Title 14 published on 2012-01-01
The following are only the Rules published in the Federal Register after the published date of Title 14.
For a complete list of all Rules, Proposed Rules, and Notices view the Rulemaking tab.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
We are superseding an existing emergency airworthiness directive (EAD) for Eurocopter France (Eurocopter) Model AS350B3 helicopters with certain part-numbered laminated half-bearings (bearings) and tail rotor (T/R) blades installed. The existing EAD currently requires installing two placards and revising the Rotorcraft Flight Manual (RFM). The EAD also requires certain checks and inspecting and replacing, if necessary, all four bearings. Finally, the EAD requires a one-time removal and inspection of the bearings, and replacing the bearings if necessary. Since we issued that EAD, we have determined that newly-designed helicopters with other part-numbered T/R blades may be affected by this unsafe condition and that the requirements should allow the bearing removal and inspection to be performed before the last flight of the day. This superseding AD removes the bearing and T/R blade part numbers (P/N) from the applicability paragraph and clarifies when the bearing removal and inspection is required. The actions are intended to prevent vibration due to a failed bearing, failure of the T/R, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Turbomeca S.A. Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, and 1S1 turboshaft engines. This AD requires daily post-flight checks of the engine tachometer's unit cycle-counting feature. This AD also requires ground-run functional checks within every 1,000 operating hours. This AD was prompted by detailed analysis and review of the accuracy of the engine's tachometer cycle-counting feature. We are issuing this AD to prevent uncontained engine failure and damage to the helicopter.
We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD requires revising the aircraft flight manual (AFM); performing operational tests of the oxygen mask oxygen assembly; and replacing affected stowage boxes, which terminates the AFM revision and operational tests. This AD was prompted by failure of the flight crew oxygen supply due to a potentially defective flight crew mask oxygen assembly. We are issuing this AD to prevent failure to supply oxygen upon demand to the flight crew in flight in “100%” and “Emergency” modes, which, in an emergency, may result in incapacitation of the flight crew.
We are adopting an airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332C, AS332L, and AS332L1 helicopters and superseding an AD for Model AS332L2 and EC225LP helicopters. This AD requires inspecting the chip detector and modifying the chip collector, both installed on the main gearbox (MGB). This AD is prompted by an investigation which showed a failure within the epicyclic reduction gear module (epicyclic module) resulted in the rupture of the MGB case and separation of the main rotor head of a Model AS332L2 helicopter. These actions are intended to prevent failure of the MGB and subsequent loss of control of the helicopter.
We are superseding an existing airworthiness directive (AD) that applies to all The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. That AD currently requires repetitive inspections for cracking of the elevator actuator fittings. This new AD requires, for previously modified airplanes, repetitive inspections for movement of the fittings or fastener heads, and eventual replacement of certain bolts (including related investigative and corrective actions if necessary). For all airplanes, this replacement, with corrected torque values, would terminate the requirements of the existing AD. This new AD also removes certain airplanes from the applicability. This AD was prompted by the manufacturer's development of a modification that was approved as an optional terminating action to the existing AD's required repetitive inspections. We have been advised that the modification procedures include certain incorrect torque values. We are issuing this AD to detect and correct a cracked actuator fitting or incorrectly installed bolts to the actuator fitting, which could lead to the elevator becoming detached and unrestrained, and a consequent unacceptable flutter condition and loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600 series airplanes. This AD was prompted by reports of early fatigue cracks at chem-mill areas on the crown skin panels. This AD requires repetitive inspections for cracking of the fuselage skin at certain locations at chem-mill areas, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the skin panel at the specified chem-mill step locations, which could result in rapid decompression of the airplane.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-300, A340-200 and A340-300 series airplanes. This AD was prompted by a report that revealed the wheel axles of the main landing gear (MLG) were machined with a radius as small as 0.4 millimeters. This AD requires replacing the wheel axle of the MLG with a serviceable part. We are issuing this AD to prevent fatigue of the wheel axle of the MLG, which could adversely affect the structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for Eurocopter France (ECF) Model AS332C, L, and L1 helicopters to require an initial and repetitive inspections of the outer skin, butt strap, and fuselage frame for a crack and modification of the helicopter. This AD was prompted by an AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, which states that a crack was discovered in a fuselage frame during a daily check. The actions of this AD are intended to detect a crack, to prevent loss of airframe structural integrity and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series airplanes. This AD was prompted by a report that during a test of the oxygen system, an operator found that the passenger oxygen masks did not properly flow oxygen, and that a loud noise occurred in the overhead area, which was caused by the flex line separating from the hard line due to a missing clamshell coupler. This AD requires, for certain airplanes, performing a detailed inspection of certain areas of the airplane oxygen system to ensure clamshell couplers are installed and fully latched, and corrective actions if necessary. For all airplanes, this AD requires performing and meeting the requirements of the low pressure leak test. We are issuing this AD to prevent the oxygen system flex line from separating from the hard line, which could cause an oxygen leak and a drop in the oxygen system pressure, resulting in improper flow of oxygen through the passenger masks and injury to passengers if emergency oxygen is needed.
We are adopting a new airworthiness directive (AD) for Grob-Werke Model G115EG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracks in the elevator trim tab arms on several Grob G 115 airplanes, which could result in failure of the part and consequent loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for Bell Model 430 helicopters, which requires replacing certain components of the air data system. This AD was prompted by the discovery of incorrect indicated airspeed when the helicopter was tested to the cold temperature limits (−40 degrees centigrade) required for Category A operations. The actions of this AD are intended to correct the published Vne and to correct the indicated airspeed.
We are adopting a new airworthiness directive (AD) for certain BRP-Powertrain GmbH & Co KG Rotax 912 F2; 912 F3; 912 F4; 912 S2; 912 S3; 912 S4; 914 F2; 914 F3; and 914 F4 reciprocating engines. This AD requires a one-time visual inspection for excessive oil deposits or carbon deposits on the No. 2 and No. 3 spark plug center and grounding electrodes, and if found, replacement of the cylinder head before further flight. This AD was prompted by a report of certain No. 2 and No. 3 cylinder heads not manufactured to proper specification. We are issuing this AD to prevent excessive oil consumption, which could result in an in-flight engine shutdown, forced landing, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for certain International Aero Engines AG (IAE), V2525-D5 and V2528-D5 turbofan engines, with a certain No. 4 bearing internal scavenge tube and a certain No. 4 bearing external scavenge tube installed. This AD was prompted by a report of an engine under-cowl fire and commanded in-flight shutdown. This AD would require replacement of certain part number (P/N) No. 4 bearing internal scavenge tubes, and alignment checks of certain P/N No. 4 bearing external scavenge tubes. We are issuing this AD to prevent engine fire and damage to the airplane.
