46 Airworthiness Directives: 26 airplane, 6 rotorcraft, 10 engine, 1 propeller, 2 glider, 1 balloon.
AD 2002-15-06 · published Aug 1, 2002, effective Sep 13, 2002
Air Tractor, Inc. Models 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-802 and AT-802A airplanes. This AD requires you to replace the rudder control cables and fairleads with parts of improved design. This AD is the result of a report that a rudder control cable broke because of wear at the aft fairlead. The actions specified by this AD are intended to prevent the rudder control cable from breaking because of the rudder control cables wearing in the fairlead area. Broken rudder control cables could result in loss of rudder control.
AD 2002-16-01 · published Aug 7, 2002, effective Aug 22, 2002
McDonnell Douglas Model DC-8-21, -31, -32, -33, -41, -42, and -43 Airplanes; and Model DC-8-50, -60, and -70 Series Airplanes; Modified per Supplemental Type Certificates SA1063SO, SA1862SO, or SA1832SO
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-8-21, -31, -32, - 33, -41, -42, and -43 airplanes; and certain Model DC-8-50, -60, and - 70 series airplanes; that have been converted from a passenger-to a cargo-carrying ("freighter") configuration. This action requires gaining access to the floor beam attachments to the lower door jamb within the main cargo door area; performing repetitive inspections to detect cracking or damage of such attachments, including splice plates, angles, and clips; and, if necessary, expanding the inspection area and replacing any cracked or damaged part with a new part. This action is necessary to prevent failure of such floor beam attachments during ground or flight operations, which could cause damage to the floor structure and consequent jamming of the flight control cables, and result in loss of controllability of the airplane in flight.
AD 2002-06-09 · published Aug 8, 2002, effective Apr 8, 2002
Airbus Model A300; A300 B4-600, B4-600R, and F4-600R (Collectively Called A300-600); and A310 Series Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to all Airbus Model A300; A300-600; and A310 series airplanes. That AD currently requires certain inspections of the airplane (including the vertical stabilizer, horizontal stabilizer, pylons, wing, and fuselage areas) following an in-flight incident resulting in extreme lateral loading. This document clarifies and corrects the information contact in the reporting requirement specified in paragraphs (b)(2) and (c)(2) of that AD. This correction is necessary to ensure that future reports are submitted to a specific point of contact.
AD 2002-16-02 · published Aug 12, 2002, effective Aug 27, 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 Airworthiness Limitations section of the maintenance requirements manual to incorporate life limits for certain horizontal stabilizer trim actuators (HSTAs), and replacing the HSTAs with new or serviceable HSTAs. This action is necessary to prevent failure of key components of the HSTAs, which could result in loss of horizontal trim control and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-16-03 · published Aug 12, 2002, effective Aug 27, 2002
Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes
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 determining exposure to runway deicing fluids containing potassium formate, and, for certain airplanes, repetitive inspections of certain electrical connectors in the wheel well of the main landing gear for corrosion, and follow-on actions. This action is necessary to prevent such corrosion, which could result in incorrect functioning of critical airplane systems essential to safe flight and landing of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-16-04 · published Aug 12, 2002, effective Sep 13, 2002
Univair Aircraft Corporation Models (ERCO) 415-C, (ERCO) 415-CD, (ERCO) 415-D, (ERCO) 415-E, (ERCO) 415-G, (Forney) F-1, and (Forney) F-1A Airplanes
This amendment supersedes two different airworthiness directives that require you to inspect the fuel line nipple for damage, replace any suspect part, and replace the elbow fitting on certain Univair Aircraft Corporation (Univair) Models (ERCO) 415-C, (ERCO) 415- CD, (ERCO) 415-D, (ERCO) 415-E, (ERCO) 415-G, (Forney) F-1, and (Forney) F-1A airplanes. This AD requires you to accomplish the following on airplanes with the gascolator connected to the side of the carburetor: Replace any aluminum fuel line nipple or elbow fitting with a brass or steel fuel line nipple or elbow fitting, inspect for double support tubes on the gascolator, install these tubes if they do not exist, and inspect the fuel line fittings between the carburetor and gascolator for cracks or misalignment and replace as necessary. This AD will not affect those airplanes with the gascolator mounted on the firewall. This AD is a result of cracks in the subject area on airplanes in compliance with the current ADs. The actions specified by this AD are intended to prevent failure of the fuel line fittings or the gascolator because of the current airplane design configuration (aluminum fuel line nipples, aluminum fuel line elbows, and/or no double support tubes on the gascolator). Such failure could result in a lack of fuel to the engine with consequent loss of control of the airplane.
