24 Airworthiness Directives: 11 airplane, 4 rotorcraft, 6 engine, 1 propeller, 1 appliance, 1 various.
AD 2002-04-08 · published Mar 1, 2002, effective Apr 5, 2002
Boeing Model 737-600, -700, -700C, and -800 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, -700C, and -800 series airplanes, that requires a one-time inspection of certain fasteners in rudder pedal housings to determine if pan-head fasteners are installed, and replacement of existing fasteners with improved fasteners, if necessary. The actions specified by this AD are intended to prevent loss of free movement of the rudder pedals, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-04-09 · published Mar 1, 2002, effective Apr 5, 2002
BAE Systems (Operations) Limited Model BAe 146 Series Airplanes and Model Avro 146-RJ Series Airplanes
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 modifying the engine start circuit. This action is necessary to prevent overheating of the soft start resistor of the engine start circuit, which could result in smoke and fumes in the cabin and consequent injury to passengers and crew. This action is intended to address the identified unsafe condition.
AD 2002-04-10 · published Mar 1, 2002, effective Apr 5, 2002
Airbus Model A319 Series Airplanes and A320-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319 series airplanes and A320-200 series airplanes, that requires repetitive inspections to detect loose or missing rivets in specified areas of the door frames of the overwing emergency exits and corrective action, if necessary. This AD also requires measurement of the grip length of all rivets in the specified areas and corrective action, if necessary, which terminates the repetitive inspections. This amendment is prompted by mandatory continuing airworthiness information from a foreign airworthiness authority. The actions specified by this AD are intended to detect and correct loose or missing rivets or discrepant rivets, which could lead to reduced structural integrity of the overwing emergency exit door frames. This action is intended to address the identified unsafe condition.
AD 2002-05-01 · published Mar 1, 2002, effective Mar 18, 2002
Boeing Model 747-100, 747-200, 747-300, 747SP, and 747SR Series Airplanes Powered by Pratt & Whitney JT9D-3 and JT9D-7 Series Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-100, 747-200, 747-300, 747SP, and 747SR series airplanes powered by Pratt & Whitney JT9D-3 or JT9D-7 series engines. That AD currently requires inspections of the vertical chords of the aft torque bulkhead of the outboard nacelle struts, corrective action, if necessary, and a modification of the vertical chords, which ends the inspections. This amendment will reduce the compliance time and repetitive intervals for the currently required inspections. These actions are necessary to prevent cracking of the vertical chords adjacent to the lower spar fitting, which could result in separation of the diagonal brace load path. Continued operation with a separated diagonal brace load path increases loads on the upper link, midspar fitting, and dual side links, which could result in separation of the strut and engine from the airplane. These actions are intended to address the identified unsafe condition.
AD 2002-05-04 · published Mar 11, 2002, effective Apr 22, 2002
SOCATA-Groupe AEROSPATIALE Models MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 150T, and Rallye 150ST Airplanes
This amendment supersedes Airworthiness Directive (AD) 77-15- 06, which applies to all SOCATA--Groupe AEROSPATIALE (Socata) Models MS 892A-150, MS 892E-150, MS 893A, MS 893E, Rallye 150T, and Rallye 150ST airplanes. AD 77-15-06 currently requires you to repetitively inspect the engine mount assembly for cracks, repair any cracks found, and modify the brackets on airplanes with right angle engine mounts. This AD is the result of the French airworthiness authority's determination that updated service information and additional aircraft should be added to the applicability of AD 77-15-06. This AD retains the inspection and repair requirements of the current AD and adds the information communicated by the French airworthiness authority. The actions specified by this AD are intended to detect and correct cracks in the engine mount assembly. Such a condition could cause the engine mount assembly to fail, which could result in loss of control of the airplane.
