37 Airworthiness Directives: 26 airplane, 3 rotorcraft, 5 engine, 1 propeller, 1 glider, 1 various.
AD 2006-18-04 · published Sep 1, 2006, effective Sep 1, 2006
Bombardier Model CL-600-2B16 (CL-604) Airplanes and Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B16 (CL- 604) airplanes and Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. These models may be referred to by their marketing designations as RJ100, RJ200, CRJ100, CRJ200, and CL-65. This AD requires revising the Emergency Procedures section of the airplane flight manual (AFM) to advise the flightcrew of additional procedures to follow in the event of stabilizer trim runaway. For certain airplanes, this AD also requires revising the Abnormal Procedures section of the AFM to advise the flightcrew of procedures to follow in the event of MACH TRIM, STAB TRIM, and horizontal stabilizer trim malfunctions. This AD results from reports of uncommanded horizontal stabilizer trim motion. We are issuing this AD to ensure that the flightcrew is advised of appropriate procedures to follow in the event of stabilizer trim runaway. Failure to follow these procedures could result in excessive uncommanded movement of the horizontal stabilizer trim actuator (HSTA) and loss of ability to use trim switches to override uncommanded movement or yoke disconnect switches to disconnect the HSTA, which could result in reduction of or loss of pitch trim control and consequent reduced controllability of the airplane.
AD 2006-18-05 · published Sep 6, 2006, effective Oct 11, 2006
McDonnell Douglas Model DC-9-14, DC-9-15, and DC-9-15F Airplanes; Model DC-9-21 Airplanes; Model DC-9-30 Series Airplanes; Model DC-9-41 Airplanes; and Model DC-9-51 Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas Model DC-9-10, DC-9- 20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. That AD currently requires a one-time inspection at a certain disconnect panel in the left forward cargo compartment to find contamination of electrical connectors and to determine if a dripshield is installed over the disconnect panel, and corrective actions if necessary. This new AD revises the applicability of the existing AD by removing certain airplanes and adding others. This AD results from a report of electrical arcing that resulted in a fire. We are issuing this AD to prevent contamination of certain electrical connectors, which could cause electrical arcing and consequent fire on the airplane.
AD 2006-18-06 · published Sep 6, 2006, effective Oct 11, 2006
Airbus Model A318, A319, A320, and A321 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 airplanes. This AD requires revising the Limitations section of the airplane flight manual (AFM); performing a one-time hardness test of certain ribs of the left- and right-hand engine pylons, as applicable, which would terminate the AFM limitations; and performing related corrective actions if necessary. This AD results from a report that certain stainless steel ribs installed in the engine pylon may not have been heat-treated during manufacture, which could result in significantly reduced structural integrity of the pylon. We are issuing this AD to detect and correct reduced structural integrity of the engine pylon, which could lead to separation of the engine from the airplane.
AD 2006-18-07 · published Sep 6, 2006, effective Oct 11, 2006
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model ERJ 170 airplanes. This AD requires replacing the very high frequency (VHF) antenna located in position 1 of the fuselage with a new, improved VHF antenna. This AD results from a report of the loss of all voice communications due to a lightning strike damaging all the VHF antennas. We are issuing this AD to prevent the loss of voice communication, which, when combined with the complexity of the national airspace system, could result in reduced flightcrew situational awareness, increased flightcrew workload, and increased risk of human error, and consequent reduced ability to maintain safe flight and landing of the airplane.
AD 2006-18-09 · published Sep 6, 2006, effective Sep 21, 2006
BAE Systems (Operations) Limited Model ATP Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to all BAe Systems (Operations) Limited Model ATP airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures; to incorporate new inspections to detect fatigue cracking of certain significant structural items (SSIs); and to revise life limits for certain equipment and various components. This new AD requires revising the ALS of the ICA to include additional and revised inspections of the fuselage. This AD results from the manufacturer review of fatigue test results that identified additional and revised inspections of the fuselage that are necessary in order to ensure the continued structural integrity of the airplane. We are issuing this AD to detect and correct fatigue cracking of certain structural elements, which could result in reduced structural integrity of the airplane and consequent rapid decompression of the airplane.
