36 Airworthiness Directives: 22 airplane, 5 rotorcraft, 7 engine, 1 propeller, 1 glider.
AD 2003-20-04 · published Oct 3, 2003, effective Nov 7, 2003
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires an inspection to detect chafing or damage to the electrical wire harnesses in the left and right wing fuel tanks, applicable corrective action(s) if necessary, and installation of harnesses. For certain airplanes, this AD also requires modifying the collector tank walls. This action is necessary to prevent chafing damage to the electrical wire harnesses in the left and right wing fuel tanks, which could cause misleading data and erroneous fuel pump cautions to be displayed to the flightcrew, and could result in electrical arcing with consequent increased potential for fire or explosion in the fuel tank. This action is intended to address the identified unsafe condition.
AD 2003-20-05 · published Oct 3, 2003, effective Nov 14, 2003
PILATUS Aircraft Ltd. Model PC-7 Airplanes
The FAA adopts a new airworthiness directive (AD) for certain PILATUS Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires you to inspect the forward and aft dihedral fittings for cracks and replace any cracked fitting. This AD also requires you to modify the aft dihedral fitting and spar-cap bolt holes. 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 prevent cracks from developing in the forward and aft dihedral fittings, which could result in failure of the wing in certain maneuvers. Such failure could lead to loss of control of the airplane.
AD 2003-20-06 · published Oct 3, 2003, effective Oct 20, 2003
McDonnell Douglas Model DC-9-31 and DC-9-32 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-31 and DC-9-32 airplanes. This action requires, among other actions, various inspections to detect cracks of the cockpit enclosure window sill, and follow-on and corrective actions, as applicable. This action is necessary to prevent fatigue cracking of the internal doublers and frame structure of the fuselage skin of the cockpit enclosure window sill, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-20-03 · published Oct 6, 2003, effective Nov 10, 2003
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, that requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness by incorporating new structural inspection intervals for the vertical beams of the pressure bulkheads at fuselage stations 409+128 and 559; repairing the vertical beams if necessary; and submitting inspection findings to the airplane manufacturer. This action is necessary to detect and correct, in a timely manner, fatigue cracks in the vertical beams of the pressure bulkheads at fuselage stations 409+128 and 559, which could result in the reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-20-08 · published Oct 6, 2003, effective Oct 21, 2003
Boeing Model 747SP and 747SR; 747-100B, -200B, -200C, -200F, -300, -400, and -400D; and 767-200 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing transport category airplanes. This action requires inspection of the attachment of the shoulder restraint harness to the mounting bracket on certain observer and attendant seats to determine if a C-clip is used in the attachment, and corrective action, if necessary. This action is necessary to prevent detachment of the shoulder restraint harness of the attendant or observer seat from its mounting bracket during service, which could result in injury to the occupant of the seat. This action is intended to address the identified unsafe condition.
AD 2003-20-13 · published Oct 9, 2003, effective Nov 13, 2003
Boeing Model 737-400, -500, -600, -700, and -800 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-400, -500, -600, -700, and -800 series airplanes, that requires either modification of the wiring to the windshield wiper motors in the flight compartment or replacement of those windshield wiper motor/converters with new motor/converters. This action is necessary to prevent a reduction in flight crew visibility due to stalled wiper motors during heavy precipitation and a period of substantial crew workload, which could result in damage to the airplane structure and injury to flight crew, passengers, or ground personnel during final approach for landing. This action is intended to address the identified unsafe condition.
AD 2003-20-14 · published Oct 9, 2003, effective Nov 13, 2003
Boeing Model 727-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727-200 series airplanes, that requires installation of four lanyards on the forward access panel/ door. This action is necessary to prevent the forward ceiling access panel/door from falling down and blocking the aisle, which would impede evacuation in an emergency. This action is intended to address the identified unsafe condition.
AD 2003-20-15 · published Oct 9, 2003, effective Oct 10, 2003
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires you to inspect for certain installed fuel booster pumps and replace that fuel booster pump, inspect other certain fuel booster pumps for defects, and either install lead protection spiral wrap or replace the defective fuel booster pumps, depending on whether defects are found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct any defective fuel booster pump, which could result in electrical arcing from the leads in an air/fuel mixture. Such failure could lead to a fire or explosion of a fuel tank.