AD 2002-05-05 · published Mar 13, 2002, effective Mar 19, 2002
Cirrus Design Corporation Models SR20 and SR22 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Cirrus Design Corporation (Cirrus) Models SR20 and SR22 airplanes. This AD requires you to incorporate temporary operating limitations into the Limitation Section of the airplane flight manual (AFM) for certain affected airplanes and install a cable clamp external to the cone adapter on the Cirrus Aircraft Parachute System (CAPS) activation cable for all affected airplanes. The operating limitations will reduce the need to use the CAPS system in a loss of aircraft control emergency situation. The installation will prevent the cable housing from going into the rocket cone and will allow the rocket to fire correctly. This AD is the result of a report from the manufacturer that certain CAPS may not activate in an emergency situation. The actions specified by this AD are intended to initially limit the chance of failure of the CAPS activation system in an emergency situation and eventually eliminate this potential failure. Failure of this system would result in occupant injury and/or loss of life and loss of aircraft.
AD 2002-05-07 · published Mar 18, 2002, effective Apr 22, 2002
Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. For certain airplanes, this action requires repetitive inspections for discrepancies of the rear spar attachments and cracks in the upper flange of the inboard track at the rear spar attachment of each outboard flap, and eventual rework of the flap track assembly and rear spar attachments, including replacement of the flap track with a new track, if necessary. For all airplanes, this action requires repetitive inspections for cracks in the upper flange of the inboard flap tracks at the rear spar attachments, and corrective action, if necessary. The actions specified by this AD are intended to find and fix discrepancies of the inboard tracks of the outboard flaps, which could result in loss of the outboard trailing edge flaps and consequent reduced controllability of the airplane. These actions are intended to address the identified unsafe condition.
AD 2002-06-02 · published Mar 19, 2002, effective Apr 3, 2002
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747 series airplanes. This action requires repetitive inspections for cracking of the upper skin of the horizontal stabilizer center section and the rear spar upper chord, and repair, if necessary. This action is necessary to find and fix such cracking, which could lead to reduced structural capability of the horizontal stabilizer center section, and result in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-06-03 · published Mar 19, 2002, effective Apr 3, 2002
Boeing Model 737-600, -700, -700C, and -800 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, -700C, and -800 series airplanes. This action requires measurement of clearance between a certain retention bracket for the elevator power control unit (PCU) and a quadrant on the inboard side of the right elevator PCU, inspection for loose fasteners in certain retention bracket assemblies for the left and right elevator PCUs, and corrective action, if necessary. This action is necessary to prevent jamming of the elevator flight controls, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-06-10 · published Mar 27, 2002, effective May 6, 2002
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC- 12/45 airplanes. This AD requires you to replace the metered connector and oxygen tubing and related components in the rear seat bench. 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 correct the potential for insufficient oxygen quantity that is available to occupants of the rear seat bench in some emergency conditions. This condition could result in reduced occupant safety at the rear bench seat location.
AD 2002-06-51 · published Mar 28, 2002, effective Apr 2, 2002
Bombardier Model CL-600-2C10 (Regional Jet Series 700 and 701) Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2002-06-51 that was sent previously to all known U.S. owners and operators of certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 and 701) series airplanes by individual notices. This AD requires revising the Airplane Flight Manual to provide procedures for addressing uncommanded transfer of fuel from wing fuel tanks to center fuel tank. This action also requires revising the Minimum Equipment List (MEL); limiting operation of the airplane to flight within 60 minutes of a suitable alternative airport; and ensuring that normal mission fuel requirements are increased by 3,000 pounds. This action was prompted by reports of uncommanded fuel transfer between the wing fuel tanks and the center fuel tank. The actions specified by this AD are intended to ensure that the flight crew has the procedures necessary to address such uncommanded fuel transfer, which could cause the center tank to overfill, and fuel to leak from the center tank vent system or to become inaccessible, and result in engine fuel starvation.
AD 2002-04-07 · published Mar 1, 2002, effective Mar 18, 2002
Eurocopter France Model AS350BA and B2 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France (ECF) Model AS350BA and B2 helicopters modified with a Eurocopter Canada Limited (ECL) Left-side-Pilot Configuration kit in accordance with Canadian Supplemental Type Certificate (STC) SH96-32 or United States STC SR00429 NY. This action requires replacing the collective locking device with a newly-designed locking device. This amendment is prompted by a report of a locking device that engaged during flight. The actions specified in this AD are intended to prevent inadvertent engagement of a locking device, the collective pitch control locking in the full-down position, and subsequent loss of control of the helicopter.
