35 Airworthiness Directives: 22 airplane, 5 rotorcraft, 5 engine, 1 appliance, 2 glider.
AD 2005-09-08 · published May 5, 2005, effective May 20, 2005
McDonnell Douglas Model MD-90-30 Airplanes
The FAA is superseding two existing airworthiness directives (ADs); both apply to the same certain McDonnell Douglas Model MD-90-30 airplanes. The superseded ADs currently require a one-time general visual inspection to detect wire chafing damage and to determine adequate clearance between the disconnect panel structure and the wires above the aft left lavatory; and corrective actions, if necessary. This new AD retains those requirements and clarifies certain requirements for recording AD compliance. This AD is prompted by the determination that the form of the existing ADs could result in confusion to operators in recording compliance with the potentially conflicting requirements. We are issuing this AD to prevent damage to certain wires due to contact between the wires and the adjacent structure, which could result in electrical arcing and consequent smoke and fire in the cabin.
AD 2005-10-02 · published May 11, 2005, effective Jun 15, 2005
Dornier Model 328-300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Dornier Model 328-300 series airplanes. This AD requires installing an additional mounting angle for the respective de-icing pipes at rib 9 in the leading edge area of the left- and right-hand wings. This AD is prompted by chafed de-icing lines in the wing leading edge area. We are issuing this AD to prevent chafing of the de-icing lines, which could result in a reduction in functionality of the anti-ice system, and possibly reduced controllability and performance of the airplane in icing conditions.
AD 2005-10-03 · published May 11, 2005, effective Jun 15, 2005
Boeing Model 777-200 and 777-300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 and -300 series airplanes. This AD requires modification of the operational program software (OPS) of the air data inertial reference unit (ADIRU). This AD is prompted by a report of the display of erroneous heading information to the pilot due to a defect in the OPS of the ADIRU. We are issuing this AD to prevent the display of erroneous heading information to the pilot, which could result in loss of the main sources of attitude data, consequent high pilot workload, and subsequent deviation from the intended flight path.
AD 2005-10-04 · published May 11, 2005, effective Jun 15, 2005
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes. This AD requires repetitive inspections of the left- and right-side main landing gear (MLG) side-stay cuff lugs and down-lock spring attachments for evidence of cracked or fractured side-stay cuff lugs or down-lock spring attachments, and repair if necessary. This AD also provides for optional terminating action for the repetitive inspections. This action is necessary to prevent failure of the MLG side-stay cuff lugs or down-lock spring attachments, which could result in improper down-lock of the MLG during a freefall extension, and possible collapse of the MLG. This action is intended to address the identified unsafe condition.
AD 2005-10-01 · published May 12, 2005, effective Jun 16, 2005
Airbus Model A310 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A310 series airplanes. This AD requires measuring the clearance between the compensator and the guide assembly of probe no. 1 on the outboard fuel tanks, and performing corrective actions if necessary. This AD is prompted by the results of fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent interference between the compensator and the guide assembly of probe no. 1, which could create an ignition source that could result in a fire or explosion.
AD 2005-10-06 · published May 12, 2005, effective Jun 16, 2005
Dornier Model 328-300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Dornier Model 328-300 series airplanes. This AD requires installing a drain hole in the lower skin of the left- and right-hand elevator horns. This AD is prompted by reports of water found in the elevator assembly. We are issuing this AD to prevent water or ice accumulating in the elevator assembly, which could result in possible corrosion that reduces the structural integrity of the flight control surface, or in an unbalanced flight control surface. These conditions could result in reduced controllability of the airplane.
AD 2005-10-07 · published May 17, 2005, effective Jun 21, 2005
Fokker Model F.28 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 series airplanes. This AD requires a one-time inspection of the area underneath the auxiliary power unit (APU) enclosure to determine if drain tubes in the area are correctly installed and to detect damaged wiring, and corrective action if necessary. This AD is prompted by a report of a fire under the APU enclosure. We are issuing this AD to prevent fuel from accumulating under the APU enclosure, which, in the presence of an ignition source, could result in a fire.
