44 Airworthiness Directives: 26 airplane, 5 rotorcraft, 10 engine, 2 propeller, 1 appliance.
AD 2003-11-12 · published Jun 2, 2003, effective Jun 5, 2003
MORAVAN a.s. Model Z-242L Airplanes
This document supersedes Airworthiness Directive (AD) 2003-03- 13, which currently establishes a technical service life for MORAVAN a.s. (Moravan) Model Z-242L airplanes by restricting Acrobatic and Utility category operations and requiring replacement of the wings after a certain operational time. AD 2003-03-13 resulted from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Czech Republic. The restrictions required by AD 2003- 03-13 only take account for the aerobatic load spectrum and do not account for the aerobatic frequency. The restrictions also address the life limit of the wings when they should address the life limit of the entire airframe (life limit of the airplane). Although the aerobatic frequency will extend the operational times, it more importantly will ensure that all airplanes (even those that have not reached the operational limits) are not subject to fatigue cracking caused by exceeding the aerobatic frequency. This AD will maintain the restrictions of AD 2003-03-13, but will incorporate the aerobatic frequency and life limit the airplane instead of just the wings. The actions specified by this AD are intended to prevent structural failure of the wing due to fatigue cracking. Such failure could result in a wing separating from the airplane with consequent loss of airplane control.
AD 2003-11-16 · published Jun 3, 2003, effective Jul 8, 2003
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. For certain airplanes that are subject to the existing AD, this amendment requires a new one- time inspection for gaps, a new one-time torque check for loose bolts, corrective actions if necessary, and eventual replacement of existing titanium bolts with steel bolts. These actions are 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. These actions are intended to address the identified unsafe condition.
AD 2003-11-14 · published Jun 4, 2003, effective Jun 20, 2003
The New Piper Aircraft, Inc. Models PA-34-200T, PA-34-220T, PA-44-180, and PA-44-180T Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) Models PA-34- 200T, PA-34-220T, PA-44-180, and PA-44-180T airplanes that have a model 91E92-1 or model 91E93-1 combustion heater fuel pump installed. This AD requires you to accomplish a one-time inspection of the combustion heater fuel pumps for fuel leakage. If leakage is found, repair or replace the fuel pump. This AD is the result of recent reports of fuel leakage. The actions specified by this AD are intended to correct quality control problems with the heater fuel pump, which could result in failure of the heater fuel pump. Such failure could lead to fire or explosion in the cockpit.
AD 2003-11-15 · published Jun 4, 2003, effective Jul 9, 2003
McDonnell Douglas Model MD-90-30 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-90-30 airplanes, that requires replacing the lanyards on the pressure relief door for the thrust reverser with new, improved lanyards, and doing associated modifications. This action is necessary to ensure that the lanyards on the pressure relief door have adequate strength. Lanyards of inadequate strength could allow the pressure relief door to detach from the thrust reverser in the event that an engine bleed air duct bursts, which could result in the detached door striking and damaging the horizontal stabilizer, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-11-17 · published Jun 6, 2003, effective Jul 28, 2003
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 inspect the front and rear surfaces of the pressure dome for damage and cracks, and, if necessary, accomplish repairs. 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 detect and correct damage and cracks to the pressure dome, which could lead to rapid decompression.
AD 2003-11-20 · published Jun 6, 2003, effective Jul 11, 2003
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, that currently requires repetitive lubrication of the slide shaft of the input plunger of the brake control valve assembly. This amendment adds requirements for modifying the brake control valve assembly, which terminates the repetitive lubrications required by the existing AD. This amendment also adds subsequent repetitive lubrications of the valve utilizing the grease fittings installed during the modification. This amendment is prompted by reports of temporary loss of braking action upon landing. The actions specified by this AD are intended to prevent temporary loss of braking action due to the freezing of moisture on the input plunger of the brake control valve during steep descent.
