46 Airworthiness Directives: 38 airplane, 3 rotorcraft, 3 engine, 1 propeller, 1 appliance.
AD 2004-22-09 · published Nov 2, 2004, effective Dec 7, 2004
Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes. This AD requires a one-time high-frequency eddy current inspection for cracking of the attachment lugs of the aileron spring tab balance unit, and corrective actions if necessary. This AD is prompted by a report indicating that, during heavy turbulence, a pilot needed to apply aileron trim to maintain level flight because cracking of the upper inboard attachment lug of the aileron spring tab balance unit, probably due to corrosion, had caused permanent deflection of the spring tab and consequent aileron damage. We are issuing this AD to prevent diminished control of the airplane in turbulence or total loss of roll control for the affected wing.
AD 2004-22-10 · published Nov 2, 2004, effective Dec 7, 2004
Boeing Model 747-400 and -400F Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400 and -400F series airplanes. This AD requires a detailed inspection(s) for cracks and fractures of the side guide support fittings in the lower lobe cargo compartments; and applicable investigative/corrective actions and operational limitations, if necessary. This AD also requires a terminating action for the repetitive inspections. This AD is prompted by reports of cracked/fractured side guide support fittings in the aft, lower lobe cargo compartment. We are issuing this AD to prevent cracked/fractured side guide support fittings in the lower lobe cargo compartments, which could result in unrestrained cargo shifting in flight and damaging the airplane structure or systems, and consequent reduced controllability of the airplane.
AD 2004-22-15 · published Nov 4, 2004, effective Dec 9, 2004
Boeing Model 747-400 and -400D Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that currently requires installation of strap assemblies on the ceiling panels and rails that support the video monitors. For certain airplanes, this amendment requires replacement of certain plate assemblies within the ceiling panel strap assemblies with new, improved plate assemblies. This amendment also revises the applicability by adding airplanes. The actions specified by this AD are intended to prevent ceiling panels from falling into the passenger cabin area in the event of failure of certain latch assemblies on the ceiling panels, which could result in consequent injury to the flightcrew and passengers. This action is intended to address the identified unsafe condition.
AD 2004-22-16 · published Nov 4, 2004, effective Nov 19, 2004
Gulfstream Model GV and GV-SP Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Model GV and GV-SP series airplanes. This AD requires a one-time general visual inspection for contact or insufficient clearance between the crew oxygen bottle/supports and any wiring harness, and related investigative and corrective actions if necessary. This AD also requires, for certain airplanes, adjusting the wiring harness to obtain a minimum clearance between the crew oxygen bottle and wiring, and applying Teflon sheeting, as applicable; and for certain other airplanes, reworking certain wiring bundles. This AD is prompted by reports of insufficient clearance between certain wiring harnesses and the crew oxygen bottle on several in-production and in- service airplanes. We are issuing this AD to prevent chafing of the electrical wires of the wiring harness against the crew oxygen bottle, which could result in electrical shorting and possible fire in the underfloor structure of the airplane.
AD 2004-22-21 · published Nov 4, 2004, effective Dec 27, 2004
GROB-WERKE Model G120A Airplanes
The FAA adopts a new airworthiness directive (AD) for all GROB-WERKE (GROB) Model G120A airplanes. This AD requires you to repetitively inspect visually the area between the vertical stabilizer main spar and the nearby vertical stabilizer skin for any disbonding/ crack; repair any disbonding/crack found; and calculate weight and balance after any repair. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct any disbonding/crack in the area between the vertical stabilizer main spar and nearby stabilizer skin, which could result in possible structural failure. This failure could lead to difficulty in airplane flight control.
AD 2004-22-14 · published Nov 5, 2004, effective Dec 10, 2004
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Saab Model SAAB SF340A and SAAB 340B series airplanes. This AD requires an inspection of the elevator and aileron trim-tab fittings, and related investigative/corrective actions if necessary. This AD is prompted by reports of improperly installed rivets in the retainers that hold the elevator trim-tab bearings. We are issuing this AD to prevent the elevator and aileron trim-tab bearings from coming loose, which could result in excessive play in the elevator and aileron trim systems, and reduced controllability of the airplane.