We are adopting a new airworthiness directive (AD) for Diamond Aircraft Industries GmbH Models DA 42, DA 42 M-NG, and DA 42NG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as overextension of the main landing gear (MLG) shock absorber that could lead to the MLG jamming in the gear bay and result in damage to the aircraft or occupant injury. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This AD was prompted by reports that inspections of the wing center section revealed defective, misapplied, or missing secondary fuel vapor barriers on the center fuel tank. This AD requires inspecting for discrepancies and insufficient coverage of the secondary fuel barrier, determining the thickness of the secondary fuel barrier, and corrective actions if necessary. We are issuing this AD to detect and correct defective surfaces and insufficient thickness of the secondary fuel barrier, which could allow fuel leaks or fumes into the pressurized cabin, and allow fuel or fuel vapors to come in contact with an ignition source, which could result in a fire or an explosion.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-700, -700C, -800, and -900ER series airplanes, Model 747-400F series airplanes, and Model 767-200 and -300 series airplanes. This AD was prompted by reports indicating that certain crew oxygen mask stowage box units were possibly delivered with a burr in the inlet fitting. The burr might break loose during test or operation, and might pose an ignition source or cause an inlet valve to jam. This final rule adds a step to identify and label certain crew oxygen mask stowage box units that have already been inspected and reworked by the supplier, and allows operators to install new or serviceable crew oxygen mask stowage box units, and requires a general visual inspection for affected serial numbers of the crew oxygen mask stowage box units, and replacement or re-identification as necessary. We are issuing this AD to prevent an ignition source, which could result in an oxygen-fed fire; or an inlet valve jam in a crew oxygen mask stowage box unit, which could result in restricted flow of oxygen.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of an incorrect procedure used to apply the wear and corrosion protective surface coating to attach pins of the horizontal stabilizer rear spar. This AD requires inspecting to determine the part number of the attach pins of the horizontal stabilizer rear spar, and replacing certain attach pins with new, improved attach pins. We are issuing this AD to prevent premature failure of the attach pins, which could cause reduced structural integrity of the horizontal stabilizer to fuselage attachment, resulting in loss of control of the airplane.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. That AD currently requires inspecting for scribe lines in the skin along lap joints, butt joints, certain external doublers, and the large cargo door hinges, and doing related investigative and corrective actions if necessary. This new AD adds an inspection for scribe lines where external decals have been applied or removed across lap joints, large cargo door hinges, and external doublers, and related investigative and corrective actions if necessary. This AD was prompted by a determination that scribe lines could occur where external decals are installed or removed across lap joints, large cargo door hinges, or external doublers. We are issuing this AD to detect and correct scribe lines, which can develop into fatigue cracks in the skin. Undetected fatigue cracks can grow and cause sudden decompression of the airplane.
We are superseding an existing airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. That AD currently requires installing spacer assemblies at the attachment points of the YZ-latches of the cargo loading system (CLS) in the forward and aft cargo compartments, as applicable. This new AD also requires modifying the attachment points of fixed YZ-latches of the CLS lower deck cargo holds on those airplanes on which one or both lower deck cargo holds have not been modified, which terminates the existing requirements. This AD was prompted by results from tests that have shown that the attachment points of the YZ-latches of the cargo loading system (CLS) fail under maximum loads and reports that installation has been applied only on one of the lower deck cargo holds, instead of on both forward and aft cargo holds, and that some airplanes could have installed the affected YZ-latches through the instructions of the cargo conversion manual. We are issuing this AD to prevent failure of the attachment points of the YZ-latches, which could result in unrestrained cargo causing damage to the fire protection system, hydraulic system, electrical wiring, or other equipment located in the forward and aft cargo compartments. This damage could adversely affect the continued safe flight of the airplane.
We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-Trent 970-84, RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211-Trent 977B-84, and RB211-Trent 980-84 turbofan engines. This AD requires inspection of the intermediate pressure compressor rear stub shaft (IPC RSS) piston ring. This AD was prompted by the failure of an oil pump drive shear neck due to a piston ring seal that was not seated properly in the IPC RSS groove. We are issuing this AD to prevent failure of the oil pump drive shear neck, which could result in loss of oil pressure in one or more engines and reduced control of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 Freighter, A330-300, A340-200, and A340-300 series airplanes; and Model A340-541 airplanes and Model A340-642 airplanes. This AD was prompted by reports of cracks in the bogie pivot pin caused by material heating due to friction between the bogie pivot pin and bush, leading to chrome detachment and chrome dragging on the bogie pivot pin. This AD requires repetitive detailed inspections for degradation of the bogie pivot pins and for any cracks and damage of the pivot pin bushes of the main and central landing gear; a magnetic particle inspection of the affected bogie pivot pins for corrosion and base metal cracks; and repairing or replacing bogie pivot pins and pivot pin bushes, if necessary. We are issuing this AD to detect and correct cracks and damage to the main and central landing gear, which could result in the collapse of the landing gear and adversely affect the airplane's continued safe flight and landing.
We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer, which revealed that certain fuel pumps under certain conditions can create an ignition source in the fuel tank. This AD requires modification of the center tank fuel pump control circuit by installation of ground fault interrupters (GFIs). This AD would also require either replacement of the GFI or deactivation of the associated fuel pump following failure of any post-modification operational test of the GFI. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
We are adopting a new airworthiness directive (AD) for Eurocopter France EC130B4 helicopters. This AD requires visually checking the center windscreen panel (center windscreen) for a crack and replacing the center windscreen if there is a crack, if the windscreen distorts during flight, or within 12 months. This AD was prompted by in-flight cracking and failure of a center windscreen. The actions of this AD are intended to detect a crack in the blending radii of the center windscreen to prevent failure of the windscreen, injury to the flight crew, and subsequent loss of control of the helicopter.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes equipped with Rolls-Royce RB211-535E engines. That AD currently requires repetitive inspections for signs of damage of the aft hinge fittings and attachment bolts of the thrust reversers, and related investigative and corrective actions if necessary. The existing AD also provides for an optional terminating modification for the repetitive inspections. For certain airplanes, this new AD adds a one-time inspection of the washers installed under the attachment bolts of the aft hinge fittings for correct installation sequence, and reinstallation if necessary. This new AD also adds an option for installing a redesigned aft hinge fitting with the trim already done, instead of trimming an existing or new hinge fitting, which is included in the existing optional terminating modification. This AD was prompted by reports of incorrectly installed washers under the attachment bolts of the aft hinge fittings of the thrust reversers. We are issuing this AD to prevent failure of the attachment bolts and consequent separation of a thrust reverser from the airplane during flight, which could result in structural damage to the airplane.
We are revising an existing airworthiness directive (AD) for all Cessna Aircraft Company (Cessna) Models 190, 195 (L-126A,B,C), 195A, and 195B airplanes that are equipped with certain inboard aileron hinge brackets. That AD currently requires you to repetitively inspect the affected inboard aileron hinge brackets for cracks or corrosion and replace them if cracks or corrosion is found. Replacement with aluminum brackets would terminate the need for the repetitive inspections. This new AD retains the actions of AD 2004-21-08 while requiring future compliance following a revised service bulletin that clarifies the casting numbers and part numbers to be inspected. This AD was prompted by reports of confusion between the casting number on the aileron hinge bracket and the part number (P/N) called out in the AD. We are issuing this AD to correct the unsafe condition on these products.