AD 2005-10-08 · published May 17, 2005, effective Jun 21, 2005
Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 airplanes. This AD requires operators to install torque tube catchers on the control columns of the flight controls. This AD is prompted by the discovery that a single malfunction of the torque tube could result in both flight control columns being supported by only one self-aligning bearing. We are issuing this AD to prevent the torque tube from fouling against the underfloor control cables, which could result in reduced controllability of the airplane.
AD 2005-10-09 · published May 17, 2005, effective Jun 21, 2005
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Saab Model SAAB SF340A and SAAB 340B series airplanes. That AD currently requires repetitive detailed inspections of the windshield wiper assembly for discrepant conditions, and corrective actions if necessary. This new AD requires repetitive detailed inspections of the left and right wiper arm assemblies for damage, and corrective/related investigative actions if necessary. This AD is prompted by an additional incident of a windshield wiper blade separating from the wiper arm. We are issuing this AD to prevent separation of a wiper arm from the airplane, which could result in damage to the fuselage skin and propeller.
AD 2005-10-10 · published May 17, 2005, effective Jun 1, 2005
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness of the Canadair Regional Jet Maintenance Requirements Manual by incorporating new repetitive detailed inspections of the secondary load path indicator for the horizontal stabilizer trim actuator (HSTA). This AD is prompted by a report of a potential failure of the horizontal stabilizer trim actuator (HSTA) secondary nut in conjunction with a latent failure of the HSTA primary load path discovered during sampling program activities. We are issuing this AD to detect and correct latent failure of the primary load path of the HSTA, which, in conjunction with a failure of the HSTA secondary nut, could result in loss of horizontal trim control and consequent reduced controllability of the airplane.
AD 2005-10-11 · published May 18, 2005, effective Jun 22, 2005
Boeing Model 737-300, -400, and -500 Series Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 737-300, -400, and -500 series airplanes. That AD currently requires repetitive inspections of certain connectors located in the main wheel well to detect discrepancies, and corrective action if necessary. This new AD instead mandates a modification. This AD is prompted by the development of a modification intended to address the unsafe condition. We are issuing this AD to prevent discrepancies of certain connectors located in the main wheel well. Those discrepancies could result in electrical arcing of the connectors, uncommanded closure of the engine fuel shut-off valves, and consequent in-flight loss of thrust or engine shutdown from lack of fuel.
AD 2005-10-15 · published May 18, 2005, effective Jun 22, 2005
Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus model airplanes, as specified above. This AD requires modifying the electrical bonding points of additional center tanks. This AD is prompted by the results of fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent electrical arcing inside the fuel tank, due to insufficient bonding, which could result in the ignition of fuel vapors with a potential risk of explosion of the fuel tank.
AD 2005-10-17 · published May 19, 2005, effective Jun 23, 2005
Boeing Model 777-200 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 and -300 series airplanes, that requires modification of the bolt holes of the lower side of the body splice t-chord common to the paddle fittings of the lower wing panel. The modification includes performing a high frequency eddy current inspection of the fastener holes for cracks, repairing the hole if necessary, and replacing the fasteners with new inconel bolts. This action is necessary to prevent fatigue cracks in the lower t-chord at the bolt holes common to the paddle fittings that could result in fractures of one or more of the t-chord segments, which could lead to detachment of the lower wing panel and consequent loss of the wing. This action is intended to address the identified unsafe condition.
AD 2005-10-18 · published May 19, 2005, effective Jun 23, 2005
Boeing Model 747-100, -100B, -100B SUD, -200B, -200C, -300, -400, and -400D Series Airplanes; and Model 747SR Series Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747 series airplanes. That AD currently requires a one-time inspection to determine the material type of the stop support fittings of the main entry doors (MEDs). That AD also currently requires repetitive detailed inspections to detect cracks of certain stop support fittings of the MEDs, and replacement of any cracked stop support fitting with a certain new stop support fitting. This new AD adds new inspections, and replacement if necessary, of the stop support fittings of MED 3, and adds airplanes to the applicability. This AD is prompted by reports of MED 3 having certain stop support fittings that are susceptible to stress corrosion cracking. We are issuing this AD to detect and correct stress corrosion cracking of the stop support fittings of the MEDs, which could result in damage to the adjacent forward edge frame of the door and consequent loss of a MED and rapid decompression of the airplane.