AD 2002-16-05 · published Aug 12, 2002, effective Aug 27, 2002
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action 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 action is necessary 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 2002-16-06 · published Aug 12, 2002, effective Aug 27, 2002
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and -145 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires determining whether a defective auxiliary power unit (APU) exhaust silencer is installed on the airplane; and corrective actions, if necessary. This action is necessary to prevent separation of the aft baffle assembly from the APU exhaust silencer and consequent separation of the assembly from the airplane, which could cause damage to other airplanes during takeoff and landing operations, or injury to people on the ground. This action is intended to address the identified unsafe condition.
AD 2002-16-14 · published Aug 14, 2002, effective Sep 18, 2002
Bombardier Model CL-600-2B19 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 series airplanes. This AD requires inspection of certain installed electrical relays to determine whether they have certain manufacturing date codes, and replacement of the electrical relays with those date codes with new relays with different manufacturing date codes. This action is necessary to prevent the failure of an electrical relay due to a defective moving blade assembly, which could result in the inability to generate electrical power from the emergency system, if needed. This action is intended to address the identified unsafe condition.
AD 2002-16-19 · published Aug 15, 2002, effective Sep 19, 2002
Boeing Model 727 Series Airplanes Modified in Accordance With Supplemental Type Certificate SA1767SO or SA1768SO
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes that have been converted from a passenger- to a cargo-carrying ("freighter") configuration, that requires, among other actions, installation of a fail-safe hinge, redesigned main deck cargo door warning and power control systems, and 9g crash barrier. This amendment is prompted by the FAA's determination that the main deck cargo door hinge is not fail-safe; that certain main deck cargo door control systems do not provide an adequate level of safety; and that the main deck cargo barrier is not structurally adequate during an emergency landing. The actions specified by this AD are intended to prevent structural failure of the main deck cargo door hinge or failure of the cargo door system, which could result in the loss or opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane, including possible loss of flight control or severe structural damage; and to prevent failure of the main deck cargo barrier during an emergency landing, which could injure occupants.
AD 2002-16-20 · published Aug 15, 2002, effective Sep 19, 2002
Boeing Model 727 Series Airplanes Modified in Accordance With Supplemental Type Certificate SA1368SO, SA1797SO, or SA1798SO
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes that have been converted from a passenger- to a cargo-carrying ("freighter") configuration, that requires require, among other actions, installation of a fail-safe hinge, redesigned main deck cargo door warning and power control systems, and 9g cargo barrier. This amendment is prompted by the FAA's determination that the main deck cargo door hinge is not fail-safe; that certain main deck cargo door control systems do not provide an adequate level of safety; and that the main deck cargo barrier is not structurally adequate during an emergency landing. The actions specified by this AD are intended to prevent structural failure of the main deck cargo door hinge or failure of the cargo door system, which could result in the loss or opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane, including possible loss of flight control or severe structural damage; and to prevent failure of the main deck cargo barrier during an emergency landing, which could injure occupants.
AD 2002-16-21 · published Aug 15, 2002, effective Sep 19, 2002
Boeing Model 727 Series Airplanes Modified in Accordance with Supplemental Type Certificate ST00015AT
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes that have been converted from a passenger- to a cargo-carrying ("freighter") configuration, that requires, among other actions, installation of a fail-safe hinge, redesigned main deck cargo door warning and power control systems, and 9g crash barrier. This amendment is prompted by the FAA's determination that the main deck cargo door hinge is not fail-safe; that certain main deck cargo door control systems do not provide an adequate level of safety; and that the main deck cargo barrier is not structurally adequate during an emergency landing. The actions specified by this AD are intended to prevent structural failure of the main deck cargo door hinge or failure of the cargo door system, which could result in the loss or opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane, including possible loss of flight control or severe structural damage; and to prevent failure of the main deck cargo barrier during an emergency landing, which could injure occupants.