AD 2006-18-10 · published Sep 6, 2006, effective Sep 21, 2006
Airbus Model A340-541 and -642 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A340-541 and -642 airplanes. This AD requires a one-time inspection of the anti-stall valve sleeve of the ram air turbine (RAT) for proper installation, determining the part number of the modification plate on the hydraulic pump of the RAT, and follow-on corrective actions if necessary. This AD results from reports of failure of the anti-stall valve on the hydraulic pump of the RAT during scheduled ground tests. We are issuing this AD to prevent failure of the RAT hydraulic pump to supply adequate pressure to activate the RAT, and consequent loss of the RAT as a source of hydraulic and electrical power in an emergency situation.
AD 2006-18-12 · published Sep 8, 2006, effective Oct 13, 2006
Saab Model SAAB-Fairchild SF340A (SAAB/SF340A) and SAAB 340B Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB-Fairchild SF340A (SAAB/SF340A) and SAAB 340B airplanes, that requires modification and repetitive inspections of the hot detection system of the tail pipe harness of the engine nacelles. The actions specified by this AD are intended to prevent false warning indications to the flightcrew from the hot detection system due to discrepancies of the harness, which could result in an unnecessary aborted takeoff on the ground or in-flight engine shutdowns. This action is intended to address the identified unsafe condition.
AD 2006-18-13 · published Sep 8, 2006, effective Oct 13, 2006
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 repairing the force link assembly wire harness. This AD results from a report indicating that the wiring harness outer shield and insulation on the primary conductors may have been inadvertently cut due to an improper method used to remove the wiring outer jacket. We are issuing this AD to prevent the loss of the hardover prevention system (HOPS) in the roll axis due to a short circuit in the wiring harness, which could result in reduced controllability of the airplane.
AD 2006-18-16 · published Sep 8, 2006, effective Oct 13, 2006
Raytheon Aircraft Company Model 390 Airplanes
We are adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company Model 390 airplanes. This AD requires you to inspect the spigot bearing, part number (P/N) MS14104-16, for the proper position in the spigot fitting assembly and to install the wing spigot bearing retainer kit, P/N 390-4304-0001. We are issuing this AD to detect spigot bearings that are not positioned flush with the fitting assembly. This condition could result in the spigot bearing becoming disengaged from the fitting assembly, which could cause motion between the wing and the fuselage and degrade the structural integrity of the wing attachment to the fuselage. This could lead to wing separation and loss of control of the airplane.
AD 2006-18-17 · published Sep 8, 2006, effective Oct 13, 2006
Boeing Model 747-400, 747-400D, and 747-400F Series Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-400, 747-400D, and 747- 400F series airplanes. The existing AD currently requires reviewing airplane maintenance records; inspecting the yaw damper actuator portion of the upper and lower rudder power control modules (PCMs) for cracking, and replacing the PCMs if necessary; and reporting all airplane maintenance records review and inspection results to the manufacturer. This new AD expands the applicability and discontinues certain requirements of the existing AD. This AD adds repetitive inspections of the PCMs, and replacement of the PCMs if necessary. This AD results from manufacturer findings that the inspections required by the existing AD must be performed at regular intervals. We are issuing this AD to detect and correct cracking in the yaw damper actuator portion of the upper and lower rudder PCMs, which could result in an uncommanded left rudder hardover, consequent increased pilot workload, and possible runway departure upon landing.
AD 2006-18-51 · published Sep 8, 2006, effective Sep 8, 2006
Raytheon Aircraft Company Models 1900, 1900C, and 1900D Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company (RAC) Models 1900, 1900C, and 1900D airplanes. This AD contains the same information as emergency AD 2006- 18-51 and publishes the action in the Federal Register. This AD requires you to do a one-time visual inspection of both the left and right wing rear spar lower caps for cracking and other damage such as loose or missing fasteners; repair any cracks or damage found; and report any cracks or damage found to the FAA and RAC. This AD results from extensive cracks found in the wing rear spar lower caps and rear spar web of two of the affected airplanes. One of the airplanes also had missing fasteners. We are issuing this AD to detect and correct cracking and other damage in the wing rear spar lower caps of the affected airplanes before the cracks or damage lead to failure. Such a wing failure could result in the wing separating from the airplane with consequent loss of control.
