Results
2004-22-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that currently requires installation of strap assemblies on the ceiling panels and rails that support the video monitors. For certain airplanes, this amendment requires replacement of certain plate assemblies within the ceiling panel strap assemblies with new, improved plate assemblies. This amendment also revises the applicability by adding airplanes. The actions specified by this AD are intended to prevent ceiling panels from falling into the passenger cabin area in the event of failure of certain latch assemblies on the ceiling panels, which could result in consequent injury to the flightcrew and passengers. This action is intended to address the identified unsafe condition.
2004-24-01: The FAA adopts a new airworthiness directive (AD) for all Bombardier Inc. Model (Otter) DHC-3 airplanes that have been modified by 524085 BC, Ltd. Supplemental Type Certificate (STC) Number ST01243NY or SA01243NY. This AD requires you to replace the existing Viking Air Ltd. elevator servo tab assembly with a redesigned Viking Air Ltd. elevator servo tab assembly. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Canada. There has been one failure of the elevator servo tab assembly. We are issuing this AD to prevent the structural failure of the elevator servo tab. This failure could lead to loss of control of the airplane.
2004-23-21: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD- 88 airplanes. This amendment requires a general visual inspection for chafing of the power feeder cables of the auxiliary power unit (APU), and repair if necessary. This amendment also requires replacement of a support bracket located on the left side of the lower cargo compartment with a new "U" shaped bracket. This action is necessary to prevent chafing of the power feeder cables of the APU, which could result in electrical arcing to adjacent structure and consequent fire in the airplane. This action is intended to address the identified unsafe condition.
2004-24-02: The FAA adopts a new airworthiness directive (AD) for certain Ostmecklenburgische Flugzeugbau GmbH (OMF) Model OMF-100-160 airplanes. This AD requires you to inspect the outside tube (cage) that supports the main landing gear leg for cracks, repair if cracks are found, and inspect the thickness of the tube if no cracks were found and reinforce the tube as necessary. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect, correct, and prevent future cracks in the outside tube of the main landing gear leg, which could result in structural failure of the fuselage tubing assembly. This failure could lead to loss of control of the airplane.
2004-23-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200, -200PF, -200CB, and -300 series airplanes, that requires inspection for damage of the W2800 wire bundle insulation, wire conductor, the wire bundle clamp bracket, and the BACC10GU( ) clamp, and repair or replacement with new or serviceable parts, if necessary. This amendment also requires installation of spacers between the clamp and the bracket. This action is necessary to prevent contact between the power feeder wires of the auxiliary power unit (APU) and the clamp bracket aft of the STA 1720 bulkhead due to chafing damage of the Adel clamp and "L" shaped bracket, which could result in electrical arcing and fire, or loss of APU electrical power in the airplane. This action is intended to address the identified unsafe condition.
2004-23-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and -145 series airplanes, that currently requires determining whether a defective auxiliary power unit (APU) exhaust silencer is installed on the airplane; and corrective actions if necessary. For certain airplanes, this amendment requires modification of the APU exhaust silencer, and reidentification of the part number for the APU exhaust silencer once the modification is accomplished. For certain other airplanes, this amendment requires repetitive inspections to determine the structural integrity of the APU exhaust silencer; corrective actions, if necessary; eventual modification of the APU exhaust silencer, which terminates the repetitive inspections; and reidentification of the part number for the APU exhaust silencer once the modification is accomplished. This amendment also adds airplanes to the applicability of the existing AD. The actions specified by this AD are intended to prevent separation of the aft baffle assembly from the APU exhaust silencer and consequent separation of the assembly from the airplane, which could cause damage to other airplanes during takeoff and landing operations, or injury to people on the ground. This action is intended to address the identified unsafe condition.
2004-22-24: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 707 and 720 series airplanes, that currently requires inspections of the upper and lower chords of the wing front and rear spars, repair if necessary, and application of corrosion inhibitor to the inspected areas. This amendment removes the requirements of the existing AD, requires new detailed inspections and new high frequency eddy current (HFEC) inspections for corrosion and cracking, and requires certain related follow-on and investigative actions, if necessary. This amendment also expands the area of inspection to include the dry bay areas. The actions specified by this AD are intended to find and fix corrosion and stress corrosion cracking of the upper and lower chords on the wing front and rear spars, which could result in reduced structural integrity of the wing. This action is intended to address the identified unsafe condition.
2004-22-20: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model MD-11 and MD-11F airplanes. This AD requires replacement of low base terminal boards, related investigative action, and corrective actions if necessary. This AD is prompted by arcing between a power feeder cable and terminal board support bracket. We are issuing this AD to prevent arcing damage to the power feeder cables, terminal boards, and adjacent structure, which could result in smoke and/or fire in the cabin.