We are superseding an existing airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. That AD currently requires repetitive inspections of the aft attach lugs of the elevator tab control mechanisms, and replacement of any discrepant elevator tab control mechanism. This new AD requires replacing the left and right elevator tab control mechanisms with elevator tab control mechanisms that have the modified attach lugs, which would terminate the existing requirements. This AD was prompted by reports of failure of the aft attach lugs on the elevator tab control mechanisms, which resulted in severe elevator vibration; and reports of gaps in elevator tab control mechanisms and analysis indicating that additional elevator tab control mechanisms might have bearings that will come loose. We are issuing this AD to prevent discrepancies in the aft attach lugs of the elevator tab control mechanism, which could result in severe elevator and tab vibration. Consequent structural failure of the elevator or horizontal stabilizer could result in loss of structural integrity and aircraft control.
We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model SA-365N1, AS-365N2, and AS 365 N3 helicopters. This AD requires revising the Limitations section of the Rotorcraft Flight Manual (RFM) to prohibit flight in instrument meteorological conditions (IMC) or night visual flight rules (VFR) for each helicopter with a vertical gyro unit GV76-1 installed upon a non-reinforced shelf in the rear cargo compartment. Also, this AD requires modifying the GV76-1 vertical gyro unit shelf and testing for correct function of the navigation systems. This AD was prompted by flight crew reports of deviations between the displayed attitude on the attitude display screen and the independent electromechanical standby attitude indicator. The actions of this AD are intended to prevent an undetected flight display error of a slow drift in the roll axis, disorientation of the pilot, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-8C and CF34-8E turbofan engines with certain part numbers (P/N) of operability bleed valves (OBV) installed. This AD was prompted by three failure events of ring lock fuel fittings on the OBV. Two of those events led to an engine fire. This AD requires the affected OBVs be removed from service and replaced with OBVs eligible for installation. We are issuing this AD to prevent failure of OBV ring lock fuel fittings, engine fuel leakage, uncontrolled fire, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports of oil residue between the stator and the rotor parts of the position resolvers of the angle of attack (AOA) vane, which was a result of incorrect removal of the machining oil during the manufacturing process of the AOA resolvers. This AD requires an inspection to determine if certain AOA probes are installed, and replacement of any affected AOA probe. We are issuing this AD to prevent erroneous AOA information and consequent delayed or non-activation of the AOA protection systems, which during flight at a high AOA, could result in reduced control of the airplane.
We are adopting a new airworthiness directive (AD) for REIMS AVIATION S.A. Model F406 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as fretting (wear and/or chafing) found between the elevator pushrod assembly and the horizontal tail structure, which could cause the elevator pushrod to jam and could result in loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 and ERJ 190 airplanes. This AD was prompted by a report that high rate discharge (HRD) bottle explosive cartridges of a cargo compartment fire extinguisher system were swapped between the forward and aft cargo compartments. Additional investigation also revealed the possibility of swapping between the electrical connectors of the HRD and low rate discharge (LRD) bottles, and a rotated installation of the HRD bottle. Improper assembly of the fire extinguishing bottle might cause the extinguishing agent to be discharged toward the unselected cargo compartment rather than toward the cargo compartment with fire. This AD requires an inspection of the HRD bottle for correct installation and to determine if the pressure switch is in the correct position, and re-installation if necessary; an inspection of the HRD and LRD bottle discharge heads to determine the part number, and replacement if necessary; and, for certain airplanes, an inspection to identify the HRD and LRD bottle electrical connectors, and relocation if necessary. We are issuing this AD to prevent the inability of the fire extinguishing system to suppress fire.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by reports that escape slides/rafts did not deploy due to galvanic corrosion of the door-mounted slide/raft packboard release mechanisms. This AD requires doing a general visual inspection of the housing assembly of the packboard release mechanism to determine if its surface treatment has been sealed, and if the surface of the housing assembly is unsealed, replacing the housing assembly with a new or serviceable housing assembly. We are issuing this AD to detect and correct corrosion of the packboard release mechanisms, which could interfere with escape slide/raft deployment, prohibit doors from opening in the armed mode, and cause consequent delay and injury during evacuation of passengers and crew from the cabin in the event of an emergency.
We are adopting a new airworthiness directive (AD) for Robinson Helicopter Company (Robinson) Model R44 and R44 II helicopters equipped with emergency floats. This AD requires replacing the inflation valve assembly. This AD was prompted by the failure of the emergency floats to deploy during a factory test because a needle was binding within the inflation valve assembly. The actions are intended to prevent the failure of the floats to inflate during an emergency landing.
We are adopting a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 369D, 369E, 369F, and 369FF helicopters with certain serial-numbered tailboom assemblies. This AD requires measuring the distance between aft longeron rivets and the outboard edge of frame rings. If the distance is too short to ensure a safe flight, the AD requires installing a doubler. This AD was prompted by the discovery of short-edge margin conditions on two tailboom assemblies. The actions are intended to detect a short-edge margin condition, prevent failure of the tailboom and loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for all Agusta S.p.A. (Agusta) Model A109, A109A, A109A II, A109C, A109K2, A109E, A109S, and A119 helicopters. This AD was prompted by a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that a Model A109E helicopter experienced a failure of the tail rotor pitch control link assembly caused by a production defect. The actions of this AD are intended to prevent failure of a tail rotor pitch control link and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC130 B4 helicopters with a cabin vibration damper installed. This AD requires installing a vibration damper casing assembly on both sides of the helicopter. This AD was prompted by a crack and failure of a cabin vibration damper blade. The actions of this AD are intended to modify the cabin vibration damper assembly to prevent contact with the flight controls in the event of a cabin vibration blade failure, jamming of a flight control, and subsequent loss of control of the helicopter.
We are rescinding an airworthiness directive (AD) for all PILATUS AIRCRAFT LTD. Models PC-12, PC-12/45, and PC-12/47 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. We issued that AD to mandate new life limits for the pitch trim actuator and pitch trim actuator attachment parts. If these new limitations were not mandated, the pitch trim actuator and the pitch trim actuator components could fail. This failure could lead to an unsafe flying configuration. Since we issued that AD, we have determined that the unsafe condition addressed in that AD is now addressed in another AD.