AD 2003-11-24 · published Jun 6, 2003, effective Jun 23, 2003
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-100 series airplanes. This action requires installation of retainers instead of washers in the upper and lower torsion bars of the rudder tab. This action is necessary to prevent a spring tab torsion bar from slipping through its retaining adapters, which could result in a loose spring tab; the loss of both tension springs could allow the spring tab to flutter and result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-11-19 · published Jun 11, 2003, effective Jul 16, 2003
Boeing Model 727-100 and 727-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727-100 and 727-200 series airplanes, that requires, under certain conditions, replacement of the installed autopilot pitch control computer with a modified computer, testing of the modified system, and revision of the Airplane Flight Manual (AFM). The actions specified by this AD are intended to prevent undesirable and potentially dangerous pitch oscillations during coupled instrument landing system (ILS) approaches. This AD is intended to address the identified unsafe condition.
AD 2003-11-25 · published Jun 11, 2003, effective Jul 16, 2003
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200F, 747-200C, 747-300, 747SR, and 747SP Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing transport category airplanes listed above. This AD requires an initial inspection to identify all H-11 steel bolts on the outer chord of the body station (BS) 2360 aft pressure bulkhead between stringers 12L and 12R, follow-on repetitive inspections to identify all remaining H-11 steel bolts on the entire outer chord of the BS 2360 aft pressure bulkhead, and follow-on and corrective actions if necessary. This AD also requires eventual replacement of all H-11 steel bolts with Inconel bolts. This action is necessary to prevent broken bolts, which could result in progressive failure of the remaining bolts and consequent structural damage, rapid depressurization, and loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-12-01 · published Jun 12, 2003, effective Jul 17, 2003
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 777 series airplanes, that requires either a one-time inspection or a review of the airplane maintenance records for both stabilizer trim control modules (STCM) of the trim system of the horizontal stabilizer to determine if STCMs having certain serial numbers are installed; and follow-on corrective actions, if necessary. This amendment also requires eventual replacement of affected STCMs with new or reworked STCMs, which would terminate the follow-on actions. The actions specified by this AD are intended to prevent an uncommanded stabilizer trim due to simultaneous failure of two static seals on one STCM, combined with failure of the automatic shutdown function of the stabilizer trim system. Such failures could result in loss of pitch control and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-12-02 · published Jun 12, 2003, effective Jul 17, 2003
BAE Systems (Operations) Limited Model ATP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited Model ATP airplanes, that requires installing a baulking device for the pintle pin in the nose landing gear (NLG). This action is necessary to prevent failure of the NLG due to an unlocked pintle pin migrating from its support housings, and consequent jamming or collapse of the NLG. This action is intended to address the identified unsafe condition.
AD 2003-12-03 · published Jun 12, 2003, effective Jul 17, 2003
Israel Aircraft Industries, Ltd., Model 1124 and 1124A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Israel Aircraft Industries, Ltd., Model 1124 and 1124A series airplanes, that requires revising the airplane flight manual to advise the flightcrew to don oxygen masks as a first and immediate step following a cabin altitude alert. This action is necessary to prevent incapacitation of the flightcrew due to lack of oxygen. This action is intended to address the identified unsafe condition.
AD 2003-12-04 · published Jun 12, 2003, effective Jul 17, 2003
Embraer S.A. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and -145 series airplanes, that requires replacing the four Gamah clamp/sleeve joints on an engine bleed air duct with new threaded coupling assemblies. For certain airplanes, this AD also requires replacing the two supports for the engine bleed air duct with two new supports. The actions specified by this AD are intended to prevent hot air leaks from the bleed air duct due to disconnection of the duct joint, which could result in heat damage to components near the duct, and consequent increased risk of fire in the rear baggage compartment. This action is intended to address the identified unsafe condition.
AD 2003-12-06 · published Jun 12, 2003, effective Jun 27, 2003
Bombardier Model CL-600-2C10 (Regional Jet Series 700 & 701) Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 & 701) series airplanes. This action requires a revision to the Airplane Flight Manual (AFM) to prohibit operations into known or forecast icing conditions under certain conditions. This action also requires an inspection to detect damage of the wing anti-ice (WAI) ducts to determine if the external shrouds of the ducts are open or cracked, and replacement of any damaged duct with a new duct or a duct with the same part number. This action also provides for an optional terminating action for the AFM revision and inspection. This action is necessary to prevent the WAI ducts from collapsing, cracking, or rupturing, which could cause leakage of hot air in the under-floor pressurized area of the fuselage when the anti-ice system is turned on. Such leakage of hot air results in insufficient heat for the anti-ice system and consequent aerodynamic degradation. This action is intended to address the identified unsafe condition.
