Results
2003-25-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-600 series airplanes, Model A300 B4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and Model A300 F4-605R airplanes. This AD requires modification of certain components of the 115 Volts Alternating Current (VAC) supply wiring and of the fuel gauging system. This action is necessary to prevent short circuits between 115 VAC wiring and certain fuel system electrical wire runs with subsequent overheating of the cadensicon sensor thermistor or fuel level sensor, which could be great enough to ignite fuel vapors in the fuel tank and cause an explosion. This action is intended to address the identified unsafe condition.
2003-25-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing airplane models, that requires a one-time inspection to identify all H-11 steel bolts installed in the latch fittings of the cargo doors, repetitive inspections for cracked or broken H-11 steel bolts, and follow-on and corrective actions if necessary. This amendment also requires eventual replacement of all H-11 steel bolts in the latch fittings of the cargo doors with Inconel bolts. This action is necessary to prevent broken bolts in the latch fittings, which could reduce the capability of the door latch to keep the door closed, and result in loss of a cargo door and consequent rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
2003-25-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 and 777-300 series airplanes, that requires application of high-temperature sealant in designated areas of the strut aft dry bay. The actions specified by this AD are intended to prevent leakage of hydraulic fluid into the strut aft dry bay, where high temperatures associated with the adjacent primary exhaust nozzle may ignite the fluid, resulting in an uncontrolled fire in the strut aft dry bay. This action is intended to address the identified unsafe condition.
2003-25-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires an inspection to detect chafing or damage of the electrical wires leading to the terminal strips in the center accessory compartment (CAC) area, and corrective actions if necessary. That AD also currently requires revising the wire connection stack up of certain cable terminals at the electrical power center bays in the CAC, and replacing certain terminal strips with new strips and removing applicable nameplates at electrical power center bays. This amendment requires additional actions for improving the terminal strips and revises the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent arcing and sparking damage to the power feeder cables, terminal strips, and adjacent structure, and consequent smoke and fire in the CAC. This action is intended toaddress the identified unsafe condition.
2003-25-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319 and A320 series airplanes, that currently requires revising the airplane flight manual to specify procedures for landing under certain conditions of gusty winds and turbulence. This amendment requires replacement of both Elevator and Aileron Computers (ELACs) having L80 standards with new ELACs having L81 standards, which terminates the requirements of the existing AD. The actions specified by this AD are intended to prevent activation of the high angle-of-attack protection during final approach for landing, which could result in loss of ability to flare properly during landings. This action is intended to address the identified unsafe condition.
2003-25-08: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (formerly Allison Engine Company) AE 3007A1, AE 3007A1/1, AE 3007A1/3, AE 3007A3, AE 3007A1E, and AE 3007A1P turbofan engines, with 1st to 2nd stage turbine spacers, part number (P/N) 23069627, 23070989, 23072849, or 23075364 installed. This AD reduces the life limit for 1st to 2nd stage turbine spacers, P/N 23072849, to a certain lower life limit, based on engine model. This AD also requires a one-time fluorescent penetrant inspection (FPI) of 1st to 2nd stage turbine spacers P/Ns 23069627, 23070989, 23072849, and 23075364 before reaching the spacer life limit, within specified cycles-since-new (CSN), and requires replacement of the spacer if found cracked, or with bent or missing aft tangs. This AD is prompted by a report that during a scheduled inspection, aft pilot tangs on a 1st to 2nd stage turbine spacer were found bent and cracked. We are issuing this AD to prevent 1st to 2nd stage turbine spacer failure, leading to uncontained turbine failure, engine shutdown, and damage to the airplane.