We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-61A, D, E, L, N, NM, R, and V helicopters to require replacing each forward and aft fuel system 40 micron fuel filter element with a 10 micron nominal (40 micron absolute) fuel filter element. This AD was prompted by a National Transportation Safety Board (NTSB) review of in-service events where engine performance degradation occurred, and the review determined that some of these events were caused by contaminants larger than 10 microns present in the engine fuel control units (FCUs). The actions are intended to prevent particulate contamination in the FCU, which could lead to malfunction of an internal valve, power loss at a critical phase of flight, and loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (Bell), Model 412 and 412EP helicopters. This AD requires establishing a lower life limit on certain swashplate outer ring assemblies (outer ring), revising the retirement life on the components' history card or equivalent record, and revising the maintenance manual or Instructions for Continued Airworthiness (ICA). This AD also prohibits installing these outer rings on any helicopter. This AD was prompted by reports of cracking in the outer rings. The actions are intended to prevent failure of an outer ring because of cracking, which could lead to the loss of main rotor (M/R) blade pitch control and subsequent loss of helicopter control.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires doing an inspection to identify the part number of the motor-operated valve (MOV) actuators of the main and center fuel tanks; replacing certain MOV actuators with new MOV actuators; and measuring the electrical resistance of the bond from the adapter plate to the airplane structure, and doing corrective actions if necessary. We are issuing this AD to prevent electrical current from flowing through an MOV actuator into a fuel tank, which could create a potential ignition source inside the fuel tank. This condition, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports of stiff operation of the elevator pitch control system and jammed elevator controls. This AD requires replacing pressure seal assemblies; doing repetitive inspections for dirt, loose particles, or blockage of the flanged tube and drain hole for the pressure seals, and corrective action if necessary; replacing the aft air-intake duct assembly with a new or modified assembly and installing a dripshield; and installing gutters on the horizontal stabilizer center section and modifying the side brace fittings. We are issuing this AD to prevent moisture from collecting and freezing on the elevator control system components, which could limit the ability of the flightcrew to make elevator control inputs and result in reduced controllability of the airplane.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by reports of in-service events related to electrical power system malfunctions resulting in damage to electrical load management system (ELMS) P200 and P300 power panels and the surrounding area. This AD requires installing enclosure trays to contain debris in certain ELMS panels, and replacing certain ELMS contactors. We are issuing this AD to prevent contactor failures, which could result in uncontained hot debris flow due to ELMS contactor breakdown, consequent smoke and heat damage to airplane structure and equipment during ground operations, and possible injuries to passengers and crew.
We are superseding an existing airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211 Trent 500 series turbofan engines. That AD currently requires a one-time inspection of the fuel tubes and fuel tube clips for evidence of damage, wear, and fuel leakage. This AD requires the same inspection, and adds additional repetitive inspections. This AD was prompted by additional RR engineering analysis. We are issuing this AD to prevent engine fuel leaks, which could result in engine damage and damage to the airplane.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -300, and -200 Freighter series airplanes; and all Airbus Model A340-200 and -300 series airplanes. This AD was prompted by a determination that the bonding lead from a certain isolation valve to a frame was too close to an electrical harness, which might cause chafing between the electrical harness and the associated bonding lead. This chafing could lead to a short circuit of the isolation valve and consequent non-closure of the isolation valve, which would prevent the air flow to be shut off in case of fire. This AD requires modifying the bonding lead installation of the isolation valve. We are issuing this AD to prevent such chafing, which could result in non-closure of the isolation valve in the event of a fire and consequent damage to the airplane and injury to its occupants.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2A12 (CL-601) and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by reports of jamming/malfunctioning of the left-hand engine thrust control mechanism. This AD requires modifying the left-hand engine upper core-cowl. We are issuing this AD to prevent jamming/malfunctioning of the left-hand engine thrust control mechanism, which could lead to loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710 series turbofan engines. This AD requires replacement of the affected fuel pump splined couplings. This AD was prompted by service experience that demonstrated premature wear of the splined coupling on the fuel pump. We are issuing this AD to prevent failure of the engine and loss of the airplane.
We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) models Tay 620-15 and Tay 650-15 turbofan engines. This AD was prompted by RRD recalculating the Declared Safe Cyclic Life (DSCL) for certain low-pressure compressor (LPC) rotor disc assemblies operating to the Plan D Flight Mission. This AD requires removing the affected LPC rotor disc assemblies at a new lower recalculated DSCL. We are issuing this AD to prevent failure of the LPC rotor disc assembly, uncontained engine failure, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611-8 turbofan engines. This AD requires inspection and replacement, if necessary, of affected bolts. This AD was prompted by a quality review determination that bolts with reduced material properties may have been installed in some engines. We are issuing this AD to prevent uncontained turbine disc fracture and damage to the airplane.
We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332C, L, and L1 helicopters to require a one-time inspection of the main rotor head (MRH) swash-plate upper bearing (bearing) for a non-smooth point (friction point). This AD was prompted by a report of the premature deterioration of the MRH bearing of the rotating star installed on a Model AS332L1 helicopter. The actions of this AD are intended to detect deterioration of the MRH bearing and to prevent overloading the scissor links which drive the main rotor system, failure of the scissors links, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Spey 511-8 turbojet engines. This AD requires inspection and, if necessary, replacement of affected bolts and, if any bolt is found broken, inspection of the adjacent disc(s) for damage. This AD was prompted by a recent quality review determination that bolts with reduced material properties may have been installed in some engines. We are issuing this AD to prevent uncontained turbine disc fracture and damage to the airplane.
We are adopting a new airworthiness directive (AD) for Diamond Aircraft Industries GmbH Models DA 42 M-NG and DA 42 NG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as the engine air inlet filter is subject to icing. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports that airplanes with a Class C cargo (baggage) compartment have liners that do not meet flammability requirements. This AD requires replacing the existing cargo compartment liners with liners that comply. We are issuing this AD to prevent inadequate fire protection in the cargo compartment and consequent uncontrolled fire.
We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by a report of an uncommanded slide back of the co-pilot seat to the end stop position. This AD requires a one-time inspection for a part number, a tensile test of the affected seats, and corrective actions if necessary. We are issuing this AD to detect and prevent unwanted movement of a pilot or co-pilot seat in the horizontal direction, which could lead to inadvertent input on the flight control commands and possibly result in loss of controllability of the airplane.
We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation-manufactured Model S-64F helicopters, now under the Erickson Air-Crane Incorporated (Erickson) Model S-64F type certificate. This AD supersedes an existing AD which requires inspections, rework, and replacement, if necessary, of the main gearbox (MGB) second stage lower planetary plate (plate). Since we issued that AD, the manufacturer has conducted a configuration review and analysis, and a review of the service history of certain components. The actions of this AD are intended to establish life limits for certain components, remove various parts from service, and require consistency in the part numbers of certain four bladed tail rotor (T/R) assemblies to prevent fatigue cracking, failure from static overload, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for the Eurocopter France (Eurocopter) Model AS332C, AS332L, and AS332L1 helicopters. This AD requires modifying the main landing gear control panel (control panel) 33G, connector 100G, and wiring. It also requires tests to ensure that these modifications function correctly. This AD was prompted by reports of electro-valve power supply disruptions while a helicopter is on the ground, causing the landing gear to retract and the helicopter nose to drop. This results in damage to the forward section of the helicopter's bottom structure. The actions of this AD are intended to prevent an uncommanded landing gear retraction that would cause the helicopter nose to drop and hit the ground while the rotor blades are spinning.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, -200, and -300 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by a report that erroneous height indication by one radio altimeter with engaged flare and retard mode, in case of go-around, might lead to a temporary loss of airplane longitudinal control. This AD requires revising the airplane flight manual. We are issuing this AD to ensure that the flightcrew applies the appropriate operational procedures in the event of an erroneous indication of the radio altimeter, which could result in temporary loss of airplane longitudinal control.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This AD was prompted by reports of cracks of the hinge bearing lugs of the center section ribs of the horizontal stabilizer. This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of the left and right rib hinge bearing lugs of the aft face of the center section of the horizontal stabilizer; measuring crack length and blending out cracks; and replacing the horizontal stabilizer center section rib, if necessary. We are issuing this AD to detect and correct cracking in the hinge bearing lugs of the horizontal stabilizer center section ribs, which could result in failure of the lugs, and consequent inability of the horizontal stabilizer to sustain the required limit loads and loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Model 750 airplanes. This AD was prompted by reports of loss of displayed airspeed. This AD requires inspecting certain logic modules to determine if certain cabin altitude/pitot static heater module assemblies are installed and replacing those assemblies with a new assembly; and revising the Non-Normal Procedures Section of the airplane flight manual (AFM) to include procedures for resetting the pitot switch in the event of pitot heater failure and for total loss of airspeed indication. We are issuing this AD to prevent the loss of all displayed airspeed, which could result in reduced ability to control the airplane.
