22 Airworthiness Directives: 12 airplane, 5 rotorcraft, 5 engine.
AD 94-09-11 R1 · published Sep 3, 2002, effective Sep 3, 2002
Raytheon Model BAe.125 Series 1000A Airplanes and Model Hawker 1000 Airplanes
This amendment rescinds an existing airworthiness directive (AD), applicable to certain Raytheon Model BAe.125 Series 1000A Airplanes and Model Hawker 1000 airplanes. That AD currently requires inspections of the thrust reverser system for integrity, and correction of any discrepancy found. The requirements of that AD were intended to prevent a significant reduction in the controllability of the airplane due to an in-flight deployment of a thrust reverser. Since the issuance of that AD, the FAA has issued a separate AD that requires the accomplishment of modifications that terminate the requirements of the existing AD.
AD 2002-18-01 · published Sep 5, 2002, effective Oct 10, 2002
Airbus Model A320 and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 and A321 series airplanes, that requires an inspection to detect trapped water in the elevator sandwich structure, reprotection of the elevator, and corrective actions if necessary. This action is necessary to prevent damage caused by water ingress into the elevator, which could lead to debonding of the elevator skins and degradation of the initial protection, and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-18-02 · published Sep 5, 2002, effective Oct 10, 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, that requires a one-time inspection to determine whether the lower bearing support of the aileron transfer mechanism directly below the first officer's control column has a "pocket," and follow-on corrective actions, if necessary. The actions specified by this AD are intended to prevent jamming of the first officer's control wheel due to the presence of a foreign object on the lower bearing support of the transfer mechanism, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-18-04 · published Sep 11, 2002, effective Oct 16, 2002
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SP, and 747SR Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SP, and 747SR series airplanes, that requires one-time inspections for cracking in certain upper deck floor beams and follow-on actions. The actions specified by this AD are intended to find and fix cracking in certain upper deck floor beams. Such cracking could extend and sever floor beams adjacent to the body frame and result in rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-19-01 · published Sep 20, 2002, effective Oct 29, 2002
SOCATA-Groupe AEROSPATIALE Model TBM 700 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all SOCATA--Groupe AEROSPATIALE (Socata) Model TBM 700 airplanes. This AD requires you to perform a test on the flight control system and adjust the control roll stop if jamming occurs during the test. 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 the flight control wheels from traveling beyond normal roll control limits, which could result in the control wheel becoming jammed. Such a condition could lead to reduced or loss of control of the airplane.
AD 2002-19-04 · published Sep 24, 2002, effective Oct 4, 2002
Raytheon Aircraft Company Model 390 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 390 airplanes. This AD requires you to replace the inboard fuel probe mounting brackets with ones of improved design. This AD is the result of reports of a design problem with the fuel probe assembly brackets. The actions specified by this AD are intended to correct the required air gap clearance between the fuel probe and the adjacent wing fuel tank access panel, which could result in arcing between the two conductive materials in the event of a lightning strike. This could serve as an ignition source inside the fuel tank and result in fire or explosion.
AD 2002-19-07 · published Sep 25, 2002, effective Oct 10, 2002
Bombardier Model CL-600-2B19 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Bombardier Model CL-600-2B19 series airplanes. This action requires revising the Canadair Regional Jet Airplane Flight Manual to provide the flightcrew with operating limitations and procedures to enable them to maintain controllability of the airplane in the event that aileron control stiffness is encountered during flight. This action is necessary to prevent aileron control stiffness during flight, which could result in the reduction or possible loss of controllability of the airplane.
AD 2002-19-08 · published Sep 25, 2002, effective Nov 8, 2002
Vulcanair S.p.A. P 68 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Vulcanair S.p.A. (Vulcanair) P 68 series airplanes. This AD requires you to inspect the flight and engine control systems to ensure that there is correct connecting bolt and linkage installation, no interference, and correct installation of certain components. This AD also requires you to make any necessary adjustments and modify and install the split link and full travel limit assembly. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent failure of the primary flight control system caused by certain configurations. Such failure could lead to loss of airplane flight control.
