23 Airworthiness Directives: 13 airplane, 2 rotorcraft, 5 engine, 2 propeller, 1 balloon.
AD 2003-04-11 · published Mar 4, 2003, effective Apr 8, 2003
Boeing Model 747-200B and -200F Series Airplanes Powered by Pratt & Whitney JT9D-70 Series Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200B and -200F series airplanes powered by Pratt & Whitney JT9D-70 series engines, that requires repetitive detailed inspections of the pylon skin and internal structure of the nacelle struts adjacent to and aft of the precooler exhaust vent for heat damage (discoloration), wrinkling, and cracking; and corrective action, if necessary. The actions specified by this AD are intended to find and fix such damage, which could result in cracking or fracture of the nacelle struts, and consequent reduced structural integrity and possible separation of the strut and engine from the airplane. This action is intended to address the identified unsafe condition.
AD 2003-04-26 · published Mar 4, 2003, effective Apr 21, 2003
Raytheon Aircraft Company Model 1900D Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 1900D airplanes. This AD requires you to inspect the alternating current (AC) inverter and modify the AC inverter and inverter sync wire shield. This AD is the result of reports that electrical noise causes the inverter to shut down in flight with loss of AC-powered flight instruments. The actions specified by this AD are intended to prevent electrical noise causing the inverter to shut down, which could result in failure of key aircraft electrical systems. Such failure could lead to loss of flight instruments during flight.
AD 2003-04-27 · published Mar 4, 2003, effective Apr 8, 2003
Bombardier Model CL-600-2C10 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier CL-600-2C10 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate functional and operational checks of the active and standby actuators of the rudder travel limiter (RTL) system. The actions specified by this AD are intended to prevent a significant latent failure in the RTL, which could lead to a critical loss of RTL function under certain conditions, and consequent loss of controllability of the airplane or structural damage. This action is intended to address the identified unsafe condition.
AD 2003-05-08 · published Mar 14, 2003, effective Apr 18, 2003
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 replacement of certain flight data recorder (FDR) and cockpit voice recorder (CVR) impact switches with certain new impact switches. This action is necessary to prevent the loss of data recorded on the FDR and CVR, which, in the event of an accident, could result in the inability to retrieve data from the FDR and CVR during the accident investigation. This loss of data could hinder the identification of the unsafe condition which caused the accident, and prevent the FAA from developing and mandating actions to prevent additional accidents caused by that same unsafe condition.
AD 2003-05-05 · published Mar 18, 2003, effective Apr 25, 2003
Robert E. Rust Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Robert E. Rust (R.E. Rust) Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A airplanes. This AD requires you to inspect the fuselage to determine if a steel fuselage center-section tie bar fitted with bushings in the end lug bolt holes is installed. If this bushed steel fuselage center-section tie bar is installed, this AD decreases the safe life limit. This AD is the result of reports that certain replacement steel fuselage center-section tie bars installed on the affected airplanes could fail before the originally published safe life limit. The actions specified by this AD are intended to prevent early failure of these bushed steel fuselage center-section tie bars, which could result in reduced structural integrity of the wings. Such a condition could lead to loss of control of the airplane.
AD 2003-05-06 · published Mar 18, 2003, effective Apr 25, 2003
Robert E. Rust Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Robert E. Rust (R.E. Rust) Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A airplanes. This AD requires you to check the airplane logbook to determine whether certain modifications have been incorporated on the airplane and incorporate the modifications that have not already been accomplished. This AD is the result of the manufacturer performing a design study on the structural integrity of certain parts and reports of service failure of other parts installed on the affected airplanes. The actions specified by this AD are intended to prevent reduced structural integrity in the primary structure of the airplane, which could result in failure of the rudder torque tube, elevator fasteners, and the vertical fin rear spar, or jamming or damage to the elevator. Such failures could lead to loss of control of the airplane.
AD 2003-05-09 · published Mar 18, 2003, effective Apr 2, 2003
Dassault Model Falcon 2000 and Mystere-Falcon 900 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Dassault Model Falcon 2000 and Mystere-Falcon 900 series airplanes. This action requires a one-time inspection to detect discrepant wires in the fire control panel for the engines and auxiliary power unit (APU), and corrective action if necessary. This action is necessary to ensure that the correct wires are installed in the fire control panel so that the flight crew can activate the fire extinguishers in the event of an engine or APU fire. This action is intended to address the identified unsafe condition.