We are adopting a new airworthiness directive (AD) for all BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 and Avro 146-RJ series airplanes. This AD was prompted by a report that certain ceramic terminal blocks, through which the wiring for the engine fire extinguishers, fire detection circuits, and engine and intake anti-ice system are routed, have been found to have moisture ingress, which can degrade the insulation resistance of the ceramic terminal blocks. This AD requires a one-time insulation resistance test of ceramic terminal blocks, and if necessary, replacement of the blocks. We are issuing this AD to prevent latent failure of the number 2 fire bottle, which, in the event of an engine fire, could result in failure of the fire bottle to discharge when activated and possibly preventing the flightcrew from extinguishing an engine fire.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -800, and -900ER series airplanes. This AD was prompted by incorrect wire support clamps installed within the left environmental control systems (ECS) bay, which could allow wiring to come in contact with the exposed metal of the improper clamp. This AD requires inspections to identify the part number of the wire support clamp, related investigative actions, and corrective actions if necessary. We are issuing this AD to prevent electrical arcing and a potential ignition source within the ECS bay, which in combination with flammable fuel vapors, could result in a center wing fuel tank explosion, and consequent loss of the airplane.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A310-204, -222, -304, -322, and -324 airplanes. This AD was prompted by the manufacturer re-classifying slat extension eccentric bolts as principle structural elements (PSE) with replacement due at or before newly calculated fatigue life limits. This AD requires replacing slat extension eccentric bolts and associated washers with new slat extension eccentric bolts and washers. We are issuing this AD to prevent fatigue cracking, which could result in the loss of structural integrity of the airplane.
We are superseding an existing airworthiness directive (AD) for all Turbomeca S.A. Makila 1A2 turboshaft engines. That AD currently requires replacement of certain serial number (S/N) N2 sensor harnesses. This AD requires replacement of the same S/N harnesses, and requires replacement of additional S/N N2 sensor harnesses. This AD was prompted by corrosion detected in affected N2 sensor harnesses. We are issuing this AD to prevent inadvertent activation of the 65% N1 back up mode, resulting in N2 speed fluctuation, significant power loss, and emergency landing of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 airplanes. This AD was prompted by reports of the loss of the fixed frequency system, leading to the loss of power to the left and right buses and all systems serviced by these buses. This AD requires modification of the wiring and changes to existing airworthiness limitations. We are issuing this AD to prevent loss of the fixed frequency system, which could lead to loss of a number of the pilot's and co-pilot's flight instruments, in addition to other avionics systems.
We are adopting a new airworthiness directive (AD) for Diamond Aircraft Industries GmbH Model H-36, HK 36 R, HK 36 TS, and HK 36 TTS airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as installation of an unsuitable self-locking nut on the bell crank of the elevator push rod that can cause failure of the elevator, resulting in loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A310-203, -204, -222, -304, -322, and -324 airplanes. This AD was prompted by a design review of the fuel tank access covers and analyses comparing compliance of the access covers to different tire burst models. ‘Type 21’ panels located within the debris zone revealed that they could not sustain the impact of the tire debris. This AD requires modifying the wing manhole surrounds and replacing certain fuel access panels. We are issuing this AD to prevent a possibility of a fire due to tire debris impact on the fuel access panels.
We are adopting a new airworthiness directive (AD) for Costruzioni Aeronautiche Tecnam srl Model P2006T airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as multiple cracks found on the outboard aileron hinge support of a P2006T airplane during an inspection. We are issuing this AD to require actions to address the unsafe condition on these products.
The FAA is correcting an airworthiness directive (AD) that published in the Federal Register . That AD applies to certain The Boeing Company Model 757 airplanes. That AD incorrectly identified certain actions that are terminated in another AD. This document corrects that error. In all other respects, the original document remains the same.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8 airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires modification of the battery system, or other actions. This AD was prompted by recent incidents involving lithium ion battery failures that resulted in release of flammable electrolytes, heat damage, and smoke. We are issuing this AD to correct damage to critical systems and structures, and the potential for fire in the electrical compartment.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracks in the skin and surrounding structure under the number 3 very high frequency (VHF) antenna on the lower external surface of the airplane at buttock line 0.0, aft of the main landing gear wheel well. This AD requires inspecting for cracking and corrosion under the number 3 VHF antenna, and corrective actions if necessary; and, for certain airplanes, replacing bonded skin panels with solid skin panels if not previously accomplished. This AD also provides an optional preventive modification (which would terminate the inspection requirements for certain airplanes). We are issuing this AD to detect and correct cracks and corrosion of the skin and surrounding structure under the number 3 VHF antenna, which could result in separation of the antenna from the airplane, and rapid depressurization of the airplane.
We are superseding an existing airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-524 series turbofan engines. That AD currently requires removal and repair of certain thrust reverser units (TRUs) prior to reinstallation. This AD requires the same actions for an expanded population of TRUs and extends the compliance time for repairing certain TRUs. This AD was prompted by additional engineering evaluation of TRUs, as a result of a translating cowl gearbox stubshaft failure and subsequent repair. We are issuing this AD to prevent failure of the attachment rivets, which may result in release of the TRU from the engine.
We are adopting a new airworthiness directive (AD) for Reims Aviation S.A. Model F406 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as improper material used in nose landing gear (NLG) attachment brackets could lead to failure of the NLG bracket with consequent damage to the airplane while landing. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) PT6C-67C turboshaft engines. This AD requires initial and repetitive borescope inspections to verify the presence of a retaining ring securing the power turbine (PT) baffle located near the second stage PT disk. If the engine fails the inspection, this AD also requires removing the engine from service before further flight. This AD was prompted by five reported incidents of second stage PT disk damage. We are issuing this AD to prevent damage to the PT disk which, if undetected, could cause uncontained PT disk failure and loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain serial number Pratt & Whitney Canada Corp. PW206B, PW206B2, PW206C, PW207C, PW207D, PW207D1, PW207D2, and PW207E turboshaft engines. This AD was prompted by the discovery that certain power turbine (PT) disks were made to specific heat codes that may not achieve the maximum in-service life. This AD requires re-identification of the PT disk to a part number (P/N) with a lower life limit. We are issuing this AD to prevent possible uncontained PT disk failure and loss of helicopter control.