AD 2002-19-13 · published Sep 26, 2002, effective Oct 1, 2002
Certain Airplanes Originally Manufactured by Lockheed
This amendment adopts a new airworthiness directive (AD) that is applicable to certain airplanes originally manufactured by Lockheed for the military as the P2V. This action requires, among other actions, repetitive dye penetrant and detailed inspections to detect cracks in certain areas located on the left- and right-side lower wing surface between the fuselage and inboard engine nacelle; repetitive detailed inspections of adjacent areas; and repair, if necessary. This action also requires operators to submit a report of the initial inspection findings. This action is necessary to detect and correct stress-related cracking on the left- and right-side lower wing surface between the fuselage and inboard engine nacelle, which could result in structural failure of the wings and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-19-14 · published Sep 26, 2002, effective Sep 26, 2002
Lockheed C-130A Airplanes, Type Certificated in the Restricted Category
This amendment adopts a new airworthiness directive (AD) that is applicable to all Lockheed C-130A airplanes, type certificated in the restricted category. This action requires repetitive inspections to detect cracks at fastener holes in the left- and right-side lower skin panels and stringers of the center wing between wing stations 41.0 and 71.0; and replacement of any cracked part with a new part, or repair and inspections at new intervals. This action is necessary to detect and correct fatigue cracking in the left- and right-side lower skin panels and stringers of the center wing, which could result in structural failure of the wings and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-19-52 · published Sep 30, 2002, effective Sep 30, 2002
Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes; Model 747 Series Airplanes; and Model 757 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-600, -700, -700C, -800, and - 900 series airplanes; Model 747 series airplanes; and Model 757 series airplanes, that currently requires revision of the FAA-approved airplane flight manual (AFM) to advise the flight crew of certain operating restrictions for maintaining minimum fuel levels; prohibits use of the horizontal stabilizer tank on certain airplanes, and prohibits the installation of certain fuel pumps. This amendment requires concurrent removal of the currently required AFM revisions and insertion of new AFM revisions; requires installation of placards to alert the flightcrew to the operating restrictions; and prohibits installation of any uninspected pumps. This amendment permits the AFM revision and placard to be removed under certain conditions. The actions specified in this AD are intended to prevent fuel vapors from coming into contact with an ignition source in the center wing fuel tank, horizontal stabilizer fuel tank, center auxiliary fuel tank (body tank), or auxiliary fuel tanks 1 and 4, which could result in fire/ explosion.
AD 2002-17-03 · published Sep 5, 2002, effective Sep 20, 2002
Bell Helicopter Textron, a Division of Textron Canada, Model 407 Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron, A Division of Textron Canada (BHT), Model 407 helicopters. This action requires a fuel filler cap assembly shimming and electrical bonding procedure. This amendment is prompted by the FAA's determination, based on information from the manufacturer, that electrical bonding may be inadequate. The actions specified in this AD are intended to prevent a lack of electrical bonding that could result in an electrical arc, ignition of fuel vapors, and an onboard fire.
AD 2002-18-05 · published Sep 16, 2002, effective Oct 21, 2002
Eurocopter France Model SA330F, SA330G, SA330J, AS332C, AS332L, and AS332L1 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires inspecting each tail rotor blade de-icing rotating collector (collector) for radial play and rotation torque at specified intervals. If the play or torque exceeds the specified standard, this AD requires replacing the collector with an airworthy part. This amendment is prompted by excessive play measured on the collector of an ECF Model AS332 helicopter. The actions specified by this AD are intended to prevent wear of a collector bearing, loss of tail rotor effectiveness, and subsequent loss of control of the helicopter.
AD 2002-18-06 · published Sep 16, 2002, effective Oct 21, 2002
Eurocopter France Model AS332C, L, L1, and Model SA330F, G, and J Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter France (ECF) Model AS332C, L, and L1 and Model SA330F, G, and J helicopters, that currently requires an inspection to determine the angular play of the tail rotor gearbox (gearbox) at specified intervals. This amendment changes the measurement limits and the load to be applied to a tail rotor blade (blade) when determining the angular play. This amendment is prompted by a review of design data and a determination that the amount of play can be increased with an increase in the amount of applied load during the inspection. The actions specified by this AD are intended to detect excessive angular play and to prevent failure of a gearbox, loss of tail rotor drive, and subsequent loss of control of the helicopter.
AD 2002-19-06 · published Sep 24, 2002, effective Oct 9, 2002
Eurocopter France Model EC 155B Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B helicopters with certain SMD45H multi-functional displays. This action requires replacing the "AC" SMD45H multi-functional display interconnection board (interconnection board) of the affected displays with a "BC" interconnection board. This amendment is prompted by an incident of smoke in a cockpit caused by overheating of the interconnection board. The actions specified in this AD are intended to prevent an electrical discontinuity in the grounding plane inside the SMD45H multi-functional display, which can result in overheating of the interconnection board, smoke in the cockpit, and subsequent loss of control of the helicopter.