2004-22-08: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, that requires repetitive inspections of the check valves and air supply ducts of the rear bulkhead for damage, and related corrective actions. This amendment also would require eventual rework or replacement of the air supply ducts, which would terminate the repetitive inspections for the air supply ducts only. This action is necessary to prevent disconnection of an air supply duct, which, if combined with failure of a bulkhead check valve, could result in rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
2004-21-08: The FAA adopts a new airworthiness directive (AD) for all Cessna Aircraft Company (Cessna) Models 190, 195 (L-126A,B,C), 195A, and 195B airplanes that are equipped with certain inboard aileron hinge brackets. This AD requires you to repetitively inspect the affected inboard aileron hinge brackets for cracks or corrosion and replace them if found cracked or corroded. Replacement with aluminum brackets would terminate the need for the repetitive inspections. This AD results from several reports of cracks and corrosion found on the magnesium aileron hinge brackets. Magnesium is known to be susceptible to corrosion. We are issuing this AD to detect and correct corrosion damage to the inboard aileron hinge brackets. Such damage could result in the brackets cracking across the bearing boss and could lead to the aileron separating from the airplane with consequent reduced or loss of control of the airplane.
2004-21-05: The FAA is superseding Airworthiness Directive (AD) 96-20-07, which applies to certain B-Series Combustion Heaters Models B1500, B2030, B3040, and B4050 that are installed on airplanes. AD 96-20-07 currently requires you to repetitively test (pressure decay) the combustion tube and overhaul any heater that does not pass any test. AD 96-20-07 also requires you to repetitively test the operation of the combustion air pressure switch and replace any combustion pressure switch that does not pass one of the tests. As a terminating action for the repetitive test requirements of AD 96-20-07, you could install a new ceramic-coated combustion tube and an improved design combustion air pressure switch. This AD is the result of reports that the new ceramic-coated combustion tubes are subject to the same distress as the non-ceramic coated combustion tubes. Consequently, this AD retains the repetitive testing requirements of AD 96-20-07, removes the terminating action for the combustion tube, and adds Models B2500, B3500, and B4500 to the applicability section. We are issuing this AD to prevent combustion by-products (carbon-monoxide exhaust) and fuel leakage from the combustion heaters caused by failure of the combustion heater system. This failure could result in fire or explosion in the airplane and possible carbon monoxide poisoning of the crew and passengers in the cabin.
2004-20-12: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2 and B4 series airplanes; Model A300 B4-600, A300 B4-600R, A300 F4-600R series airplanes, and A300 C4- 605R Variant F airplanes (collectively called A300-600); and Model A310 series airplanes. This amendment requires a detailed inspection of certain pulleys and control cables in the rear fuselage for corrosion and damage; and corrective action, if necessary. This action is necessary to detect and correct frayed or corroded control cables for the elevator and rudder, which could result in a ruptured control cable, and possible reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2004-20-09: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires repetitive inspections for cracks, sealant damage, and corrosion of the main fittings of the main landing gear (MLG), and corrective actions if necessary. This AD is prompted by a report of a cracked main fitting of the MLG. We are issuing this AD to detect and correct fatigue cracking of the main fitting of the MLG and consequent failure of the main fitting, which could result in the collapse of the MLG.
2004-20-04: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) PT6B-36A and PT6B-36B turboshaft engines with compressor rear hubs, part number (P/N) 3018111 installed. This AD requires reviewing, and correcting if necessary the critical part record for compressor rear hubs, P/N 3018111. This AD also requires removing compressor rear hubs from service that exceed the published part life limit, before further flight. This AD results from the discovery of a compressor rear hub, P/N 3018111, that exceeded the published life limit. This occurred because the operator used an incorrect life limit calculation contained in a PWC Service Bulletin. We are issuing this AD to prevent uncontained failure of the compressor rear hub and damage to the airplane.
2004-19-06: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767-200, -300, and -300F series airplanes, that requires inspections to detect cracking or corrosion of the fail-safe straps between the side fitting of the rear spar bulkhead at body station 955 and the skin; and follow-on/corrective actions. This action is necessary to detect and correct fatigue cracking or corrosion of the fail-safe straps, which could result in cracking of adjacent structure and consequent reduced structural integrity of the fuselage. This action is intended to address the identified unsafe condition.
2004-19-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102 airplanes, that requires modification of the electrical power circuit. This action is necessary to prevent component failure in the radar indicator, resulting in an overcurrent condition and consequent overheating or burning of an internal component or the ribbon cable. This could lead to smoke in the cockpit, resulting in incapacitation of the flight crew and loss of control of the airplane. This action is intended to address the identified unsafe condition.