AD 2006-18-11 · published Sep 12, 2006, effective Sep 27, 2006
Boeing Model 737-200, -300, -400, and -500 Series Airplanes Equipped With an Auxiliary Fuel System Installed in Accordance With Supplemental Type Certificate (STC) SA83NE, SA1078NE, SA725NE, ST00040NY, or ST01337NY
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-200, -300, -400, and -500 series airplanes equipped with an auxiliary fuel system installed in accordance with STC SA83NE, SA1078NE, SA725NE, ST00040NY, or ST01337NY. This AD requires a one-time deactivation of the auxiliary fuel system, repetitive venting of the auxiliary fuel tanks, and revising the Limitations section of the airplane flight manual to limit the maximum cargo weight. This AD results from a re-evaluation of the floor structure and cargo barriers conducted by the STC holder. We are issuing this AD to prevent structural overload of the auxiliary fuel tank support structure, which could cause the floor beams to fail and resultant damage to the primary flight controls and the auxiliary power unit fuel lines that pass through the floor beams, and consequent loss of control of the airplane. We are also issuing this AD to prevent structural overload of the cargo barriers, which could cause the barriers to fail, allowing the cargo to shift, resulting in possible damage to the auxiliary fuel tanks, residual fuel leakage, and consequent increased risk of a fire.
AD 2006-19-02 · published Sep 12, 2006, effective Oct 17, 2006
Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300-600 series airplanes. That AD currently requires repetitive eddy current inspections to detect cracks of the outer skin of the fuselage at certain frames, and repair or reinforcement of the structure at the frames, if necessary. That AD also requires eventual reinforcement of the structure at certain frames, which, when accomplished, terminates the repetitive inspections. This new AD requires, for airplanes that were previously reinforced but not repaired in accordance with the existing AD, a one- time inspection for cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, and repair if necessary. This AD results from a report that the previously required actions were not sufficient to correct cracking before the structural reinforcement was installed. We are issuing this AD to prevent such fatigue cracking, which could result in reduced structural integrity, and consequent rapid decompression of the airplane.
AD 2006-19-03 · published Sep 12, 2006, effective Oct 17, 2006
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 fabrication and installation of a wire harness guard in the right wheel well of the main landing gear (MLG), and related investigative and corrective actions as necessary. For certain airplanes, this AD also requires replacement of the electrical connectors of the auxiliary hydraulic pumps with improved electrical connectors and related investigative and corrective actions. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent damage to the wire support bracket and wiring of the auxiliary hydraulic pump and, for certain airplanes, water intrusion through the electrical connectors of the auxiliary hydraulic pump. These conditions could lead to a potential ignition source in the right wheel well of the MLG around the fuel tank, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
AD 2006-19-04 · published Sep 12, 2006, effective Oct 17, 2006
Honeywell RCZ-833J/K, -851J/K, and -854J Communication (COM) Units, Equipped with XS-852E/F Mode S Transponders; and Honeywell XS-856A/B and -857A Mode S Transponders; Installed on But Not Limited to Certain Transport Category Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Honeywell COM units and transponders, installed on but not limited to certain transport category airplanes. This AD requires a revision to the Normal Procedures section of the airplane flight manual to advise the flightcrew to check the status of the transponder after changing the air traffic control (ATC) code. This AD also requires replacing certain identification plate(s) with new plate(s), testing certain COM units or transponders as applicable, and corrective action if necessary. For certain airplanes, this AD requires replacing the transponders of certain COM units with new or modified transponders. For certain other airplanes, this AD requires installing a modification into certain transponders. This AD results from the transponder erroneously going into standby mode if the flightcrew takes longer than five seconds when using the rotary knob of the radio management unit to change the ATC code. We are issuing this AD to prevent the transponder of the COM unit from going into standby mode, which could increase the workload on the flightcrew and result in improper functioning of the traffic alert and collision avoidance system.