We are adopting a new airworthiness directive (AD) for all Gulfstream Aerospace LP (Type Certificate Previously Held by Israel Aircraft Industries, Ltd.) Model Gulfstream G150 airplanes. This AD was prompted by a review that determined that the runway slope and anti-ice corrections to V 1 and take-off distances in the Gulfstream G150 Airplane Flight Manual (AFM) were presented in a non-conservative manner. This AD requires revising the performance section of the AFM to include procedures to advise the flightcrew of certain runway slope and anti-ice corrections and take-off distance values. We are issuing this AD to prevent the use of published non-conservative data, which could result in the inability to meet the required take-off performance, with consequent hazard to safe operation during performance-limited take-off operations.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD was prompted by reports of fuel leaking from the front spar of the wing through the slat track housing. This AD requires a detailed inspection of the inboard and outboard main slat track downstop assemblies and a torque application to the main track downstop assembly nuts of slat numbers 1 through 10, excluding the outboard track of slats 1 and 10; a detailed inspection of all slat track housings for foreign object debris (FOD) and visible damage; and corrective actions if necessary. We are issuing this AD to detect and correct incorrectly installed main slat track downstop assemblies, which, when the slat is retracted, could cause a puncture in the slat track housing and lead to a fuel leak and potential fire.
We are superseding an existing airworthiness directive (AD) for all Pilatus Aircraft Ltd. Models PC-12, PC-12/45, PC-12/47, and PC-12/47E airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a need to incorporate new revisions into the Limitations section, Chapter 4, of the FAA-approved maintenance program (e.g., maintenance manual). We are issuing this AD to require actions to address the unsafe condition on these products.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. That AD currently requires replacing wiring for the fuel boost pumps and override pumps with new wiring, installing Teflon sleeving on the wiring, and doing associated actions; and doing repetitive inspections to detect damage of the wiring or evidence of a fuel leak. This new AD reduces the repetitive inspection interval. This AD was prompted by a determination that an inspection interval must be reduced. We are issuing this AD to detect and correct damaged wiring for the fuel boost pumps and override pumps, which could cause electrical arcing that could puncture the conduit containing the wire, and result in a fuel tank explosion or a fire adjacent to the fuel tank.
We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A1-10 and BR700-710A2-20 turbofan engines, and certain BR700-710C4-11 model engines. This AD was prompted by RRD performing an evaluation that determined that certain high-pressure turbine (HPT) stage 1 and stage 2 discs from a specific supplier may contain steel inclusions that may cause the discs to fail before they reach their current life limits. This AD requires reducing the life limits for certain HPT stage 1 and stage 2 discs. We are issuing this AD to prevent failure of the HPT stage 1 and stage 2 discs, which could result in uncontained failure of the engine and damage to the airplane.
We are superseding an existing airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B, EC155B1, SA-365N1, AS-365N2 and AS 365 N3 helicopters. That AD currently requires inspecting certain tail rotor hubs (TRH) for a crack and removing any cracked TRH. This AD requires the same actions but adds more part numbers to the list of affected TRHs. This AD is prompted by further analysis that indicates that additional part-numbered TRHs must be inspected for cracks. The actions specified by this AD are intended to detect a crack in the TRH and prevent the tail rotor from jamming, which could lead to reduced or loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation (Type Certificate previously held by Raytheon Aircraft Company; Beech Aircraft Corporation) Model 400A airplanes. This AD was prompted by a report that the wiring for the 5-volt direct current (DC) system is undersized and does not have adequate circuit protection for the smaller gauge wire. This AD requires installing an in-line fuse in the 5-volt DC system for each of the five instrument lighting control power supplies. We are issuing this AD to prevent failure of the wiring, which could result in smoke in the cockpit, loss of cockpit lighting, and potential damage to surrounding wiring for other cockpit equipment such as the stick shaker function or angle-of-attack indicators.
We are superseding an existing airworthiness directive (AD) for all Pacific Aerospace Limited Models FU24-954 and FU24A-954 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as aircraft operating outside the aircraft aft center of gravity (C of G) limits during parachute-drop operations. Exceeding C of G limits could result in loss of control of the aircraft. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, & CL-604 Variants) airplanes. This AD was prompted by reports of cracking found on the upper and lower Web of the engine support beam. This AD requires revising the maintenance program. We are issuing this AD to detect and correct fatigue cracking of the engine support beam, which could result in failure of the engine support beam and affect the structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for certain Lindstrand Hot Air Balloons Ltd female ACME threaded hose connectors, part numbers HS6139 and HS6144, installed on balloons. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as insufficient tightness of the threaded hose connector in the assembly area that could result in fuel leakage. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Airbus Model A310 series airplanes. This AD was prompted by fuel system reviews conducted by the European Aviation Safety Agency (EASA). This AD requires modifying the electrical control circuits of the inner, center, and trim tank pumps, as applicable. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
We are adopting a new airworthiness directive (AD) for the Schweizer Aircraft Corporation (Schweizer) Model 269D and Model 269D Configuration A helicopters. The type certificate for these models is currently held by Sikorsky Aircraft Corporation (Sikorsky). This AD requires inspecting the aft fuselage assembly in the area around the attachment point of the horizontal stabilizer, including the paint, for a crack. This AD also requires inspecting the tailboom interior support structure, and if necessary, installing an inspection panel kit in the aft fuselage assembly, and installing doublers in the stabilizer support brackets. This AD is prompted by reports of loose horizontal stabilizers and cracks in the stabilizer support structure for the extruded tailboom. The actions are intended to prevent separation of the horizontal stabilizer from the helicopter and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for DG Flugzeugbau GmbH Model DG-1000T gliders equipped with Solo Kleinmotoren Model 2350 C engines. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a material defect of the propeller shaft, most likely caused by a manufacturing error. We are issuing this AD to require actions to address the unsafe condition on these products.
We are superseding an existing airworthiness directive (AD) for the Bell Helicopter Textron (Bell) Model 212 helicopters and adopting requirements for Bell Model 204B, 205A, 205A-1, 205B and 210 helicopters with certain part-numbered main rotor hub inboard strap fittings (fittings). This AD requires magnetic particle inspecting (MPI) the fittings for a crack, and if a crack exists, replacing the fittings with airworthy fittings. This AD is prompted by reports of additional cracked fittings and the determination that additional part-numbered fittings may not have been manufactured in accordance with approved manufacturing processes and controls. These actions are intended to identify a crack in the fitting, which may lead to the fitting's failure, loss of a main rotor blade, and subsequent loss of helicopter control.
We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Models 172R and 172S airplanes. This AD was prompted by reports of chafing of a new configuration of the fuel return line assembly, which was caused by the fuel return line assembly rubbing against the right steering tube assembly during rudder pedal actuation. This AD requires you to install the forward and aft fuel return line support clamps and brackets; inspect for a minimum clearance between the fuel return line assembly and the steering tube assembly and clearance between the fuel return line assembly and the airplane structure; and, if any damage is found, replace the fuel return line assembly. We are issuing this AD to correct the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model Mystere-Falcon 50 airplanes. This AD was prompted by a manufacturer revision to the airplane maintenance manual (AMM) that introduces new or more restrictive maintenance requirements and airworthiness limitations. This AD requires revising the maintenance program to incorporate new or revised maintenance requirements and airworthiness limitations. We are issuing this AD to prevent reduced structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 and ERJ 190 airplanes. This AD was prompted by reports of the cockpit door falling off the hinges when it is being opened or closed. This AD requires replacing the striker and quick-release pin of the passive lock of the cockpit door, and replacing the upper and lower hinges of the cockpit door. We are issuing this AD to prevent the cockpit door from falling off the hinges, which could cause injury to airplane occupants.