AD 2002-16-22 · published Aug 15, 2002, effective Sep 19, 2002
Boeing Model 727 Series Airplanes Modified in Accordance With Supplemental Type Certificate SA1444SO, SA1509SO, SA1543SO, or SA1896SO
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes that have been converted from a passenger-to a cargo-carrying ("freighter") configuration, that requires, among other actions, installation of a fail-safe hinge, redesigned main deck cargo door warning and power control systems, and 9g crash barrier. This amendment is prompted by the FAA's determination that the main deck cargo door hinge is not fail-safe; that certain main deck cargo door control systems do not provide an adequate level of safety; and that the main deck cargo barrier is not structurally adequate during an emergency landing. The actions specified by this AD are intended to prevent structural failure of the main deck cargo door hinge or failure of the cargo door system, which could result in the loss or opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane, including possible loss of flight control or severe structural damage; and to prevent failure of the main deck cargo barrier during an emergency landing, which could injure occupants.
AD 2002-16-09 · published Aug 16, 2002, effective Sep 3, 2002
McDonnell Douglas Model 717-200 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model 717-200 airplanes. This action requires repetitive tests to detect failure of the solenoid operated shut-off valve (SOV) of the inboard and outboard spoiler actuator assemblies, and corrective action if necessary. This action is necessary to detect and correct conditions associated with high electrical resistance in the solenoid, which, in combination with the failure of a spoiler actuator, could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-16-11 · published Aug 16, 2002, effective Sep 20, 2002
Boeing Model 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that requires inspection of certain aft axle pivot pins of the main landing gear (MLG) for heat damage and either reworking of damaged pins or replacement of damaged pins with new or serviceable pins. This action is necessary to prevent breakage of the aft axle pivot pin of the MLG, which could overload the center axle, causing the tires to blow out upon landing, and could disengage the aft axle so that it jams the gear in the wheel well, preventing proper extension of the MLG. This action is intended to address the identified unsafe condition.
AD 2002-16-12 · published Aug 16, 2002, effective Sep 20, 2002
Airbus Model A330 and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires revising the Limitations Section of the FAA-approved Airplane Flight Manual to ensure the flightcrew is advised of the proper procedures in the event of uncommanded movement of a spoiler during flight. Such uncommanded movement could result in reduced controllability of the airplane, and consequent significant increased fuel consumption during flight, which could necessitate an in-flight turn-back or diversion to an unscheduled airport destination. This action is intended to address the identified unsafe condition.
AD 2002-16-13 · published Aug 16, 2002, effective Sep 20, 2002
Dornier Model 328-100 and 328-300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and 328-300 series airplanes, that requires replacement of the bolts with new bolts with wirelocking on the Support One of the rudder spring tab. This action is necessary to ensure replacement of improper bolts installed on the rudder spring tab that could back out over time, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-16-23 · published Aug 16, 2002, effective Sep 3, 2002
Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, -700C, -800, and "900 series airplanes. This action requires repetitive tests of the rudder pedal force or repetitive inspections of the rudder feel and centering unit to determine the condition of the inner spring; corrective action if necessary; and eventual replacement of the spring assembly on the rudder feel and centering unit with a new assembly, which would terminate the repetitive requirements. This action is necessary to prevent reduced rudder pedal feel and centering force, which, combined with failure of the outer spring of the spring assembly, could result in pilot-induced oscillation and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-16-16 · published Aug 19, 2002, effective Sep 23, 2002
Dornier Model 328-100 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and -300 series airplanes, that requires inspecting the identification plate on the fire extinguisher bottle of the auxiliary power unit (APU), and replacing the existing actuating cartridge of the fire extinguisher bottle with a correct actuating cartridge, if necessary. This AD also requires removing the fire extinguisher bottle equipped with the actuating cartridge from the APU, and reinstalling the fire extinguisher bottle equipped with the correct actuating cartridge into the APU. The actions specified by this AD are intended to prevent failure of the actuating cartridge on the APU fire extinguisher, which could result in the inability to extinguish an APU fire in-flight, and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2002-16-24 · published Aug 19, 2002, effective Sep 23, 2002
Airbus Model A300 B4-600, B4-600R, and F4-600R (Collectively Called A300-600) Series Airplanes; and Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 and A310 series airplanes, that requires replacement of certain symbol generator units (SGUs) in the electronic flight instrument system with new, improved SGUs, and modification of associated equipment and wiring. This action is necessary to ensure that the flightcrew has adequate flight information by preventing temporary loss of data from the primary flight and navigation displays. Inadequate flight information could result in reduced situational awareness for the flightcrew, which could contribute to loss of control or impact with obstacles or terrain. This action is intended to address the identified unsafe condition.