AD 2003-20-10 · published Oct 10, 2003, effective Oct 15, 2003
Raytheon Aircraft Company Beech Models 1900, 1900C, and 1900D Airplanes
The FAA is adopting a new airworthiness directive (AD) that applies to all Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C, and 1900D airplanes. This AD requires you to make a correction to the elevator trim system maintenance procedures, incorporate a temporary revision to the applicable maintenance manual, and incorporate procedures that will enhance the existing elevator trim operational check every time you have maintenance done on the elevator trim system. This AD is the result of an analysis of the maintenance procedures of the elevator trim system. We are issuing this AD to detect and correct any maintenance-induced problems with the elevator trim system installation before problems occur during operation. Such a condition could lead to difficulties in controlling the airplane or a total loss of pitch control.
AD 2003-20-16 · published Oct 14, 2003, effective Nov 18, 2003
Boeing Model 747SP, 747SR, 747-100, 747-200, and 747-300 Series Airplanes; Equipped With Pratt & Whitney Model JT9D-3, -7, and -7Q Series Engines and Model JT9D-7R4G2 Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747SP, 747SR, 747-100, 747- 200, and 747-300 series airplanes, that currently requires repetitive operational tests of the reversible gearbox pneumatic drive unit (PDU) or the reversing air motor PDU to ensure that the unit can restrain the thrust reverser sleeve, and correction of any discrepancy found. This amendment requires installation of a terminating modification, repetitive functional tests of that installation to detect discrepancies, and repair if necessary. This amendment also removes airplanes from the applicability and adds certain new requirements. The actions specified by this AD are intended to ensure the integrity of the fail-safe features of the thrust reverser system by preventing possible failure modes in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight. This action is intended to address the identified unsafe condition.
AD 2003-21-01 · published Oct 14, 2003, effective Dec 1, 2003
Univair Aircraft Corporation Models Alon A-2 and A2-A; ERCO 415-C, 415-CD, 415-D, 415-E, and 415-G; Forney F-1 and F-1A; and Mooney M10 Airplanes
The FAA supersedes Airworthiness Directive (AD) 94-18-04 R1, which currently applies to all Univair Aircraft Corporation (Univair) Models Alon A-2 and A2-A; ERCO 415-C, 415-CD, 415-D, 415-E, and 415-G; Forney F-1 and F-1A; and Mooney M10 airplanes. AD 94-18-04 R1 requires installing inspection openings in the outer wing panels, inspecting (one-time) the wing outer panel structural components for corrosion, and repairing any corroded wing outer panel structural component. Several reports of corrosion in the outer wing panels of the affected airplanes prompted that AD. This AD is the result of additional reports of corrosion on airplanes in compliance with AD 94- 18-04 R1. This AD makes the inspection required in AD 94-18-04 R1 repetitive. We are issuing this AD to prevent wing damage caused by a corroded wing outer panel structural component, which, if not detected and corrected, could progress to the point of structural failure.
AD 2003-21-02 · published Oct 16, 2003, effective Nov 20, 2003
McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 Airplanes; Model DC-8-50 Series Airplanes; Model DC-8F-54 and DC-8F-55 Airplanes; Model DC-8-60 Series Airplanes; Model DC-8-70 Series Airplanes; and Model DC-8-70F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas transport category airplanes, that requires an inspection to determine the material composition of the lower inboard auxiliary spar cap of the left and right wings. For certain airplanes, this AD also requires repetitive detailed and dye penetrant inspections for cracking of the spar cap, and corrective actions if necessary. This action is necessary to detect and correct stress corrosion cracking of the auxiliary spar cap, which could cause excessive loads to the structure attaching the support fitting of the main landing gear (MLG) to the wing, and result in loss of the MLG. This action is intended to address the identified unsafe condition.
AD 2003-21-04 · published Oct 17, 2003, effective Oct 21, 2003
Cessna Aircraft Company Models 208 and 208B Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This AD requires you to inspect the right inboard forward flap bell crank for cracks, deformation, and missing/incomplete welds. If cracks, deformation, or missing/incomplete welds are found, the AD would require you to immediately replace the flap bell crank or temporarily incorporate certain flap limitations. This AD is the result of reports of cracks and missing/incomplete welds in the right inboard forward flap bell crank. We are issuing this AD to prevent failure of the right inboard forward flap bell crank due to cracks, deformation, or missing/ incomplete welds. Such failure could lead to damage to the flap system and surrounding structure and result in reduced or loss of control of the airplane.