AD 2003-04-21 R1 · published Mar 25, 2003, effective Apr 4, 2003
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 440) series airplanes. That AD currently requires replacement of the overwing emergency exit placards, door weight placards, and no baggage placards with new placards. This document corrects the applicability of AD 2003-04-21 to identify affected model designations as published in the most recent type certificate data sheet. This correction is necessary to ensure that operators of all affected airplanes accomplish the requirements of this AD.
AD 2003-06-05 · published Mar 26, 2003, effective Apr 30, 2003
Saab Model SAAB SF340A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A series airplanes, that requires modifying the structure of the air recirculation fan support, and replacing the air recirculation fans with two upgraded air recirculation fans; or replacing the air recirculation fans with two new air recirculation fans with brushless motors. 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 incidents of smoke or a burning smell in the cabin during flight, caused by incorrect brush insulation in the motors of the air recirculation fans that provide air to the flight compartment and the passenger compartment.
AD 2003-06-06 · published Mar 26, 2003, effective Apr 30, 2003
Raytheon Model Hawker 800XP and 800 (Including Variant U-125A) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 800XP and 800 (including variant U-125A) airplanes, that requires a one-time inspection to identify the bolts installed at certain locations in the wing or fuselage, and corrective actions if necessary. The actions specified by this AD are intended to prevent failure of certain attachment bolts due to manufacturing discrepancies, which could result in reduced structural integrity of the airplane, and loss of system function for flaps, controls, and landing gear. This action is intended to address the identified unsafe condition.
AD 2003-06-04 · published Mar 27, 2003, effective May 1, 2003
Airbus Model A300 B2 and B4 Series Airplanes; and A300 B4-600, B4-600R, and F4-600R (Collectively Called A300-600) Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes, that currently requires repetitive inspections to detect cracking of the upper radius of the forward fitting of frame 47, and repair if necessary. This amendment retains those requirements but shortens the initial compliance time and the repetitive inspection intervals. This amendment also expands the applicability to include additional airplanes. This amendment is prompted by issuance of mandatory continuing airworthiness information by a civil airworthiness authority. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in propagation of the cracking to the rear fitting and reduced structural integrity of fuselage frame 47.
AD 2003-06-07 · published Mar 27, 2003, effective May 16, 2003
Socata-Groupe Aerospatiale Models MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 150T, and Rallye 150ST Airplanes
This amendment supersedes Airworthiness Directive (AD) 2002- 05-04, which applies to certain Socata--Groupe Aerospatiale (Socata) Models MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 150T, and Rallye 150ST airplanes. AD 2002-05-04 requires you to repetitively inspect any engine mount assembly that is not part number 892-51-0-035-0 (or FAA-approved equivalent part number) for cracks; repair cracks that do not exceed a certain length; and replace the engine mount when the cracks exceed a certain length and cracks are found on an engine mount that already has been repaired twice. This AD is the result of the French airworthiness authority's determination that airplanes equipped with an engine mount assembly part number 892- 51-0-035-0 also display the unsafe condition. This AD retains the repetitive inspection and repair requirements of AD 2002-05-04, changes the applicability section, removes the terminating action, and requires replacement of all part number 892-51-0-035-0 engine mount assemblies. The actions specified by this AD are intended to prevent failure of the engine mount assembly. Such failure could result in loss of control of the airplane.
AD 2003-06-08 · published Mar 27, 2003, effective May 16, 2003
Dornier-Werke G.m.b.H. Model Do 27 Q-6 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Dornier-Werke G.m.b.H. (Dornier) Model Do 27 Q-6 airplanes. This AD requires you to inspect the aileron and flap control cables for proper clearance from the fuel lines in the fuselage and make necessary adjustments; and inspect the fuel lines for damage and correct routing. This AD also requires you to replace all damaged fuel lines and reroute incorrectly routed fuel lines. After all other corrective action is taken, this AD also requires you to install protective sleeves on the fuel lines. 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 detect and correct damaged fuel lines and prevent the potential for further damage occurring to the fuel lines in the fuselage. Damage to the fuel lines could result in fuel leaking into the fuselage, which could cause a fire or explosion.