AD 2002-16-10 · published Aug 22, 2002, effective Sep 26, 2002
Bombardier Model DHC-8-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires various modifications of the airstair (main passenger) door. This action is necessary to prevent failure of the airstair door to open after a landing, which could result in a blocked escape route during an emergency evacuation. This action is intended to address the identified unsafe condition.
AD 2002-16-15 · published Aug 22, 2002, effective Sep 26, 2002
Boeing Model 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that requires modification of the supports for the wire bundles of the fuel quantity indicator system (FQIS), and follow-on actions, if necessary. The actions specified by this AD are intended to prevent chafing of the FQIS wiring on surrounding structures and systems. Such chafing could result in exposure of the bare conductor in close proximity to structures or other electrically conductive return paths, and potential electrical arcing and explosion in the fuel tank in the event of an additional wiring failure outside the fuel tank. This action is intended to address the identified unsafe condition.
AD 2002-17-01 · published Aug 28, 2002, effective Sep 12, 2002
Learjet Model 45 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 45 airplanes. This action requires pulling the FOOT WARM circuit breaker located on the copilot's circuit breaker panel, and installing a collar on that circuit breaker. This action is necessary to prevent an electrical short circuit between the pilot's and copilot's foot warmers and the composite floorboards, which could result in outgassing of the faceply material of the composite floorboards, and consequent smoke in the cockpit. This action is intended to address the identified unsafe condition.
AD 2002-17-05 · published Aug 30, 2002, effective Sep 16, 2002
Boeing Model 727 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 727 series airplanes. This action requires a one-time inspection to find discrepancies of the wire bundles and hydraulic tubing in the aft stairwell area, and corrective action, if necessary. This action is necessary to find and fix such discrepancies, which could result in electrical arcing between the wiring and hydraulic tubing, and consequent fire and damage to adjacent structure. This action is intended to address the identified unsafe condition.
AD 2002-17-06 · published Aug 30, 2002, effective Sep 16, 2002
McDonnell Douglas Model MD-11 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 airplanes, that currently requires repetitive general visual inspections of the power feeder cables, terminal strip, fuseholder, and fuses of the galley load control unit (GLCU) within the No. 3 bay electrical power center to detect damage; and corrective actions, if necessary. That AD also currently requires replacement of the electrical wiring of the galley in the electrical power center in bays 1, 2, and 3 with larger gage cable assemblies, which terminates the repetitive inspections. This amendment removes the replacement requirement and reinstates the repetitive inspections and corrective actions if necessary. This amendment is prompted by information from the airplane manufacturer that accomplishment of the replacement required by the existing AD could result in additional wire chafing damage in the electrical power center (EPC) due to insufficient clearance from structure. The actions specified in this AD are intended to prevent such chafing, and consequent arcing and smoke and fire in the EPC, and to prevent damage to the wire assembly terminal lugs and overheating of the power feeder cables on the No. 3 and No. 4 galley load control unit, which could result in smoke and fire in the center accessory compartment.
AD 2002-13-51 · published Aug 2, 2002, effective Aug 19, 2002
Overseas Aircraft Support Inc, San Joaquin Helicopters, Smith Helicopters, Southwest Florida Aviation International, Arrow Falcon Exporters Inc., AST Inc., Bell Helicopter Textron Inc., International Helicopters Inc., Global Helicopter Technology Inc., Hagglund Helicopters LLC, Richards Heavylift Helo Inc., Robinson Air Crane Inc., Rotorcraft Development Corporation, Sout
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2002-13-51, sent previously to all known U.S. owners and operators of the specified helicopters by individual letters. This AD requires cleaning and inspecting a certain tail rotor (T/R) grip with a magnet to determine if it is made of steel. If it is not made of steel, this AD requires replacing each affected T/R grip with an airworthy, steel T/R grip. This AD is prompted by reports of timed-out T/R grips being improperly remarked and reinstalled on certain helicopters. This unsafe condition, if not detected, could result in failure of the T/R grip and subsequent loss of control of the helicopter.