AD 2003-21-05 · published Oct 17, 2003, effective Nov 21, 2003
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 a one-time detailed visual inspection of the wire bundle installation behind the first observer's station to detect damaged or chafed wires; and corrective action, if necessary. This amendment requires a new inspection of the wire bundle installation behind the first observer's station to detect damaged or chafed wires; repair if necessary; installation of a grommet around the lower edge of the feed-through; replacement of the support bracket with a new bracket; and relocation of the support clamp of the wire bundle; as applicable. The actions specified by this AD are intended to prevent the wire bundle contained in the feed-through from contacting the bottom of the feed-through, which could cause cable chafing, electrical arcing, and smoke or fire in the cockpit. This action is intended to address the identified unsafe condition.
AD 2003-21-06 · published Oct 17, 2003, effective Nov 3, 2003
Airbus Model A330-301, -321, -322, -341, and -342 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-301, -321, -322, -341, and -342 airplanes. This action requires modifying the rear fuselage to reinforce a certain frame segment. This action is necessary to prevent fatigue cracking of the rear fuselage, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-21-07 · published Oct 21, 2003, effective Oct 22, 2003
The Cessna Aircraft Company Model 525 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain The Cessna Aircraft Company (Cessna) Model 525 airplanes. This AD requires you to disengage the pitch trim circuit breaker and AP servo circuit breaker and then tie strap each of them to prevent them from being engaged. This AD is the result of analysis that reveals the potential for a single-wire shorting to 28 volts or a failure of a relay in the electric pitch trim system such that the relay contacts remain closed. We are issuing this AD to correct this single-point failure in the electric pitch trim system, which will result in a runaway pitch trim condition where the pilot could not disconnect using the control wheel autopilot/trim disconnect switch. Failure of the electric trim system would result in a large pitch mistrim and would cause excessive control forces that the pilot could not overcome.
AD 2003-21-10 · published Oct 22, 2003, effective Nov 26, 2003
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires an inspection to detect arcing damage of the terminal strips, surrounding structure, and electrical cables in the forward cargo compartment; and repair or replacement of any damaged part with a new part. This amendment also requires modification of the applicable terminal strip installation in the cargo compartment, and replacement of the applicable terminal strips in the cargo compartment with new strips. This action is necessary to prevent arcing and consequent damage to the terminal strips and adjacent structure and smoke/fire in the forward cargo compartment. This action is intended to address the identified unsafe condition.
AD 2003-19-05 · published Oct 23, 2003, effective Oct 27, 2003
McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F Airplanes; and Model MD-10-10F and -30F Airplanes
This document corrects an error that appeared in airworthiness directive (AD) 2003-19-05 that was published in the Federal Register on September 22, 2003 (68 FR 54992). The error resulted in an incorrect Type Certificate holder name. This AD is applicable to certain McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC- 10), -40, and -40F airplanes; and certain Model MD-10-10F and -30F airplanes. This AD requires inspections for cracking and corrosion of the bolt assemblies and bushings on the hinge fittings of the inboard and outboard flaps of the left and right wings, and follow-on and corrective actions.
AD 98-16-17 R1 · published Oct 23, 2003
Cessna Model 750 Citation X Series Airplanes
This amendment rescinds Airworthiness Directive (AD) 98-16-17 R1, which is applicable to all Cessna Model 750 Citation X series airplanes. That AD requires repetitive in-flight functional tests to verify proper operation of the secondary horizontal stabilizer pitch trim system, and repair if necessary. The requirements of that AD were intended to detect and correct contamination and damage in the system actuator, which could result in simultaneous failure of both primary and secondary pitch trim systems, and consequent reduced controllability of the airplane. Since the issuance of that AD, an improved part has been developed, which, if installed, would terminate the repetitive tests; that improved part has been installed on all affected airplanes or is being installed in production. Therefore, the identified unsafe condition no longer exists.