AD 2002-19-05 · published Sep 25, 2002, effective Oct 30, 2002
Bell Helicopter Textron, Inc. Model 212 Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 212 helicopters that currently requires, at specified intervals, inspecting for a cracked tail boom and replacing any cracked tail boom. That AD also requires modifying the tail fin and tail boom within 100 hours time-in- service (TIS). This amendment requires modifying and visually inspecting certain vertical fin left-hand spar caps for cracking, loose fasteners, corrosion, or disbonding. If corrosion or loose fasteners are found, this AD requires repairing the vertical fin left-hand spar cap (spar cap) and if a crack or disbonding is found, replacing any cracked or disbonded part with an airworthy part. This AD also requires replacing certain spar caps within 24 months. This AD is prompted by an accident and four failures of the spar cap involving helicopters of similar type design. The actions specified by this AD are intended to prevent failure of a vertical fin spar, loss of a tail rotor, and subsequent loss of control of the helicopter.
AD 97-09-02 R1 · published Sep 9, 2002, effective Sep 24, 2002
CFM International, S.A. Engines
This amendment revises an existing airworthiness directive (AD) that is applicable to CFM International (CFMI) CFM56-5C series turbofan engines. This action establishes new life limits for certain low pressure turbine rotor (LPTR) stage 3 disks and all high pressure turbine rotor (HPTR) disks listed in the existing AD. This amendment is prompted by the results of an extensive life management program performed by the manufacturer. The actions specified in this AD are intended to prevent low-cycle-fatigue (LCF) failure of certain HPTR front shafts, HPTR front air seals, HPTR disks, booster spools, and LPTR stage 3 disks, which could result in an uncontained engine failure and damage to the airplane.
AD 2002-18-03 · published Sep 11, 2002, effective Oct 16, 2002
Rolls-Royce plc Models Spey 506-14A, 555-15, 555-15H, 555-15N, and 555-15P Turbojet Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce plc (RR) Spey 506-14A, 555-15, 555-15H, 555-15N, and 555-15P turbojet engines. This amendment requires replacing certain stage 2 low pressure turbine (LPT) blades with new redesigned stage 2 LPT blades. This amendment is prompted by several reports of failures of stage 2 LPT blades. The actions specified by this AD are intended to prevent failure of the stage 2 LPT blades, which could result in an engine shutdown.
AD 2002-19-02 · published Sep 18, 2002, effective Oct 3, 2002
Turbomeca S.A. Makila Models 1A, 1A1, and 1A2 Turboshaft Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Turbomeca S.A. Makila Models 1A, 1A1, and 1A2 turboshaft engines with exhaust pipes incorporating modification TU 200A installed. This action requires visual inspections of exhaust pipes for cracks and tears, upon completion of the last flight of each day, and replacement of cracked and torn exhaust pipes before further flight. This action also requires removal from service of modification TU 200A exhaust pipes at the next shop visit or no later than a certain date. This amendment is prompted by several reports of modification TU 200A exhaust pipes cracking at several of the ejector attachment tabs. The actions specified in this AD are intended to prevent the ejector from becoming loose from the exhaust pipe, resulting in damage to the main rotor and tail rotor and loss of helicopter control.
AD 2002-19-03 · published Sep 20, 2002, effective Sep 20, 2002
Textron Lycoming IO-540, LTIO-540 and TIO-540 Series Reciprocating Engines
This amendment supersedes emergency airworthiness directive (AD) 2002-17-53 that was sent previously to all known U.S. owners and operators of Textron Lycoming LTIO-540 and TIO-540 series engines, rated at 300 horsepower (HP) or higher. That action requires, before further flight, replacing certain serial-numbered crankshafts that were hammer forged with crankshafts that were press forged. That AD was prompted by reports of crankshaft failures in LTIO-540 and TIO-540 engines, rated at 300 HP or higher. This amendment expands the suspect population of engines to include engines with crankshafts that were manufactured between March 1997 and the present and all IO-540 engines with crankshafts that were manufactured between March 1997 and the present that have been modified by supplemental type certificate (STC) by installing a turbocharger system. The actions specified by this AD are intended to prevent failure of the crankshaft, which could result in total engine power loss, in-flight engine failure and possible forced landing.
AD 2002-19-09 · published Sep 25, 2002, effective Oct 10, 2002
Bombardier-Rotax GmbH 912 F and 912 S Series Reciprocating Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to all Bombardier-Rotax GmbH 912 F series and 912 S series reciprocating engines with fuel pump assembly part number (P/N) 996.596 installed. This action requires initial and repetitive visual inspections and tests of the fuel pump assembly for fuel leakage. This amendment is prompted by two reports of fuel pump assembly fuel leaks. The actions specified in this AD are intended to prevent in-flight fuel leaks of the fuel pump assembly, which could result in an engine fire.
