54 Airworthiness Directives: 40 airplane, 5 rotorcraft, 5 engine, 1 propeller, 1 appliance, 1 glider, 1 various.
AD 2005-19-28 · published Oct 3, 2005, effective Oct 18, 2005
Airbus Model A330-301, -321, -322, -341, and -342 Airplanes; and Model A340-200 and A340-300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-301, -321, -322, -341, and -342 airplanes; and Model A340-200 and A340-300 series airplanes. This AD requires repetitive inspections for cracks in the aft face of the rear spar at the area adjacent to the bolt holes and the end of the build slot, and repair if necessary. The AD also provides an optional terminating action for the repetitive inspections. This AD results from a report that, during fatigue tests of the wing, cracks were found in the vertical web of the rear spar between ribs 1 and 2 having initiated at the build slot. We are issuing this AD to detect and correct fatigue cracking in the vertical web of the wing rear spar, which could result in reduced structural integrity of the wing.
AD 2005-20-07 · published Oct 4, 2005, effective Oct 19, 2005
Airbus Model A330-300 Series Airplanes
The FAA adopts a new airworthiness directive (AD) for certain Airbus Model A330-300 series airplanes. This AD requires reinforcing the structure of the center fuselage by installing external stiffeners (butt straps) at frame (FR) 53.3 on the fuselage skin between left-hand and right-hand stringer 13, and related investigative actions. This AD results from a report that, during fatigue tests of the fuselage, cracks initiated and grew at the circumferential joint of FR53.3. We are issuing this AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage.
AD 2005-20-09 · published Oct 4, 2005, effective Oct 19, 2005
BAE Systems (Operations) Limited Model ATP Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model ATP airplanes. This AD requires doing an inspection of each bolt attaching the aft isolators to both engine subframes and replacing bolts if necessary. This AD results from reports of failures of the bolts attaching the aft isolators to the engine subframe. We are issuing this AD to prevent failure of the bolts attaching the aft isolators to the engine subframe, which may result in an engine separating from the airplane.
AD 2005-20-10 · published Oct 4, 2005, effective Oct 19, 2005
Airbus Model A330-243, -341, -342, and -343 Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-243, -341, -342, and -343 airplanes. This AD requires revising the airplane flight manual to provide the flightcrew with new, ground ice-shedding procedures during long taxi periods in certain icing conditions. This AD results from reports of engine damage to the blades of the first stage of the intermediate pressure compressor due to ice accumulation. We are issuing this AD to prevent engine damage due to ice accumulation, which could result in an engine shutdown and cause the flightcrew to divert to the nearest available airport.
AD 2005-20-18 · published Oct 4, 2005, effective Nov 8, 2005
Boeing Model 747-100, -200B, -200F, -200C, -100B, -300, -100B SUD, -400, -400D, and -400F Series Airplanes; and Model 747SR Series Airplanes
The FAA is superseding two existing airworthiness directives (AD), which apply to certain Boeing transport category airplanes. One AD currently requires doing certain inspections to detect cracks and corrosion around the lower bearing of the actuator attach fittings of the inboard and outboard flaps; repairing if necessary; and either overhauling the fittings or replacing them, which ends certain repetitive inspections. The other AD currently requires certain other inspections to detect discrepancies of the actuator attach fittings of the flaps, and follow-on and corrective actions if necessary, which ends the repetitive inspections of the first AD. For certain airplanes, this AD requires new inspections for discrepancies of the actuator attach fittings of the flaps, and follow-on and corrective actions if necessary, which ends the repetitive inspections of both existing ADs. For all airplanes, this AD requires repetitive overhaul/replacements of the actuator attach fittings of both the inboard and outboard flaps. This AD results from reports of cracks of the actuator attach fittings of the trailing edge flaps. We are issuing this AD to prevent cracking and other damage of the actuator attach fittings of the trailing edge flaps, which could result in abnormal operation or retraction of a trailing edge flap, and possible loss of controllability of the airplane.
AD 2004-19-06 R1 · published Oct 5, 2005, effective Nov 1, 2004
Boeing Model 767-200, -300, and -300F Series Airplanes
The FAA is revising an existing airworthiness directive (AD) that applies to all Boeing Model 767-200, -300, and -300F series airplanes. The existing AD currently requires inspections to detect cracking or corrosion of the fail-safe straps between the side fitting of the rear spar bulkhead at body station 955 and the skin; and follow- on/corrective actions. The existing AD results from reports of cracked and/or corroded fail-safe straps at body station (BS) 955 on Boeing Model 767-200 series airplanes. We issued the existing AD to detect and correct fatigue cracking or corrosion of the fail-safe straps, which could result in cracking of adjacent structure and consequent reduced structural integrity of the fuselage. This new AD revises the applicability of the existing AD to reduce the number of affected airplanes. We are issuing this AD to detect and correct fatigue cracking or corrosion of the fail-safe straps, which could result in cracking of adjacent structure and consequent reduced structural integrity of the fuselage.
