Results
2004-05-12: This amendment adopts a new airworthiness directive (AD) that is applicable to all Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This action requires repetitive inspections of the left and right engine throttle control gearboxes for wear, and corrective action if necessary. This action is necessary to prevent excessive wear of the gearboxes and subsequent movement or jamming of the engine throttle; movement of the throttle towards the idle position brings it close to the fuel shut-off switch, which could result in an in-flight engine shutdown. This action is intended to address the identified unsafe condition.
2004-05-14: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 707 and 720 series airplanes, that requires inspection of the bolt forward of the wing front spar upper chord on the overwing support fittings of the inboard and outboard nacelle struts to verify that BACB30US type bolts are installed. If any other type of bolt is found, this amendment requires replacement with a new BACB30US type bolt. This action is necessary to prevent separation of the engine from the airplane due to stress corrosion cracking and consequent fracturing of the bolts. This action is intended to address the identified unsafe condition.
2004-05-23: This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that currently requires certain inspections of the main rotor swashplate bearing (bearing) and plugging the nonrotating swashplate vent holes and barrel nut orifices. This amendment eliminates most of those AD actions, which are now included in the Airworthiness Limitations section of the maintenance manual, but retains the requirements for the inspections and lubrication of the main rotor swashplate. This amendment also clarifies that repetitive maintenance of the main rotor swashplate and bearing is required at intervals not to exceed 100 hours time-in-service (TIS). This amendment is prompted by the need to clarify the AD wording to avoid any misinterpretation of the required interval for inspecting and lubricating the main rotor swashplate and bearing. The actions specified by this AD are intended to prevent failure of the bearing and subsequent loss of control of the helicopter.
2004-05-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and -300 series airplanes, that requires repetitive inspections of the aft pressure bulkhead web, and corrective action, if necessary. This action is necessary to detect and correct fatigue cracks in the aft pressure bulkhead web, which could result in uncontrolled rapid decompression. This action is intended to address the identified unsafe condition.
2004-05-19: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This action requires an inspection of the rear spar attach pins and front spar attach bolts that attach the horizontal stabilizers to the horizontal stabilizer center section for damage; and follow-on or corrective actions, as applicable. This action is necessary to detect and correct damaged rear spar attach pins or front spar attach bolts, which may lead to failure of the bolts or pins, and consequent loss of the stabilizer and loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
2004-05-05: This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-2C, B4-103, and B4-203 series airplanes, that currently requires a one-time inspection of the space between the fuel quantity indication (FQI) probes and any adjacent structures for minimum clearance, and corrective action if necessary. This amendment expands the applicability in the existing AD and requires the subject one-time inspection on additional airplanes. The actions specified by this AD are intended to prevent the possibility of electrical arcing to the fuel tank if the airplane should be struck by lightning. Such arcing could create a potential ignition source within the fuel tank and an increased risk of a fuel tank explosion and fire. This action is intended to address the identified unsafe condition.
2004-05-09: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplane models, that requires a one-time inspection for chafing of wiring in the left-hand tunnel area of the forward cargo compartment, repair if necessary, and coiling and stowing of excess wiring. This action is necessary to prevent wire chafing and subsequent shorting to structure in the forward cargo compartment, which could result in smoke or fire in the airplane. This action is intended to address the identified unsafe condition.
2003-22-07 R1: The FAA is revising Airworthiness Directive (AD) 2003-22-07, which applies to all Mitsubishi Heavy Industries, Ltd. (Mitsubishi) MU- 2B series airplanes. AD 2003-22-07 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 2003-22-07 resulted from the development of a new training video that includes information that is critical to safety of the MU-2B series airplanes. This AD revision is the result of the FAA incorrectly stating in the actions required by AD 2003-22-07 that on or before June 15, 2004 (the effective date of AD 2003-22-07), no person may serve as pilot-in-command (PIC) of a MU-2B series airplane in a flight into known or forecast icing conditions, unless the PIC has received the required training. Consequently, this AD will correct the actions required in AD 2003-22-07 to require those actions on or after June15, 2004. We are issuing this AD to ensure that the Icing Awareness Training (IAT) requirement continues after June 15, 2004, in order to decrease the chance of icing-related incidents or accidents of the MU-2B series airplanes due to pilot error.
2004-04-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Mystere-Falcon 50 series airplanes, that requires applying PR (fuel tank sealant) and installing PR patches over the internal side panel recesses of the left-hand and right-hand feeder tanks at certain frames and stringers. This action is necessary to prevent possible fuel ignition in the event of a lightning strike and consequent uncontained rupture of the fuel tank(s). This action is intended to address the identified unsafe condition.
2004-01-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2004-01-51, which was sent previously to all known U.S. owners and operators of the specified Eurocopter France (Eurocopter) model helicopters by individual letters. This AD requires, before further flight, for helicopters with less than 10 hours time-in-service (TIS) since installing a main or combiner gearbox received from Eurocopter Marignane, France, replacing these affected gearboxes with appropriate airworthy gearboxes received from another source. This action is prompted by a report of a free wheel unit slipping during the single engine phase of an acceptance flight that resulted in an engine overspeed and an engine shutdown. The actions specified by this AD are intended to prevent engine overspeed, an engine shut-down, and subsequent loss of control of the helicopter.