AD 2006-19-07 · published Sep 19, 2006, effective Oct 24, 2006
Airbus Model A330, A340-200, and A340-300 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330, A340-200, and A340-300 airplanes. This AD requires replacing the attachment landing assemblies of certain blow- down panels of the wing leading edges with new, improved landing assemblies. This AD results from several reports of full or partial loss of certain blow-down panels of the wing leading edges during flight. We are issuing this AD to prevent damage to the airplane and hazards to persons or property on the ground.
AD 2006-19-09 · published Sep 19, 2006, effective Oct 24, 2006
Raytheon Aircraft Company Model B300 Airplanes
We are adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company (RAC) Model B300 airplanes. This AD requires you to modify the cabin passenger seats by installing a modification kit on each passenger seat, removing the existing technical standard order (TSO) label, and re-identifying each modified passenger seat assembly with a new part number. This AD results from the seats not meeting the ultimate load requirements of 14 CFR part 23 during structural testing of the seat with design changes. We are issuing this AD to prevent the passenger seats from failing during emergency landing conditions when high inertial loadings occur. Passenger seat failure may result in occupant injury.
AD 2006-19-10 · published Sep 19, 2006, effective Oct 24, 2006
Cirrus Design Corporation Models SR20 and SR22 Airplanes
We are adopting a new airworthiness directive (AD) that supersedes AD 2005-17-19, which applies to certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. AD 2005-17-19 currently requires you to measure and adjust the crew seat break-over bolts and to replace the crew seat recline locks on both crew seats. Since we issued AD 2005-17-19, CDC developed new crew seat break-over pins to replace the old crew seat break-over bolts. Consequently, this AD retains the action from AD 2005-17-19 of replacing the crew seat recline locks on both seats and adds the action of replacing the crew seat break-over bolts with the new crew seat break-over pins on both seats. We are issuing this AD to prevent the crew seats from folding forward during emergency landing dynamic loads with consequent occupant injury.
AD 2006-19-11 · published Sep 20, 2006, effective Oct 25, 2006
Gippsland Aeronautics Pty. Ltd. Model GA8 Airplanes
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to require actions to correct the unsafe condition on these products.
AD 2006-19-12 · published Sep 25, 2006, effective Oct 30, 2006
Boeing Model 777-200 and -300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 and -300 series airplanes. This AD requires inspecting the lower web of the aft fairing of engine struts for any discoloration and doing any related investigative and corrective action if necessary; inspecting the heat shield castings for any damage and doing any corrective action if necessary; installing gap cover strips; and replacing insulation blankets with new insulation blankets. This AD results from a report that several discolored fairing lower webs and some damaged/deteriorated insulation blankets were found in the aft fairings of engine struts. We are issuing this AD to prevent cracking of lower webs of the aft fairings, which could result in flammable hydraulic fluid leaking onto or near an ignition source, and possibly result in an uncontrollable fire in the engine strut area.
AD 2006-20-01 · published Sep 28, 2006, effective Nov 2, 2006
Airbus Model A310 Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A310 airplanes. This AD requires revising the Limitations section of the airplane flight manual by incorporating restrictions for high altitude operations. This AD results from several incidents of pitch oscillations with high vertical loads that occurred during turbulence at high altitudes. We are issuing this AD to prevent pitch oscillations during turbulence, which could result in reduced controllability of the airplane.
AD 2006-20-02 · published Sep 28, 2006, effective Nov 2, 2006
Boeing Model 747 Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747 airplanes. That AD currently requires inspections to detect disbonding, corrosion, and cracking at the longitudinal rows of fasteners in the bonded skin panels in section 41 of the fuselage, and repair, if necessary. This new AD adds airplanes to the applicability, and requires new inspections of airplanes that may have Alodine-coated rivets installed. This AD results from a report of cracking discovered in a skin lap joint that was previously inspected using the eddy current method. We are issuing this AD to prevent rapid decompression of the airplane due to disbonding and subsequent cracking of the skin panels.
AD 2006-20-03 · published Sep 28, 2006, effective Nov 2, 2006
Airbus Model A319, A320, and A321 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 airplanes. This AD requires an inspection to determine if the stiff part of the girt and girt bar position of the forward left-hand and right-hand passenger doors is incorrect, and repair if necessary. This AD results from cases of girt bar disengagement from the floor fitting during deployment tests of slide rafts at the forward passenger doors. We are issuing this AD to prevent disengagement of the telescopic girt bar from the airplane when the door is opened in emergency situations, which could result in the inability to open the passenger door and to use the escape slide/raft at that door during an emergency evacuation of the airplane.