AD 2005-20-13 · published Oct 5, 2005, effective Nov 9, 2005
Boeing Model 727 Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 727 airplanes. This AD requires a one-time inspection of the lower lobe frames of body section 43 to find open holes between stringers 17L and 17R and to record their location; repetitive high frequency eddy current (HFEC) inspections for cracks of all open holes; and related investigative and corrective actions if necessary. This AD also includes an optional terminating action of installing rivets in all open tooling holes and all unused lining holes, which would terminate the repetitive open-hole HFEC inspections once a hole is plugged with a rivet. This AD results from reports of cracks at open tooling holes in the lower lobe frames of body section 43. We are issuing this AD to detect and correct cracks in the frames, which could result in cracks in the skin panels and rapid decompression of the airplane.
AD 2005-20-16 · published Oct 5, 2005, effective Nov 9, 2005
Boeing Model 737-100, -200, and -200C Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, and -200C series airplanes. This AD requires a one-time detailed inspection for cracking of the lugs of the inboard attach fittings of the wing leading edge slat tracks at slat numbers 2 and 5; prior or concurrent actions for certain airplanes; repetitive high-frequency eddy current (HFEC) inspections for cracking of the lug surfaces of those inboard attach fittings if necessary; and replacement of the attach fittings with new, improved fittings. This AD results from reports of damage to the lugs of certain inboard attach fittings of the leading edge slat tracks. We are issuing this AD to prevent a lifted slat, which, if the airplane performs any non-normal maneuver during takeoff or landing at very high angles of attack, could lead to the loss of the slat and reduced control of the airplane.
AD 2005-20-17 · published Oct 5, 2005, effective Nov 9, 2005
Airbus Model A319-100 Series Airplanes; Model A320-111 Series Airplanes; Model A320-200 Series Airplanes; and Model A321-100 and -200 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus airplane models, as specified above. This AD requires modifying the parking brake system to automatically restore the normal brake if the parking brake pressure decreases below a certain threshold. This AD results from a report of failure of the parking brake while the airplane was on the holding point of the runway before takeoff, leading to a runway departure. We are issuing this AD to ensure normal braking is available to prevent possible runway departure in the event of failure of the parking brake.
AD 2005-20-31 · published Oct 5, 2005, effective Oct 5, 2005
Honeywell Flight Management System (FMS) One Million Word (1M or 700K) Data Bases (9104 Cycle or Earlier), as Installed in, but Not Limited to, McDonnell Douglas Model MD-11 and MD-11F Airplanes, Boeing Model 747-400 Series Airplanes, and Boeing Model 757 and 767 Airplanes
The FAA is rescinding an existing airworthiness directive (AD) that applies to Honeywell FMS one million word (1M or 700K) data bases (9104 cycle or earlier) as installed in, but not limited to McDonnell Douglas Model MD-11 and MD-11F airplanes, Boeing Model 747-400 series airplanes, and Boeing Model 757 and 767 airplanes. That AD requires a revision to the FAA-approved Airplane Flight Manual (AFM) and installation of a placard to prohibit the use of Nondirectional Beacon (NDB) approaches for landing. That AD was prompted by an anomaly in the Honeywell FMS one million word (1M or 700K) data bases (9104 cycle or earlier). We issued that AD to prevent an airplane deviating from the published approach to the runway, which could lead to premature ground contact before reaching the runway. Since we issued that AD, we have determined that the Honeywell FMS one million word (1M or 700K) databases (9104 cycle or earlier) no longer exist on any of the affected airplanes.
AD 2005-20-14 · published Oct 6, 2005, effective Nov 10, 2005
Airbus Model A300 B4-620, A310-304, A310-324, and A310-325 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-620, A310-304, A310-324, and A310-325 airplanes. This AD requires installing fused adaptors between the external wiring harness and the in-tank wiring at the connectors on the fuel tank wall of the auxiliary center tank (ACT). This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent an ignition source in the ACT, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
AD 2005-20-15 · published Oct 6, 2005, effective Nov 10, 2005
McDonnell Douglas Model DC-10-10 and DC-10-10F Airplanes; Model DC-10-15 Airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) Airplanes; Model DC-10-40 and DC-10-40F Airplanes; Model MD-10-10F and MD-10-30F Airplanes; and Model MD-11 and MD-11F Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This AD requires an inspection of the rudder pedal torque tube assembly for cracking; an inspection of the torque tube assembly to determine the thickness of the torque tube wall, if necessary; and replacing the rudder torque tube with a new or serviceable rudder torque tube, if necessary. This AD results from a report of a broken rudder pedal torque tube. We are issuing this AD to prevent failure of a rudder pedal torque tube, which could result in loss of rudder control and nose wheel steering controlled by the rudder pedal, and consequent reduced controllability of the airplane.
AD 2005-20-19 · published Oct 6, 2005, effective Oct 21, 2005
BAE Systems (Operations) Limited Model ATP Airplanes
The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model ATP airplanes. This AD requires one-time inspections for corrosion of the engine sub-frame tubes in zone 1 and of the engine attachment struts in zone 5, and corrective action if necessary. This AD results from reports of reduced thickness in localized areas of the engine sub-frame tubes due to corrosion, and reports that corrosion may also exist in the engine attachment struts in zone 5. We are issuing this AD to prevent failure of the engine sub- frame tubes or the engine attachment struts, which could result in separation of an engine from the airplane.