AD 2002-05-06 · published Mar 18, 2002, effective Apr 22, 2002
Sikorsky Aircraft Corporation Model S-76A Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Sikorsky Aircraft Corporation Model S-76A helicopters that currently requires a service life limit on certain landing gear parts based on hours time-in-service (TIS). This amendment adds another method of calculating the life limit for certain landing gear parts based on cycles and requires the operator to choose and record the method of calculating the service life of each part in the rotorcraft history or equivalent record. This amendment also requires replacing the part based upon either the maximum hours TIS or the maximum cycles but not both. This amendment is prompted by the need to add flight cycles as a method of calculating the life limit for certain landing gear parts based on fatigue analyses. The actions specified by this AD are intended to add or revise the retirement life for certain landing gear parts to prevent fatigue failure of the landing gear and subsequent loss of control of the helicopter.
AD 2002-03-52 · published Mar 20, 2002, effective Apr 4, 2002
Eurocopter France Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and EC130 B4 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2002-03-52, sent previously to all known U.S. owners and operators of Eurocopter France (ECF) helicopters by individual letters. This AD requires checking for a gap between the adhesive bead and the metal bushing bonded on each STARFLEX star arm end (arm end) and, if a gap is found, replacing the STARFLEX with an airworthy part. This AD is prompted by reports of bonding failure between the metal bushing and the arm end that led to severe vibrations resulting in several emergency landings. The actions specified in this AD are intended to detect bonding failure between the metal bushing and each arm end, severe lateral vibrations, and subsequent loss of control of the helicopter.
AD 2002-06-04 · published Mar 20, 2002, effective Apr 24, 2002
Eurocopter France Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and AS355N Helicopters
This amendment adopts a new airworthiness directive (AD) for specified Eurocopter France (ECF) helicopters that requires replacing the tail rotor hub pitch change plate "SNR" bearing (bearing). This amendment is prompted by fatigue cracks found in the bearings. The actions specified by this AD are intended to prevent seizure of the bearing, loss of tail rotor effectiveness, and subsequent loss of control of the helicopter.
AD 2002-04-11 · published Mar 4, 2002, effective Apr 8, 2002
General Electric Company GE90 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain General Electric Company (GE) GE90 series turbofan engines, that currently requires revisions to the Life Limits Section of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action modifies the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. This amendment is prompted by additional focused inspection procedures that have been developed by the manufacturer. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2002-05-02 · published Mar 8, 2002, effective Apr 12, 2002
General Electric Company CF34-3A1 and -3B1 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to General Electric Company (GE) CF34-3A1 and -3B1 series turbofan engines, that currently requires revisions to the Engine Maintenance Program specified in the manufacturer's Instructions for Continued Airworthiness (ICA) for GE CF34-3A1 and -3B1 series turbofan engines. Those revisions require enhanced inspection of selected critical life-limited parts at each piece-part exposure. The existing AD also requires that an air carrier's approved continuous airworthiness maintenance program incorporate these inspection procedures. This amendment modifies the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. An FAA study of in-service events involving uncontained failures of critical rotating engine parts has indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2002-05-03 · published Mar 8, 2002, effective Apr 12, 2002
General Electric Company CF6-6, CF6-45, and CF6-50 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to General Electric Company (GE) CF6-6, CF6- 45, and CF6-50 series turbofan engines, that currently requires revisions to the Time Limits Section of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required inspection of selected critical life-limited parts at each piece-part exposure. This amendment modifies the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. A Federal Aviation Administration (FAA) study of in- service events involving uncontained failures of critical rotating engine parts has indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2002-03-09 R1 · published Mar 21, 2002, effective Mar 27, 2002
Honeywell International Inc. (formerly AlliedSignal Inc. and Textron Lycoming) LTS101 Series Turboshaft and LTP101 Series Turboprop Engines
This amendment revises an existing airworthiness directive (AD), that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc. and Textron Lycoming) LTS101 series turboshaft and LTP101 series turboprop engines. The existing AD will become effective on March 27, 2002, and requires a one-time visual inspection for surface finish and a one-time fluorescent penetrant inspection for cracks of certain impellers installed on LTS101 series turboshaft and LTP101 series turboprop engines. This amendment requires the same inspections, and in addition, allows installation of impellers that pass those inspections. This revision to the existing AD is prompted by an inadvertent omission in the existing AD to include allowance of installation of impellers that pass inspections required by the AD. The actions specified by this AD are intended to prevent impeller failure from cracks in the impeller back face area, which could result in an uncontained engine failure.
