Results
2005-13-40: The FAA is adopting a new airworthiness directive (AD) for Boeing Model 727 airplanes equipped with an auxiliary fuel tank having a fuel pump installed. This AD requires revising the airplane flight manual to include limitations on operating the fuel pumps for the auxiliary fuel tank. This AD is prompted by a design review of the fuel pump installation, which revealed a potential unsafe condition related to the auxiliary fuel tank(s). We are issuing this AD to prevent dry operation of the fuel pumps for the auxiliary fuel tank, which could create a potential ignition source inside the auxiliary fuel tank that could result in a fire or explosion of the auxiliary fuel tank.
2005-13-31: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 airplanes, that requires performing repetitive inspections of the shear attachment fittings of the vertical stabilizer for corrosion, and performing corrective actions if necessary. The actions specified by this AD are intended to detect and correct corrosion in the area of the main spar web fittings of the vertical stabilizer, which could result in reduced structural integrity of the vertical stabilizer. This action is intended to address the identified unsafe condition.
2005-12-19: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This AD requires replacing the cargo ventilation extraction duct at frame 65 with a new duct, and relocating the temperature sensor in the aft cargo compartment. This AD is prompted by a report indicating that, during a test of the fire extinguishing system, air leakage around the temperature sensor for the aft cargo compartment reduced the concentration of fire extinguishing agent to below the level required to suppress a fire. We are issuing this AD to prevent air leakage around the temperature sensor for the aft cargo compartment, which, in the event of a fire in the aft cargo compartment, could result in an insufficient concentration of fire extinguishing agent, and consequent inability of the fire extinguishing system to suppress the fire.
2005-13-13: This amendment adopts a new airworthiness directive (AD) for the Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This action requires replacing a certain part-numbered tail gear box output housing that has 600 or more hours time-in-service (TIS) with an airworthy part. Also, this AD revises the Airworthiness Limitations section of the maintenance manual by reducing the life limit of the tail gear box output housing. This amendment is prompted by the premature failure of the tail gear box output housing during fatigue testing by the manufacturer. The actions specified in this AD are intended to prevent fatigue failure of the tail gear box output housing, loss of tail rotor drive, and subsequent loss of control of the helicopter.
2005-13-16: The FAA adopts an airworthiness directive to supersede AD 93- 24-14 applicable to all The New Piper Aircraft, Inc. (Piper) PA-34 series airplanes. This AD results from many service difficulty reports related to the collapse of the nose landing gear (NLG). Consequently, this AD retains the actions required in AD 93-24-14, requires you to inspect the NLG and components of the NLG using new procedures for rigging the nose gear installation, and requires you to replace unserviceable parts. We are issuing this AD to detect, correct, and prevent failure in certain components of the NLG, lack of cleanliness of the NLG due to inadequate maintenance, or lack of lubricant in the NLG or NLG components. This failure of the NLG could lead to loss of control of the airplane during take-off, landing, or taxiing operations.
2005-13-06: The FAA is adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. This AD requires modifying the auxiliary power unit (APU) exhaust duct in the environmental control system (ECS) bay; installing new, improved insulation on this APU exhaust duct; and replacing the existing drain pipe with a new exhaust drain pipe blank. This AD is prompted by a determination that the temperature of the skin of the APU exhaust duct in the ECS bay is higher than the certificated maximum temperature for this area. We are issuing this AD to prevent the potential for ignition of fuel or hydraulic fluid, which could leak from pipes running through the ECS bay. Ignition of these flammable fluids could result in a fire in the ECS bay.
2005-12-16: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0100 airplanes. This AD requires an inspection to determine the part number of the passenger service unit (PSU) panels for the PSU modification status, and corrective actions if applicable. This AD is prompted by reported incidents of smoke in the passenger compartment during flight. One of those incidents also included a burning smell and consequently led to emergency evacuation of the airplane. We are issuing this AD to prevent overheating of the PSU panel due to moisture ingress, which could result in smoke or fire in the passenger cabin.
2005-12-11: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200 series airplanes. This AD requires modifying the frequency converters located in the closet assembly in the passenger compartment, and making various wiring changes in and between the closet assembly and forward purser work station. This AD also requires modifying the in-flight entertainment system prior to or concurrently with the modification of the frequency converters. This AD is prompted by a certification review that revealed a frequency converter failure mode not identified in the original system design. We are issuing this AD to prevent a short circuit between the frequency converter output and the distribution circuit breakers, which could result in overheating and failure of adjacent wiring and consequent adverse effects on other systems sharing the affected wire bundle.