AD 2005-20-20 · published Oct 6, 2005, effective Oct 21, 2005
Airbus Model A330-301, -321, -322, -341, and -342 Airplanes; and Model A340-200 and A340-300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-301, -321, -322, -341, and -342 airplanes; and Model A340-200 and A340-300 series airplanes. This AD requires installing lockplates on the main landing gear (MLG) and center landing gear (CLG) wheel assemblies, as applicable, to keep the tie bolts in position in the wheel assembly in the event of a tie bolt failure. This AD results from reports of tie bolts that were broken or missing from the MLG wheel assembly; in some cases the wheels have ruptured and caused damage to other equipment in the adjacent area. We are issuing this AD to prevent damage to the wheel assembly and equipment in the area adjacent to the MLG and CLG, which could result in a decrease in braking function and possible runway over-run.
AD 2005-20-21 · published Oct 6, 2005, effective Oct 21, 2005
Fokker Model F27 Mark 050 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Fokker Model F27 Mark 050 airplanes. This AD requires repetitive visual checks for oil leaks of both engines between the spinner and the engine cowling, and directly behind the heated intake lip of the engine; repetitive inspections for oil leaks at the feathering pump on both engines; and corrective actions if necessary. This AD results from reports of oil leakage at the engine feathering pump. We are issuing this AD to prevent oil loss from the feathering pump, which could cause the engine to shut down in flight.
AD 2005-20-22 · published Oct 6, 2005, effective Oct 21, 2005
BAE Systems (Operations) Limited Model ATP Airplanes
The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model ATP airplanes. This AD requires repetitive inspections for environmental damage, including corrosion, of the fuselage and wing structure, and corrective actions if necessary. This AD results from information indicating the potential for environmental damage of the fuselage and wing structure. We are issuing this AD to detect and correct such damage, including corrosion, in the fuselage and wing structure, which could result in cracking and consequent reduced structural integrity of the fuselage and wing structure.
AD 2005-20-24 · published Oct 12, 2005, effective Nov 9, 2005
SOCATA-Groupe AEROSPATIALE Model TBM 700 Airplanes
The FAA adopts a new airworthiness directive (AD) for certain SOCATA--Groupe AEROSPATIALE (SOCATA) Model TBM 700 airplanes. This AD requires you to inspect the fuselage skin in the VHF1 antenna mounting area for cracks and loose rivets. This AD also requires you to modify the area if you find cracks or loose rivets. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. We are issuing this AD to detect and correct cracks in the fuselage skin, which could result in loss of aircraft pressurization. Loss of aircraft pressurization could lead to flight crew incapacitation.
AD 2005-20-25 · published Oct 12, 2005, effective Nov 9, 2005
The Cessna Aircraft Company Models 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425, and 441 Airplanes
The FAA adopts a new airworthiness directive (AD) for certain The Cessna Aircraft Company (Cessna) Models 401, 401A, 401B, 402, 402A, 402B, 402C, 404, 411, 411A, 414, 414A, 421, 421A, 421B, 421C, 425, and 441 airplanes equipped with certain avionics bus circuit breaker switches. This AD requires you to inspect the avionics bus circuit breaker switch to determine the date code and replace any without a date code. This AD also imposes a 1,000-hour safe life limit on avionics bus circuit breaker switches with a date code earlier than 0434. This AD results from reports of smoke and a burning smell in the cockpit. We are issuing this AD to prevent failure of the avionics bus circuit breaker switch, which could result in smoke and a burning smell in the cockpit. This failure could lead to reduced ability to control the airplane.
AD 2005-20-27 · published Oct 12, 2005, effective Oct 27, 2005
Airbus Model A340-211, -212, -311, and -312 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A340-211, -212, -311, and -312 airplanes. This AD requires an initial rotating probe inspection and initial and repetitive ultrasonic inspections for discrepancies of the first fastener hole of the horizontal flange of the keel beam on previously modified airplanes, installation of new fasteners, and corrective action if necessary. This AD results from a report that certain inspections done before accomplishing the modification of the lower keel beam fitting and forward lower shell connection, revealed cracking that was outside the modification limits specified in the service bulletin; the cracking was repaired by installing a titanium doubler. We are issuing this AD to find and fix discrepancies of the fastener holes of the horizontal flange of the keel beam, which could result in reduced structural integrity of the fuselage.
AD 2005-20-28 · published Oct 12, 2005, effective Nov 16, 2005
Airbus Model A319-100 Series Airplanes; Model A320-111 Airplanes; Model A320-200 Series Airplanes, and Model A321-100 and -200 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus airplane models, as specified above. This AD requires modifying the floor proximity emergency escape path marking system. This AD results from information that the existing system design for interconnection of the emergency power supply units of the floor proximity emergency escape path marking system does not provide adequate floor path lighting and marking for safe evacuation of the airplane in the event of an emergency. We are issuing this AD to prevent inadequate lighting and marking of the escape path, which could delay or impede the flightcrew and passengers when exiting the airplane during an emergency landing.