2003-24-10: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, DC-10-10F, DC- 10-15, DC-10-30, DC-10-30F, DC-10-30F (KC10A and KDC-10), DC-10-40, DC- 10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes, that requires a one-time inspection to determine the thickness of the walls of the rudder pedal arm assembly for the captain's and first officer's rudder pedals, and follow-on actions. This action is necessary to prevent failure of the rudder pedal arm assembly, which, under certain conditions, could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2003-24-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 airplanes, that currently requires repetitive general visual inspections of the power feeder cables, terminal strip, fuseholder, and fuses of the galley load control unit (GLCU) within the No. 3 bay electrical power center (EPC) to detect damage; and corrective actions, if necessary. For certain airplanes, this amendment requires replacement of the electrical wiring of the galley in the EPC. For certain other airplanes, this amendment requires an inspection to detect damage of the electrical wiring of the galley in the EPC; corrective actions if necessary; modification of the wiring support; and removal of spare fuses; as applicable. These new actions terminate the repetitive inspection requirements. This amendment also limits the applicability of the existing AD. This amendment is prompted by the FAA's determination that additional rulemaking is necessary. The actions specified by this AD are intended to prevent chafing damage to the wire assembly, and consequent arcing and smoke and fire in the EPC, and to prevent damage to the wire assembly terminal lugs and overheating of the power feeder cables on the No. 3 and No. 4 GLCU, which could result in smoke and fire in the center accessory compartment. This action is intended to address the identified unsafe condition.
2003-24-07: This amendment adopts a new airworthiness directive (AD) that applies to all The New Piper Aircraft, Inc. (Piper) Models PA-31, PA- 31-300, PA-31-325, PA-31-350, PA-31P, PA-31T, PA-31T1, PA-31T2, PA- 31T3, and PA-31P-350 airplanes. This AD requires you to install an inspection hole (or use for inspection the tooling hole in the rudder bottom rib), conduct a detailed visual inspection of the rudder torque tube and associated ribs for corrosion, and, if corrosion is found, replace or repair the rib/rudder torque tube assembly. This AD is the result of reports of rudder tube corrosion. The actions specified by this AD are intended to detect and correct corrosion in the rudder torque tube assembly and rudder rib, which could result in failure of the rudder torque tube. This failure could lead to loss of rudder control.
2003-24-08: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, that currently requires repetitive inspections to find cracks, fractures, or corrosion of each carriage spindle of the left and right outboard mid-flaps; and corrective action, if necessary. That AD also provides for an optional action of overhaul or replacement of the carriage spindles. This amendment requires repetitive gap checks of the inboard and outboard carriage of the outboard mid-flaps to detect fractured carriage spindles; and corrective actions, if necessary. This amendment also reduces the interval for the existing inspections and revises the overhaul procedures. The actions specified in this AD are intended to detect and correct cracked, corroded, or fractured carriage spindles and to prevent severe flap asymmetry, which could result in reduced control or loss of controllability of the airplane. This actionis intended to address the identified unsafe condition. \n\nDATES: Effective December 4, 2003.\n\nThe incorporation by reference of Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated November 25, 2003, as listed in the regulations, is approved by the Director of the Federal Register as of December 4, 2003.\n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 737-57A1277, dated July 25, 2002, as listed in the regulations, was approved previously by the Director of the Federal Register as of November 15, 2002 (67 FR 66316, October 31, 2002).\n\n\tComments for inclusion in the Rules Docket must be received on or before January 30, 2004.
2003-24-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 and -400F series airplanes. This action requires replacing the rudder feel, centering, and trim mechanism with a new or serviceable rudder feel, centering, and trim mechanism. This action is necessary to prevent degradation/loss of rudder feel and centering, which could result in increased pilot workload and could lead to loss of control of the airplane. This action is intended to address the identified unsafe condition.
2003-23-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, and -200C series airplanes, that currently requires repetitive inspections to detect discrepancies in the upper and lower skins of the fuselage lap joint, and repair if necessary. This amendment adds new inspections, reduces the repetitive inspection intervals for certain airplanes, and mandates a terminating modification. The actions specified by this AD are intended to detect and correct discrepancies in the upper and lower skins of the fuselage lap joint and circumferential joint, which could result in sudden fracture and failure of a lap joint or circumferential joint and rapid decompression of the airplane fuselage. This action is intended to address the identified unsafe condition. \n\nDATES: Effective December 23, 2003.\n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 737-53A1224, Revision 1, dated March 14, 2002, as listed in the regulations, is approved by the Director of the Federal Register as of December 23, 2003.\n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 737-53A1224, dated August 17, 2000, as listed in the regulations, was approved previously by the Director of the Federal Register as of September 11, 2000 (65 FR 51750, August 25, 2000).