AD 2005-10-19 · published May 19, 2005, effective Jun 23, 2005
Boeing Model 747-100, 747-100B, 747-200B, 747-300, 747-400, 747-400D, 747SR, and 747SP Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-200B, 747-300, 747-400, 747-400D, 747SR, and 747SP series airplanes. This AD requires replacing or modifying the control panels for the galley cart lift and modifying related electrical cable assemblies, as applicable. This AD is prompted by reports of injuries to catering personnel and flight attendants who were loading or unloading galley carts on one deck when, due to a disabled or malfunctioning safety interlock door switch, the galley cart lift unexpectedly moved when it was activated from the control panel on the other deck. We are issuing this AD to ensure that the galley cart lift can be sent only from the deck on which it is in use, which will prevent unexpected movement of the cart lift that could result in possible injury to catering personnel or flight attendants.
AD 2005-10-20 · published May 19, 2005, effective Jun 23, 2005
Boeing Model 777-200 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 series airplanes. This AD requires replacing the pressure switches on the override/jettison fuel pumps with new pressure switches, and replacing the ship side electrical connectors for the pressure switches on override/jettison fuel pumps with new connectors. This AD is prompted by reports that the "FUEL LOW CENTER" message does not activate when the fuel level in the center tank is low. We are issuing this AD to prevent the fuel pumps in the center fuel tank from running dry and becoming a potential ignition source, which could result in a fuel tank explosion.
AD 2005-10-21 · published May 19, 2005, effective Jun 23, 2005
Boeing Model 747 Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747 airplanes. That AD currently requires inspections to detect cracks in the front spar pressure bulkhead chord, and repair if necessary. This new AD requires repetitive high frequency eddy current (HFEC) inspections of the body station (BS) 1000 bulkhead chord for cracks, repetitive detailed inspections of the bathtub fittings, if installed, for cracks, and corrective action if necessary. Initiation of the new inspections ends the inspections of the existing AD. This AD also revises the applicability of the existing AD to include additional airplanes. This AD is prompted by reports of cracks in the BS 1000 bulkhead chord. We are issuing this AD to detect and correct fatigue cracks in the BS 1000 bulkhead chord, which, if not repaired before they reach critical length, could result in the failure of the adjacent structure and skin and lead to in-flight depressurization of the airplane.
AD 2005-10-22 · published May 23, 2005, effective Jun 27, 2005
Boeing Model 747-200C and 747-200F Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 747-200C and 747-200F series airplanes. This AD requires repetitive inspections for cracking of the left and right C-3 frame upper closure fittings of the nose cargo door, and corrective actions if necessary. This AD also provides an optional modification that, if done, terminates inspections in certain areas. This AD is prompted by reports indicating that fatigue cracking was found in the inboard flange above the flight deck floor on the C-3 frame upper closure fittings of the nose cargo door. We are issuing this AD to detect and correct cracking of the C-3 frame upper closure fittings, which could extend and result in rapid depressurization of the airplane.
AD 2005-10-24 · published May 23, 2005, effective Jun 30, 2005
AeroSpace Technologies of Australia Pty Ltd. Models N22B, N22S, and N24A Airplanes
The FAA adopts a new airworthiness directive (AD) to supersede AD 2003-14-20, which applies to all AeroSpace Technologies of Australia Pty Ltd. (ASTA) Models N22B and N24A airplanes. AD 2003-14-20 requires you to repetitively inspect, using either dye penetrant or magnetic particle methods, the rudder control lever shafts for cracks; inspect (one-time) all lever shaft side plates by measuring the thickness; and if cracks or discrepancies in thickness are found, replace unserviceable parts with new or serviceable parts. Since AD 2003-14-20 was issued, we determined that the AD should also affect Model N22S airplanes. The manufacturer has also revised the service information to include a rudder control lever shaft part number (P/N) that was not part of AD 2003-14-20. Consequently, this AD retains the actions of AD 2003-14-20, adds Model N22S airplanes to the applicability, and adds rudder control lever shaft P/N 1/N-45-1102 to the inspection requirements. We are issuing this AD to detect and correct cracks in the rudder control lever torque shafts and discrepancies in the thickness of the lever shaft side plates, which could result in failure of the rudder control lever torque shaft. Such failure could lead to reduced controllability of the airplane.
