34 Airworthiness Directives: 19 airplane, 7 rotorcraft, 5 engine, 3 appliance.
AD 2002-19-10 · published Oct 1, 2002, effective Nov 15, 2002
Air Tractor, Inc. Models AT-402, AT-402A, AT-402B, AT-602, AT-802, and AT-802A Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Air Tractor, Inc. (Air Tractor) Models AT-402, AT- 402A, AT-402B, AT-602, AT-802, and AT-802A airplanes. This AD requires you to repetitively inspect the upper longeron and upper diagonal tube on the left hand side of the aft fuselage structure for cracks and contact the manufacturer for a repair scheme if cracks are found. This AD is the result of reports of excessive movement in the empennage due to the loss of fuselage torsional rigidity. The actions specified by this proposed AD are intended to prevent failure of the fuselage caused by cracks. Such failure could result in loss of control of the airplane.
AD 2002-19-11 · published Oct 1, 2002, effective Nov 5, 2002
Boeing Model 767-200 and -300 Series Airplanes Powered by Pratt & Whitney JT9D Series Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and -300 series airplanes powered by Pratt & Whitney JT9D series engines, that requires replacement of the existing deactivation pin, aft cascade pin bushing, and pin insert on each thrust reverser half, with new, improved components. This action is necessary to prevent failure of the thrust reverser deactivation pins, which could result in deployment of the thrust reverser in flight and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-19-12 · published Oct 1, 2002, effective Nov 5, 2002
Boeing Model 747-200B, -300, -400, -400D, and -400F Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-200B, -300, -400, -400D, and -400F series airplanes; that currently requires repetitive inspections to detect cracking of fire extinguisher discharge tubes in certain engine struts, and corrective action, if necessary. For certain airplanes, that AD also provides for an optional modification of the fire extinguisher discharge tubes, which constitutes terminating action for the repetitive inspections. This amendment makes the previously optional modification of the fire extinguisher discharge tubes mandatory for all affected airplanes and adds one airplane to the applicability. This amendment is prompted by a report that the check tee valve at the top of an engine strut can be damaged such that no extinguishing agent can get to the engine. The actions specified by this AD are intended to prevent blockage of the check tee valve and cracks in the fire extinguisher discharge tubes in the engine struts, preventing the fire extinguishing agent from being delivered to the engine or reducing the amount delivered to the engine, which could permit a fire to spread from the engine to the wing of the airplane.
AD 2002-20-04 · published Oct 3, 2002, effective Nov 18, 2002
SOCATA-Groupe AEROSPATIALE Model TB 21 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA--Groupe AEROSPATIALE (Socata) Model TB 21 airplanes. This AD requires you to modify the exhaust system. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent high levels of carbon monoxide from entering the cockpit during certain flight configurations, which could result in the pilot becoming incapacitated or impairing his/her judgement. Such a condition could lead to the pilot not being able to make critical flight safety decisions and result in loss of control of the airplane.
AD 2002-19-51 R1 · published Oct 7, 2002, effective Oct 15, 2002
Boeing Model 737 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2002-19-51 R1 that was sent previously to all known U.S. owners and operators of all Boeing Model 737 series airplanes by individual notices. This AD revises existing AD 2002-19-51 that currently requires, for certain airplanes, an inspection to determine the serial number of certain flight control modules (FCM), having P/N 65-44891-7, and corrective actions if necessary. That AD was prompted by reports of failed FCMs, which resulted in sluggish response of the aileron, elevator, and rudder surfaces. This AD revises the existing AD to provide operators with additional options for compliance, to specify the serial numbers of the affected compensator, and to make other editorial changes. The actions specified by this AD are intended to prevent operation with one failed FCM, which could result in reduced controllability of the airplane, or with two failed FCMs, which could result in loss of control of the airplane.