AD 2002-06-08 · published Mar 22, 2002, effective Apr 26, 2002
Rolls-Royce Corporation (Formerly Allison Engine Company) 250-C28 Series Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to certain Rolls-Royce Corporation (formerly Allison Engine Company) 250-C28 series engines. This amendment requires removal of third stage turbine wheels, part number (P/N) 6899383, with certain serial numbers (SN's), from service before exceeding new, reduced life limits. This amendment also establishes a drawdown program to require the removal of those turbine wheels that exceed the new lower limits. This amendment is prompted by the potential to experience uncommanded shutdown caused by fractures of third stage turbine blade tips and shrouds. The actions specified by this AD are intended to prevent uncommanded shutdown of the engine due to fractures of third stage turbine blade tips and shrouds.
AD 2002-06-07 · published Mar 27, 2002, effective May 1, 2002
General Electric Company CF6-80E1 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-80E1 series turbofan engines, installed on Airbus Industrie A330 series airplanes. This action requires initial and repetitive pressure testing of the directional pilot valve (DPV) assembly, with replacement of DPV assemblies that fail the pressure test, or, replacing the DPV assembly without performing pressure testing, with a serviceable DPV assembly, or, deactivating the fan reverser for no longer than 10 days until replacement of the DPV assembly is done. This amendment is prompted by a review of thrust reverser safety analyses following a report of inadvertent thrust reverser deployment on another make and model engine. The actions specified in this AD are intended to prevent inadvertent thrust reverser deployment, which, if it occurred in- flight, could result in loss of control of the airplane.
AD 2002-06-06 · published Mar 25, 2002, effective May 3, 2002
Rockwell Collins, Inc. TDR-94 and TDR-94D Mode S Transponders
This amendment adopts a new airworthiness directive (AD) that applies to certain Rockwell Collins TDR-94 and TDR-94D Mode S transponders that derive altitude information from a Gillham (gray code) encoded pressure altitude source and are installed on airplanes. This AD requires you to have the unit modified to prevent erroneous altitude reporting. This AD is the result of reports that erroneous altitude resolutions could occur when the affected transponders are utilized in areas with other airplanes equipped with certain aircraft collision avoidance system (ACAS) or traffic alert and collision avoidance system (TCAS) configurations. The actions specified by this AD are intended to prevent these erroneous altitude resolutions from causing a reduction in the intended ACAS or TCAS Change 7 separation margins. Such a condition could result in air traffic control or the pilot making flight decisions that put the airplane in unsafe flight conditions.
AD 2002-06-05 · published Mar 22, 2002, effective Apr 26, 2002
Various Transport Category Airplanes Equipped With Air Traffic Control (ATC) Transponders Manufactured by Rockwell Collins, Inc.
This amendment adopts a new airworthiness directive (AD), applicable to various transport category airplanes equipped with certain Mode C air traffic control (ATC) transponders manufactured by Rockwell Collins, Inc. This amendment requires testing each transponder; replacing certain parts in any transponder that fails the initial test with new parts and performing additional test(s); and making repairs, as necessary, so that the transponder passes the test. This amendment is prompted by reports that indicate that the equipment used to conduct earlier tests of certain transponders did not detect certain malfunctions. An airplane equipped with such malfunctioning transponders could transmit inaccurate data concerning its altitude to a nearby airplane equipped with the traffic alert and collision avoidance system (TCAS II), causing the TCAS II to issue an erroneous resolution advisory to the pilot. The actions specified by this AD are intended to prevent transmission of inaccurate data concerning altitude from one airplane to another, which could cause the pilot receiving the data to change course, either ascending or descending, and possibly lead to a mid-air collision or near mid-air collision.