AD 2005-20-29 · published Oct 12, 2005, effective Nov 16, 2005
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SP, and 747SR Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 300, 747SP, and 747SR series airplanes. This AD requires repetitive inspections to detect cracks in various areas of the upper deck floor beams, and repair if necessary. This AD results from fatigue testing that revealed severed upper chords of the upper deck floor beams due to fatigue cracking. We are issuing this AD to detect and correct cracking in the upper chords of the upper deck floor beams. Undetected cracking could result in large deflection or deformation of the upper deck floor beams, resulting in damage to wire bundles and control cables for the flight control system, and reduced controllability of the airplane. Multiple adjacent severed floor beams could result in rapid decompression of the airplane.
AD 2005-20-30 · published Oct 12, 2005, effective Nov 16, 2005
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SP, and 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 repetitive inspections to detect cracks in various areas of the fuselage internal structure, and repair if necessary. This new AD requires repetitive inspections of additional areas of the fuselage internal structure, and related investigative/ corrective actions if necessary. This new AD also removes certain requirements from the existing AD. This AD results from fatigue testing of the fuselage structure of a Boeing Model 747SR series airplane. We are issuing this AD to prevent the loss of the structural integrity of the fuselage, which could result in rapid depressurization of the airplane.
AD 2005-20-32 · published Oct 12, 2005, effective Nov 16, 2005
Airbus Model A330-200 and -300 and A340-200 and -300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-200 and -300 and A340-200 and -300 series airplanes. This AD requires inspecting to determine the part number and serial number of the left- and right-hand elevator assemblies, performing related investigative and corrective actions if necessary, and re- protecting the elevator assembly. This AD results from reports that areas on the top skin panel of the right-hand elevator have disbonded due to moisture penetration. We are issuing this AD to prevent disbonding of the elevator assembly, which could reduce the structural integrity of the elevator and result in reduced controllability of the airplane.
AD 2005-20-33 · published Oct 12, 2005, effective Nov 16, 2005
Boeing Model 727, 727C, 727-100, and 727-100C Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727, 727C, 727-100, and 727-100C series airplanes. This AD requires repetitive inspections of the frame inner chord, outer chord, and web of the forward and aft edge frames of the lower lobe forward cargo door (FCD) cutout, and corrective action if necessary. The actions specified by this AD are intended to detect and correct fatigue cracking of the forward and aft edge frames of the lower lobe FCD cutout, which could result in the loss of the FCD and rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
AD 2005-20-34 · published Oct 12, 2005, effective Oct 27, 2005
British Aerospace Model HS 748 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain British Aerospace Model HS 748 airplanes. This AD requires relocating the battery earth posts located on the nose landing gear (NLG) pintle webs. This AD results from an accident in which the nose landing leg, together with the pintle webs, detached from the airplane. As a result, the battery earth return cables were severed from their earth posts. We are issuing this AD to prevent loss of safety critical services including fuel shut-off and nacelle fire extinguishing services.
AD 2005-20-35 · published Oct 12, 2005, effective Oct 27, 2005
Airbus Model A320-111 Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A320-111 airplanes. The existing AD currently requires repetitive inspections for cracking in the front and rear faces and at the crown fittings of the upper stringers of the center wing box and applicable repairs. This new AD requires continuing the repetitive inspections at revised thresholds and intervals, and applicable repairs. This AD results from a manufacturer survey of airplanes affected by the existing inspection program that led to the consequent revision of the thresholds and intervals of the repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the upper stringers of the center wing box, which could lead to loss of structural integrity of the wing.
AD 2005-20-36 · published Oct 12, 2005, effective Nov 16, 2005
Airbus Model A320-111 Airplanes; and Model A320-200, A321-100, and A321-200 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A320-111 airplanes; and Model A320-200, A321-100, and A321-200 series airplanes. This AD requires installing a bonding lead between the low pressure valve and the adjacent pipe assembly in each wing. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent an ignition source for fuel vapor in the wing, which could result in fire or explosion in the adjacent wing fuel tank.
AD 2005-20-37 · published Oct 12, 2005, effective Nov 16, 2005
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ, -135ER, -135KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes
The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model EMB-135 airplanes and Model EMB-145, -145ER, -145MR, - 145LR, -145XR, -145MP, and -145EP airplanes. This AD requires repetitive detailed inspections for surface bruising of the main landing gear (MLG) trailing arms and integrity of the MLG pivot axle sealant, and corrective actions if necessary. This AD also provides for optional terminating action for the repetitive detailed inspections. This AD results from a report of a fractured axle of the trailing arm of the MLG due to corrosion of the axle. We are issuing this AD to prevent a broken trailing arm and consequent failure of the MLG, which could lead to loss of control and damage to the airplane during takeoff or landing.