AD 2002-20-07 · published Oct 7, 2002, effective Nov 12, 2002
Boeing Model 737 Series Airplanes
This amendment supersedes seven existing airworthiness directives (ADs), applicable to certain Boeing Model 737 series airplanes that, among other things, currently require replacing the main rudder power control unit (PCU) and PCU vernier control rod bolts; testing the main rudder PCU to detect certain discrepancies and to verify proper operation of the PCU; and revising the FAA-approved Airplane Flight Manual procedures to correct a jammed or restricted flight control condition. Instead, this amendment requires installation of a new rudder control system and changes to the adjacent systems to accommodate that new rudder control system. This amendment is prompted by FAA determinations that the existing system design architecture is unsafe due to inherent failure modes, including single-jam modes and certain latent failures or jams, which, when combined with a second failure or jam, could cause an uncommanded rudder hardover event and consequent loss of control of the airplane. Additionally, the current rudder operational procedure is not effective throughout the entire flight envelope. The actions specified by the proposed AD are intended to prevent the identified unsafe condition.
AD 2002-21-02 · published Oct 16, 2002, effective Nov 8, 2002
Cirrus Design Corporation Model SR20 and SR22 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Cirrus Design Corporation (Cirrus) Model SR20 and SR22 airplanes. This AD requires you to replace the self-locking retaining nut on the roll and yaw trim cartridges with a new self- locking retaining nut with a higher axial load capability. This AD is the result of a report that, during a production flight test, the self- locking retaining nut on the yaw trim cartridge came off. The actions specified by this AD are intended to prevent loss of the self-locking retaining nut on the roll and yaw trim cartridges during flight, which could result in jamming of the corresponding flight control system. Such jamming could lead to loss of control of the airplane.
AD 2002-21-03 · published Oct 16, 2002, effective Oct 21, 2002
Gulfstream Model G-V Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-V series airplanes. This action requires performing a one-time general visual inspection of the pilot's overhead circuit breaker panel wiring for discrepancies; rerouting the P45-12 wire; and repair, if necessary. This action is necessary to prevent circuit breaker wiring from becoming pinched or damaged, causing arcing between the wire and attaching bracket, which could result in smoke and/or fire in the pilot's circuit breaker panel. This action is intended to address the identified unsafe condition.
AD 2002-21-05 · published Oct 17, 2002, effective Oct 23, 2002
REVO, Incorporated Models Lake LA-4, Lake LA-4A, Lake LA-4P, Lake LA-4-200, and Lake Model 250 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain REVO, Incorporated (REVO) Models Lake LA-4, Lake LA- 4A, Lake LA-4P, Lake LA-4-200, and Lake Model 250 airplanes. This AD requires you to inspect the upper and lower wing spar doublers and angles for cracks at a certain time after the incorporation of Modification Kit B-79 or FAA-approved equivalent, replace any cracked wing spar doubler or angle, and report the results of the inspection to the Federal Aviation Administration (FAA). The kit modification consists of installing a doubler kit to give the spar an adequate fatigue life. This AD is the result of an incident of a crack found at the most outboard wing attachment fitting hole on one of the affected airplanes with the modification incorporated. The actions specified by this AD are intended to prevent wing spar failure caused by cracks in the wing spar doublers or angles, which could result in the wing separating from the airplane with consequent loss of control.
AD 2002-21-08 · published Oct 21, 2002, effective Dec 6, 2002
Pilatus Aircraft Ltd. Model PC-6 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Model PC-6 airplanes. This AD requires you to inspect the aileron assembly for correct configuration and modify as necessary. 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 improper aileron assembly configuration, which could result in failure of the aileron mass balance weight. Such failure could lead to loss of control of the airplane.
AD 2002-20-08 · published Oct 22, 2002, effective Dec 18, 2002
British Aerospace Jetstream Model 3201 Airplanes
This amendment supersedes AD 2000-09-13, which currently requires you to inspect the fuel quantity indication system for damage to the insulation of the wiring within the fuel tanks on British Aerospace Jetstream Model 3201 airplanes and requires you to repair or replace damaged wiring. This AD retains the actions of AD 2000-09-13 and requires you to replace the fuel quantity indication system wiring harness with improved design parts, inspect the fuel boost pump area for damage, and replace any damaged component. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect, correct, and prevent damage to the insulation of the wiring within the fuel tanks of the fuel quantity indication system. If not detected, corrected, and prevented, such damaged wiring could result in damage to the fuel boost pump and a malfunction in the cockpit indicators and/or electrical sparking inside the fuel tank with consequent fire or explosion.