AD 2002-15-08 · published Aug 2, 2002, effective Sep 6, 2002
Eurocopter France Model EC120B, EC 155B, SA330F, SA330G, SA330J, AS332C, AS332L, AS332L1, AS332L2, AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, AS365N2, AS 365 N3, SA-365N, and SA-365N1 Helicopters
This amendment adopts a new airworthiness directive (AD) for specified Eurocopter France (ECF) model helicopters. This AD requires determining the load release unit (cargo hook) serial number, measuring the clearance between the locking catch and the cargo hook, and removing unairworthy cargo hooks from service. This amendment is prompted by the discovery of a defect on certain cargo hooks that may prevent load release. The actions specified by this AD are intended to prevent failure of a cargo hook to release a load creating an additional hazard in an emergency situation and subsequent loss of control of a helicopter.
AD 2002-08-54 · published Aug 6, 2002, effective Aug 21, 2002
Bell Helicopter Textron Canada Model 222, 222B, 222U, and 230 Helicopters
This document publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (EAD) 2002-08-54, which was sent previously to all known U.S. owners and operators of the specified Bell Helicopter Textron Canada (BHTC) model helicopters by individual letters. This AD requires a visual check of each main rotor grip assembly (grip) and pitch horn at specified intervals and a visual inspection using a 10-power or higher magnifying glass of each affected grip and pitch horn for a crack at specified intervals. If a crack is found, this AD requires replacing each unairworthy grip or pitch horn with an airworthy part before further flight. This AD is prompted by three reports each of a fatigue crack in the grip and pitch horn found during routine inspection of the rotor head. This condition, if not detected, could result in failure of the grip or pitch horn and subsequent loss of control of the helicopter.
AD 2002-15-07 · published Aug 6, 2002, effective Sep 10, 2002
MD Helicopters, Inc., Model MD900 Helicopters
This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc., Model MD900 helicopters that requires, for the lateral-mixer bellcrank assembly (bellcrank), establishing a life limit, creating a component history card or equivalent record, determining the hours time-in-service (TIS), and applying a serial number (S/N). This amendment is prompted by additional testing that revealed that the original load test to establish the life limits of the bellcrank did not accurately represent the actual loading. The actions specified by this AD are intended to prevent fatigue failure of the bellcrank and subsequent loss of lateral control of the helicopter.
AD 2002-09-51 · published Aug 7, 2002, effective Aug 22, 2002
Bell Helicopter Textron, Inc. Model 204B, 205A, A-1, and B Helicopters
This document publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (EAD) 2002-09-51, sent previously to all known U.S. owners and operators of specified Bell Helicopter Textron, Inc. (Bell) model helicopters by individual letters. This AD requires cleaning and inspecting the tail rotor (T/R) grip to determine if the grip is made of steel and replacing any grip not made of steel with an airworthy, steel TR grip. This AD is prompted by reports of a certain timed-out life limited T/R grips being improperly identified and reinstalled on Bell Model 204B, 205A, A-1, and B helicopters. The actions specified by this AD are intended to prevent failure of the T/R grip and subsequent loss of helicopter control.
AD 2002-15-05 · published Aug 1, 2002, effective Aug 16, 2002
Turbomeca Makila 1 A, 1 A1, and 1 A2 Turboshaft Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Turbomeca Makila 1 A, 1 A1, and 1 A2 turboshaft engines. This action requires replacing certain digital electronic control units (DECU's) and electronic control units (ECU's) with modified DECU's and ECU's. This amendment is prompted by a report of an uncontained engine turbine wheel failure and the subsequent loss of control of the helicopter. The actions specified in this AD are intended to prevent an engine overspeed condition resulting from the failure of two or more NTL channels.