AD 2004-22-17 · published Nov 9, 2004, effective Dec 14, 2004
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F airplanes, that requires an inspection of the connector cables for signs of arcing and/or signs of moisture penetration into the overhead decoder units (ODU), and replacement of the affected ODU(s) with a new ODU, if necessary. This action also requires modification and reidentification of the cable assemblies and the connect cable assemblies at shipside power to the ODU, ODU to ODU, and adjacent bag racks; and replacing certain connectors of the ODU and shipside power cable assemblies. The actions specified by this AD are intended to prevent moisture from entering through the rear of the connector of the ODUs located in the overhead baggage stowage racks, which could result in a short, damage to the connector pins, and consequent smoke and/or fire in the cabin. This action is intended to address the identified unsafe condition.
AD 2004-22-18 · published Nov 9, 2004, effective Dec 14, 2004
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires an inspection of the auto throttle servo (ATS) assembly and corrective actions if necessary. The actions specified by this AD are intended to prevent electrical shorting of the brake coils of the ATS, which could result in smoke in the cockpit and/or passenger cabin. This action is intended to address the identified unsafe condition.
AD 2004-22-19 · published Nov 9, 2004, effective Dec 14, 2004
McDonnell Douglas Model MD-11 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model MD-11 airplanes. This AD requires revising the cable connection stackups for mid-cabin terminal strips, replacing the terminal strips, and removing a nameplate, as applicable. This AD also requires an inspection for arcing damage in the mid-cabin area, and corrective actions if necessary. This AD is prompted by an incident in which arcing occurred between the power feeder cables and support bracket of the terminal strips. We are issuing this AD to prevent arcing damage to the terminal strips and damage to the adjacent structure, which could result in smoke and/or fire in the mid-cabin compartment.
AD 2004-22-20 · published Nov 9, 2004, effective Dec 14, 2004
McDonnell Douglas Model MD-11 and MD-11F Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model MD-11 and MD-11F airplanes. This AD requires replacement of low base terminal boards, related investigative action, and corrective actions if necessary. This AD is prompted by arcing between a power feeder cable and terminal board support bracket. We are issuing this AD to prevent arcing damage to the power feeder cables, terminal boards, and adjacent structure, which could result in smoke and/or fire in the cabin.
AD 2004-22-22 · published Nov 9, 2004, effective Dec 14, 2004
Airbus Model A310 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes; and Model C4-605R Variant F Airplanes (Collectively Called A300-600)
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A310 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes; and Model C4- 605R Variant F airplanes (collectively called A300-600). That AD currently requires modifying the ram air turbine (RAT) by replacing the ejection jack. This new AD requires a one-time inspection of the RAT ejection jack to determine the part number, and further investigative and corrective actions if necessary. This AD is prompted by the discovery of a rupture in the housing of one of the RAT ejection jacks installed as specified in the existing AD. We are issuing this AD to prevent rupture of the housing of the RAT ejection jack due to overpressure in the jack caused by overfilling the hydraulic fluid, and consequent failure of the RAT ejection jack. Failure of the ejection jack could result in a lack of hydraulic pressure or electrical power in an emergency.
AD 2004-22-23 · published Nov 9, 2004, effective Dec 14, 2004
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, that requires a one-time inspection of the shafts of the main landing gear (MLG) side-brace fittings to detect corrosion, and the forward and aft bushings in the left-hand and right-hand MLG side-brace fittings to detect discrepancies. This AD also requires corrective and related actions if necessary. This action is necessary to prevent fractures of the MLG side-brace fitting shafts, and possible collapse of the MLG. This action is intended to address the identified unsafe condition.
AD 2004-22-24 · published Nov 9, 2004, effective Dec 14, 2004
Boeing Model 707 and 720 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 707 and 720 series airplanes, that currently requires inspections of the upper and lower chords of the wing front and rear spars, repair if necessary, and application of corrosion inhibitor to the inspected areas. This amendment removes the requirements of the existing AD, requires new detailed inspections and new high frequency eddy current (HFEC) inspections for corrosion and cracking, and requires certain related follow-on and investigative actions, if necessary. This amendment also expands the area of inspection to include the dry bay areas. The actions specified by this AD are intended to find and fix corrosion and stress corrosion cracking of the upper and lower chords on the wing front and rear spars, which could result in reduced structural integrity of the wing. This action is intended to address the identified unsafe condition.