AD 2005-11-02 · published May 27, 2005, effective Jul 1, 2005
Boeing Model 767-200, -300, and -300F Series Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 767-200, -300, and -300F series airplanes. That AD currently requires inspections for fatigue cracking of the horizontal stabilizer pivot bulkhead, and repetitive inspections or other follow-on actions. That action also provides a permanent repair, which is optional for airplanes with no cracks, and, if accomplished, ends the repetitive inspections. For airplanes on which the permanent repair is not installed, this new AD requires repetitive inspections of the same and additional inspection locations at new inspection intervals; a one-time torque test; and related investigative and corrective actions. For airplanes on which the permanent repair is installed, this new AD would require repetitive inspections of the repaired area and, if necessary, corrective action. This AD is prompted by reports of loose tension bolts and crack indications in the fuselage skin. We are issuing this AD to find and fix fatigue cracking of the horizontal stabilizer pivot bulkhead and adjacent structure, which could result in loss of the horizontal stabilizer.
AD 2005-11-03 · published May 27, 2005, effective Jul 1, 2005
McDonnell Douglas Model 717-200 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This AD requires replacing eight brake fuses of the hydraulic quantity limiter with new or modified and reidentified fuses. This AD is prompted by reports indicating that brake fuses of the hydraulic quantity limiter of the main landing gear have failed. We are issuing this AD to prevent loss of both hydraulic and brake systems if one fuse on each hydraulic system were to fail simultaneously, and consequent reduced controllability of the airplane.
AD 2005-11-04 · published May 27, 2005, effective May 27, 2005
Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) Airplanes Modified by Supplemental Type Certificate (STC) SA4900SW
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) airplanes modified by STC SA4900SW. This AD requires revising the airplane flight manual (AFM) to require repetitive visual checks of the microphone jack assemblies on both control columns to detect damage that may interfere with movement of the control column. This AD also requires modification of the microphone jack assembly, related investigative actions, and corrective actions if necessary, which allows the AFM revision to be removed from the AFM. This AD is prompted by a report of a rejected take-off and subsequent runway overrun due to restricted movement of the co-pilot's control column, which resulted in collapse of the nose landing gear and consequent damage of the forward fuselage. We are issuing this AD to prevent a damaged microphone jack assembly from interfering with movement of the control column, which could result in loss of control of the airplane.
AD 2005-09-05 · published May 9, 2005, effective Jun 13, 2005
Eurocopter France Model EC120 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC120 helicopters that requires inspecting the tail rotor drive shaft (drive shaft) damper half-clamps (half-clamps) to determine if they are centered on the friction ring, and if not correctly positioned, centering the half-clamps on the friction ring. This amendment is prompted by the discovery of half- clamps that were incorrectly positioned. The actions specified by this AD are intended to detect incorrect positioning of the drive shaft half-clamps, and to prevent interference of the half-clamps with the drive shaft, which could result in scoring on the drive shaft, failure of the drive shaft, and subsequent loss of control of the helicopter.
AD 2005-09-06 · published May 9, 2005, effective Jun 13, 2005
Agusta S.p.A. Model A119 Helicopters
This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A119 helicopters that requires visually inspecting each main transmission support fitting (fitting) attachment bolt (bolt) for a fracture, a crack, or looseness, and verifying the torque on each fitting bolt. This amendment is prompted by two incidents of fatigue failure of the bolts that secure the transmission rear support fittings to the helicopter. The actions specified by this AD are intended to detect a fracture, a crack, or looseness of a fitting bolt, and prevent fatigue failure of a fitting bolt and subsequent loss of control of the helicopter.
AD 2005-09-07 · published May 9, 2005, effective Jun 13, 2005
Agusta S.p.A. Model A109E Helicopters
This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters that requires visually inspecting each main transmission support fitting (fitting) attachment bolt (bolt) for a fracture, a crack, or looseness, and verifying the torque on each fitting bolt. This amendment is prompted by two incidents of fatigue failure of the bolts that secure the transmission rear support fittings to the helicopter. The actions specified by this AD are intended to detect a fracture, a crack, or looseness of a fitting bolt, and prevent fatigue failure of a fitting bolt and subsequent loss of control of the helicopter.