AD 2003-22-01 · published Oct 28, 2003, effective Nov 17, 2003
Aerostar Aircraft Corporation Models PA-60-600, PA-60-601, PA-60-601P, PA-60-602P, and PA-60-700P Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Aerostar Aircraft Corporation (Aerostar) Models PA-60-600, PA-60-601, PA-60-601P, PA-60-602P, and PA-60-700P airplanes that incorporate supplemental type certificate (STC) SA1608NM (Machen Inc. Kit No. 76-1 Auxiliary Fuel Tank). This AD requires you to repetitively inspect all auxiliary fuel transfer pumps for leaks, seeping, or any sign of staining. This AD also requires you to replace any pump found with leaks, seeping, and any sign of staining. This AD is the result of reports of fuel leaking from the fuel transfer pumps installed below the auxiliary fuel tank. We are issuing this AD to detect and correct leaks in the auxiliary fuel transfer pumps, which could result in fire or explosion in the cargo/passenger compartment. Such a condition could result in loss of the airplane.
AD 2003-19-51 · published Oct 29, 2003, effective Nov 3, 2003
Bombardier Model CL-600-2C10 (Regional Jet Series 700 & 701) and CL-600-2D24 (Regional Jet Series 900) Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2003-19-51 that was sent previously to all known U.S. owners and operators of certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 & 701) and CL-600-2D24 (Regional Jet Series 900) series airplanes by individual notices. This AD requires repetitive detailed inspections for cracking or deformation, or pulled or missing fasteners, on the lower panel of the left- and right-hand main landing gear (MLG) doors, as applicable, and corrective actions if necessary. The actions specified by this AD are intended to prevent failure of the lower panel of the MLG door, the lower panel's departure from the airplane, and consequent damage to airplane structure, which could adversely affect the airplane's continued safe flight and landing. This action is intended to address the identified unsafe condition.
AD 2003-22-07 · published Oct 29, 2003, effective Dec 15, 2003
Mitsubishi Heavy Industries, Ltd., MU-2B Series Airplanes
The FAA is superseding Airworthiness Directive (AD) 97-20-14, which applies to all Mitsubishi Heavy Industries, Ltd. (Mitsubishi) MU- 2B series airplanes. AD 97-20-14 currently requires incorporating information into the Limitations Section of the Airplane Flight Manual (AFM) that requires pilot training before flight into known or forecast icing conditions after a certain date. AD 97-20-14 resulted from the Federal Aviation Administration's analysis that the training level of the pilots-in-command (PIC) of the MU-2B series airplanes made it difficult for pilots to recognize adverse operating conditions and operate safely while flying in icing conditions. Since issuance of AD 97-20-14, a new training video has been developed that includes information that is critical to safety of the MU-2B series airplanes. This AD requires you to update the AFM information to require this new video as the mandatory pilot training. We are issuing this AD to decrease the chance of icing-related incidents or accidents of the MU- 2B series airplanes due to pilot error.
AD 2003-20-11 · published Oct 10, 2003, effective Nov 14, 2003
Eurocopter Deutschland GmbH Model EC135 P1, P2, T1, and T2 Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model EC135 P1 and EC135 T1 helicopters. That AD currently requires adding the AD or a statement to the Rotorcraft Flight Manual (RFM) informing the pilot to reduce power and land as soon as practicable if a thump-like sound followed by unusual vibration occurs during flight. That AD also requires visually inspecting the main rotor drive torque strut assembly (strut) for a crack or a break, recording the inspections in the historical or equivalent record, and re-marking and relocating the strut, as appropriate, and replacing any unairworthy strut with an airworthy strut. Also, that AD establishes life limits for certain struts and revises the life limit for other struts. This amendment retains the same requirements but adds the ECD Model EC135 P2 and EC135 T2 helicopters to the applicability and requires replacing certain life- limited struts with titanium struts. This amendment is prompted by the manufacture of a titanium strut that provides a permanent correction to the unsafe condition that led to limiting the life of other struts that have failed. The actions specified by this AD are intended to prevent failure of a strut and subsequent loss of control of the helicopter.
AD 2003-20-12 · published Oct 14, 2003, effective Nov 18, 2003
Eurocopter France Model AS 350B3, SA-365N, N1, AS-365N2, AS 365N3, and EC 155B Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires modifying the SIREN cargo hook and inspecting the cargo hook locking catch (locking catch) for corrosion. This amendment is prompted by the discovery of internal corrosion on a Siren locking catch that may weaken the locking catch. The actions specified by this AD are intended to detect internal corrosion of the locking catch, which can cause the locking catch to return to an incomplete locking position, undetectable by the operator, and result in an unexpected cargo load release.