AD 2004-22-25 · published Nov 9, 2004, effective Dec 14, 2004
Boeing Model 767-200, -300, and -300F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200, -300, and -300F series airplanes, that requires a one-time inspection for discrepancies of all wire bundles, including certain power feeder cables, of the electrical system in the forward cargo compartment ceiling at certain stations; and corrective actions if necessary. This action is necessary to prevent damage to wire bundles, particularly those of the fuel quantity indication system (FQIS), which are located in the subject area. Damage of FQIS wires could cause arcing between those wires and power wires in the damaged wire bundle, and may lead to transmission of electrical energy into the fuel tank, which would result in a potential source of ignition in the fuel tank. This action is intended to address the identified unsafe condition.
AD 2004-22-26 · published Nov 9, 2004, effective Dec 14, 2004
Airbus Model A330, A340-200, and A340-300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330, A340-200, and A340-300 series airplanes. This AD requires repetitive inspections for evidence of corrosion and sheared attachment bolts of the sensor struts at flap track 4 on the left and right sides of the airplane; related investigative and corrective actions as necessary; and a terminating action for the repetitive inspections, by requiring the eventual replacement of all sensor struts with new, improved sensor struts that are less sensitive to corrosion. The actions specified by this AD are intended to prevent loss of the sensor strut function, resulting in the inability to detect flap drive disconnection at flap track stations 4 and 5, which could lead to separation of the outboard flap from the airplane, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-22-27 · published Nov 9, 2004, effective Dec 14, 2004
Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes, that requires a general visual inspection for sealant at the interface between the diagonal brace fitting and the aft bulkhead and at the four bolts common to the interface. It also requires applying sealant if none is present or if it is not continuous. This action is necessary to prevent flammable fluid in the upper or rear pylon areas from leaking past unsealed areas and onto a hot engine nozzle, which could result in ignition of the fluid, causing an undetected and uncontrollable fire to spread into the engine struts. This action is intended to address the identified unsafe condition.
AD 2004-22-28 · published Nov 9, 2004, effective Dec 27, 2004
Raytheon Aircraft Company Model B100 Airplanes
The FAA adopts a new airworthiness directive (AD) for certain Raytheon Aircraft Company (Raytheon) Model B100 airplanes. This AD requires you to drill holes in the hot lip tube "B" nuts, tighten the "B" nuts to specified torque ranges, and secure the "B" nuts with safety wire. This AD is the result of reports of loose "B" nuts on the engine inlet that may loosen and permit a leak in the engine inlet anti-ice system. We are issuing this AD to detect and correct loose "B" nuts on the engine inlet, which could result in failure of the engine inlet anti-ice system and consequent ice buildup. This failure and ice buildup could lead to an engine's ingestion of ice with loss of engine power or loss of engine.
AD 2004-23-01 · published Nov 9, 2004, effective Dec 27, 2004
Pilatus Aircraft Ltd. Model PC-7 Airplanes
The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes with any Lear Romec RR53710B type or Lear Romec RR53710K fuel booster pump (Pilatus part number 968.84.11.401; 968.84.11.403; or 968.84.11.404) installed. This AD requires you to check the airplane logbook to determine whether any installed fuel booster pump has been modified with spiral wrap to protect the wire leads and has the suffix letter "B" added to the serial number of the fuel booster pump identification plate. If any installed fuel booster pump has not been modified, you are required to inspect any installed fuel booster pump wire lead for defects; if defects are found, replace the fuel booster pump with a modified fuel booster pump with spiral wrap that protects the wire leads; or if no defects are found, install spiral wrap to protect any wire leads and add the suffix letter "B" to the serial number of the fuel booster pump identification plate. The pilot is allowed to do the logbook check. If the pilot can positively determine that the fuel booster pump wire leads with spiral wrap are installed following the service information and that the suffix letter "B" is included in the serial number of the fuel booster pump identification plate, no further action is required. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct any defects in the leads of any fuel booster pump, which could result in electrical arcing. This failure could lead to a fire or explosion in the fuel tank.
