Results
2004-03-02: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A321 series airplanes. This action requires revising the Limitations section of the airplane flight manual to include an instruction to use Flap 3 for landing when performing an approach in conditions of moderate to severe icing, significant crosswind (i.e., crosswinds greater than 20 knots, gust included), or moderate to severe turbulence. This action is necessary to prevent roll oscillations during approach and landing in certain icing, crosswind, and turbulent conditions, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2004-02-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes. This amendment requires, for certain airplanes, replacement of the hinge assemblies on certain escape slide compartments of the forward doors with new, stronger hinge assemblies; and, for certain other airplanes, an inspection for incorrectly crimped hinge assemblies, and corrective action if necessary. The actions specified by this AD are intended to prevent forward door escape slides from falling out of their compartments into the airplane interior and inflating, which could impede an evacuation in the event of an emergency. This action is intended to address the identified unsafe condition.
2004-02-02: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes, that requires relocating the pitot 1 and pitot 2 drain valves from the nose landing gear compartment to the forward electronic compartment, and accomplishing follow-on actions. This action is necessary to prevent ice from damaging the pitot drain valves, which could cause airspeed indication errors, resulting in display of erroneous or misleading information to the flight crew. This action is intended to address the identified unsafe condition.
2004-01-21: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-22B, RB211-524, and RB211-535 series turbofan engines. This AD requires the installation of a front engine mount housing and link support assembly that has a serialized, life limited, spherical bearing installed. This AD results from reports of corrosion and fatigue cracks in the mount pins, the spherical bearings, and the support links and their respective spherical bearings. We are issuing this AD to prevent failure of the front engine mount housing and link support assembly due to cracks that could result in loss of the engine.
2004-01-15: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model 717-200 airplanes, that requires repetitive inspections of the electric motor of the auxiliary hydraulic pump for electrical resistance, continuity, mechanical rotation, and associated wiring resistance/voltage; and corrective actions, if necessary. This action is necessary to prevent various failures of the electric motor of the auxiliary hydraulic pump and associated wiring, which could result in fire at the auxiliary hydraulic pump and consequent damage to the adjacent electrical equipment and/or structure. This action is intended to address the identified unsafe condition.
2004-01-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires an inspection to detect moisture and migrated bushings of the guide fittings of the safety locking pins of the passenger doors, removal of any moisture, application of grease, and reinstallation of any migrated bushing. That AD also requires installation of a greasing nipple on the guide fitting of the locking pin and on three telescopic rods on the passenger doors. This amendment adds a requirement for modification of the upper guide fitting of the locking pin, and expands the applicability in the existing AD. The actions specified by this AD are intended to prevent jamming of the locking pin of the passenger door, which could result in inability to open the passenger door and delay of evacuation in an emergency, resulting in possible injury to passengers or crew. This action is intended to address the identified unsafe condition.
2004-01-14: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC130B4 helicopters with a certain air intake cowling attachment fitting (fitting) installed. This action requires inspecting for broken or cracked forward fittings. If a broken or cracked fitting is found, inspecting the four center and aft fittings for cracks is required. Replacing broken fittings or certain cracked fittings is also required. This amendment is prompted by reports of cracked and broken fittings; one fitting failed after only 418 hours time-in-service (TIS). This condition, if not corrected, could result in failure of a forward fitting, an excess load on the other fittings, which could cause them to crack and break, which could result in loss of the air intake cowling in flight, and subsequent damage or loss of control of the helicopter, or both.
2004-01-12: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and -145 series airplanes, that requires operators to inspect the pitot-true air temperature (TAT) relays and the full authority digital engine control (FADEC) electronic interface resistor modules to detect contamination. This AD also requires operators to perform corrective action if necessary, clean the relay/connector pins and sockets, modify the seal between the cockpit console panels and the storm window, and/or install a new protective frame (protective sheets) at the cockpit relay supports. This action is necessary to detect and correct oxidation of the pitot-TAT relay, which could result in increased resistance and overheating of the relay and consequent smoke in the cockpit; and to detect and correct oxidation of the FADEC electronic interface resistor modules, which could result in in-flight uncommanded engine power roll back to idle. This action is intended to address the identified unsafe condition.
2003-26-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, 737-700, 737-800, 757-200, and 757-300 series airplanes, that requires replacing existing video distribution unit (VDU) connectors with new, improved connectors or new wire assemblies (jumpers), and performing related actions, as applicable. This action is necessary to prevent a short circuit in a VDU connector and consequent arcing and damage to wiring within the connector, which could result in damage to adjacent systems or structure and possible smoke or fire in the airplane cabin. This action is intended to address the identified unsafe condition.
2003-26-07: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes, that requires a one-time general visual inspection of the circuit breakers to determine if discrepant circuit breakers are installed, and corrective action if necessary. This action is necessary to prevent internal overheating and arcing of circuit breakers and airplane wiring due to long-term use and breakdown of internal components of the circuit breakers, which could result in smoke and fire in the flight compartment and main cabin. This action is intended to address the identified unsafe condition.
2003-25-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 900 EX and Mystere-Falcon 900 series airplanes. This action requires installing an attachment support assembly for the fire extinguishing piping in the baggage compartment. For certain airplanes this action also requires modifying the liner panel of the baggage compartment. The actions specified by this AD are intended to prevent distortion of the fire extinguishing discharge nozzle as a result of the nozzle not being secure, which could result in poor diffusion of the fire extinguishing agent in the event of a fire in the baggage compartment. This action is intended to address the identified unsafe condition.
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.