AD 2003-21-09 · published Oct 22, 2003, effective Nov 26, 2003
Eurocopter France Model AS355E, F, F1, F2, and N Helicopters
This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters. The existing AD currently requires certain checks of the magnetic chip detector plug (chip detector) and the main gearbox (MGB) oil-sight glass; and certain inspections of the lubrication pump (pump) and replacing the MGB and the pump with an airworthy MGB and pump, if necessary. Also, the AD requires that a before a MGB or pump with any time-in-service (TIS) can be installed, it must meet the AD requirements. This amendment requires the same actions as the existing AD but corrects the wording to state that the check of the chip detector is for sludge rather than metal particles. This amendment is prompted by the need to correct the wording because the term "metal particles" may be misleading. The actions specified by this AD are intended to detect sludge on the chip detector, to prevent failure of the MGB pump, seizure of the MGB, loss of drive to an engine and main rotor, and subsequent loss of control of the helicopter.
AD 2003-21-08 · published Oct 24, 2003, effective Nov 28, 2003
Eurocopter France Model AS332C, AS332L, AS332L1, and AS332L2 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires inspecting certain main rotor blades for disbonds, which may be indicated by cracking, and repairing or replacing each main rotor blade (MRB) as necessary. This amendment is prompted by the discovery of disbonded leading edge protective strips. The actions specified by this AD are intended to detect disbonding between the stainless steel protective strip and the MRB skin, which could cause loss of the protective strip, an out-of-balance condition, and subsequent loss of control of the helicopter.
AD 2003-22-06 · published Oct 29, 2003, effective Dec 3, 2003
Eurocopter France Model AS350B, B1, B2, B3, BA, C, D, D1, and AS355E, F, F1, F2, and N Helicopters
This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that currently requires measuring the tail rotor pitch control rod (control rod) outboard spherical bearing (bearing) for radial and axial play. This amendment revises the requirement to measure control rod play. This amendment also adds the Eurocopter France Model AS350B3 helicopter and an additional control rod to the applicability, a daily check of the control rod bearing, a larger axial play limit, a more frequent AD compliance interval, and makes editorial changes for clarification. This amendment is prompted by additional service information and comments resulting in the FAA determination that the inspection interval should coincide with the normal maintenance interval, that the AD should apply to the ECF Model AS350B3 helicopter and an additional control rod, that the daily inspection should be a daily check, and that certain editorial changes are needed for clarification. The actions specified by this AD are intended to prevent separation of the bearing ball from its outer race, rubbing of the body of the control rod against the tail rotor blade pitch horn clevis, failure of the control rod, and subsequent loss of control of the helicopter.
AD 2003-20-07 · published Oct 3, 2003, effective Nov 3, 2003
General Electric Company (GE) CF6-80E1A2 Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-80E1A2 turbofan engines with forward engine mount platforms part numbers (P/Ns) 1520M53G04 and 1846M24G15 installed. This AD requires initial and repetitive fluorescent penetrant inspections of cast material forward engine mount platforms. This AD is prompted by the airframe manufacturer's revised analyses of loads on the forward engine mount. We are issuing this AD to prevent engine separation that could result from cracking of the forward engine mount platform.
AD 2003-05-10 R1 · published Oct 14, 2003, effective Nov 18, 2003
General Electric Aircraft Engines Engines
This amendment revises an existing airworthiness directive (AD), that applies to General Electric Company (GE) CF34-3A1, -3B, and -3B1 turbofan engines with scavenge screens part numbers (P/Ns) 4047T95P01 and 5054T86G02 installed in the B-sump oil scavenge system. That AD currently requires initial and repetitive visual inspections and cleaning of the B-sump scavenge screens until a screenless fitting is installed. This amendment requires the same initial and repetitive visual inspections and cleaning of the B-sump scavenge screens until a screenless fitting is installed. This amendment also corrects a typographical error, and introduces a less restrictive terminating action schedule. This amendment is prompted by the need to correct a typographical error and by the need to introduce a less restrictive terminating action schedule. We are issuing this AD to prevent B-sump scavenge screen blockage due to coking which could result in ignition of B-sump oil in the secondary air system, fan drive shaft separation, and uncontained engine failure.