AD 2005-20-39 · published Oct 13, 2005, effective Nov 17, 2005
Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires examining the airplane's maintenance records to determine if the main landing gear (MLG) has been overhauled and if Titanine JC5A (also known as Desoto 823E508) corrosion- inhibiting compound ("CIC") was used during the overhaul. For airplanes for which the maintenance records indicate that further action is necessary, or for airplanes on which CIC JC5A may have been used during manufacture, this AD requires a one-time detailed inspection for discrepancies of certain components of the MLG, and corrective action if necessary. This AD results from twelve reports of severe corrosion on one or more of three components of the MLG. We are issuing this AD to prevent collapse of the MLG, or damage to hydraulic tubing or the aileron control cables, which could result in possible departure of the airplane from the runway and loss of control of the airplane.
AD 2005-20-40 · published Oct 13, 2005, effective Nov 17, 2005
Boeing Model 757-200, -200CB, and -200PF Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200CB, and -200PF series airplanes. This AD requires an inspection of each trailing edge flap transmission assembly to determine the part number and serial number, and related investigative and corrective actions and part marking if necessary. This AD results from a report indicating that cracked flap transmission output gears have been discovered during routine overhaul of the trailing edge flap transmission assemblies. We are issuing this AD to prevent an undetected flap skew, which could result in a flap loss, damage to adjacent airplane systems, and consequent reduced controllability of the airplane.
AD 2005-20-41 · published Oct 13, 2005, effective Nov 17, 2005
Boeing Model 757-200, -200PF, and -300 Series Airplanes, Powered by Pratt & Whitney PW2000 Series Engines
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200PF, and -300 series airplanes, powered by Pratt & Whitney PW2000 series engines. This AD requires repetitive inspections for loose or damaged components of the support brackets and associated fasteners for the hydraulic lines located in the nacelle struts, and any related investigative and corrective actions. This AD results from reports of damage and subsequent failure of the support brackets and associated fasteners for the hydraulic lines located internal to the upper fairing cavity of the nacelle struts. We are issuing this AD to prevent such failure, which, in conjunction with sparking of electrical wires, failure of seals that would allow flammable fluids to migrate to compartments with ignition sources, or overheating of the pneumatic ducts beyond auto-ignition temperatures, could result in an uncontained fire.
AD 2005-21-06 · published Oct 21, 2005, effective Nov 25, 2005
Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires repetitive inspections of the aft pressure bulkhead web for fatigue cracks, crack indications, discrepant holes, and corrosion; and repair if necessary. This AD results from reports of fatigue cracks in the aft pressure bulkhead web. We are issuing this AD to detect and correct such fatigue cracks, which could result in a rapid decompression of the airplane.
AD 2005-22-02 · published Oct 25, 2005, effective Nov 17, 2005
Gippsland Aeronautics Pty. Ltd. Model GA8 Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Gippsland Aeronautics Pty. Ltd. (Gippsland) Model GA8 airplanes. This AD requires you to repetitively inspect the upper and lower grooves of the forward cargo door slide for cracks, excessive wear, and excessive width. This AD also requires you to replace the forward cargo door slide if any of the above conditions are found during any inspection. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. We are issuing this AD to prevent failure of the forward cargo door slide caused by cracks, excessive wear, or excessive width. This failure could result in the cargo door detaching from the airplane in flight, potentially causing damage by hitting the back end of the airplane.
AD 2005-22-04 · published Oct 26, 2005, effective Dec 12, 2005
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires you to determine (maintenance records check and/or inspection) whether certain nose landing gear (NLG), main landing gear (MLG), and MLG shock absorber assemblies with a serial number beginning with "AM" are installed, and, if installed, would require you to replace them with ones without the "AM." 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 the NLG, MLG, and MLG shock absorber assemblies that are affected by hydrogen embrittlement, which could result in failure of the landing gear. This failure could lead to nose or main landing gear collapse during operation with consequent loss of airplane control.
AD 2005-22-05 · published Oct 26, 2005, effective Nov 30, 2005
Airbus Model A320-111, -211, -212, and -231 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A320-111, -211, -212, and -231 airplanes. This AD requires, for certain airplanes, modifying the cables and access holes to the inner tank fuel pumps; and, for certain other airplanes, inspecting the fuel pump access holes and modifying the access holes, if necessary. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent chafing of the fuel pump cables, which could result in electrical arcing and possible ignition of fuel vapors and consequent explosion of the fuel tank.
AD 2005-22-06 · published Oct 26, 2005, effective Nov 30, 2005
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. This AD requires doing a one-time high-frequency eddy current inspection and repetitive detailed inspections for cracks in the frame web of main entry door number 1; and repairing the door frame web if necessary. This AD also provides for optional terminating action for the repetitive inspections. This AD is prompted by reports of cracking at the upper aft corner of the cutout for main entry door number 1 in the station 488 frame web. We are issuing this AD to detect and correct cracks in the frame web. These cracks could cause the frame to break and lead to rapid decompression of the airplane.