AD 2004-23-02 · published Nov 9, 2004, effective Dec 23, 2004
Raytheon Aircraft Company 65, 90, 99, 100, 200, and 1900 Series Airplanes, and Models 70 and 300 Airplanes
The FAA supersedes Airworthiness Directive (AD) 87-22-01 R1, which applies to certain Raytheon Aircraft Company (Raytheon) 65, 90, 99, 100, 200, and 1900 series airplanes, and Models 70 and 300 airplanes. AD 87-22-01 R1 currently requires you to repetitively inspect the nose landing gear (NLG) fork for cracks. If cracks are found that exceed certain limits, AD 87-22-01 R1 requires you to replace the NLG fork with a serviceable part or an improved NLG fork (Kit No. 101-8030-1 S or Kit No. 114-8015-1 S, as applicable). Incorporating an improved NLG fork kit terminates the repetitive inspection requirements. This AD is the result of FAA's policy (since 1996) to disallow airplane operation when known cracks exist in primary structure. This AD retains the inspection requirements of AD 87-22-01 R1, requires you to incorporate an improved NLG fork kit anytime a crack is found, and adds additional airplanes to the applicability section of this AD. We are issuing this AD to detect and correct cracks in the NLG fork, which could result in reduced structural integrity and inability of the NLG fork to carry design limit and ultimate loads. The reduced residual strength may cause separation failure of the NLG fork, which could result in loss of control of the airplane during take off, landing, and taxi operations.
AD 2004-23-04 · published Nov 15, 2004, effective Dec 20, 2004
Airbus Model A319 and A320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319 and A320 series airplanes, that requires a modification and replacement affecting all fuel tanks. All affected airplanes require the installation of fuses in the wiring of the fuel quantity indicating probes of all fuel tanks. Some affected airplanes also require replacement of the high-level sensors of the additional center tanks (ACTs) with new sensors. For all affected airplanes, these actions are necessary to prevent overheating of the fuel probes due to a short circuit. For some affected airplanes, these actions are necessary to prevent fuel leakage due to inadequate space for thermal expansion within the ACTs. Such conditions could result in fuel vapors or fuel contacting an ignition source and/or consequent fire/explosion in the center fuel tanks. These actions are intended to address the identified unsafe condition.
AD 2004-23-05 · published Nov 15, 2004, effective Dec 20, 2004
McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplanes, that requires reversing the ground stud installation of the main battery, and installing a new nameplate on the cover of the battery. This action is necessary to prevent damage to equipment or possible fire in the electrical/electronics equipment compartment due to electrical arcing between the ground stud of the main battery and adjacent structure. This action is intended to address the identified unsafe condition.
AD 2004-23-07 · published Nov 15, 2004, effective Dec 20, 2004
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that currently requires modification of certain fuselage support structure for the number 2 galley. This amendment requires modification of the same support structure using new methods based on new calculations. This amendment also expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent the galley from shifting, which could limit access to the galley door during emergencies, and result in injury to passengers and flightcrew. This action is intended to address the identified unsafe condition.
AD 2004-23-08 · published Nov 15, 2004, effective Dec 20, 2004
Airbus Model A300 B4-600R and A300 F4-600R Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to Airbus Model A300 B4-600R and A300 F4-600R series airplanes, that currently requires a one-time detailed inspection for damage of the center tank fuel pumps and fuel pump canisters, and replacement of damaged fuel pumps and fuel pump canisters with new or serviceable parts. That AD also requires repetitive detailed inspections of the fuel pumps and repetitive eddy current inspections of the fuel pump canisters, and replacement of damaged fuel pumps and fuel pump canisters with new or serviceable parts. This amendment mandates modification of the canisters of the center tank fuel pumps, which would terminate the repetitive inspections required by the existing AD. The actions specified by this AD are intended to prevent damage to the fuel pump and fuel pump canister, which could result in loss of flame trap capability and could provide a fuel ignition source in the center fuel tank. This action is intended to address the identified unsafe condition.
AD 2004-23-09 · published Nov 15, 2004, effective Dec 20, 2004
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and -145 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and -145 series airplanes, that currently requires determining whether a defective auxiliary power unit (APU) exhaust silencer is installed on the airplane; and corrective actions if necessary. For certain airplanes, this amendment requires modification of the APU exhaust silencer, and reidentification of the part number for the APU exhaust silencer once the modification is accomplished. For certain other airplanes, this amendment requires repetitive inspections to determine the structural integrity of the APU exhaust silencer; corrective actions, if necessary; eventual modification of the APU exhaust silencer, which terminates the repetitive inspections; and reidentification of the part number for the APU exhaust silencer once the modification is accomplished. This amendment also adds airplanes to the applicability of the existing AD. The actions specified by this AD are intended to prevent separation of the aft baffle assembly from the APU exhaust silencer and consequent separation of the assembly from the airplane, which could cause damage to other airplanes during takeoff and landing operations, or injury to people on the ground. This action is intended to address the identified unsafe condition.