2003-22-10: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France model helicopters that requires operators to either temporarily or permanently secure the electrical bonding braid (bonding braid) that is installed on the left cyclic pitch control stick base within 10 hours time-in-service (TIS) and, if temporarily secured, installing a permanent attachment system for the bonding braid within 500 hours TIS or 12 months, whichever occurs first. This amendment is prompted by a report of a bonding braid twisting around the attachment nut installed on the bolt that connects the roll channel torque link to the left-hand cyclic pitch control stick. The actions specified by this AD are intended to prevent an unsecured bonding braid from restricting travel to the cyclic pitch control stick, and subsequent loss of control of the helicopter.
2003-22-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires a one-time inspection of the barrel nut holes of the upper spar caps and skin panel of the horizontal stabilizer for corrosion, and follow-on and corrective actions if necessary. This action is necessary to prevent such corrosion, which could result in structural damage and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2003-22-07: The FAA is superseding Airworthiness Directive (AD) 97-20-14, which applies to all Mitsubishi Heavy Industries, Ltd. (Mitsubishi) MU-2B series airplanes. AD 97-20-14 currently requires incorporating information into the Limitations Section of the Airplane Flight Manual (AFM) that requires pilot training before flight into known or forecast icing conditions after a certain date. AD 97-20-14 resulted from the Federal Aviation Administration's analysis that the training level of the pilots-in-command (PIC) of the MU-2B series airplanes made it difficult for pilots to recognize adverse operating conditions and operate safely while flying in icing conditions. Since issuance of AD 97-20-14, a new training video has been developed that includes information that is critical to safety of the MU-2B series airplanes. This AD requires you to update the AFM information to require this new video as the mandatory pilot training. We are issuing this AD to decrease the chance of icing-relatedincidents or accidents of the MU-2B series airplanes due to pilot error.
2003-19-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2003-19-51 that was sent previously to all known U.S. owners and operators of certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 & 701) and CL-600-2D24 (Regional Jet Series 900) series airplanes by individual notices. This AD requires repetitive detailed inspections for cracking or deformation, or pulled or missing fasteners, on the lower panel of the left- and right-hand main landing gear (MLG) doors, as applicable, and corrective actions if necessary. The actions specified by this AD are intended to prevent failure of the lower panel of the MLG door, the lower panel's departure from the airplane, and consequent damage to airplane structure, which could adversely affect the airplane's continued safe flight and landing. This action is intended to address the identified unsafe condition.
2003-16-19: This amendment adopts a new airworthiness directive (AD) that is applicable to all Learjet Model 45 airplanes. This action requires replacement of the horizontal stabilizer actuator assembly (HSAA) with a new HSAA. This action is necessary to prevent structural failure of the HSAA, which could result in possible loss of control of the airplane. This action is intended to address the identified unsafe condition.
2003-14-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2003-14-51, which was sent previously to all known U.S. owners and operators of the specified MD Helicopters, Inc. (MDHI) helicopters by individual letters. This AD requires checking and inspecting each main rotor blade retention bolt (bolt) and replacing the bolt with an airworthy bolt if necessary. The actions specified by this AD are intended to prevent failure of a bolt, loss of main rotor blade, and subsequent loss of control of the helicopter.
2003-15-06: This amendment adopts a new airworthiness directive (AD) that applies to Rolls-Royce plc (RR) RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines with high pressure (HP) compressor rotor rear stage 5 and 6 discs and cone shafts, part numbers (P/Ns) FK25230 and FK27899 installed. This amendment requires removal from service of these HP compressor rotor rear stage 5 and 6 discs and cone shafts, before reaching newly reduced life limits. This amendment is prompted by three reports of crack indications in the stage 5 and stage 6 blade loading slots, found during engine overhaul. We are issuing this AD to prevent stage 5 and 6 disc crack initiation and propagation leading to uncontained disc failure and damage to the airplane.