AD 2003-12-09 · published Jun 18, 2003, effective Jul 23, 2003
BAE Systems (Operations) Limited Model BAe 146 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 series airplanes, that requires modification of the flight annunciator box. This action is necessary to prevent traffic collision avoidance system (TCAS) aural messages and resolution advisories of the TCAS from being inhibited following a ground proximity warning system alert or test message, which could prevent the TCAS from providing attention- getting alerts, and could result in the consequent possibility of a mid-air collision or near mid-air collision. This action is intended to address the identified unsafe condition.
AD 2003-12-10 · published Jun 18, 2003, effective Jul 23, 2003
Aerospatiale Model ATR42-200, -300, -320, and -500 Series Airplanes; and Model ATR72-102, -202, -212, and 212A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200, -300, -320, and - 500 series airplanes; and Model ATR72-102, -202, -212, and 212A series airplanes; that requires modification of the flight attendant's seat located in the front of the cabin, and follow-on actions. This action is necessary to prevent release of the forward flight attendant's shoulder restraint harness, which could result in injury to the flight attendant in case of turbulence. This action is intended to address the identified unsafe condition.
AD 2003-12-11 · published Jun 18, 2003, effective Jul 23, 2003
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires a one-time ultrasonic inspection of the maneuvering actuator piston rod of the main landing gear (MLG) to ensure adequate wall thickness of the piston rods, and replacement of any discrepant piston rod with a new piston rod. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the maneuvering actuator piston rod of the MLG, which would impede retraction of the MLG, and consequent reduced controllability of the airplane.
AD 2003-12-12 · published Jun 23, 2003, effective Jul 28, 2003
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires either revising the Airplane Flight Manual (AFM) to require a maximum operating altitude of 25,000 feet; or modifying the flight attendant's seat or reworking the oxygen bottle kit, as applicable, and revising the AFM to require a maximum operating altitude of 30,000 feet. This action is necessary to prevent the unavailability of supplemental oxygen to the flight attendant in the event of cabin decompression, which could result in loss of consciousness of the flight attendant. This action is intended to address the identified unsafe condition.
AD 2003-13-02 · published Jun 23, 2003, effective Jul 8, 2003
Airbus Model A321-131 Series Airplanes; Equipped with International Aero Engines (IAE) V25()()-A5 Series Engines
This amendment adopts a new airworthiness directive (AD), applicable to all Model A321-131 series airplanes, equipped with International Aero Engines (IAE) V25()()-A5 series engines. This action requires revising the Limitations section of the airplane flight manual to incorporate new procedures to follow in the event of an oil filter clog message. This action is necessary to require the flightcrew to follow the procedures necessary to prevent smoke caused by an oil filter clog from entering the cabin during flight. This action is intended to address the identified unsafe condition.
AD 2003-13-01 · published Jun 24, 2003, effective Jul 29, 2003
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires an inspection to detect cracks and fractures of the outboard hinge fitting assemblies on the trailing edge of the inboard main flap, and follow-on and corrective actions if necessary. For certain airplanes, this amendment also requires a one-time inspection to determine if a tool runout procedure has been performed in the area. The actions specified by this AD are intended to prevent the inboard aft flap from separating from the wing and potentially striking the airplane, which could result in damage to the surrounding structure and potential personal injury. This action is intended to address the identified unsafe condition.