AD 2006-20-04 · published Sep 28, 2006, effective Nov 2, 2006
Bombardier Model DHC-8-102, -103, and -106 Airplanes, and Model DHC-8-200 and DHC-8-300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-102, -103, and -106 airplanes, and Model DHC-8-200 and DHC-8-300 series airplanes. This AD requires performing a one-time general visual inspection for non-conforming chain links of chain assemblies of the elevator trim system and gust lock system, and corrective actions if necessary. This AD also requires temporary revisions to the airplane flight manuals of the affected airplanes, which describe procedures for elevator trim checks. This AD results from reports of several failures of the elevator trim chain, due to hydrogen embrittlement. We are issuing this AD to prevent breakage of the elevator trim chain, which would prevent the actual position of the elevator trim tab from being annunciated to the flightcrew. Attempting to adjust the trim tab from the full nose up or full nose down position with a broken trim chain could result in misleading information relative to takeoff trim settings and consequent loss of control on takeoff.
AD 2006-20-05 · published Sep 28, 2006, effective Nov 2, 2006
BAE Systems (Operations) Limited Model BAe 146 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 airplanes. This AD requires repetitive inspections to measure the depth of chafing or scoring in the skin along the full length of the wing-to-fuselage fairing from forward to aft ends at the contact between the seal and fuselage, and related investigative/corrective actions if necessary. This AD results from a report of chafing in this area. We are issuing this AD to detect and correct such chafing or scoring, which could result in reduced structural integrity of the fuselage.
AD 2006-20-10 · published Sep 29, 2006, effective Nov 3, 2006
Air Tractor, Inc. Models AT-802 and AT-802A Airplanes
We are adopting a new airworthiness directive (AD) for certain Air Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A airplanes. This AD requires you to repetitively inspect the attach angles on the firewall mounted hopper rinse tank shelf for damage and/or cracks and replace damaged and/or cracked attach angles with steel attach angles. Replacing the attach angles with steel attach angles terminates the repetitive inspection requirement. Reports of an uncommanded change in the engine power setting caused by separation of the hopper rinse tank shelf from the firewall prompted this AD. We are issuing this AD to detect and correct damage and/or cracks in the attach angles on the firewall mounted hopper rinse tank shelf, which could result in failure of the attach angles. This failure could lead to shelf movement under maneuver load and shifting of the engine power cables, which could result in an uncommanded engine power setting change.
AD 2006-17-51 · published Sep 1, 2006, effective Sep 18, 2006
Agusta S.p.A. Model AB139 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2006-17-51, sent previously to all known U.S. owners and operators of Agusta S.p.A. (Agusta) Model AB139 helicopters by individual letters. This AD requires, before further flight and at specified intervals, certain visual inspections of each tailpipe assembly for a crack and for overheating. If you find areas of overheating, this AD also requires, before further flight, certain inspections for damage to the surrounding structure, outside of the cowling, and inside of each tailpipe assembly in certain areas. This AD also requires, before further flight, if you find a crack, replacing the tailpipe assembly with an airworthy tailpipe assembly. This AD is prompted by several reports of tailpipe assembly cracks. The actions specified by this AD are intended to prevent a fire due to the structure in the cowling area overheating, separation of a part of a tailpipe assembly, and subsequent loss of control of the helicopter.