2003-14-20: This amendment supersedes Airworthiness Directive (AD) 82-12- 06, which applies to certain AeroSpace Technologies of Australia Pty Ltd. (ASTA) Models N22B and N24A airplanes. AD 82-12-06 currently requires repetitive visual inspections of all rudder control lever shaft assemblies for cracks and discrepancies, and, if cracks or discrepancies are found, it requires replacement with new or serviceable rudder control shafts, and a check of the fit of all rod end bearings in lever shafts. AD 82-12-06 also allows you to inspect all lever shafts by magnetic particle inspection or dye penetrant methods as terminating action for the repetitive visual inspections. This AD is the result of recent reports of failures of the upper control lever torque shaft due to fatigue loading on the affected airplanes, including those that included the terminating actions. This AD requires more detailed repetitive inspections (than there are in AD 82-12-06) of the upper and lower rudder pedal torque shafts and a one- time inspection for discrepancies in the thickness of the lever shaft side plates with appropriate follow-up action. The actions specified by this AD are intended to detect and correct cracks in the rudder control lever torque shafts and discrepancies in the thickness of the lever shaft side plates, which could result in failure of the rudder control lever torque shaft. Such failure could lead to reduced controllability of the airplane.
2003-14-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires inspections for cracking of the forward end clevis lugs of the flap track, and replacement of the flap track with a new flap track if necessary. That AD also currently provides for an optional modification of the forward end clevis lugs, which terminates the required inspections. This amendment expands the applicability of the existing AD, and requires new repetitive inspections for evidence of rotation or migration of the bushings or cracking of the lugs of the forward end clevis of the flap tracks that support the wing trailing edge flaps, corrective actions if necessary, and eventual accomplishment of a terminating action. These actions are necessary to prevent cracking and fracture of the forward end clevis of the flap track, which could result in reduced structural capability of the flap and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2003-12-11: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires a one-time ultrasonic inspection of the maneuvering actuator piston rod of the main landing gear (MLG) to ensure adequate wall thickness of the piston rods, and replacement of any discrepant piston rod with a new piston rod. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the maneuvering actuator piston rod of the MLG, which would impede retraction of the MLG, and consequent reduced controllability of the airplane.
2003-14-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200, -300, -320, and - 500 series airplanes; and Model ATR72 series airplanes; that requires replacement of a certain Automatic Takeoff Power Control System (ATPCS) test selector switch with a different test selector switch. This action is necessary to prevent shorting of a contact in the ATPCS test selector switch due to abnormal wear of contact surfaces, which could result in dual engine power drop with associated loss of both alternating current wild and main hydraulic power during ground maneuvers, and consequent reduced controllability of the airplane and increased flightcrew workload. This action is intended to address the identified unsafe condition.
2003-14-07: This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/ 45 airplanes. This AD requires you to repetitively replace the nose landing gear (NLG) drag link right-hand part every 4,000 landings until an improved design NLG drag link right-hand part is installed. This AD also requires you to install an improved design NLG drag link right- hand part as terminating action for the repetitive replacements. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent structural failure of the nose landing gear (NLG) caused by fatigue damage to the NLG drag link right-hand part that develops over time. Such failure could result in either an unintended NLG extension during flight or the NLG not properly locking upon extension, which could lead to loss of airplane control during landingoperations.
2003-14-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain transport category airplanes as listed above. This action requires modification of the reinforced flight deck door installed on the airplane. This action is necessary to prevent inadvertent release of the decompression latch and consequent opening of the decompression panel in the flight deck door. If an airplane crewmember is in close proximity to the flight deck door when the decompression panel opens, the decompression panel could hit and injure the crewmember. This action is intended to address the identified unsafe condition.