2005-11-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Mystere-Falcon 50 and 900 series airplanes, and Model Falcon 2000 and 900EX series airplanes. This proposal requires temporary changes to the Airplane Flight Manual to prohibit the use of certain functions depending on whether or not the operator chooses to deactivate the global positioning system (GPS). For airplanes on which the GPS is deactivated, this proposal requires installing a deactivation locking collar on certain circuit breakers. For certain airplanes, this proposal also requires modifying the wiring of the global positioning/inertial reference system. This action is necessary to prevent the erroneous cockpit display of ground speed, wind velocity and direction, flight path angle, and true track angle when using certain autopilot and/or flight management system functions. Erroneous cockpit displays could cause the pilot to lose situational awareness, and possibly lose control of the airplane. This action is intended to address the identified unsafe condition.
2005-12-01: This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters that requires, within 5 hours time-in-service (TIS), locating relay K7212 and its associated cable in the overhead panel assembly and visually inspecting the electrical cable in the splice area for arcing or burns. If arcing or burns are found, this AD requires, before further flight, replacing an unairworthy cable with an airworthy cable kit. This AD is prompted by an overhead panel inspection report of incorrect crimping of the pins on the cable that connects to the relay. An electrical cable fault during assembly could result in arcing or burning of the cable junction at a relay in the overhead electrical panel. The actions specified by this AD are intended to detect arcing or burns of the cable or relay and to prevent burning of the cable junction at a relay, a fire in the cockpit, and subsequent loss of control of the helicopter.
2005-11-06: The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires you to insert a temporary revision into the Limitations Section of the Pilot Operating Handbook (POH). This AD also requires you to replace the pitch actuator with an improved design pitch actuator and make the necessary wiring and circuit breaker changes, as applicable. Installing the improved design pitch actuator terminates the need for the temporary revision in the POH. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to prevent an out-of-trim condition from occurring when the flaps are at a 40-degree flight phase and the pilot disconnects the autopilot. This condition could lead to reduced ability to control the airplane.
2003-24-02: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires inspecting the cockpit pedal unit (pedal unit) adjustment lever (lever) for a crack at specified time intervals by a dye- penetrant inspection and replacing any cracked lever with an airworthy lever before further flight. Modifying the pedal unit is also required and is a terminating action for the requirements of this AD. This amendment is prompted by cracks detected in the lever that creates an unsafe condition. The actions specified by this AD are intended to prevent failure of the lever, loss of access to the brake pedals on the ground or loss of yaw control in flight, and subsequent loss of control of the helicopter.
2005-11-12: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-200, -300, and -300F series airplanes. This AD requires installing a new, improved foam seal around certain ducts in the forward cargo compartment. This AD is prompted by the detection of incorrectly installed smoke barrier seals around the electrical/ electronic equipment air supply and exhaust ducts. We are issuing this AD to prevent fire extinguishing agent from leaking out of the seals around the ducts in the forward cargo compartment in the event of an in-flight fire, which could result in failure to extinguish the fire and consequent smoke or fire extinguishing agent entering a compartment occupied by passengers or crew.
2005-11-03: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This AD requires replacing eight brake fuses of the hydraulic quantity limiter with new or modified and reidentified fuses. This AD is prompted by reports indicating that brake fuses of the hydraulic quantity limiter of the main landing gear have failed. We are issuing this AD to prevent loss of both hydraulic and brake systems if one fuse on each hydraulic system were to fail simultaneously, and consequent reduced controllability of the airplane.