AD 2006-19-05 · published Sep 11, 2006, effective Oct 16, 2006
California Department of Forestry, Overseas Aircraft Support Inc, San Joaquin Helicopters, Smith Helicopters, Southwest Florida Aviation International, West Coast Fabrications, Arrow Falcon Exporters Inc., AST Inc., Bell Helicopter Textron Inc., Global Helicopter Technology Inc., Hagglund Helicopters LLC, International Helicopters Inc., Richards Heavylift Helo Inc., Robin
This amendment adopts a new airworthiness directive (AD) for the specified restricted category type-certificated helicopters. The AD requires a review of the helicopter records to determine the Commercial and Government Entity (CAGE) code of the tail rotor (T/R) slider. If the T/R slider is FAA approved or has a certain legible CAGE code, this AD requires no further action. If you cannot determine whether the T/R slider is FAA approved and it has no stamped CAGE code, an illegible stamped CAGE code, or an affected CAGE code, the AD also requires, before further flight and at specified intervals, magnaflux inspecting the T/R slider for a crack. If a crack is found, the AD requires, before further flight, replacing the T/R slider with an airworthy T/R slider. The AD also requires replacing the T/R slider with an airworthy T/R slider on or before accumulating 1,000 hours time-in-service (TIS) or on or before 12 months, whichever occurs first. This amendment is prompted by two accidents attributed to sub-standard T/R sliders that failed during flight. The actions specified by this AD are intended to prevent failure of a T/R slider, loss of T/R control, and subsequent loss of control of the helicopter.
AD 2006-19-01 · published Sep 12, 2006, effective Sep 27, 2006
Eurocopter Model AS350B, B1, B2, B3, BA, D, and AS355E Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter helicopters. This action requires, within 10 hours time-in-service (TIS), inspecting the tapered housing of each main servo-control (MSC) for a crack. If no crack is found, this AD requires, before further flight, retorquing the upper ball-end attachment nut of the MSC. If a crack is found, this AD requires, before further flight, replacing the MSC with an airworthy MSC. This amendment is prompted by the discovery of cracks in the tapered housings of MSCs. The actions specified in this AD are intended to detect a crack in the MSC tapered housing and to prevent loss of the attachment of the MSC to the upper attachment yoke, loss of the main rotor control, and subsequent loss of control of the helicopter.
AD 2006-18-14 · published Sep 8, 2006, effective Oct 13, 2006
Rolls-Royce Deutschland Ltd & Co KG Tay 650-15 and Tay 651-54 Turbofan Engines
The FAA is superseding an airworthiness directive (AD) for Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 650-15 and Tay 651-54 turbofan engines. That AD currently establishes cyclic life limits for certain part number (P/N) stage 1 high pressure turbine (HPT) discs and stage 1 low pressure turbine (LPT) discs operating under certain flight plan profiles. This AD requires calculating and re-establishing the achieved cyclic life of stage 1 HPT discs, P/N JR32013 or P/N JR33838, and stage 1 LPT discs, P/N JR32318A, that have been exposed to different flight plan profiles. This AD also requires removing from service those stage 1 HPT discs and stage 1 LPT discs operated under Tay 650-15 engine flight plan profiles A, B, C, and D, and operated under Tay 651-54 engine datum flight profile, at reduced cyclic life limits, using a drawdown schedule. This AD results from RRD updating their low-cycle-fatigue analysis for stage 1 HPT discs and stage 1 LPT discs and reducing their cyclic life limits. We are issuing this AD to prevent cracks leading to turbine disc failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2006-19-06 · published Sep 14, 2006, effective Sep 29, 2006
Pratt & Whitney Canada Corp. Engines
The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (P&WC) Models PW118, PW118A, PW118B, PW119C, PW120, PW120A, PW121, PW121A, PW123, PW123B, PW123C, PW123D, PW123E, PW124B, PW125B, PW127, and PW127E turboprop engines with certain propeller shafts installed. This AD requires before further flight, replacing certain serial-numbered propeller shafts, and performing initial and repetitive visual inspections on others. This AD results from two reports of through-cracks in the propeller shaft. We are issuing this AD to detect through-cracks in the propeller shaft. Through-cracks at the No. 19 bearing area of the propeller shaft could result in uncontained engine failure and damage to the airplane.
AD 2006-20-07 · published Sep 28, 2006, effective Nov 2, 2006
Rolls-Royce Corporation Models 250-C30, 250-C40, and 250-C47 Series Turboshaft Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (RRC) models 250-C30, 250-40, and 250-C47 series turboshaft engines with a third-stage turbine wheel, part number (P/N) 6898663 or P/N 23065843 installed, or a fourth-stage turbine wheel, P/N 6892764 or P/N 23066744, installed. This AD adds an additional life limit for third- and fourth-stage turbine wheels. This AD results from analysis by RRC of failures of third-stage turbine wheels. We are issuing this AD to prevent loss of power, possible engine shutdown, or uncontained engine failure.