AD 2004-23-10 · published Nov 15, 2004, effective Dec 20, 2004
Boeing Model 737-700 and -800 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-700 and -800 series airplanes. This AD requires doing an initial inspection for pitting and cracks of the lower skin panel at the lap joint; trimming the inner skin; installing exterior doublers; replacing the fuselage skin assembly; doing repetitive supplemental inspections; and repairing if necessary; as applicable. This AD is prompted by a report indicating that localized pitting in the lower skin panels was found during production on a limited number of airplanes. We are issuing this AD to detect and correct premature fatigue cracking at certain lap splice locations and consequent rapid decompression of the airplane.
AD 2004-23-11 · published Nov 15, 2004, effective Dec 20, 2004
McDonnell Douglas Model DC-9-14 and DC-9-15 Airplanes; and Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-9-14 and DC-9-15 airplanes; and Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. This AD requires repetitive high frequency eddy current inspections to detect cracks in the vertical radius of the upper cap of the center wing rear spar, and repair if necessary. This AD is prompted by reports of cracks in the upper cap of the center wing rear spar that resulted from stress corrosion. We are issuing this AD to detect and correct cracking of the left or right upper cap of the center rear spar, which would cause a possible fuel leak and structural failure of the upper cap, and result in reduced structural integrity of the airplane.
AD 2004-23-12 · published Nov 16, 2004, effective Dec 21, 2004
Boeing Model 757-200 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 and -300 series airplanes. This AD requires inspection of the guide arm assembly on passenger door number 1 left for a part mark to determine whether the guide arm assembly contains an adjuster rod, which was incorrectly manufactured, and replacement of any such adjuster rod. This action is necessary to prevent failure of the adjuster rod in the passenger door guide arm assembly, which could prevent the door from opening or closing during normal or emergency operations, resulting in the inability to evacuate the crew and passengers in an emergency. This action is intended to address the identified unsafe condition.
AD 2004-23-13 · published Nov 16, 2004, effective Dec 21, 2004
Airbus Model A330, A340-200, and A340-300 Series Airplanes
This amendment adopts a new airworthiness directive (AD); applicable to certain Airbus Model A330, A340-200, and A340-300 series airplanes; that requires inspecting the ram air turbine (RAT) actuator to determine its serial number; and re-identifying the RAT actuator, inspecting the RAT actuator to determine whether the rotary solenoids are in the correct position, and replacing the RAT actuator, as applicable. This action is necessary to prevent failure of the RAT actuator to deploy when necessary during flight, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-23-14 · published Nov 16, 2004, effective Dec 1, 2004
Boeing Model 767-200, -300, and -300F Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-200, -300, and -300F series airplanes. This AD requires reworking the surface of the ground stud brackets of the transformer rectifier unit (TRU) and the airplane structure mounting surface, and measuring the resistance from the bracket to the structure and the ground lug to the bracket using a bonding meter. This AD is prompted by a report of loss of all direct current (DC) power generation during a flight, due to inadequate electrical ground path between the ground bracket of the TRU and the structure. We are issuing this AD to prevent depletion of the main battery and consequent loss of all DC power, which could cause the loss of flight critical systems.
AD 2004-23-17 · published Nov 22, 2004, effective Dec 1, 2004
Mooney Airplane Company, Inc., Model M20M Airplanes
The FAA is adopting a new airworthiness directive (AD) to supersede Airworthiness Directive 91-03-15, which applies to certain Mooney Airplane Company, Inc., (Mooney) Model M20M airplanes. AD 91-03- 15 currently requires you to replace the tailpipe coupling with improved tailpipe coupling. Since we issued AD 91-03-15, a fire erupted in the lower left cockpit area on one of the airplanes affected by AD 91-03-15. The V-clamp that attaches the exhaust tailpipe to the turbocharger fell off, which allowed the exhaust tailpipe to detach from the turbocharger. Hot exhaust gases from the turbocharger outlet blasted the lower left firewall. This AD requires you to replace the existing radiant heat shield with the new improved design heat shield, deflector kit; replace the existing exhaust tailpipe-to-turbocharger V- band clamp with the new design V-band clamp; and modify the hydraulic brake fluid poly line. We are issuing this AD to prevent the V-clamp from detaching from the turbocharger and to prevent exposure of the firewall to hot exhaust gases, which could result in an in-flight fire. An in-flight fire could lead to loss of control of the airplane and passenger injury.