We are adopting a new airworthiness directive (AD) for certain 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); and Model A310 series airplanes. This AD was prompted by reports of cracking through the honeycomb core closed with phenolic resin. This condition could result in extended debonding and could adversely affect the structural integrity of the rudder. This AD requires inspecting to determine the serial number of a certain rudder and replacing the rudder with a new or serviceable rudder if necessary. We are issuing this AD to prevent extended de-bonding, which could result in loss of the rudder and consequent reduced controllability of the airplane.
We are adopting a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 500N, 600N and MD900 helicopters to require determining the cure date for each NOTAR fan blade tension-torsion strap (T-T strap), establishing a calendar-time retirement life for certain T-T straps, reducing the retirement life of certain T-T straps, marking each T-T strap with the expiration date, creating a component record card for each T-T strap, and revising the airworthiness limitations section of the maintenance manual to reflect the changes to the retirement life. This AD was prompted by a report from the T-T strap manufacturer that, over a period of time, moisture may reduce the strength of a T-T strap. The actions are intended to prevent failure of a T-T strap, loss of directional control and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350B3 and EC130B4 helicopters. This AD requires revising the Limitations section of the Rotorcraft Flight Manual (RFM) to reduce the starter generator operating current to 180 amperes (amps) and installing a placard in the instrument panel indicating the revised limitation. This AD was prompted by the determination that the manufacturer-installed Aircraft Parts Corporation (APC) starter generator has exceeded the shaft horse power extractions allowed for Turbomeca engines. The actions of this AD are intended to prevent the engine surge margin being reduced, which can result in engine failure.
We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (type certificate previously held by The New Piper Aircraft Inc.) PA-28, PA-32, PA-34, and PA-44 airplanes. This AD was prompted by reports of control cable assembly failures that may lead to failure of the horizontal stabilator control system and could result in loss of pitch control. This AD requires inspections of the stabilator control system and replacement of parts as necessary. We are issuing this AD to correct the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (Bell), Model 412 and 412EP helicopters. This AD requires creating a component history card or equivalent record and begin counting and recording the number of accumulated landings for each high aft crosstube assembly (crosstube). Also, this AD requires installing “caution” decals regarding towing of a helicopter at or above 8,900 pounds. This AD also requires confirming the crosstube is within the horizontal deflection limits and replacing it if it is not. This AD also requires a recurring fluorescent penetrant inspection (FPI) of each crosstube and upper center support for a crack, any corrosion, nick, scratch, dent, or any other damage. This AD requires repairing damaged crosstubes and upper center supports that are within acceptable limits, reworking crosstubes by bonding on abrasion strips, and replacing each unairworthy crosstube with an airworthy crosstube. This AD was prompted by analysis of the crosstubes conducted as a result of recent field failures and corrosion problems of the affected crosstubes. The actions are intended to prevent failure of a crosstube, collapse of the landing gear, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for all Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a report that the safe life limit and inspection requirements for the horizontal stabilizer trim actuator (HSTA) attachment pins and trunnions were not listed in the Airworthiness Limitations Section of the maintenance program. This AD requires inspecting the trunnions and upper and lower pins for gouges, scratches, and corrosion, and replacing the trunnions if necessary; and adding serial numbers and new part numbers to certain trunnions, and upper and lower pins. This AD also requires revising the maintenance program to incorporate the information specified in certain temporary revisions of the limitations section. We are issuing this AD to detect and correct cracking, gouges, scratches, and corrosion of the HSTA attachment pins and trunnions, which could result in failure of these pins and trunnions and consequent disconnection of the horizontal stabilizer and subsequent loss of controllability of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A310-203 airplanes. This AD was prompted by a report of an analysis that demonstrated a reduced fatigue life for the side link bolts, center sway link bolts, and thrust link bolts on the forward engine mounts. This AD requires repetitive replacement of those bolts. We are issuing this AD to prevent deterioration of the structural integrity of the bolts, which could result in possible damage to an engine or wing.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter series airplanes; Model A330-200 and -300 series airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by a report of a manufacturing defect in certain rods installed in the belly fairing, which could lead to cracks at the crimped end of the rod. This AD requires an inspection of the rods to determine the manufacturer; and for affected parts, an inspection for any cracking of the rods, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct cracking of the rods, which could result in rupture of rods that attach the belly fairing to the airframe, leading to separation of the belly fairing from the airframe, and consequent damage to airplane structure and airplane systems.
We are adopting a new airworthiness directive (AD) for all BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146, and Avro 146-RJ series airplanes. This AD was prompted by a report of loss of the end caps on the anti-icing piccolo tube of the wing leading edge. This AD requires a detailed inspection of the end caps on the anti-icing piccolo tube for lost or loose end caps, and replacing or repairing the end caps if necessary. We are issuing this AD to detect and correct lost and loose end caps on the anti-icing piccolo tube, and ice accretion on the wing leading edge or run-back ice, which could lead to a reduction in the stall margin on approach and loss of controllability of the airplane.
We are adopting a new airworthiness directive (AD) for all EADS CASA (Type Certificate previously held by Construcciones Aeronáuticas, S.A.) Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes. This AD was prompted by reports of incorrect electrical polarity connections on engine fire extinguishing discharge cartridges. This AD requires a one-time inspection to identify the correct polarity for each pair of electrical connectors on each engine fire extinguisher cartridge, and repair if necessary. We are issuing this AD to detect and correct incorrect polarity connections, which could prevent the actuation of the discharge cartridge in case of automatic fire detection or manual initiation during a potential engine fire, and could result in damage to the airplane and injury to passengers.
