flight hours] has been defined by the actuator manufacturer. Initially, this life limit had no repercussions, as it was situated well beyond the initial Design Service Goal (DSG) of the aircraft. However, due to the Extended Service Goal (ESG) activities, the spoiler actuator life limit can be reached in service, and therefore the spoiler actuators must be replaced before exceeding this limit. In order to mitigate the risk to have aircraft on which the three hydraulic circuitswould be impacted by affected spoiler actuators, which could result in the loss of controllability of the aircraft, this Airworthiness Directive (AD) requires actions to ensure that at least the level of safety of one hydraulic circuit will be restored within an acceptable timeframe. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2009-21-03: The FAA is adopting a new airworthiness directive (AD) for Hamilton Sundstrand Power Systems T-62T-46C12 auxiliary power units (APUs). This AD requires upgrading the software in the APU full- authority digital controller (FADEC) from software version 02.01.000 to version 03.00.000. This AD results from two reports of APU compartment explosions due to over-fueling of the APU at low revolutions-per-minute during the start sequence. We are issuing this AD to prevent over- fueling of the APU during the start sequence, which could lead to fuel explosions, injury, and damage to the APU and the airplane.
2003-24-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 & 701) series airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) to prohibit operations into known or forecast icing conditions under certain conditions. That AD also requires an inspection to detect damage of the wing anti-ice (WAI) ducts to determine if the external shrouds of the ducts are open or cracked, and replacement of any damaged duct with a new duct or a duct with the same part number, and an optional terminating action. This amendment requires accomplishment of the previously optional terminating action for the AFM revision and inspection. The actions specified by this AD are intended to prevent the WAI ducts from collapsing, cracking, or rupturing, which could cause leakage of hot air in the under-floor pressurized area of the fuselage when the anti- ice system is turned on. Such leakage of hot air results in insufficient heat for the anti-ice system and consequent aerodynamic degradation. This action is intended to address the identified unsafe condition. DATES: Effective December 31, 2003. The incorporation by reference of a certain publication listed in the regulations was approved previously by the Director of the Federal Register as of June 27, 2003 (68 FR 35152, June 12, 2003).
96-13-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires modification of the existing diaphragms on the surround structure of the Type II emergency exit. This amendment is prompted by a report indicating that, during fatigue tests on a Model 4101 test article, fatigue-related cracking was found in the surround structure of a Type II emergency exit. The actions specified by this AD are intended to prevent such cracking in the surround structure, which could result in reduced structural integrity of the fuselage pressure vessel.