AD 2003-05-03 · published Mar 13, 2003, effective Apr 17, 2003
Bell Helicopter Textron Canada Model 407 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (Bell) model helicopters that requires preflight checking and repetitively inspecting for a crack in certain tailbooms that have not been redesigned and replacing the tailboom if a crack is found; modifying and re-identifying certain tailbooms and installing an improved horizontal stabilizer assembly; and assigning a 5,000 hour time-in-service (TIS) life limit. This amendment is prompted by cracking discovered in other areas of certain tailbooms and introduction of a redesigned tailboom with a chemically milled skin, which does not require the current inspections. The actions specified by this AD are intended to prevent separation of the tailboom and subsequent loss of control of the helicopter.
AD 2003-05-11 · published Mar 18, 2003, effective Apr 2, 2003
Bell Helicopter Textron Canada Model 407 Helicopters
This amendment supersedes an existing emergency airworthiness directive (EAD), which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (Bell) helicopters by individual letters. That EAD requires a visual check to ensure that the two swashplate drive link cup washers (cup washers) are installed correctly. If a cup washer is installed incorrectly, removing and replacing the swashplate outer ring, each cup washer, bearing and liner, and drive link where the cup washer was installed incorrectly are also required. This amendment requires the same actions as the existing EAD, but clarifies that only the visual check may be performed by the owner/operator. This amendment is prompted by two reported failures of the stud portion of the swashplate drive link. The actions specified by this AD are intended to detect an incorrectly installed cup washer, which could limit the travel of the swashplate outer ring and lead to failure of the stud portion of the swashplate drive link, and subsequent loss of control of the helicopter.
AD 2003-05-01 · published Mar 6, 2003, effective Mar 21, 2003
Wytwornia Sprzetu Komunikacyjnego (WSK) PZL-Rzeszow S.A. Franklin 6A-350-C1, -C1A, -C1L, -C1R -C2, -C2A, and 4A-235 Series Reciprocating Engines
This amendment supersedes an emergency airworthiness directive (AD) that was sent previously to all known U.S. owners and operators of WSK PZL-Rzeszow S.A. Franklin 6A-350-C1, -C1A, -C1L, -C2, -C2A, and 4A- 235 series reciprocating engines. This action requires removing diaphragm type AC4886 fuel pump, AC part number (P/N) 5656774, PZL P/N 26.11.1710, before further flight, and prohibits installing diaphragm type AC4886 fuel pump, AC P/N 5656774, PZL P/N 26.11.1710. This amendment is prompted by several reports of failures of the valves and diaphragms in certain diaphragm type AC4886 fuel pumps, AC P/N 5656774, PZL P/N 26.11.1710, and adds the 6A-350-C1R engine to the applicability. The actions specified by this AD are intended to prevent reduction or loss of engine power or external fuel leaks.
AD 2003-05-04 · published Mar 11, 2003, effective Mar 26, 2003
Rolls-Royce Deutschland Ltd. & Co KG, Model Tay 611-8, 620-15, 650-15, and 651-54 Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD) that is applicable to Rolls-Royce Deutschland Ltd. & Co KG (RRD) Model Tay 620-15 and 650-15 turbofan engines. That AD currently requires initial and repetitive inspections of certain low pressure (LP) fuel tubes. This amendment requires the same inspections and adds two engine models to the applicability. This amendment is prompted by a report that certain Tay 611-8 and 651-54 turbofan engines may use the same LP fuel tube. The actions specified in this AD are intended to prevent a dual-engine flameout due to fuel exhaustion, which could lead to forced landing and possible damage to the airplane.
AD 2003-05-07 · published Mar 13, 2003, effective Apr 17, 2003
Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, - 9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines. This amendment requires removal from service of certain part number (P/ N) 3rd-4th and 4th-5th stage compressor rotor spacer assemblies and incorporation of a new tierod retention configuration. This amendment is prompted by two reports of uncontained failure of JT8D turbofan engines, caused by turbine rotor overspeed resulting from first and second stage fan section separation from the low pressure compressor (LPC). The actions specified by this AD are intended to prevent first and second stage fan section separation from the LPC, resulting in turbine rotor overspeed, uncontained engine failure, and damage to the airplane.