AD 2005-22-07 · published Oct 26, 2005, effective Nov 30, 2005
Boeing Model 757-200, -200PF, and -300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200PF, and -300 series airplanes. This AD requires inspecting for damage of the ground brackets, ground wires, and terminal lugs of the auxiliary power unit (APU) battery and the APU start transformer rectifier unit (TRU) as applicable; and corrective and related investigative actions. This AD results from reports indicating that during inspections on two airplanes, the ground brackets for the APU battery were found damaged. We are issuing this AD to detect and correct a damaged electrical bonding surface of the APU battery and APU start TRU ground connections, which could cause overheating of the ground connections and lead to possible consequent ignition of the adjacent insulating blankets.
AD 2005-22-08 · published Oct 26, 2005, effective Nov 30, 2005
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ, -135ER, -135KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER airplane models as identified above. This AD requires modifying the total air temperature (TAT) sensor heating system. This AD also allows replacing the fully automated digital electronic control (FADEC) assemblies with new or modified assemblies as an additional means of compliance. This AD results from a report indicating that the FADEC unit failed to compensate for ice accretion on the engine fan blades due to a false temperature signal from the TAT sensor to the FADEC. We are issuing this AD to prevent failure of the TAT sensor, which could result in insufficient thrust to take off or (if coupled with the loss of an engine during takeoff) to abort the takeoff in a safe manner, and consequent reduced controllability of the airplane.
AD 2005-22-09 · published Oct 28, 2005, effective Nov 14, 2005
Aerospatiale Model ATR42 and ATR72 Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Aerospatiale Model ATR42 and ATR72 airplanes. This AD requires a one- time inspection to determine the part number or markings of the fuel quality indicator (FQI) and replacement of any FQI having an incorrect part number. This AD results from a report that an FQI having an incorrect part number was installed on a Model ATR72 airplane. We are issuing this AD to ensure that a correct FQI is installed. An incorrect FQI could result in fuel starvation to the engine and consequent engine shutdown during flight.
AD 2005-22-10 · published Oct 31, 2005, effective Dec 5, 2005
Airbus Model A320-111 Airplanes, and Model A320-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111 airplanes, and Model A320- 200 series airplanes, that requires a detailed inspection of the tail cone triangle to determine its position, and corrective actions if necessary. This action is necessary to prevent excessive vibrations of the elevators, which could result in reduced structural integrity and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2005-20-38 · published Oct 13, 2005, effective Oct 28, 2005
Bell Helicopter Textron Model 212, 412, and 412EP Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron (Bell) model helicopters modified with Aeronautical Accessories, Inc. (AAI), Supplemental Type Certificate (STC) SH2820SO or that have the affected AAI Parts Manufacturer Approval (PMA) parts installed. This action requires inspecting a certain part-numbered reservoir assembly adapter (adapter) for the counter bore depth (dimension D). If the dimension D of the adapter exceeds .860 inch, before further flight, this AD requires replacing the reservoir assembly and adapter with airworthy parts. This amendment is prompted by a report of a rupture of an adapter during nitrogen charging because of inadequate wall thickness for the operating pressures. The actions specified in this AD are intended to prevent the rupture of an adapter, uncontrolled jetting of pressurized gas from the nitrogen bottle, and subsequent injury to occupants or damage to the helicopter.
AD 2005-21-02 · published Oct 17, 2005, effective Nov 1, 2005
MD Helicopters, Inc. Model 369D, 369E, 369F, 369FF, 500N, and 600N Helicopters
This amendment supersedes an existing airworthiness directive (AD) for the MD Helicopters, Inc. (MDHI) Model 369A, H, HE, HM, HS, D, and E helicopters with a certain part-numbered main rotor blade (blade) and modified with a Helicopter Technology Company, LLC (HTC), Supplemental Type Certificate (STC) No. SR09172RC, SR09074RC, or SR09184RC. That AD currently requires recording on the component history card or equivalent record (record) each torque event (TE) on each blade, inspecting both surfaces of the blade, and replacing any cracked blade with an airworthy blade. Also, that AD establishes life limits for certain part-numbered blades. This amendment revises the model applicability, adds MDHI part-numbered blades, removes any reference to the life limits of the blades, changes the requirements for inspecting the blades, and revises the STC applicability. This amendment also provides that compliance with portions of certain documents constitutes alternative methods of compliance with portions of this AD, contains editorial changes for clarification, and makes some corrections. This amendment is prompted by additional reports of cracked blades and by the comments received in response to AD 2003-24- 01. The actions specified in this AD are intended to detect fatigue cracking of the blade to prevent blade failure and subsequent loss of control of the helicopter.
AD 2005-21-03 · published Oct 17, 2005, effective Nov 21, 2005
Bell Helicopter Textron Canada Model 206A, A-1, B, B-1, L, L-1, L-3, L-4 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (BHTC) model helicopters that requires, before the first flight of each day, checking the tail rotor blade (blade) root doublers (doublers) for an edge void or de- bond on both sides of each blade, and if an edge void or de-bond is found, replacing the unairworthy blade with an airworthy blade. This AD also requires replacing any affected serial-numbered blade with an airworthy blade. This amendment is prompted by reports of de-bond of the doublers due to inadequate surface preparation resulting in poor adherence of the doublers. The actions specified by this AD are intended to prevent loss of a blade, loss of tail rotor control, and subsequent loss of control of the helicopter.