AD 2004-23-18 · published Nov 26, 2004, effective Jan 3, 2005
Airbus Model A319, A320, and A321 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This AD requires revising the airplane flight manual (AFM) to prohibit operators from performing CAT 2 or CAT 3 automatic landings or roll- outs at certain airports. This AD also provides for an optional terminating action for the AFM revision. This AD is prompted by data showing that the magnetic variation table installed in the Honeywell inertial reference system (IRS) is obsolete at certain airports. We are issuing this AD to prevent the airplane from departing the runway during a CAT 2 or CAT 3 automatic landing or roll-out, due to magnetic and IRS deviations.
AD 2004-23-19 · published Nov 26, 2004, effective Jan 3, 2005
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and -145 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and -45 series airplanes. The existing AD currently requires a one-time inspection to detect incorrect wiring of the electrical connectors to the pressure switches and cartridges on the fire extinguisher bottles for the engines and the auxiliary power unit (APU); disconnection and reconnection of the wiring, as necessary; and adjustment of the length of the harnesses on the fire extinguisher bottles to avoid future misconnections. This amendment requires additional adjustment of the length of the harnesses; installation of a color-coded identification system to avoid misconnections during maintenance; and a functional test of the engine fire extinguisher system. This amendment also expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent the issuance of erroneous commands or the receipt of erroneous information pertaining to the fire extinguisher system for the engines and the APU, which could result in the inability to put out a fire in an engine or in the APU. This action is intended to address the identified unsafe condition.
AD 2004-23-20 · published Nov 26, 2004, effective Jan 3, 2005
Airbus Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R Series Airplanes; and Model A300 C4-605R Variant F and A300 F4-605R Airplanes
The FAA is superseding an existing airworthiness directive (AD) that applies to all Airbus Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-605R, A300 B4-622R, and A300 F4-605R airplanes. That AD currently requires repetitive inspections for cracking in the area surrounding certain fuselage attachment holes, installation of new fasteners for certain airplanes, and certain follow-on corrective actions if necessary. This new AD requires modifying certain fuselage frames, which would terminate certain repetitive inspections. This AD also adds airplanes to the applicability. This AD is prompted by the development of a modification intended to prevent cracking of the center section of the fuselage, which could result in a ruptured frame foot and reduced structural integrity of the airplane.
AD 2004-23-21 · published Nov 26, 2004, effective Jan 3, 2005
McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) Airplanes; and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD- 88 airplanes. This amendment requires a general visual inspection for chafing of the power feeder cables of the auxiliary power unit (APU), and repair if necessary. This amendment also requires replacement of a support bracket located on the left side of the lower cargo compartment with a new "U" shaped bracket. This action is necessary to prevent chafing of the power feeder cables of the APU, which could result in electrical arcing to adjacent structure and consequent fire in the airplane. This action is intended to address the identified unsafe condition.
AD 2004-24-02 · published Nov 26, 2004, effective Dec 28, 2004
Ostmecklenburgische Flugzeugbau GmbH Model OMF-100-160 Airplanes
The FAA adopts a new airworthiness directive (AD) for certain Ostmecklenburgische Flugzeugbau GmbH (OMF) Model OMF-100-160 airplanes. This AD requires you to inspect the outside tube (cage) that supports the main landing gear leg for cracks, repair if cracks are found, and inspect the thickness of the tube if no cracks were found and reinforce the tube as necessary. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect, correct, and prevent future cracks in the outside tube of the main landing gear leg, which could result in structural failure of the fuselage tubing assembly. This failure could lead to loss of control of the airplane.