AD 2006-20-06 · published Sep 29, 2006, effective Oct 16, 2006
General Electric Company CF34-10E Series Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-10E series turbofan engines. This AD requires removing the main fuel pump (MFP) inlet strainer from certain MFPs, installing a certain replacement flange as an interim repair, and performing initial and repetitive visual inspections of the main fuel filter. This AD results from three reports of release of the tripod support legs on the MFP inlet strainer, leading to engine in-flight shutdown. We are issuing this AD to prevent engine in-flight shutdown due to MFP malfunctions.
AD 2006-20-09 · published Sep 29, 2006, effective Nov 3, 2006
Lycoming Engines (L)O-360, (L)IO-360, AEIO-360, O-540, IO-540, AEIO-540, (L)TIO-540, IO-580, and IO-720 Series Reciprocating Engines.
The FAA is adopting a new airworthiness directive (AD) for certain Lycoming Engines (L)O-360, (L)IO-360, AEIO-360, O-540, IO-540, AEIO-540, (L)TIO-540, IO-580, and IO-720 series reciprocating engines. This AD requires replacing certain crankshafts. This AD results from reports of 23 confirmed failures of similar crankshafts in Lycoming Engines 360 and 540 series reciprocating engines. We are issuing this AD to prevent failure of the crankshaft, which will result in total engine power loss, in-flight engine failure, and possible loss of the aircraft.
AD 2006-18-15 · published Sep 8, 2006, effective Sep 25, 2006
Hartzell Propeller Inc. ( )HC-( )2Y( )-( ) Series Propellers
The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller Inc. ( )HC-( )2Y( )-( ) series propellers with non- suffix serial number (SN) propeller hubs installed on Lycoming O-, IO-, LO-, and AEIO-360 series reciprocating engines. This AD requires initial and repetitive eddy current inspections (ECI) of the front cylinder half of the propeller hub for cracks and removing cracked hubs from service before further flight. In addition, this AD allows installation of an improved design propeller hub (suffix SN "A" or "B") as terminating action to the repetitive ECI. This AD results from a report of a propeller blade separating from a propeller hub. We are issuing this AD to prevent failure of the propeller hub causing blade separation and subsequent loss of airplane control.
AD 2006-19-08 · published Sep 19, 2006, effective Oct 10, 2006
Stemme GmbH & Co. KG Model STEMME S10-VT Sailplanes
The FAA is adopting a new airworthiness directive (AD) for certain Stemme GmbH & Co. KG Model STEMME S10-VT sailplanes. This AD requires you to do a one-time inspection of all exhaust bends (each cylinder 1 to 4) in the area of the curvature bend near the cylinder flange, replace any damaged exhaust pipes found, and recondition the heat protection wrapping. This AD results from deformations and cracks found at an exhaust bend during maintenance work. We are issuing this AD to detect and correct cracks in the exhaust pipes. Damaged exhaust pipes could cause exhaust gases to expand into the engine compartment and/or carbon monoxide (CO) to leak into the cockpit section.
AD 2006-18-08 · published Sep 6, 2006, effective Oct 11, 2006
Goodyear Aviation Tires, Part Number 217K22-1, Installed on Various Transport Category Airplanes, Including But Not Limited to Bombardier Model BD-700-1A10 and BD-700-1A11 Airplanes; and Gulfstream Model G-1159, G-1159A, G-1159B, G-IV, GIV-X, GV, and GV-SP Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain aviation tires installed on various transport category airplanes. This AD requires a one-time inspection of the nosewheel tires to determine if they are within a designated serial number range, and replacement if necessary. This AD results from reports of tread separations and tread-area bulges on the nosewheel tires. We are issuing this AD to prevent tread separation from a nosewheel tire during takeoff or landing, which could result in compromised nosewheel steering or ingestion of separated tread by an engine, and consequent reduced controllability of the airplane on the runway or in the air.
