Results
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.
2004-15-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-101, -102, -103, -106, - 201, -202, -301, -311, and -315 airplanes. This amendment requires an inspection of the fuel tube assembly of the auxiliary power unit (APU) for clearance from adjacent components; and an inspection of the fuel tube assembly and the bleed air duct shroud for discrepancies (insufficient clearance, nicks, dents, chafing, or other damage); and related investigative and corrective actions if necessary. This amendment also requires relocation of certain support clamps on the APU fuel tube assembly. This action is necessary to prevent a fuel leak caused by chafing of the APU fuel tube assembly, which could result in fire in the center wing area. This action is intended to address the identified unsafe condition.
2004-15-05: This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes, that requires replacing the existing bellows inlet duct of the auxiliary power unit (APU) system with a new, improved rectangular metallic bellows inlet duct. This action is necessary to prevent air from the APU bay being ingested into the flight deck and passenger cabin resulting in poor air quality and, if the air is contaminated, possible incapacitation of the flightcrew and passengers. This action is intended to address the identified unsafe condition.
2004-15-01: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company (Raytheon) Model 390 airplanes. This AD requires you to inspect the hydraulic tube/hose assemblies, the engine fuel feed tube assemblies, and the engine wire harnesses for proper clearance and damage (as applicable). If improper clearance or damage is found on any assembly, you must replace and/or modify the affected assembly. This AD is the result of reports of loss of the hydraulic system functions during different operations caused by improper clearance between certain components. This resulted in damage to the tubing in the hydraulic system assemblies. Analysis shows a similar condition on the engine fuel feed assemblies. We are issuing this AD to detect, correct, and prevent such damage or improper clearance in the affected areas, which could result in failure of one or more of these systems. These failures could lead to loss of hydraulic system operations, engine shutdown, and false readings for fuel pressure, oil pressure, and other oil indications. These conditions could consequently result in reduced or loss of control of the airplane.
2004-14-24: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 series airplanes, that currently requires measuring the gap between the bellcrank and the body of the rotary variable inductive transducers (RVITs) of the aileron and elevator, performing corrective action if necessary, and torquing the bolt that attaches the bellcrank to the RVIT shaft. This amendment requires replacing the aileron and elevator RVIT bellcranks with new, improved bellcranks. The actions specified by this AD are intended to prevent restricted movement of the aileron or elevator, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2004-14-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 and A310 series airplanes, that requires modification of the attachment system of the insulation blankets of the forward cargo compartment and related corrective action. This action is necessary to prevent failure of the attachment system of the cargo insulation blankets, which could result in detachment and consequent tearing of the blankets. Such tearing could result in blanket pieces being ingested into and jamming the forward outflow valve of the pressure regulation subsystem, which could lead to cabin depressurization and adversely affect continued safe flight of the airplane. This action is intended to address the identified unsafe condition.
2004-14-21: The FAA adopts a new airworthiness directive (AD) for all Stemme GmbH & Co. Models S10, S10-V, and S10-VT sailplanes. This AD requires you to remove the drive shaft assembly and ship it to the service department of Stemme GmbH & Co. The engine is mounted behind the two side-by-side seats. The engine combined with the carbon fiber drive shaft turn the centrifugally extended propeller. After an initial visual inspection, the service department will perform an operational check to determine whether the drive shaft can be further used or must be replaced. Once corrective action is identified, a drive shaft will be shipped to you for installation. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct incorrectly glued drive shafts, which could result in drive shaft failure. During self-takeoff or critical periods of landing, failure of the drive shaft could leadto loss of control of the sailplane.