AD 94-20-04 R1 · published Oct 22, 2002, effective Dec 10, 2002
Raytheon Aircraft Company Beech Models C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A and V35B Airplanes
This amendment revises Airworthiness Directive (AD) 94-20-04, which currently requires ruddervator inspections, modifications, and operating limitations on certain Raytheon Aircraft Company (Raytheon) Beech Models 35, 35R, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A, and V35B airplanes. This AD is the result of information received from the field on the ability to accomplish and understand the existing AD. This AD will condense and clarify information presented in AD 94-20-04 and will remove Beech Models 35, 35R, A35, and B35 airplanes from the applicability of AD 94- 20-04. We are incorporating the actions that apply to Beech Models 35, 35R, A35, and B35 airplanes into another AD action. The actions specified by this AD are intended to prevent structural failure of the V-tail, which could result in loss of control of the airplane.
AD 2002-21-06 · published Oct 24, 2002, effective Nov 8, 2002
McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-81 (MD-81), DC-9- 82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes, that currently requires revisions to the Airplane Flight Manual; installation of inspection aids on the wing upper surfaces; and, among other actions, installation of an overwing heater blanket system or primary upper wing ice detection system, and installation of a heater protection panel or an equipment protection device on certain overwing heater blanket systems. This amendment retains those requirements and adds a requirement to disable the anti-ice systems for the upper wing surface on certain airplanes. The actions specified in this AD are intended to prevent ingestion of ice into one or both engines and consequent loss of thrust from one or both engines; and damage to the upper wing skin surface and its structure, due to prolonged short- circuit electrical arcing of certain anti-ice systems.
AD 2002-21-09 · published Oct 24, 2002, effective Nov 29, 2002
McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes. This AD requires, among other actions, various inspections to detect cracks of the cockpit enclosure window sill, and follow-on and corrective actions, as applicable. The actions specified by this AD are intended to prevent fatigue cracking of the internal doublers and frame structure of the fuselage skin of the cockpit enclosure window sill, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-21-13 · published Oct 24, 2002, effective Dec 10, 2002
Raytheon Aircraft Company Beech Models 35, 35R, A35, and B35 Airplanes
This amendment supersedes Airworthiness Directive (AD) 98-13- 02, which currently requires operating limitations on Raytheon Aircraft Company (Raytheon) Beech Models 35, 35R, A35, and B35 airplanes. This AD is the result of Raytheon developing inspection and modification procedures that, when accomplished on the affected airplanes, will eliminate the need for the operating limitations. This AD retains the operating limitations for the affected airplanes until the recently developed inspection and modification procedures are accomplished. This AD also requires repetitive inspections of the fuselage structure. The actions specified by this AD are intended to prevent structural failure of the V-tail, which could result in loss of control of the airplane.
AD 2002-21-11 · published Oct 25, 2002, effective Dec 17, 2002
EXTRA Flugzeugbau GmbH Model EA-300S Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain EXTRA Flugzeugbau GmbH (EXTRA) Model EA-300S airplanes. This AD requires you (for all affected airplanes) to inspect the upper longeron at the horizontal stabilizer attachment for cracks using a fluorescent dye check penetrant method, repair any cracks found, and modify the horizontal stabilizer. This AD also requires a limit on operation to the Normal category until accomplishment of the initial inspection and modification on airplanes with less than 200 hours time-in-service (TIS). This AD is the result of reports of fatigue cracks at the horizontal stabilizer attachment on the affected airplanes. The actions specified by this AD are intended to detect and correct cracks in the horizontal stabilizer attachment, which could result in structural failure of the aft fuselage with consequent loss of control of the airplane.
AD 2002-21-14 · published Oct 25, 2002, effective Nov 29, 2002
Boeing Model 757-200, -200CB, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200, -200CB, and -300 series airplanes. This AD requires determining the part numbers of the master control valve on the pressure bottles that activate the off-wing escape slides, and performing corrective action if necessary. This action is necessary to prevent failure of an escape slide to deploy or inflate correctly, which could cause the slide to be unusable during an emergency evacuation and result in consequent injury to passengers or crewmembers. This action is intended to address the identified unsafe condition.