AD 2005-21-04 · published Oct 17, 2005, effective Nov 21, 2005
Bell Helicopter Textron Model 47D1, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A and Coastal Helicopters, Inc. Model OH-13H (Tomcat Mark 5A, 6B, 6C) Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron (Bell) Model 47D1, 47G, 47G-2, 47G-2A, 47G-2A- 1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A and Coastal Helicopters, Inc. Model OH-13H (Tomcat Mark 5A, 6B, 6C) helicopters that have a certain scissors assembly or weld assembly scissors bracket installed. The AD requires, within 60 days, determining and recording the total hours time-in-service (TIS) for each Parts Manufacturer Approval (PMA)-produced scissors assembly and weld assembly scissors bracket and establishes a life limit for each affected part. This amendment is prompted by the need to establish a life limit on scissors assemblies and weld assembly scissors brackets produced under PMA No. PQ808SW or installed per Supplemental Type Certificate (STC) No. SH2772SW. The actions specified by this AD are intended to establish a life limit to prevent using a scissors assembly or weld assembly scissors bracket past it's life limit, which could result in failure of the part and subsequent loss of control of the helicopter.
AD 2005-22-01 · published Oct 26, 2005, effective Nov 10, 2005
Sikorsky Aircraft Corporation Model S-76A, B, and C Helicopters
This amendment adopts a new airworthiness directive (AD) for the Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, B, and C helicopters. This action requires certain inspections of the main rotor lower bifilar arm assembly in the attachment area around the lower bifilar lugs for a crack. If a crack is found on any bifilar lug, this AD requires replacing the bifilar arm assembly with an airworthy bifilar arm assembly. If no crack is found, this AD requires a one-time test for the required torque on the lug nuts and, if necessary, applying the required torque and conducting the torque stabilization tests. This amendment is prompted by four reports of cracked bifilars. The actions specified in this AD are intended to prevent failure of a bifilar lug, damage to the main rotor control system, and subsequent loss of control of the helicopter.
AD 2005-20-11 · published Oct 3, 2005, effective Oct 18, 2005
Rolls-Royce Corporation (RRC) (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) Models 250-C28, -C28B, and -C28C 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) (RRC) Models 250-C28, - C28B, and -C28C turboshaft engines. This AD requires a onetime visual inspection of the seal joint in each passage between airfoils at the hub and shroud of third-stage turbine wheels, part number (P/N) 6899383. This AD results from reports of three failed third-stage turbine wheels and from the manufacturer's analysis of those failures. We are issuing this AD to prevent loss of power and uncommanded engine shutdown due to failure of the third-stage turbine wheel.
AD 2005-20-23 · published Oct 4, 2005, effective Nov 8, 2005
Rolls-Royce plc RB211 Trent 875, 877, 884, 884B, 892, 892B, and 895 Series Turbofan Engines
The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 875, 877, 884, 892, 892B, and 895 series turbofan engines. That AD currently requires repetitive application of dry film lubricant (DFL) to low pressure compressor (LPC) fan blade roots. This AD requires the same actions but at more frequent intervals than the existing AD. This AD also adds the Trent 884B engine to the list of engine models affected, adds a fan blade part number (P/N) to the affected list of fan blades, and relaxes the initial DFL repetitive application compliance time for certain fan blades that have never been removed from the disk. This AD results from discovering DFL in worse condition than anticipated on fan blades fitted to disks previously run for a significant period. This AD also results from the need to update the list of engine models affected, and to update the list of fan blade part numbers affected. We are issuing this AD to prevent LPC fan blade loss, which could result in an uncontained engine failure and possible aircraft damage.
AD 2005-21-01 · published Oct 17, 2005, effective Nov 21, 2005
Pratt & Whitney JT8D-200 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD) that applies to Pratt & Whitney (PW) JT8D-200 series turbofan engines. That AD currently requires installing and periodically inspecting individual or sets of certain part number (P/N) temperature indicators on the No. 4 and 5 bearing compartment scavenge oil tube and performance of any necessary corrective action. This AD requires installing and periodically inspecting two temperature indicators on all PW JT8D-200 series turbofan engines, including those incorporating high pressure turbine (HPT) containment hardware. This AD results from five uncontained HPT shaft failures. We are issuing this AD to prevent oil fires and the resulting fracture of the HPT shaft which can result in uncontained release of engine fragments; engine fire; in-flight engine shutdown; and possible airplane damage.
AD 2005-21-05 · published Oct 21, 2005, effective Nov 25, 2005
Rolls-Royce Deutschland Ltd & Co KG (Formerly Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH) Models BR700-710A1-10 and BR700-710A2-20 Turbofan Engines
The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly Rolls- Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH) models BR700- 710A1-10 and BR700-710A2-20 turbofan engines. That AD currently requires initial and repetitive visual and ultrasonic inspections of fan discs, part numbers (P/Ns) BRR18803, BRR19248, and BRR20791 for cracks, and if necessary, replacement with serviceable parts. This ad requires those same inspections for discs having old design P/N fan blades installed, and, extends the inspection interval for fan discs having new design P/N fan blades installed. Also, this AD adds as optional terminating action to the inspections, installation of certain P/N new fan discs, certain P/N new fan blades, and engine fan speed (N1) Keep Out Zone software. This AD results from a revised RRD service bulletin (SB) that introduces relaxed inspection intervals for certain P/N combinations of fan discs and fan blades, and introduces improved design fan discs and fan blades.