2004-17-01: The FAA supersedes Airworthiness Directive (AD) AD 2002-22-17, which applies to all Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes; and AD 2003-21-04, which applies to certain Cessna Models 208 and 208B airplanes. This AD requires you to repetitively inspect the flap bellcranks for cracks and eventually replace these bellcranks. The installation of a newly designed bellcrank to increase the life limits is terminating action for the repetitive inspections. This AD is the result of these developments: Since FAA issued AD 2002- 22-17 and AD 2003-21-04, Cessna designed a new flap bell crank with a life limit of 40,000 landings instead of 7,000 landings. Also, FAA has done more analysis and examination of cracks and missing/incomplete welds in all of the bell cranks. This failure could lead to damage to the flap system and surrounding structure and result in reduced or loss of control of the airplane. DATES: This AD becomes effective on September 26, 2004.As of December 31, 2002 (67 FR 68508, November 12, 2002), the Director of the Federal Register approved the incorporation by reference of Cessna Service Bulletin No. CAB02-1, dated February 11, 2002. As of October 21, 2003 (68 FR 59707, October 17, 2003), the Director of the Federal Register approved the incorporation by reference of the following: Cessna Caravan Service Bulletin No.: CAB03-11, Revision 1, dated September 24, 2003; Cessna Caravan Service Bulletin No.: CAB02-12, revision 1, dated January 27, 2003; and Cessna Caravan Service Kit No.: SK208-148A, dated January 27, 2003 (Original issue: October 21, 2002).
2004-18-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-200, -200C, -300, -400, and -500 series airplanes, that requires repetitive inspections to find fatigue cracking of certain upper and lower skin panels of the fuselage, and follow-on and corrective actions, if necessary. This amendment also includes terminating action for the repetitive inspections of certain modified or repaired areas only. This action is necessary to find and fix fatigue cracking of the skin panels, which could result in sudden fracture and failure of the skin panels of the fuselage, and consequent rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
2004-17-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes. This action requires an inspection to determine the part number of the filter/ regulator on the fire extinguishing system installed in the lower cargo compartment of the airplane, and re-identification of the filter/ regulator, or replacement of the filter/regulator with a new filter/ regulator, if necessary. This action is necessary to prevent leakage of fire extinguishing agent through the filter/regulator of the cargo fire extinguishing system, which could result in the inability of the fire extinguishing system to suppress a fire in the cargo compartment of the airplane. This action is intended to address the identified unsafe condition.
2004-16-15: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) helicopters. This action requires inspecting the main gearbox (MGB) baseplate for a crack and replacing the MGB if a crack is found in the MGB base plate. This amendment is prompted by the discovery of a crack in a MGB base plate. The actions specified in this AD are intended to detect a crack in a MGB base plate and prevent failure of one of the MGB attachment points to the frame, which could result in severe vibration and subsequent loss of control of the helicopter.
2004-16-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 and 767 series airplanes, that requires inspection to determine the serial number of the hydraulic pump in the ram air turbine (RAT), and corrective action if necessary. This action is necessary to prevent a cracked hanger arm of the hydraulic pump of the RAT that can fracture under load and lead to failure of the RAT to provide hydraulic power to the primary flight control system during an emergency when both engines have failed. Loss of hydraulic power to the primary flight controls could result in loss of control of the airplane. This action is intended to address the identified unsafe condition.
2004-16-07: The FAA is adopting a new airworthiness directive (AD) for GE CT7-2D1 turboshaft engines. This AD requires replacing certain turbine stage 2 aft cooling plates, part number (P/N) 6064T0P02. This AD results from an uncontained failure of a turbine stage 2 aft cooling plate in a GE CT7 turboprop engine. We are issuing this AD to prevent a similar uncontained failure of turbine stage 2 aft cooling plates in GE CT7-2D1 turboshaft engines.
2004-15-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires modification of certain wires in the right-hand wing. This action is necessary to ensure that fuel quantity indication wires are properly separated from wires carrying 115-volt alternating current (AC). Improper separation of such wires, in the event of wire damage, could lead to a short circuit and a possible ignition source, which could result in a fire in the airplane. This action is intended to address the identified unsafe condition.
2004-15-19: The FAA adopts a new airworthiness directive (AD) for certain the New Piper Aircraft, Inc. (Piper) Model PA-46-500TP airplanes. This AD requires you to inspect (one-time) for the existence of any protective cover over the percussion caps or silicon tube installed over the end of the trigger mechanism pin of the oxygen generators, and remove any protective cover or silicon tube found. This AD is the result of reports of the above conditions found on the affected airplanes. We are issuing this AD to detect and remove any protective cover over the percussion cap, or any silicon tube over the end of the trigger mechanism pin, which could result in failure of the emergency oxygen system. This failure could lead to the crew and passengers not being able to get oxygen in an emergency situation.
2004-15-13: This amendment adopts a new 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), and Model MD-88 airplanes, that requires replacement of certain freeze protection ribbon heaters in the lavatory water supply system, and flushing, cleaning, and sterilizing the potable water system; disconnecting, coiling, and stowing the wiring of the freeze protection ribbon heater; or removal of freeze protection heaters. This action is necessary to prevent failure of freeze protection ribbon heaters, which could result in the charring, scorching, smoking, and shorting out of freeze protection ribbon heaters in the lavatory water supply system. This condition, if not corrected, could also result in electrical arcing of freeze protection ribbon heaters, leading to fire and damage to water lines and components under the lavatory sink. This action is intended to address the identified unsafe condition.