AD 2004-24-01 · published Nov 29, 2004, effective Dec 28, 2004
Bombardier Inc. Model (Otter) DHC-3 Airplanes
The FAA adopts a new airworthiness directive (AD) for all Bombardier Inc. Model (Otter) DHC-3 airplanes that have been modified by 524085 BC, Ltd. Supplemental Type Certificate (STC) Number ST01243NY or SA01243NY. This AD requires you to replace the existing Viking Air Ltd. elevator servo tab assembly with a redesigned Viking Air Ltd. elevator servo tab assembly. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Canada. There has been one failure of the elevator servo tab assembly. We are issuing this AD to prevent the structural failure of the elevator servo tab. This failure could lead to loss of control of the airplane.
AD 2004-24-07 · published Nov 29, 2004, effective Jan 3, 2005
Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires replacing the bracket for the wire bundle of the fuel quantity indicating system (FQIS), performing a general visual inspection of the FQIS wire bundle for damage, and doing corrective actions if necessary. This AD is prompted by a report of an incorrectly installed FQIS wire bundle. We are issuing this AD to prevent chafing of the FQIS wire(s) in the center fuel tank, which, when combined with a lightning strike or a power wire short to the FQIS wire(s), could result in arcing in the center fuel tank and consequent fuel tank explosion.
AD 2004-24-06 · published Nov 30, 2004, effective Jan 4, 2005
Saab AB, Saab Aerosystems Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes. This AD requires replacement of the retract actuator bracket attachment bolt (RABAB) of the main landing gear (MLG) with a new RABAB; reidentification of the MLG shock strut; an inspection for corrosion, fretting, or other damage of certain RABABs; and applicable corrective actions. The actions specified by this AD are intended to prevent failure of the RABAB, which could result in loosening of the actuator bracket and consequent failure of the MLG to retract, with considerable damage to other landing gear parts, including the MLG trunnion fitting. This action is intended to address the identified unsafe condition.
AD 2004-22-11 · published Nov 2, 2004, effective Dec 7, 2004
Eurocopter Deutschland GmbH Model EC135 P1, P2, T1, and T2 Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model EC135 P1, P2, T1, and T2 helicopters. That AD currently requires adding the AD or a statement to the Rotorcraft Flight Manual (RFM) informing the pilot to reduce power and land as soon as practicable if a thump-like sound followed by an unusual vibration occurs during flight. That AD also requires visually inspecting the main rotor drive torque strut assembly (strut) for a crack or a break, recording the inspections in the historical or equivalent record, re-marking and relocating the strut, as appropriate, and replacing any unairworthy strut with an airworthy strut. Also, that AD establishes life limits for certain struts and revises the life limit for other struts. This amendment requires the same actions as the existing AD except that it changes the visual inspection from a one-time inspection to daily inspections; reduces the life limit for aluminum struts; and eliminates the once-only transfer and remarking of certain struts. This amendment is prompted by an incident in which a pilot felt an in-flight increase in vibration and subsequent discovery of a failed strut. The actions specified by this AD are intended to prevent failure of a strut and subsequent loss of control of the helicopter.
AD 2004-22-13 · published Nov 2, 2004, effective Dec 7, 2004
Bell Helicopter Textron Canada Model 206L-1 and 206L-3 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (Bell) model helicopters that requires a one-time inspection of the adjustable stop screws of the magnetic brake assembly; repairing, as appropriate, certain mechanical damage to the cyclic and collective flight control magnetic brake arm assembly (arm assembly), if necessary; and installing the stop screw with the proper adhesive, adjusting the arm assembly travel and applying slippage marks. This amendment is prompted by reports that the magnetic brake adjustable screws have backed out, which limited travel of the arm assembly. The actions specified by this AD are intended to detect loose adjustable stop screws, that could result in limiting the travel of the cyclic and collective arm assembly, and subsequent loss of control of the helicopter.
AD 2004-23-15 · published Nov 22, 2004, effective Dec 7, 2004
MD Helicopters, Inc. Model MD900 Helicopters
This amendment adopts a new airworthiness directive (AD) for the MD Helicopters, Inc. (MDHI) Model MD900 helicopters. This action requires reducing the life limit of certain Notar fan system tension- torsion (TT) straps. This action also requires, at a specified time interval, removing each affected TT strap from the helicopter, doing a visual and x-ray inspection, and replacing any unairworthy part before further flight. Reporting the discovery of any unairworthy TT strap is also required. This amendment is prompted by two recent in-flight TT strap failures. The actions specified in this AD are intended to prevent failure of a TT strap resulting in loss of directional control and subsequent loss of control of the helicopter.