AD 2002-22-07 · published Oct 30, 2002, effective Nov 14, 2002
Boeing Model 767 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires a one-time inspection for missing bolts on the inboard and outboard support of the inboard main flap, and follow-on inspections and corrective actions, if necessary. This amendment adds an inspection that was inadvertently omitted from the existing AD. The actions specified in this AD are intended to detect missing, loose, or cracked bolts on the supports of the inboard main flap and prevent loss of the inboard main flap, which could result in loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-22-05 · published Oct 31, 2002, effective Nov 15, 2002
Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This action 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. This action also provides for an optional action of overhaul or replacement of the carriage spindles, which would extend the repetitive inspection interval. This action is necessary to prevent severe flap asymmetry due to fractures of the carriage spindles on an outboard mid- flap, which could result in reduced control or loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-20-01 · published Oct 2, 2002, effective Nov 6, 2002
Overseas Aircraft Support Inc, San Joaquin Helicopters, Smith Helicopters, Southwest Florida Aviation International, Rotorcraft Development Corporation, Arrow Falcon Exporters Inc., AST Inc., Bell Helicopter Textron Inc., Global Helicopter Technology Inc., Hagglund Helicopters LLC, International Helicopters Inc., Richards Heavylift Helo Inc., Robinson Air Crane Inc., Sout
This amendment adopts a new airworthiness directive (AD) for the specified military surplus helicopters that requires updating the product identification, extending the application of the AD to other models, continuing the existing retirement time for certain main rotor tension-torsion (TT) straps, and adding the TT strap part numbers to the applicability. This amendment is prompted by the need to expand the applicability to additional military surplus helicopters and to add two part numbers to the applicability. The actions specified by this AD are intended to prevent failure of a TT strap, loss of a main rotor blade, and subsequent loss of control of the helicopter.
AD 2002-20-03 · published Oct 2, 2002, effective Nov 6, 2002
Eurocopter France Model AS332C, L, L1, and L2; AS350B, BA, B1, B2, B3, and D; AS355E, F, F1, F2, and N; AS-365N2; AS 365 N3; SA330F, G, and J; SA-360C; SA-365C, C1, and C2; SA.316B and C; and SA.319B Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires a one-time measurement of the electrical resistance between the ferry fuel tank (tank) electrostatic ground connector and the tank filler neck before the next refueling of an installed tank or before the first fueling after installing a tank. If the electrical resistance has a value more than 1.5 milliohms, this AD prohibits refueling the tank. This amendment is prompted by reports of an inadequate electrical bond between the electrostatic ground connector and its support on several tank installations. The actions specified by this AD are intended to prevent refueling a tank that is not adequately electrically bonded, which could generate an electric arc between the refueling nozzle and the tank, causing an explosion.
AD 2002-15-51 · published Oct 3, 2002, effective Oct 18, 2002
Sikorsky Aircraft Corporation Model S76A, B, and C Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2002-15-51, sent previously to all known U.S. owners and operators of the specified Sikorsky Aircraft Corporation (Sikorsky) helicopters by individual letters. This AD requires, before further flight, identifying and removing any main rotor blade (blade) that has been damaged by lightning and any blade with an unclear service history. This AD is prompted by the failure of a blade due to lightning strike damage. The actions specified by this AD are intended to prevent failure of a blade and subsequent loss of control of the helicopter.
AD 2002-20-02 · published Oct 3, 2002, effective Nov 7, 2002
Bell Helicopter Textron, A Division of Textron Canada Model 222, 222B, 222U, 230, and 430 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron, A Division of Textron Canada (BHTC), model helicopters that requires removing sealant from the forward tooling hole in the right-hand upper fuel enclosure area. This amendment is prompted by the determination that fuel or water could accumulate in the right-hand upper fuel enclosure. The actions specified by this AD are intended to prevent accumulation of fuel in the right-hand upper fuel enclosure area, a fire, and a subsequent forced landing.
AD 2002-21-04 · published Oct 16, 2002, effective Oct 31, 2002
Agusta S.p.A. Model A119 Helicopters
This amendment supersedes an existing emergency airworthiness directive (EAD) for Agusta S.p.A. (Agusta) Model A119 helicopters. EAD 2002-17-52, which was issued on August 21, 2002, was sent to all known U.S. owners and operators of Agusta Model A119 helicopters by individual letters. That AD currently requires installing a placard in the helicopter and marking the airspeed indication at 132 knots indicated airspeed (KIAS) before further flight; visually checking the tail rotor blades on both sides for a crack before each start of the helicopter engine; visually inspecting the tail rotor blades with a 5x or higher magnifying glass and conducting a dye-penetrant inspection if you are unable to determine by the visual inspection whether or not there is a crack; replacing any cracked tail rotor blade; modifying the tail rotor hub and blade assembly, reidentifying the modified tail rotor hub and grips assembly and the modified tail rotor hub and blade assembly, which is a terminating action for the never-exceed speed (Vne) reduction; and establishing a retirement life for the tail rotor control rod. This amendment requires the same actions as that EAD, but corrects the airspeed indication marking, which should have been stated as 122 KIAS instead of 132 KIAS. This amendment is prompted by the failure of a tail rotor blade due to a fatigue crack. The actions specified by this AD are intended to prevent failure of the tail rotor blade and subsequent loss of control of the helicopter.