2004-04-04: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-8E series turbofan engines, with certain serial number (SN) master variable geometry (VG) actuators installed. This AD requires initial and repetitive reviews of the airplane computer systems for master VG actuator fault messages. This AD also requires replacement of actuators reported faulty by the Full Authority Digital Engine Control (FADEC). This AD results from nine reports of CF34-8C master VG actuator electrical signal faults, one report of which was a dual-channel fault, resulting in the FADEC commanding the engine power to idle. We are issuing this AD to prevent VG master actuator dual-channel electrical signal faults which will cause an uncommanded reduction of thrust to idle with a subsequent loss of the ability to advance thrust above idle; and which could result in a multi-engine loss of thrust if dual-channel faults occur on more than one engine simultaneously.
2004-03-36: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time inspection of certain engine control cables to determine the batch number on the end fitting, and replacement of affected cables with new cables. This action is necessary to prevent failure of defective engine control cables, which could result in loss of the engine controls, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2004-04-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires replacing the dual shuttle valve in the number 2 hydraulic system with a new, improved valve. This action is necessary to prevent failure of the dual shuttle valve in the number 2 hydraulic system, with reduced maximum elevator rate on the left side, which could result in pilot-induced pitch oscillation and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2004-03-32: 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 replace all electronic control modules in the airplane electrical system with newly designed modules. This AD is the result of smoke in the cockpit and loss of electrical systems function. We are issuing this AD to prevent short circuit failure and electrical arcing of the electronic control modules, which could result in loss of the electrical systems components or burning of wiring insulation and cause smoke in the cockpit. This condition could lead to the inability to properly control the airplane.
2004-04-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that currently requires a one-time general visual inspection of the seat locks and seat tracks of the flightcrew seats to ensure that the seats lock in position and to verify that lock nuts and bolts of adequate length are installed on the rear track lock bracket, and corrective action, if necessary. This amendment revises the applicability of the existing AD by adding airplanes. The actions specified by this AD are intended to prevent uncommanded movement of the flightcrew seats during acceleration and take-off of the airplane, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2004-03-27: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires inspecting the bevel gear for a crack using a borescope. This amendment is prompted by a crack that was detected on a bevel gear during a main gearbox teardown inspection. The actions specified by this AD are intended to prevent failure of the bevel gear, loss of torque to the main rotor system, and subsequent loss of control of the helicopter.
2004-03-09: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200F, 747-200C, 747-300, 747SR, and 747SP series airplanes. This AD requires repetitive inspections for discrepancies of the structure near and common to the upper chord and splice fittings of the rear spar of the wing, and repair if necessary. This AD also provides for an optional modification that, if accomplished, terminates the repetitive inspection requirement, but would necessitate eventual post-modification inspections. This action is necessary to find and fix fatigue cracking of structure near and common to the upper chord and splice fittings of the rear spar of the wing, which could result in loss of structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2004-03-21: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model 717-200 airplanes, that requires inspection of the inboard ends of the outer skin panels of the horizontal stabilizer at Station Xh=7.234 for material defects, and corrective action, if necessary. This action is necessary to detect material defects in the inboard ends of the outer skin panels of the horizontal stabilizer, which could lead to cracks and an associated loss of strength in the attachments, and consequent reduced structural integrity of the horizontal stabilizer. This action is intended to address the identified unsafe condition.
2004-03-29: The FAA adopts a new airworthiness directive (AD) for all Pacific Aerospace Corporation, Ltd. Models FU24-954 and FU24A-954 airplanes. This AD requires you to perform repetitive detailed visual inspections of the forward vertical fin base for cracks. If any cracks or discrepancies are found, you must repair the structure before further flight and notify the FAA. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for New Zealand. We are issuing this AD to detect and correct cracks in the vertical fin base, which could result in loss of the fin and loss of aircraft control.
2004-03-06: This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A320 series airplanes, that currently requires repetitive ultrasonic inspections to detect fatigue cracking in the wing/fuselage joint cruciform fittings, and corrective actions if necessary. This amendment requires repetitive ultrasonic inspections for fatigue cracking in the wing/fuselage joint cruciform fittings at a reduced inspection threshold and repetitive interval. This amendment also adds airplanes to the applicability. The actions specified by this AD are intended to detect and correct fatigue cracks on the wing/fuselage joint cruciform fittings, which could result in reduced structural integrity of the wing/fuselage. This action is intended to address the identified unsafe condition.
2004-03-12: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes, that currently requires initial and repetitive inspections to detect fatigue cracking in certain areas of the fuselage, and corrective actions if necessary. For certain airplanes, this amendment requires a new inspection for oversized fastener holes and cracking, and repair if necessary. The actions specified by this AD are intended to prevent fatigue cracking of the fuselage and the passenger and service doors, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition. DATES: Effective March 15, 2004. The incorporation by reference of a certain publication, as listed in the regulations, is approved by the Director of the Federal Register as of March 15, 2004. The incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of April 3, 2000 (65 FR 10381, February 28, 2000).
2004-03-23: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-200 and -300 series airplanes, that currently requires a one-time inspection to detect cracks of the lower frames and reinforcing angles of the main deck cargo door where the door latch fittings attach between certain fuselage stations and water lines, and replacement of any cracked part with a new part having the same part number. This amendment continues to require the existing actions and corrects a reference to an incorrect fuselage station. The actions specified by the AD are intended to detect and correct cracking of the lower portion of the main deck cargo door frames, which could result in sudden depressurization, loss or opening of the main deck cargo door during flight, and loss of control of the airplane.
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.