AD 2004-23-03 · published Nov 8, 2004, effective Nov 23, 2004
Rolls-Royce plc RB211 Trent 700 Series Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 700 series turbofan engines. This AD requires initial and repetitive borescope inspections of the high pressure-and-intermediate pressure (HP-IP) turbine internal and external oil vent tubes for coking and carbon buildup, and cleaning or replacing the vent tubes if necessary. This AD results from a report of a RB211 Trent 700 series engine experiencing a disk shaft separation, overspeed of the IP turbine rotor, and multiple blade release of IP turbine blades. Preliminary findings suggest these events resulted from an internal oil fire in the HP-IP turbine oil vent tubes due to coking and carbon buildup. This fire led to a second fire in the internal air cavity below the IP turbine disk drive shaft. We are issuing this AD to prevent internal oil fires due to coking and carbon buildup, that could cause uncontained engine failure and damage to the airplane.
AD 2004-24-05 · published Nov 24, 2004, effective Dec 29, 2004
Rolls-Royce Deutschland Ltd. & Co KG (formerly Rolls-Royce plc), Models Spey 555-15, 555-15H, 555-15N, and 555-15P Turbojet Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Deutschland Ltd. & Co KG (RRD) (formerly Rolls-Royce plc), models Spey 555-15, 555-15H, 555-15N, and 555-15P turbojet engines, with magnesium split low pressure (LP) compressor case, part number (P/ N) EU.73418A installed. This AD requires replacement of the magnesium split LP compressor case with a serviceable compressor case that is a combination of a steel front LP compressor case and a shortened split compressor case. This AD results from several reports of bird ingestion and LP compressor stage 1 rotor blade failures that have resulted in penetration of the magnesium LP compressor case, and damage to the airplane.
AD 2004-24-04 · published Nov 26, 2004, effective Jan 3, 2005
Rolls-Royce Corporation (Formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) (RRC) Models 250-C30R/3, -C30R/3M, -C47B, and -C47M Turboshaft Engines
The FAA is superseding an existing airworthiness directive (AD) for RRC models 250-C30R/3, -C30R/3M, -C47B, and -C47M turboshaft engines. That AD currently requires initial and repetitive electrical signal inspections of the hydromechanical unit (HMU) Power Lever Angle (PLA) potentiometer. This ad continues to require those inspections and adds replacement of the existing HMU with a new design HMU as a mandatory terminating action to the repetitive inspection requirements. This AD results from the manufacturer releasing a redesigned HMU that has a dual-element potentiometer. We are issuing this AD to prevent uncommanded and sudden changes in engine power.
AD 2004-23-16 · published Nov 22, 2004, effective Dec 7, 2004
McCauley Propeller Systems Five-Blade Propeller Assemblies
The FAA is adopting a new airworthiness directive (AD) for McCauley Propeller Systems propeller assemblies, part numbers (P/Ns) B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/114HCA-0, and C5JFR36C1104/L114HCA-0, installed on BAE Systems (Operations) Limited Jetstream Model 4100 series airplanes. This AD requires a one- time eddy-current inspection of the propeller hub for cracks, and if necessary, replacing the propeller assembly. This AD results from three reports of cracked hubs. We are issuing this AD to detect cracked hubs, which could cause failure of the propeller hub and loss of control of the airplane.
AD 2004-24-03 · published Nov 26, 2004, effective Jan 3, 2005
Hamilton Sundstrand Power Systems T-62T Series Auxiliary Power Units (APUs)
The FAA is adopting a new airworthiness directive (AD) for Hamilton Sundstrand Power Systems Models T-62T-46C12 and T-62T-40C14 (APS 500R) APUs with fuel filter housing assembly, part number (P/N) 4951627, 4951960, or 4952039, installed. This AD requires installation of a bracket to prevent a failed bypass button from protruding beyond the internal o-ring seal. This AD results from reports of leaks caused by cracked bypass buttons that protruded beyond the o-ring seal. We are issuing this AD to prevent a fire or explosion caused by a fuel leak from a failed bypass button on the fuel filter housing.