AD 2002-21-07 · published Oct 21, 2002, effective Nov 25, 2002
Sikorsky Aircraft Corporation Model S-76A, S-76B and S-76C Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) model helicopters that requires removing and inspecting each main rotor spindle attachment bolt (bolt) to ensure that the correct bolts are installed. This amendment is prompted by the discovery of improper bolts installed on a helicopter during its production. The actions specified by this AD are intended to detect installation of incorrect bolts, which could result in reduced hub or bolt fatigue life, separation of the main rotor blade at the spindle attachment, and subsequent loss of control of the helicopter.
AD 2002-21-12 · published Oct 22, 2002, effective Nov 26, 2002
Agusta S.p.A. Model A109E Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Agusta S.p.A. (Agusta) helicopters that requires establishing or reducing the life limits of various parts listed in the airworthiness limitations section (ALS) of the maintenance manual. This amendment is prompted by the results of fatigue tests and analysis to determine life limits for various parts. The actions specified by this AD are intended to establish or reduce the life limits to prevent failure of specified parts and subsequent loss of control of the helicopter.
AD 2002-20-51 · published Oct 1, 2002
Textron Lycoming, AVCO Corporation, Lycoming Engines Engines
AD 2002-21-15 · published Oct 22, 2002, effective Nov 26, 2002
Honeywell International Inc. TPE331 Series Turboprop and TSE331-3U Series Turboshaft Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Engine Division, Garrett Turbine Engine Company, and AiResearch Manufacturing Company of Arizona) TPE331 series turboprop and TSE331-3U series turboshaft engines. This amendment requires replacing second stage turbine stator assemblies, part numbers (P/N's) 894528-1, -2, -3, -5, -6, -10, and -11, with serviceable turbine stator assemblies. This amendment is prompted by reports of six uncontained separations of the second stage turbine wheels associated with obstructed internal cooling holes or passage in the vanes of the second stage turbine stator which may result in contact and rub into the turbine rotor. The actions specified by this AD are intended to prevent uncontained turbine rotor separation and damage to the aircraft.
AD 2002-21-16 · published Oct 23, 2002, effective Oct 28, 2002
Bombardier-Rotax GmbH Type 912 F, 912 S and 914 F Series Reciprocating Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Bombardier-Rotax GmbH Type 912 F, 912 S and 914 F series reciprocating engines. This action requires venting of the lubrication system and inspection of the valve train on all engines. This action also requires venting of the lubrication system of all engines on which the lubrication system has been opened, and any engine on which the propeller has been rotated one full turn in the reverse direction. This amendment is prompted by reports of several in-flight engine failures, all of which resulted in forced landings. The actions specified in this AD are intended to prevent damage to the engine valve train due to inadequate venting of the lubrication system which can result in an in-flight engine failure and forced landing.