AD 2003-13-03 · published Jun 24, 2003, effective Jul 29, 2003
Boeing Model 767-200 and 767-300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and 767-300 series airplanes, that requires modification of the installation of the aft pressure bulkhead-to-floor insulation blankets. The actions specified by this AD are intended to prevent interference with venting during a rapid decompression in the bulk cargo compartment; such interference could cause damage to the floor structure and damage to certain control cables leading to the empennage, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-13-04 · published Jun 24, 2003, effective Aug 15, 2003
Pilatus Aircraft Ltd. Model PC-6 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) Model PC-6 airplanes. This AD requires you to inspect the integral fuel tank wing ribs for cracks and the top and bottom wing skins for distortion, repair any cracks or distortion before further flight, and accomplish a fuel tank ventilating system installation. 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 detect and correct cracks in the ribs of the inboard integral fuel tanks in the left and right wings, which could lead to wing failure during flight.
AD 2003-13-05 · published Jun 24, 2003, effective Aug 11, 2003
Iniziative Industriali Italiane S.p.A. Models Sky Arrow 650 TC and 650 TCN Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Iniziative Industriali Italiane S.p.A. (3I) Models Sky Arrow 650 TC and 650 TCN airplanes. This AD requires you to repetitively inspect the engine mount for cracks and modify or replace the engine mount if cracks are found. 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 detect and correct cracks in the engine mount, which could result in failure of the engine mount. Such failure could lead to separation of the engine from the airplane.
AD 2003-13-06 · published Jun 24, 2003, effective Aug 11, 2003
Iniziative Industriali Italiane S.p.A. Models Sky Arrow 650 TC and 650 TCN Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Iniziative Industriali Italiane S.p.A. (3I) Models Sky Arrow 650 TC and 650 TCN airplanes. This AD requires you to modify the nose gear support bulkhead (STA600). 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 nose gear support bulkhead (STA600). Such failure could lead to loss of control of the airplane during landing or take-off.
AD 2003-13-07 · published Jun 30, 2003, effective Aug 11, 2003
Short Brothers and Harland Ltd. Models SC-7 Series 2 and SC-7 Series 3 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Short Brothers and Harland Ltd. (Shorts) Models SC-7 Series 2 and SC-7 Series 3 airplanes. This AD requires you to repetitively inspect all flight control system rods for corrosion and cracks, replace any cracked rod, and repair corrosion damage or replace any corroded rod depending on the extent of the damage. 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 prevent failure of any flight control system rod caused by cracks or corrosion. Such failure could lead to complete failure of the flight control system with consequent loss of control of the airplane.
AD 2003-13-09 · published Jun 30, 2003, effective Jul 15, 2003
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires repetitive inspections for cracking of the upper skin of the outboard and center sections of the horizontal stabilizer and the rear spar structure, hinge fittings, terminal fittings, and splice plates; and repair if necessary. This action is necessary to find and fix such cracking, which could lead to reduced structural capability of the outboard and center sections of the horizontal stabilizer, and result in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-11-13 · published Jun 3, 2003, effective Jun 18, 2003
Eurocopter France Model AS332C, L, and L1 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters. This action requires replacing a certain elbow adapter (adapter) with an airworthy adapter. This amendment is prompted by reports of a cracked adapter on the hydraulic reservoir resulting in leakage of hydraulic fluid and loss of hydraulic power. This condition, if not corrected, could result in failure of an adapter on the hydraulic reservoir, loss of hydraulic fluid, loss of hydraulic power, and subsequent loss of control of the helicopter.
AD 2003-08-53 · published Jun 5, 2003, effective Jun 20, 2003
Eurocopter France Model SA-365N1, AS365-N2, AS 365 N3, and SA-366G1 Helicopters
This document publishes in the Federal Register an amendment adopting a superseding Airworthiness Directive (AD) 2003-08-53, sent previously to all known U.S. owners and operators of the specified Eurocopter France (Eurocopter) model helicopters by individual letters. This AD requires, in addition to the checks and tapping test inspections required in the existing AD, adding the Eurocopter Model AS 365 N3 to the applicability and correcting tail rotor blade (blade) part numbers. Also, this AD requires doing tapping tests for bonding separation on blades and removing certain blades at specified intervals. The actions specified by this AD are intended to prevent failure of a blade, loss of tail rotor control, and subsequent loss of control of the helicopter.