AD 2003-05-10 · published Mar 18, 2003, effective Apr 2, 2003
General Electric Company CF34-3A1, -3B, and -3B1 Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable 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. This amendment requires initial and repetitive visual inspections and cleaning of the B-sump scavenge screens until a screenless fitting is installed. This amendment is prompted by six reports of B-sump oil scavenge system failure causing engine in-flight shutdowns. The actions specified by this AD are intended 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 2003-06-03 · published Mar 20, 2003, effective Apr 24, 2003
General Electric Aircraft Engines CT7 Series Turboprop Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain General Electric Aircraft Engines (GEAE) CT7 series turboprop engines. This amendment requires initial and repetitive inspections of the propeller gearbox (PGB) oil filter impending bypass button (IBB) for extension (popping), requires follow- on inspections, maintenance, and replacement actions if the PGB oil filter IBB is popped, and if necessary, replacement of the PGB with a serviceable PGB. In addition, this amendment requires replacement of certain left-hand and right-hand idler gears at time of overhaul of PGBs, and the replacement of certain SN PGBs before accumulating 2,000 flight hours. This amendment is prompted by an on-going investigation that concluded that low-time PGB removals are due to accelerated wear of the PGB idler gears, rather than improperly hardened PGB input pinions. The actions specified by this AD are intended to prevent separation of PGB left-hand and right-hand idler gears, which could result in uncontained PGB failure and internal bulkhead damage, possibly prohibiting the auxiliary feathering system from fully feathering the propeller on certain PGBs.
AD 2003-04-25 · published Mar 4, 2003, effective Apr 8, 2003
Dowty Aerospace Propellers, Models R354, R375, R389, and R390 Propellers
This amendment adopts a new airworthiness directive (AD), that is applicable to Dowty Aerospace Propellers, R354/4-123-F/13, R354/4- 123-F/20, R375/4-123-F/21, R389/4-123-F/25, R389/4-123-F/26, and R390/ 4-123-F/27 propellers. This amendment requires a one-time inspection of the hub joint mating surfaces for fretting. This amendment is prompted by reports of fretting on the joint mating faces of propeller hubs. The actions specified by this AD are intended to prevent failure of the hub due to loose hub through bolts.
AD 2003-06-02 · published Mar 25, 2003, effective Apr 29, 2003
Hartzell Propeller Inc. Model HC-C2Y(K,R)-1BF/F8477-4 Propellers
This amendment adopts a new airworthiness directive (AD), that is applicable to certain Hartzell Propeller Inc. model HC-C2Y(K,R)-1BF/ F8477-4 propellers with TKS (Aircraft De-icing) Ltd. anti-ice boots that were installed by SOCATA-Groupe AEROSPATIALE, the aircraft manufacturer, using TKS Ltd. Procedure P232, Specification for the Attachment of Propeller Overshoes. This amendment requires removal of the anti-ice boots, inspection and rework of the anti-ice boot area of the propeller blades, and installation of new anti-ice boots. This amendment is prompted by a report of TKS (Aircraft De-icing) Ltd. anti- ice boots on the blades of a model HC-C2Y(K,R)-1BF/F8477-4 propeller that were installed by SOCATA-Groupe AEROSPATIALE using processes that could lead to blade corrosion and failure. The actions specified by this AD are intended to prevent propeller blade separation, damage to the airplane, and possible loss of the airplane.
AD 2003-05-02 · published Mar 11, 2003, effective May 2, 2003
Lindstrand Balloons Ltd Fuel Hoses
This amendment adopts a new airworthiness directive (AD) that applies to all aircraft (specifically balloons) that incorporate certain Lindstrand Balloons Ltd (Lindstrand) fuel hoses. This AD requires you to inspect for certain batches of installed fuel hoses and replace any of these fuel hoses. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect and replace defective fuel hoses before they result in propane fuel leaks. Such propane fuel leaks could lead to a propane fuel fire.