AD 2002-15-04 · published Aug 6, 2002, effective Sep 10, 2002
Honeywell International, Inc., (formerly AlliedSignal, Inc. and Textron Lycoming) T5313B, T5317 Series, and T53 Series Turboshaft Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc. and Textron Lycoming) T5313B, T5317 series and former military T53 series, turboshaft engines having certain serial number centrifugal compressor impellers, installed. This amendment requires for T53 series engines, a revised operating cycle count (prorate) for those compressor impellers if installed, and initial and repetitive inspections, with eventual compressor impeller replacement. In addition, this amendment requires the marking of those compressor impellers. This amendment is prompted by a report from the supplier that four centrifugal compressor impellers may have been inadvertently misidentified. The actions specified by this AD are intended to prevent premature failure of the impellers from being operated beyond their design service life, which could result in an uncontained engine failure, in-flight shutdown, or damage to the helicopter.
AD 2002-16-18 · published Aug 14, 2002, effective Sep 18, 2002
CFM International CFM56-5B and -7B Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to CFM International (CFMI) CFM56-5B and -7B series turbofan engines. This amendment requires retirement of stage 2 low pressure turbine (LPT) nozzle segments and stage 3 LPT nozzle segments, listed in Table 1 of this AD, from service before accumulating 25,000 cycles-since-new (CSN) or at the next LPT module shop visit when either stage 2 LPT nozzle segments or stage 3 LPT nozzle segments are exposed, whichever occurs first. This amendment also requires installation of new design (either new or reworked) nozzle segments, that will aid in containment of the LPT rotor in the event of LPT shaft failure. This amendment is prompted by a report of an LPT shaft failure caused by a hydromechanical unit (HMU) malfunction that induced a higher than anticipated LPT rotor overspeed. The actions specified by this AD are intended to aid in containment of the LPT rotor in the event of LPT shaft failure, which could result in uncontained engine failure and damage to the airplane.
AD 2002-16-26 · published Aug 15, 2002, effective Sep 16, 2002
Bombardier-Rotax GmbH Type 912 F and 914 F Series Reciprocating Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain serial numbers (SN's) of Bombardier-Rotax GmbH type 912 F and 914 F series reciprocating engines. This action requires initial and repetitive visual inspections of the engine crankcase for cracks. This amendment is prompted by reports of several instances of engine crankcases found cracked in service. The actions specified in this AD are intended to prevent oil loss caused by cracks in the engine crankcase, which could lead to in-flight failure of the engine and forced landing.
AD 2002-16-07 · published Aug 16, 2002, effective Sep 3, 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 certain serial numbers (SN's) of Bombardier-Rotax GmbH type 912 F, 912 S and 914 F series reciprocating engines. This action requires replacement of the valve spring retainers, part number (P/N) 854.182, with the new-reinforced valve spring retainers, P/N 854.184. This amendment is prompted by reports of several cracked valve spring retainers discovered in-service. The actions specified in this AD are intended to prevent cracking of the valve spring retainers resulting in possible engine failure while in-flight.
AD 2002-16-08 · published Aug 16, 2002, effective Sep 20, 2002
Pratt & Whitney Models JT8D-209, -217, -217A, -217C and -219 Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to Pratt & Whitney (PW) JT8D models -209, - 217, -217A, -217C and -219 turbofan engines. That AD currently requires initial and repetitive fluorescent magnetic particle inspections or fluorescent penetrant inspections of the combustion chamber outer case (CCOC) for cracks, and, if necessary, replacement with serviceable parts. Also that AD requires a one-time material verification of drain and Ps4 bosses, and, if necessary, replacement with serviceable parts. Finally, that AD requires replacement of CCOC's with welded-on bosses with improved, one-piece CCOC's. This amendment requires lower initial inspection thresholds for all CCOC's installed in any JT8D model -209, -217, -217A, -217C or -219 turbofan engine. This amendment is prompted by reports of cracked CCOC's that had accumulated fewer cycles in service than the initial inspection thresholds required by the current AD. Also, a CCOC part number was discovered with incorrect material not identified by serial number in JT8D Alert Service Bulletin (ASB) A6359, Revision 2, dated July 31, 2000. The actions specified by this AD are intended to prevent uncontained failure of the CCOC, which could cause release of debris, damage to the airplane, or fire.