AD 2003-11-21 · published Jun 11, 2003, effective Jun 26, 2003
Eurocopter France Model AS332 C, L, and L1 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332 C, L, and L1 helicopters. This action requires revising the Rotorcraft Flight Manual (RFM) Limitations section if certain fuel control units are installed. This AD is prompted by the discovery of an anomaly in certain fuel control units that may lead to inadequate fuel flow in single-engine flight. This condition, if not corrected, could result in failure of the engine to develop the maximum 2\1/2\ minute one engine inoperative (OEI) power, reduced helicopter performance, and subsequent loss of control of the helicopter during OEI operation.
AD 2003-12-13 · published Jun 26, 2003, effective Jul 11, 2003
Agusta S.p.A. Model A109K2 Helicopters
This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A (Agusta) Model A109K2 helicopters. This action requires a visual check of each tail rotor blade (blade) for a crack; a visual inspection of each blade for a crack at specified intervals; and if necessary, a dye-penetrant inspection. Replacing any cracked blade with an airworthy blade before further flight is also required. This amendment is prompted by a report of a crack that occurred on an Agusta Model A109K2 blade. The actions specified in this AD are intended to detect fatigue cracks on the blades, which could result in loss of the blades and loss of control of the helicopter.
AD 2003-10-03 R1 · published Jun 4, 2003, effective Jun 20, 2003
Rolls-Royce plc Engines
This amendment revises an existing airworthiness directive (AD) that is applicable to Rolls-Royce plc (RR) model RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 turbofan engines. The existing AD will become effective on June 20, 2003, and requires removal from service of certain high pressure (HP) turbine discs before they reach newly established life limits. This amendment requires the same actions, but removes the model RB211-535E4-37 turbofan engine from the applicability. This revision to the existing AD is prompted by further data gathering by the FAA that demonstrates that the model RB211-535E4- 37 turbofan engine is not affected by machining-induced cracking within the currently published life of the HP turbine disc. The actions specified in this AD are intended to prevent machining-induced cracking of the HP turbine disc which could cause an uncontained HP turbine disc failure and damage to the airplane.
AD 2003-11-23 · published Jun 5, 2003, effective Jun 20, 2003
International Aero Engines AG (IAE) V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, and V2530-A5 Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for certain IAE V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, and V2530-A5 turbofan engines. This AD requires initial and repetitive inspections of the master magnetic chip detector (MCD) or the No. 1, 2, 3 bearing chamber MCD. This AD is prompted by reports of No. 3 bearing failures that resulted in in-flight engine shutdowns (IFSDs) and significant smoke in the cockpit and cabin. The actions specified in this AD are intended to prevent failure of the No. 3 bearing, which could result in IFSDs and smoke in the cockpit and cabin.
AD 2003-11-18 · published Jun 6, 2003, effective Jul 7, 2003
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 AD currently requires interim actions to address engine takeoff power loss events until the high-pressure-compressor (HPC) case is redesigned and available for incorporation on the PW4000 engines. This amendment requires the same actions as that AD, adds on- wing Testing-21 to engines installed on Boeing 747 and MD-11 airplanes, and adds the requirement to install a new Ring Case Configuration (RCC) rear HPC on engines installed in the Boeing fleet as terminating action to the requirements of this AD. This amendment is prompted by the development of an RCC rear HPC for PW4000 series turbofan engines installed in the Boeing fleet. The actions specified by this AD are intended to prevent engine takeoff power losses due to HPC surge.
AD 2003-12-07 · published Jun 13, 2003, effective Jul 18, 2003
Pratt & Whitney JT8D Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines. That AD currently requires a determination of the utilization rate and protective coating type of the 7th, 8th, 9th, 10th, 11th, and 12th stage high pressure compressor (HPC) disks, and removal, inspection for corrosion, and recoating of those HPC disks based on utilization rate. This amendment requires removal and replacement of protective coating of 7th, 8th, 9th, 10th, 11th, and 12th stage HPC disks, initial and repetitive inspections for corrosion pits and cracks, and removal from service as required. This amendment is prompted by operator reports of cracks found on several JT8D steel HPC disks since the existing AD was published. The actions specified by this AD are intended to prevent fracture of the HPC disks, which can result in uncontained release of engine fragments, inflight engine shutdown, and airframe damage.