AD 2002-21-10 · published Oct 25, 2002, effective Nov 12, 2002
Pratt and Whitney PW4000 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD) that is applicable to Pratt and Whitney (PW) model 4000 series turbofan engines. That action required PW4000 engines with potentially reduced stability margin to be limited to no more than one engine on each airplane, and required removing engines that exceed high pressure compressor (HPC) cycles-since-overhaul (CSO) or cycles-since-new (CSN) from service based on the engine's configuration and category. That action also required establishing a minimum build standard for engines that are returned to service, and performing cool-engine fuel spike testing (Testing-21) on engines to be returned to service after having exceeded HPC cyclic limits or after shop maintenance. This amendment establishes requirements similar to those in the existing AD being superseded, and introduces a rules-based criterion to determine the engine category classification for engines installed on Airbus A300 airplanes. This amendment also adds requirements to manage the engine configurations installed on Boeing 747 airplanes, and requires that repetitive Testing-21 be performed on certain configuration engines. This amendment also establishes criteria that requires Testing-21 on certain engines with Phase 0 or Phase 1, FB2T, or FB2B fan blade configurations. In addition, this amendment re- establishes high pressure compressor (HPC)-to-high pressure-turbine (HPT) cycles-since-overhaul (CSO) cyclic mismatch criteria, and adds criteria to address engine installation changes, engine transfers, and thrust rating changes. Also, this amendment establishes criteria to allow engine stagger without performing Testing-21 for engines which are over their respective limits. This amendment also introduces new requirements on the Phase 3, first run subpopulation engines which were identified after the issuance of NPRM Docket No. 2000-NE-47-AD. The Phase 3, first run subpopulation engines have a significant increase in surge rate and Testing-21 failure rate than the rest of the PW4000 fleet. In order to manage the subpopulation engines to preclude a dual-engine surge, immediate action is required. This immediately adopted rule includes the requirements proposed in the NPRM as well as the required actions for the Phase 3, first run subpopulation engines. This amendment is prompted by investigation and evaluation of PW4000 series turbofan engines surge data, and continuing reports of surges in the PW4000 fleet. The actions specified in this AD are intended to prevent engine takeoff power losses due to HPC surge.
AD 2002-21-17 · published Oct 25, 2002, effective Nov 29, 2002
Pratt & Whitney JT8D-200 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Pratt & Whitney (PW) JT8D-200 series turbofan engines. This amendment requires the installation of stops on the fan exit guide vane case. This amendment is prompted by reports of the flange between the fan duct case and the fan exit guide vane case separating due to a fan blade fracture event. The actions specified by this AD are intended to prevent the flange between the fan duct case and the fan exit guide vane case from separating due to a fan blade failure. Separations of that flange could result in damage to the airplane.
AD 2002-20-05 · published Oct 3, 2002, effective Nov 7, 2002
Breeze Eastern Aerospace Rescue Hoists
This amendment adopts a new airworthiness directive (AD), that is applicable to certain Breeze Eastern Aerospace rescue hoists. This amendment requires a one-time inspection of the mounting brackets for cracks, and, if necessary, replacement with serviceable parts. This amendment is prompted by reports of cracked mounting brackets. The actions specified by this AD are intended to prevent mounting bracket cracks, which could result in mounting bracket failure and separation of the rescue hoist from the helicopter.
AD 2002-20-09 · published Oct 16, 2002, effective Nov 12, 2002
Rockwell Collins, Inc. AFD-3010 Adaptive Flight Display Units
This amendment adopts a new airworthiness directive (AD) that applies to certain Rockwell Collins, Inc. (Rockwell Collins) AFD-3010 adaptive flight display units that are installed on aircraft. This AD requires you to inspect the AFD-3010 unit to determine if it contains an MFP386 Application Specific Integrated Circuit (ASIC) device with a date code of 0128. This AD also requires you to have any AFD-3010 units with an MFP386 device with a date code of 0128 modified. This AD is the result of reports of a manufacturing defect. The actions specified by this AD are intended to prevent premature failure of the ASIC, which could result in the AFD-3010 unit displaying erroneous primary flight and engine parameter information. Such failure could lead to the pilot using incorrect information when making critical flight safety decisions.
AD 2002-21-01 · published Oct 23, 2002, effective Nov 27, 2002
Britax Sell GmbH & Co. OHG Water Boilers, Coffee Makers, and Beverage Makers
This amendment supersedes an existing airworthiness directive (AD), that is applicable to Britax Sell GmbH & Co. OHG water boilers, coffee makers, and beverage makers. That AD currently requires inspecting the wiring for indications of overheating or electrical arcing, and if indications are found, replacing the wiring. This amendment requires replacing the wiring on those water boilers, coffee makers, and beverage makers whether or not they show indications of overheating or electrical arcing. This amendment is prompted by revisions to the manufacturer's service bulletin that were not incorporated in the proposed rule. The actions specified by this AD are intended to prevent a fire in the galley compartment due to inadequate crimping of the electrical terminal contact pins, which could result in smoke in the cockpit and cabin and loss of control of the airplane.