AD 2002-16-25 · published Aug 22, 2002, effective Sep 26, 2002
Turbomeca S.A. Arriel Models 2 S1, 2 B, and 2 C Turboshaft Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Turbomeca S.A. Arriel models 2 S1, 2 B, and 2 C turboshaft engines. This amendment requires initial and repetitive visual inspections for fuel leaks, and replacement of fuel pumps that are found leaking fuel. In addition, this amendment requires that fuel pumps found with pump wall thickness below minimum be removed from service. This amendment is prompted by a manufacturing investigation of pump bodies found to have below minimum material thickness, which could cause fuel leakage through thin, porous walls, reducing fuel pump fire resistance. The actions specified by this AD are intended to prevent fuel leakage, which may cause engine fires that could lead to an in- flight engine shutdown, damage to the helicopter, and forced landing.
AD 2002-18-51 · published Aug 27, 2002
Wytwornia Sprzetu Komunikacyjnego Engines
AD 2002-17-02 · published Aug 28, 2002, effective Feb 24, 2003
Pratt & Whitney JT8D Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to certain Pratt & Whitney JT8D series turbofan engines. That AD currently requires revisions to the Time Limits Section (TLS) of the manufacturer's Engine Manuals (EM's) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment requires modification of 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 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 96-18-14 · published Aug 28, 2002
Hartzell Propeller Inc. HC-A3V, HC-B3M, HC-B3T, HC-B4M, HC-B4T, and HC-B5M Series Propellers
This document contains corrections to the final airworthiness directive (AD), which was published in the Federal Register on September 11, 1996, (61 FR 47809). The regulations related to Hartzell Propeller Inc. HC-A3V, HC-B3M, HC-B3T, HC-B4M, HC-B4T, and HC-B5M series propellers blade inspection and replacement.
AD 2002-16-17 · published Aug 16, 2002, effective Aug 30, 2002
Barry Aviation, LLC Model PZL-Krosno KR-03A “Peregrine” (Puchatek) Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Barry Aviation, LLC Model PZL-Krosno KR-03A "Peregrine" (Puchatek) sailplanes. This AD requires you to inspect to ensure that the correct horizontal stabilizer attachment fittings are installed, install the correct fittings if necessary, and incorporate a "NO LIFT" placard to the vertical stabilizer. This AD is the result of reports of cracks in the horizontal stabilizer attachment fittings on the affected sailplanes. Analysis of these incidents reveals that incorrect fittings were installed. The actions specified by this AD are intended to prevent such cracks in the horizontal stabilizer attachment fittings, which could result in the horizontal stabilizer separating from the sailplane with consequent loss of control of the sailplane.
AD 2002-15-01 R1 · published Aug 30, 2002, effective Sep 3, 2002
Diamond Aircraft Industries GmbH Models HK 36 R “Super Dimona”, HK 36 TC, HK 36 TS, HK 36 TTC, HK 36 TTC-ECO, HK 36 TTC-ECO (Restricted Category), and HK 36 TTS Sailplanes
This amendment clarifies information contained in Airworthiness Directive (AD) 2002-15-01, which currently requires you to inspect the long aileron push rods in both wings for damage and modify the push rods on all Diamond Aircraft Industries GmbH (Diamond) Models H-36 "Dimona", HK 36 R "Super Dimona", HK 36 TC, HK 36 TS, HK 36 TTC, HK 36 TTC-ECO, HK 36 TTC-ECO (Restricted Category), and HK 36 TTS sailplanes. The Model H-36 "Dimona" sailplane has a different flight control system than the rest of the affected sailplanes. This particular flight control system makes it impossible for the Model H-36 "Dimona" sailplanes to be in compliance with AD 2002-15-01. This document deletes these sailplanes from the AD applicability. The actions specified by this AD are intended to detect and correct damage in the long aileron push control rods, which could result in failure of the aileron push rods and decreased control. Such failure could lead to aeroelastic flutter.
AD 2002-17-04 · published Aug 30, 2002, effective Sep 30, 2002
Ballonbau Worner GmbH Model K-630/1-Stu Manned Free Gas Balloons
This amendment adopts a new airworthiness directive (AD) that applies to all Ballonbau Worner GmbH (Ballonbau) Model K-630/1-Stu manned free gas balloons. This AD requires you to replace the PVC tubes that cover the steelwire loops of the basket with an electrostatic conductive braided rope. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent the chance of an electrostatic charge buildup between the steelwire loops of the basket and the balloon envelope, which could result in ignition of combustible lifting gas fumes in the balloon envelope. Such a condition could lead to gas explosion and fire.