AD 2003-12-08 · published Jun 18, 2003, effective Jul 23, 2003
General Electric Company CF6-80A1/A3 and CF6-80C2A PMC Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric Company (GE) CF6-80A1/A3 and CF6- 80C2A PMC series turbofan engines. This amendment requires performing either a directional pilot valve (DPV) pressure switch moisture purge procedure and an operational check of the fan reverser or replacing the DPV assembly with a serviceable assembly and performing an operational check of the fan reverser. Thereafter, this AD requires one of these actions on a repetitive basis. This amendment is prompted by a review of fan reverser safety analyses resulting from the discovery of an undetectable failure mode of the DPV pressure switch on certain GE CF6- 80C2A and CF6-80A1/A3 engine models. The actions specified by this AD are intended to prevent inadvertent fan reverser deployment, which, if it occurred in-flight, could result in loss of control of the airplane.
AD 2003-12-14 · published Jun 20, 2003, effective Jul 25, 2003
Turbomeca S.A. Arriel 1 Turboshaft Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Turbomeca S.A. Arriel 1 series turboshaft engines. This amendment requires initial and repetitive visual inspections for ingestive erosion, and cleaning if necessary, of M02 and M03 modules. This amendment is prompted by reports from the manufacturer of an unbalance due to accumulation of dust in the M03 module. The actions specified by this AD are intended to prevent an unbalance of the gas generator rotating assembly which may lead to deterioration of the gas generator rear bearing and uncommanded engine shutdown.
AD 2003-12-15 · published Jun 25, 2003, effective Jul 30, 2003
Rolls-Royce RB211 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce (RR) plc RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines. This amendment requires introducing an alternative technique to ultrasonically inspect installed fan blades on-wing using a surface wave ultrasonic probe. This action also adds the application of Metco 58 blade root coating as an optional terminating action. This amendment is prompted by the discovery of cracks on LPC fan blade roots during an engine overhaul. The actions specified by this AD are intended to detect cracks in LPC fan blade roots, which if not detected, could lead to uncontained multiple fan blade failure, and damage to the airplane.
AD 2003-13-12 · published Jun 27, 2003, effective Aug 1, 2003
Rolls-Royce plc RB211-22B Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc (RR) RB211-22B series turbofan engines with intermediate pressure (IP) compressor stage 6 to 7 rotor shaft assembly part number (P/N) UL37094 installed. This amendment requires removal from service of IP compressor stage 6 to 7 rotor shaft assemblies P/N UL37094 before reaching newly reduced life limits. This amendment is prompted by the discovery of corrosion during inspection and analysis of IP compressor stage 6 to 7 rotor shaft assemblies returned from the field. The actions specified by this AD are intended to prevent corrosion-induced cracking of the IP compressor stage 6 to 7 rotor shaft assembly, resulting in an uncontained engine failure and damage to the airplane.
AD 2003-13-10 · published Jun 30, 2003, effective Jul 15, 2003
Rolls-Royce Corporation (Formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) Models 250-C30R/3, -C30R/3M, -C47B, and -C47M Turboshaft Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) models 250-C30R/3, -C30R/ 3M, -C47B, and -C47M turboshaft engines. This AD requires initial and repetitive electrical signal inspections of the hydromechanical unit (HMU) Power Lever Angle (PLA) potentiometer. This AD is prompted by an investigation by the National Transportation Safety Board (NTSB), which revealed that a potential undetected failure of the PLA potentiometer electrical signal could cause uncommanded and sudden changes in engine power. The actions specified in this AD are intended to prevent uncommanded and sudden changes in engine power.