2005-09-02: The FAA is superseding an existing airworthiness directive (AD) that applies to all Boeing Model 747 series airplanes. The existing AD currently requires repetitive inspections for cracking of the top and side panel webs and panel stiffeners of the nose wheel well (NWW), and corrective actions if necessary. This new AD expands the area of inspection, adds a new "secondary" inspection if certain cracking is found, and reduces the intervals for the repetitive inspections. This AD is prompted by a report of an in-flight decompression of a Model 747-100 series airplane that had accumulated 27,241 total flight cycles. We are issuing this AD to detect and correct fatigue cracks in the top and side panel webs and stiffeners of the NWW, which could compromise the structural integrity of the NWW and could lead to the rapid decompression of the airplane. \n\nDATES: Effective May 10, 2005. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 747-53A2465, Revision 4, datedFebruary 24, 2005, as listed in the AD, is approved by the Director of the Federal Register as of May 10, 2005. \n\n\tOn January 27, 2005 (69 FR 76839, December 23, 2004), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 747-53A2465, Revision 1, dated October 16, 2003; and Boeing Alert Service Bulletin 747-53A2465, Revision 2, dated November 11, 2004. \n\n\tWe must receive any comments on this AD by June 24, 2005.
2005-10-22: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 747-200C and 747-200F series airplanes. This AD requires repetitive inspections for cracking of the left and right C-3 frame upper closure fittings of the nose cargo door, and corrective actions if necessary. This AD also provides an optional modification that, if done, terminates inspections in certain areas. This AD is prompted by reports indicating that fatigue cracking was found in the inboard flange above the flight deck floor on the C-3 frame upper closure fittings of the nose cargo door. We are issuing this AD to detect and correct cracking of the C-3 frame upper closure fittings, which could extend and result in rapid depressurization of the airplane.
2005-10-20: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 series airplanes. This AD requires replacing the pressure switches on the override/jettison fuel pumps with new pressure switches, and replacing the ship side electrical connectors for the pressure switches on override/jettison fuel pumps with new connectors. This AD is prompted by reports that the "FUEL LOW CENTER" message does not activate when the fuel level in the center tank is low. We are issuing this AD to prevent the fuel pumps in the center fuel tank from running dry and becoming a potential ignition source, which could result in a fuel tank explosion.
2005-10-15: The FAA is adopting a new airworthiness directive (AD) for certain Airbus model airplanes, as specified above. This AD requires modifying the electrical bonding points of additional center tanks. This AD is prompted by the results of fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent electrical arcing inside the fuel tank, due to insufficient bonding, which could result in the ignition of fuel vapors with a potential risk of explosion of the fuel tank.
2005-10-09: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Saab Model SAAB SF340A and SAAB 340B series airplanes. That AD currently requires repetitive detailed inspections of the windshield wiper assembly for discrepant conditions, and corrective actions if necessary. This new AD requires repetitive detailed inspections of the left and right wiper arm assemblies for damage, and corrective/related investigative actions if necessary. This AD is prompted by an additional incident of a windshield wiper blade separating from the wiper arm. We are issuing this AD to prevent separation of a wiper arm from the airplane, which could result in damage to the fuselage skin and propeller.
2005-06-07: The FAA is superseding an existing airworthiness directive (AD) for GE CF6-80A1/A3 and CF6-80C2A series turbofan engines. That AD currently requires completing one of the following actions before further flight: Performing a directional pilot valve (DPV) pressure check for leakage, and, if necessary, replacing the DPV assembly with a serviceable assembly, or Replacing the DPV assembly with a serviceable assembly, or Deactivating the thrust reverser, and revising the FAA- approved airplane flight manual (AFM) to require applying performance penalties for certain takeoff conditions if a thrust reverser is deactivated. That AD also requires revising the Emergency Procedures Section of the FAA-approved AFM to include a flight crew operational procedure for use in the event of any indication of an in-flight thrust reverser deployment. This AD specifies the same requirements for leak checks, but increases the interval between required checks. This AD also removes the requirement to revise the Limitations Section and the Emergency Procedures Section of the applicable AFM when deactivating one or both thrust reversers. This AD results from Airbus Industrie, the airplane manufacturer, revising the master minimum equipment list (MMEL) to include procedures for operating the airplane with the thrust reversers deactivated, and revising the AFM to include procedures for emergency operation if the thrust reversers deploy while in flight. This AD also results from the engine manufacturer recommending extending the interval between inspecting or replacing the DPV. We are issuing this AD to prevent inadvertent thrust reverser deployment, which, if it occurs in-flight, could result in loss of control of the airplane.