AD 2005-10-14 · published May 17, 2005, effective Jun 21, 2005
Eurocopter France Model AS355E, F, F1, F2, and N Helicopters
This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters. That AD currently requires replacing certain main or combiner gearboxes with airworthy gearboxes. Further investigation has shown that the main gearbox is not affected, and this amendment requires replacing a certain combiner gearbox with a modified airworthy gearbox. This amendment is prompted by a report of a freewheel unit slipping resulting in an engine overspeed and shutdown. Also, this amendment is prompted by the conclusion of the investigation, which finds the freewheel slippage is due to the surface treatment applied to certain freewheel rollers in the combiner gearbox. The actions specified by this AD are intended to prevent an engine overspeed, an engine shutdown, and subsequent loss of control of the helicopter.
AD 2005-10-12 · published May 18, 2005, effective Jun 2, 2005
Schweizer Aircraft Corporation Model 269C, C-1, and D Helicopters
This amendment adopts a new airworthiness directive (AD) for the Schweizer Aircraft Corporation (Schweizer) Model 269C, C-1, and D helicopters. This action requires inspecting, modifying, and testing the lateral control trim actuator assembly on certain serial-numbered helicopters. This amendment is prompted by three reported incidents of the inner spring tube separating from the lateral trim control housing resulting in a lateral cyclic control restriction. The actions specified in this AD are intended to prevent separation of the inner spring tube from the lateral trim control housing and the associated loss of trim control, increased local resistance to right cyclic stick movement, and an emergency landing or subsequent loss of control of the helicopter.
AD 2005-10-05 · published May 10, 2005, effective Jun 14, 2005
CFM International CFM56-5, -5B, and -5C Series Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for CFM International CFM56-5, -5B, and -5C series turbofan engines. This AD requires removing certain part number (P/N) air turbine starters from service. This AD results from several reports of uncontained failures of air turbine starters where high-energy particles were not contained within the containment feature of the starter. We are issuing this AD to prevent uncontained failures of air turbine starters, which could result in damage to the airplane.
AD 2005-10-13 · published May 18, 2005, effective Jun 22, 2005
Rolls-Royce Corporation (Formerly Allison Engine Company) 250-B17B, -B17C, -B17D, -B17E, -C20, -C20B, -C20F, -C20J, -C20S, and -C20W Turboprop and Turboshaft Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls- Royce Corporation (RRC) (formerly Allison Engine Company) 250-B17B, - B17C, -B17D, -B17E, -C20, -C20B, -C20F, -C20J, -C20S, and -C20W turboprop and turboshaft engines that do not have turbine energy absorbing ring, RRC part number (P/N) 23035175, or an equivalent FAA- approved serviceable turbine energy absorbing ring, installed. This AD requires installation of a turbine energy absorbing ring in the plane of the 1st stage turbine wheel. This AD results from an unacceptable rate of uncontained 1st stage turbine wheel failures. We are issuing this AD to minimize the risk of uncontained 1st stage turbine wheel fragments from causing damage to the aircraft or damage to the second engine on twin-engine installations, which could lead to loss of control and loss of the aircraft.
AD 2005-09-51 · published May 19, 2005, effective Jun 3, 2005
Turbomeca Arrius 2F Turboshaft Engines
This document publishes in the Federal Register an amendment adopting emergency airworthiness directive (AD) 2005-09-51 that we sent previously to all known U.S. owners and operators of certain Turbomeca Arrius 2F turboshaft engines. This AD requires before further flight, replacing the Module 2 on certain engines listed by serial number (SN) in this AD. This AD results from a report of the failure of a high pressure turbine (HPT) blade and damage to two other HPT blades in a Turbomeca Arrius 2F turboshaft engine. We are issuing this AD to prevent failure of the engine and subsequent loss of power.