AD 2003-21-03 · published Oct 16, 2003, effective Nov 20, 2003
Pratt & Whitney Canada Models PW118, PW120, PW120A, and PW121 Turboprop Engines
The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) models PW118, PW120, PW120A, and PW121 turboprop engines. This AD requires replacing the low pressure rotor speed (NL) sensor port sealing tube and reworking or replacing the external air tube connecting the P2.5/P3 switching valve to the rear inlet case. This AD is prompted by a report of an internal oil fire in the engine intercompressor case (ICC). A fire in the ICC could cause the existing tubes to disengage due to melted brazing on the tubes. Once these tubes disengage, the ICC fire then develops into an external fire within the engine nacelle cavity. We are issuing this AD to prevent fire in the engine nacelle cavity, in-flight engine shutdown, and airplane damage.
AD 2003-21-11 · published Oct 24, 2003, effective Nov 10, 2003
Rolls-Royce plc RB211-524 Series Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-524 series turbofan engines. This AD requires replacing the dedicated generator rotor assembly, the adaptor casing on the high speed gearbox (HSGB), and bearings with new design parts on certain engines. This AD is prompted by several reports of dedicated generator rotor assembly bearing failures. We are issuing this AD to prevent possible uncommanded engine acceleration with no reaction to throttle movement, which could result in uncontrollable asymmetric engine thrust levels during takeoff or climb.
AD 2003-22-04 · published Oct 28, 2003, effective Nov 12, 2003
Rolls-Royce plc RB211-524 Series Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-524 series turbofan engines with certain part number (PN) and serial number (SN) low pressure (LP) compressor fan blades installed. This AD requires inspection of certain LP compressor fan blade roots and replacement or repair of blades if damage is not within acceptable limits. This AD is prompted by the discovery of damaged LP compressor fan blade roots resulting from entrapment of ceramic polishing media between the blade roots and the masking boot during blade root repair. We are issuing this AD to prevent possible uncontained multiple LP compressor fan blade release, and damage to the airplane.
AD 2003-22-02 · published Oct 30, 2003, effective Nov 14, 2003
Rolls-Royce plc Trent 556-61 Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce (RR) plc RB211 Trent 556-61 turbofan engines. This AD requires a gauge inspection of the space between the high pressure (HP) fuel tubes adaptor face and seals, and a gauge inspection of the space between the fuel flow transmitter and seals, for evidence of permanent distortion of the face of the fuel tube connecting flanges, and replacement of parts if necessary. This AD is prompted by a report of fuel leaking from the engine fan cowl during an aircraft taxi. We are issuing this AD to prevent in-flight fuel leaks, which could result in an engine fire.
AD 2003-22-03 · published Oct 30, 2003, effective Nov 14, 2003
Rolls-Royce plc Trent 768-60 and Trent 772-60 Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211 Trent 768-60 and Trent 772-60 turbofan engines. This AD requires reworking the low pressure (LP) turbine nozzle vane case, the LP turbine bearing support exhaust case, and the support arm bracket assemblies. This AD is prompted by a report of an LP stage 4 blade failure at the blade shank, resulting in severe radial distortion of the rear flange of the LP turbine case and failure of a number of attaching bolts, resulting in enough flange separation to allow the release of high energy debris. We are issuing this AD to prevent possible uncontained LP turbine case failure and damage to the airplane.
AD 2003-22-05 · published Oct 29, 2003, effective Nov 13, 2003
Hartzell Propeller Inc. Model HC-A6A-3 Series Propellers.
The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller Inc. model HC-A6A-3 series propellers with A10460 series composite blades. This AD requires initial and repetitive visual inspections of A10460 series composite blades for cracks. This AD is prompted by reports of cracks in propeller blades, including an in- flight separation of a blade that caused damage to the airplane. We are issuing this AD to prevent separation of the propeller blade due to possible fatigue failure, which could result in damage to the airplane and possible loss of control of the airplane.
AD 2003-20-09 · published Oct 9, 2003, effective Oct 20, 2003
Stemme GmbH & Co. KG Model STEMME S10-VT Sailplanes
The FAA is adopting a new airworthiness directive (AD) for all Stemme GmbH & Co. KG Model STEMME S10-VT sailplanes that incorporate a certain gear box. This AD requires you to incorporate flight restrictions into the Limitations Section of the sailplane flight manual and fabricate and install a placard close to the throttle lever indicating these restrictions. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent the potential for the lower cog wheel in the gear box to rupture, which could result in loss of power and possible loss of control of the sailplane.