AD 2003-13-11 · published Jun 30, 2003, effective Jul 15, 2003
Pratt & Whitney PW4074, PW4074D, PW4077, PW4077D, PW4090, and PW4090-3 Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) PW4074, PW4074D, PW4077, PW4077D, PW4090, and PW4090-3 turbofan engines with high pressure compressor (HPC) rear cases, part numbers (P/Ns) 55H425-01, 55H385-01, and 56H396-01 installed. This AD requires initial and repetitive visual or fluorescent penetrant inspections (FPI) of the J flange on the HPC rear case, and removal from service of the rear case based on certain inspection results. This AD is prompted by reports of cracks propagating from bolt holes in the HPC rear case J flange, and reports of high-cycle HPC rear cases exhibiting cracks propagating into the shell wall. The actions specified in this AD are intended to prevent fracturing and rupturing of the HPC rear case, resulting in uncontained engine failure.
AD 2003-12-05 · published Jun 12, 2003, effective Jul 17, 2003
McCauley Propeller Systems 1A103/TCM Series Propellers
This amendment supersedes an existing airworthiness directive (AD), that is applicable to McCauley Propeller Systems 1A103/TCM series propellers. That AD currently requires an initial inspection for cracks in the propeller hub in accordance with a dye penetrant inspection procedure, replacement of propellers with cracks that do not meet acceptable limits, rework of propellers with cracks that meet acceptable limits, and repetitive inspections of all affected propellers. This amendment allows additional rework operations to be performed at more than one bolt hole location. This amendment is prompted by the need to clarify the requirement to use a steel backing plate and Mylar gasket during installation of the propeller, and to relax the replacement requirements. The actions specified in the proposed AD are intended to prevent propeller separation due to hub fatigue cracking, which can result in loss of control of the airplane.
AD 97-18-02 R1 · published Jun 26, 2003, effective Jul 31, 2003
Hartzell Propeller, Inc., TRW Hartzell Propeller Propellers
This amendment revises an existing airworthiness directive (AD), that is applicable to Hartzell Propeller Inc. ( )HC-( )(2,3)(X,V)( )-( ) series and HA-A2V20-1B series propellers with aluminum blades. That AD currently requires initial and repetitive dye penetrant and eddy current inspections of the blade and an optical comparator inspection of the blade retention area, and, if necessary, replacement with serviceable parts. In addition, that AD currently requires initial and repetitive visual and magnetic particle inspection of the blade clamp, dye penetrant inspection of the blade internal bearing bore, and, if necessary, replacement with serviceable parts. Also, for all HC-(1,4,5,8)(2,3)(X,V)( )-( ) steel hub propellers, that AD currently requires an additional initial and repetitive visual and magnetic particle inspection of the hub, and, if necessary, replacement with serviceable parts. This amendment revises that AD by permitting the replacement of affected propellers with Hartzell Propeller Inc. model "MV" series propellers as an optional terminating action for the initial and repetitive inspections of that AD. This amendment is prompted by type certification approval of the Hartzell "MV" series propellers that are direct replacements for the affected propellers, and service bulletin approval to allow modification of affected propellers to the "MV" type design configuration. The actions specified by this AD are intended to prevent blade separation due to cracked blades, hubs, or blade clamps, which can result in loss of control of the airplane.
AD 2003-13-08 · published Jun 30, 2003, effective Jul 21, 2003
Goodrich Avionics Systems, Inc. TAWS8000 Terrain Awareness Warning System
This amendment adopts a new airworthiness directive (AD) that applies to all Goodrich Avionics Systems, Inc. (Goodrich) TAWS8000 terrain awareness warning systems (TAWS) that are installed on airplanes. This AD requires you to inspect the TAWS installation and remove any TAWS where both the TAWS and any other device are connected to the same baro set potentiometer. This AD also prohibits future installation of any TAWS8000 TAWS that incorporates hardware "Mod None", "Mod A", or "Mod B". This AD is the result of a test that showed that TAWS8000 TAWS cause altitude errors in other instruments. The actions specified by this AD are intended to prevent the loading of the baro set potentiometer, which could result in an unacceptable attitude error. Such a condition could cause the pilot to make flight decisions that put the airplane in unsafe flight conditions.