AD 2005-10-16 · published May 19, 2005, effective Jun 3, 2005
General Electric (GE) CF6-80E1 Series Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for General Electric (GE) CF6-80E1 series turbofan engines that have an electronic control unit (ECU) with software version E.1.M. or earlier installed. This AD requires installing improved software for the ECU. This AD results from an uncommanded engine acceleration event caused by a failure of the ECU digital interface unit (DIU). We are issuing this AD to prevent an undetected failure of the ECU DIU, which could result in uncommanded acceleration to the overspeed limit without response to throttle commands. The airplane could then experience asymmetric thrust.
AD 2005-11-01 · published May 27, 2005, effective Jun 13, 2005
Turbomeca S.A. Arrius 1A Turboshaft Engines
The FAA is adopting a new airworthiness directive (AD) for Turbomeca S.A. Arrius 1A turboshaft engines. This AD requires initial and repetitive testing of the Free Turbine Overspeed Protection System. This AD results from an investigation into the Digital Electronic Control Unit (DECU) that revealed a malfunction of the Free Turbine Overspeed Protection System. This malfunction can exist despite the DECU passing all functional tests specified in the Engine Maintenance Manual. We are issuing this AD to prevent uncontained engine failure if a free turbine overspeed occurs.
AD 2004-25-16 R1 · published May 6, 2005, effective Jun 20, 2005
Kelly Aerospace Power Systems Part Number (P/N) 14D11, A14D11, B14D11, C14D11, 23D04, A23D04, B23D04, C23D04, or P23D04 Fuel Regulator Shutoff Valves (Formerly Owned by ElectroSystems, JanAero Devices, Janitrol, C&D Airmotive Products, FL Aerospace, and Midland-Ross Corporation)
The FAA is revising Airworthiness Directive (AD) 2004-25-16, which applies to aircraft equipped with a fuel regulator shutoff valve part number (P/N) 14D11, A14D11, B14D11, C14D11, 23D04, A23D04, B23D04, C23D04, or P23D04 used with B1500, B2030, B2500, B3040, B3500, B4050, or B4500 B-Series combustion heaters. AD 2004-25-16 currently requires you to repetitively inspect the fuel regulator shutoff valve (visually or by pressure test) for fuel leakage and replace the fuel regulator shutoff valve with an improved design replacement part with a manufacturer's date code of 02/02 or later if fuel leakage is found. AD 2004-25-16 also allows you to disable the heater as an alternative method of compliance. Since we issued AD 2004-25-16, we received several comments requesting a revision to paragraph (e)(2). Consequently, this AD retains the actions required in AD 2004-25-16 and revises the requirements in paragraph (e)(2) to remove a required action. We are issuing this AD to prevent failure of the fuel regulator shutoff valve, which could result in fuel leakage in aircraft with these combustion heaters. This failure could result in an aircraft fire.
AD 2005-08-06 · published May 10, 2005, effective Jun 2, 2005
CENTRAIR 101 Series Gliders
This document incorporates corrections to clarify the intent of Airworthiness Directive (AD) 2005-08-06, which was published in the Federal Register on April 19, 2005 (70 FR 20271). AD 2005-08-06 applies to all CENTRAIR 101 series gliders. This action clarifies the applicability to point out that the affected hinge pins were installed at manufacturer on serial numbers 101A600 through 101A637 and could be replaced on other serial number gliders with hinge pins that Centrair delivered between February 20, 1995, and February 28, 2001. We are re- issuing the AD in its entirety to help eliminate any confusion that this AD may have created.
AD 2005-10-23 · published May 23, 2005, effective Jun 30, 2005
DG Flugzeugbau GmbH Model DG-500MB Sailplanes and Glaser-Dirks Flugzeugbau GmbH Model DG-800B Sailplanes
The FAA adopts a new airworthiness directive (AD) for all DG Flugzeugbau GmbH Model DG-500MB sailplanes equipped with a Solo engine and Glaser-Dirks Flugzeugbau GmbH Model DG-800B sailplanes equipped with a Solo engine. This AD requires you to inspect the propeller for damage, specifically foam core separation, and replace any damaged propeller. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct damage to the propeller, which could result in failure of the propeller to perform properly. This failure could lead to reduced or loss of control of the sailplane.