2005-09-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88, and MD-90-30 airplanes. The existing AD currently requires repetitive inspections to detect cracking of the main landing gear (MLG) shock strut pistons, and replacement of a cracked piston with a new or serviceable part. This amendment removes certain airplanes but requires that the existing inspections, and corrective actions if necessary, be accomplished on additional MLG shock strut pistons. This amendment also requires replacing the MLG shock strut pistons with new improved parts, which would terminate the repetitive inspections. The actions specified by this AD are intended to prevent fatigue cracking of the MLG pistons, which could result in failure of the pistons and consequent damage to the airplane structure or injury to airplane occupants. This action is intended to address the identified unsafe condition. \n\n\nDATES: Effective June 2, 2005. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin MD80-32A308, Revision 04, dated June 12, 2001, as listed in the regulations, is approved by the Director of the Federal Register as of June 2, 2005. \n\n\tThe incorporation by reference of Boeing Service Bulletin MD80-32- 309, Revision 01, dated April 25, 2001, as listed in the regulations, was approved previously by the Director of the Federal Register as of June 20, 2002 (67 FR 34823, May 16, 2002). \n\n\tThe incorporation by reference of McDonnell Douglas Alert Service Bulletin MD80-32A308, dated March 5, 1998; and McDonnell Douglas Alert Service Bulletin MD80-32A308, Revision 01, dated May 12, 1998; as listed in the regulations; was approved previously by the Director of the Federal Register as of as of July 28, 1999 (64 FR 33392, June 23, 1999).
2005-06-14: The FAA is superseding an existing airworthiness directive (AD), which applies to certain British Aerospace Model BAe 146 and Model Avro 146-RJ series airplanes. That AD currently requires a one- time measurement of the thickness of the outer links on the side stays of the main landing gear (MLG), and related investigative and corrective actions as necessary; and provides for replacement of a thin outer link with a new or serviceable part in lieu of certain related investigative inspections. This new AD requires repetitive inspections for cracking of the outer links on the MLG side stays, and corrective actions if necessary. This new action also expands the applicability, provides for optional terminating action for the repetitive inspections, and reduces the repetitive inspection interval. This AD is prompted by new crack findings on airplanes not subject to the existing AD, and the determination that the profile gauge's slipping over the outer link profile is not a factorin the identified unsafe condition. We are issuing this AD to prevent cracking of the outer links of the MLG side stays, which could result in failure of a side stay and consequent collapse of the landing gear.
2005-07-24: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 and -300 series airplanes. This AD requires inspecting the thrust reversers for damage of the insulation blankets, the inner wall, and the compression and drag link fittings; and repair if necessary. This AD also requires applying sealant to certain areas of the thrust reverser. This AD is prompted by two reports of thrust reverser failure; investigation revealed that the inner wall of the thrust reversers had collapsed from exposure to hot engine core compartment air. We are issuing this AD to prevent failure of a thrust reverser and adjacent components and their consequent separation from the airplane, which could result in a rejected takeoff (RTO) and cause asymmetric thrust and consequent loss of control of the airplane during reverse thrust operation. If an RTO does not occur, these separated components could cause structural damage to the airplane or damage to other airplanes and possible injury to people on the ground.
2005-07-26: The FAA is adopting a new airworthiness directive (AD) for certain Saab Model SAAB 2000 series airplanes. This AD requires a one- time inspection to detect a broken terminal stud on a main relay of the electrical power generator, and corrective action if necessary. This AD is prompted by disconnection of an electrical power generator during an inspection flight, which was caused by a broken terminal stud on the main relay. We are issuing this AD to prevent a broken terminal stud on the main relay of an electrical power generator, which could reduce the redundancy of electrical power systems, result in increased pilot workload, and contribute to reduced controllability of the airplane.
2005-07-10: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce (1971) Limited, Bristol Engine Division (RR) model Viper Mk.601-22 turbojet engines. That AD currently requires reducing the life of certain 1st stage turbine rotor blades from 7,000 hours time-in-service (TIS) to 4,600 hours TIS, and provides a drawdown schedule for blades that have already exceeded the new reduced life limit. This AD requires the same actions but changes certain compliance times to be in agreement with RR Alert Service Bulletin (ASB) No. 72- A184, dated January 2001. This AD results from comments received on AD 2004-13-03, that the AD is unnecessarily more restrictive than the requirements in the associated RR ASB No. 72-A184. We are issuing this AD to prevent multiple failures of 1st stage turbine rotor blades that could result in a dual-engine shutdown.