AD 2005-22-03 · published Oct 25, 2005, effective Nov 29, 2005
Rolls-Royce Corporation (Formerly Allison Engine Company) 501-D22A, 501-D22C, and 501-D22G Turboprop Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (RRC) (formerly Allison Engine Company) 501- D22A, 501-D22C, and 501-D22G turboprop engines. This AD requires a onetime inspection for proper metal hardness of certain 1st stage, 2nd stage, 3rd stage, and 4th stage turbine wheels. This AD results from a report of a turbine wheel found to be over dimensional limits, caused by improper metal hardness. We are issuing this AD to prevent uncontained turbine wheel failure, leading to damage of the airplane and total loss of engine power.
AD 2005-20-12 · published Oct 13, 2005, effective Oct 28, 2005
Dowty Aerospace Propellers Type R321/4-82-F/8, R324/4-82-F/9, R333/4-82-F/12, and R334/4-82-F/13 Propeller Assemblies
The FAA is superseding an existing airworthiness directive (AD) for Type R321/4-82-F/8, R324/4-82-F/9, R333/4-82-F/12, and R334/4- 82-F/13 propeller assemblies. That AD currently requires initial and repetitive ultrasonic inspections of propeller hubs, part number (P/N) 660709201. This AD requires the same initial and repetitive ultrasonic inspections, but reduces the initial and repetitive compliance times for Type R334/4-82-F/13 propeller assemblies when used on Construcciones Aeronauticas, S.A. (CASA) 212 airplanes. This AD results from a report of a hub separation on a CASA 212 airplane. We are issuing this AD to prevent propeller hub failure due to cracks in the hub, which could result in loss of control of the airplane.
AD 2005-20-26 · published Oct 12, 2005, effective Nov 16, 2005
Aviointeriors S.p.A. (formerly ALVEN), Series 312 Box Mounted Seats
The FAA is adopting a new airworthiness directive (AD) for Aviointeriors S.p.A. (formerly ALVEN), series 312 box mounted seats. This AD requires initial and repetitive inspections of the seat attachments for cracks, and if necessary, replacing the attachments. This AD results from 10 reports of cracked attachments of series 312 box mounted seats. We are issuing this AD to prevent series 312 box mounted seats from detaching from the passenger compartment floor, which could result in injury to the occupant of the seat, and prevent evacuation of passengers in the event of an emergency.
AD 2003-19-14 R2 · published Oct 12, 2005, effective Nov 30, 2005
BURKHART GROB LUFT-UND RAUMFAHRT GmbH & CO KG Models G103 TWIN ASTIR, G103A TWIN II ACRO, and G103C TWIN III ACRO Sailplanes
The FAA is revising Airworthiness Directive (AD) 2003-19-14 R1, which applies to certain BURKHART GROB LUFT--UND RAUMFAHRT GmbH & CO KG (GROB) Models G103 TWIN ASTIR, G103A TWIN II ACRO, and G103C TWIN III ACRO sailplanes. AD 2003-19-14 R1 requires you to modify the airspeed indicators, install flight speed reduction and aerobatic maneuver restrictions placards (as applicable), and revise the flight and maintenance manuals. AD 2003-19-14 R1 approves simple aerobatic maneuvers for Model G103A TWIN II ACRO sailplanes and provides an option for modifying the rear fuselage for Models G103A TWIN II ACRO and G103C TWIN III ACRO sailplanes to terminate the flight limitation restrictions for aerobatic maneuvers. This AD retains all the actions from AD 2003-19-14 R1 for Models G103A TWIN II ACRO and G103C TWIN III ACRO and reinstates certain operating limits for Model G103 TWIN ASTIR sailplanes. We are issuing this AD to prevent damage to the fuselage during limit load flight, which could result in reduced structural integrity. This condition could lead to loss of control of the sailplane.
AD 2003-17-07 R1 · published Oct 3, 2005, effective Sep 24, 2003
Various Transport Category Airplanes Manufactured by McDonnell Douglas
The FAA is revising an existing airworthiness directive (AD) that applies to various transport category airplanes manufactured by McDonnell Douglas. We issued that AD to require a one-time test of the fire extinguishers for the engine and auxiliary power unit (APU), as applicable, to determine the capability of the Firex electrical circuits to fire discharge cartridges, and troubleshooting actions if necessary. This new AD removes certain transport category airplanes from the applicability of the existing AD. This AD results from reports indicating that fire extinguishers for the engine and auxiliary power unit had failed to discharge when commanded. We are issuing this AD to prevent failure of the fire extinguishers to fire discharge cartridges, which could result in the inability to put out a fire in an engine or in the APU.