We are adopting a new airworthiness directive (AD) for Turbomeca S.A. Arriel 2D turboshaft engines. This AD was prompted by a low fuel pressure event caused by deterioration and a loss of the low-pressure drive function within the hydro-mechanical metering unit (HMU). This AD requires replacing the HMU at a reduced life. We are issuing this AD to prevent an uncommanded in-flight shutdown of the engine, and possible loss of the helicopter.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports from the manufacturer that center overhead stowage (COS) boxes could fall from their supports under forward load levels less than the 9 g forward load requirements as defined by certain regulations. This AD requires modifying COS boxes by installing new brackets, stiffeners, and hardware as needed. We are issuing this AD to prevent detachment of COS boxes at forward load levels less than 9 g during an emergency landing, which would cause injury to passengers and/or crew, and could impede subsequent rapid evacuation.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD requires, for certain airplanes, installing two warning level indicator lights on each of the P1-3 and P3-1 instrument panels in the flight compartment. This AD also requires, for certain airplanes, replacing the existing P5-16 and P5-10 panels; and, for certain airplanes, replacing the basic P5-16 panel with a high altitude landing P5-16 panel. Additionally, this AD requires revising the airplane flight manual to remove certain requirements of previous AD actions, and to advise the flightcrew of certain changes. This AD was prompted by a design change in the cabin altitude warning system that would address the identified unsafe condition. We are issuing this AD to prevent failure of the flightcrew to recognize and react to a valid cabin altitude warning horn, which could result in incapacitation of the flightcrew due to hypoxia (a lack of oxygen in the body), and consequent loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc RB211-Trent 970-84, RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211-Trent 977B-84 and RB211-Trent 980-84 turbofan engines. This AD requires on-wing inspections of low-pressure turbine (LPT) disk seal fins and interstage seals when post-flight review indicates Engine Health Monitoring (EHM) vibratory maintenance-alert limits were exceeded in flight. The AD also requires in-shop inspections of the LPT disk seal fins and interstage seals to detect cracks or damage and, depending on the findings, accomplishment of corrective action. This AD is prompted by a Trent 900 engine experiencing LPT stage 2 disk interstage seal material loss and increased low-pressure rotor vibration while in flight. We are issuing this AD to prevent cracks in the LPT disk, which could result in uncontained engine failure and damage to the airplane.
We are adopting a new airworthiness directive (AD) for all Engine Alliance GP7270 and GP7277 turbofan engines. This AD requires initial and repetitive borescope inspections and removal from service before further flight if one or more burn holes are detected, in certain high-pressure turbine (HPT) stage 2 nozzles. This AD also requires mandatory removal from service of these HPT stage 2 nozzles at the next engine shop visit. This AD was prompted by a report received of inadequate cooling of the HPT stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn-through of the turbine case, and engine shutdown. We are issuing this AD to prevent HPT stage 2 nozzle failure, leading to uncontrolled fire, engine shutdown, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for CFM International, S.A. CFM56-3, CFM56-3B, and CFM56-3C turbofan engines. This AD requires removal from service of certain high-pressure turbine (HPT) disks manufactured by Global Material Solutions of Pratt & Whitney, at reduced maximum life limits. This AD was prompted by a report of a forging process error during manufacture of these HPT disks. We are issuing this AD to prevent uncontained release of multiple turbine blades, damage to the engine, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-Trent 970-84, 970B-84, 972-84, 972B-84, 977-84, 977B-84, and 980-84 turbofan engines. This AD requires replacement of the fuel oil heat exchanger (FOHE). This AD was prompted by a report of an in-flight increase of N2 intermediate pressure rotor vibrations resulting in an engine surge and pilot shut down of the engine. We are issuing this AD to prevent rotor bearing oil starvation, uncontained engine failure, and damage to the airplane.
We are superseding four airworthiness directives related to the main rotor yoke (yoke) on the Bell Model 204B, 205A, 205A-1, 205B, and 212 helicopters, to retain certain inspections and certain life limits, to require an increased inspection frequency for certain yokes, and to expand these inspections and retirement lives to other yokes. This airworthiness directive is prompted by past reports of cracks in the yoke, another recent report of a cracked yoke, and the decision that other yokes, approved based on identicality, need to be subject to the same inspection requirements and retirement lives. The actions are intended to detect a crack in a yoke to prevent failure of the yoke, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for Bell Model 206L, 206L-1, 206L-3, and 206L-4 helicopters. This AD requires inspecting certain hydraulic servo actuator assemblies (servo) for a loose nut, shaft, and clevis assembly, modifying or replacing the servo as necessary, and reidentifying the servo. This AD is prompted by an investigation after an accident and the determination that there was a loose connection due to improper lock washer installation. These actions are intended to detect loose or misaligned parts of the servo to prevent failure of the servo and subsequent loss of control of the helicopter.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes; and certain Model 757-200, -200PF, and -300 series airplanes. That AD currently requires replacing the control switches of the forward, aft, and nose cargo doors of Model 747 airplanes; and requires replacing the control switches of cargo doors 1 and 2 of Model 757 series airplanes. This new AD adds airplanes to the applicability and revises the initial compliance times for those airplanes. This AD was prompted by reports of problems associated with the uncommanded operation of cargo doors. We are issuing this AD to prevent injuries to persons and damage to the airplane and equipment.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, 737-400, 737-500, and 757-200 series airplanes. This AD was prompted by a report of damage caused by electrical arcing to the wires that connect seat electronics boxes (SEBs). This AD requires installing a new relay and doing certain wiring changes of the entertainment control switch. We are issuing this AD to prevent power from being supplied to passenger seats when the entertainment control switch is in the OFF position, which could cause an electrical shock hazard resulting in serious or fatal injury to maintenance personnel.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400F, and 747SR series airplanes. This AD was prompted by reports of broken and damaged latch pin retention bolts and subsequent migration of the latch pins of the main deck side cargo door (MDSCD). This AD requires various repetitive inspections of the MDSCD latch pin fittings, measuring the latch pin, and related investigative and corrective actions if necessary. This AD also requires modifying the latch pin fittings and installing new latch pins and latch pin fasteners. We are issuing this AD to prevent loss of the cargo door and rapid depressurization of the airplane.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200PF, and -200CB series airplanes powered by Rolls-Royce engines. That AD currently requires repetitive inspections of the shim installation between the drag brace fitting vertical flange and bulkhead, and repair if necessary; for certain airplanes, an inspection for cracking of the four critical fastener holes in the horizontal flange, and repair if necessary; and, for airplanes without conclusive records of previous inspections, performing the existing actions. This new AD reduces the repetitive inspection interval; adds repetitive detailed inspections for cracking of the bulkhead, and repair if necessary; allows an extension of the repetitive intervals for certain airplanes by also doing repetitive ultrasonic inspections for cracking of the bulkhead, and repair if necessary; and provides an option for a high frequency eddy current inspection for cracking of the critical fastener holes, and repair if necessary. This action also adds a terminating action for certain repetitive inspections. This AD was prompted by reports of loose fasteners and cracks at the joint common to the aft torque bulkhead and strut-to-diagonal brace fitting, and one report of such damage occurring less than 3,000 flight cycles after the last inspection. We are issuing this AD to detect and correct cracks, loose and broken bolts, and shim migration in the joint between the aft torque bulkhead and the strut-to-diagonal brace fitting, which could result in damage to the strut and consequent separation of the strut and engine from the airplane.
We are adopting a new airworthiness directive (AD) for PILATUS Aircraft Ltd. Model PC-7 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracks in the engine mount fittings caused by stress corrosion. We are issuing this AD to require actions to address the unsafe condition on these products.
The FAA is correcting an airworthiness directive (AD) that published in the Federal Register . That AD applies to Lycoming Engines TSIO-540-AK1A, and Continental Motors, Inc. TSIO-360-MB, TSIO-360-SB, and TSIO-360-RB reciprocating engines, with certain Hartzell Engine Technologies (HET) turbochargers, model TA0411, part number 466642-0001; 466642-0002; 466642-0006; 466642-9001; 466642-9002; or 466642-9006, or with certain HET model TA0411 turbochargers overhauled or repaired since August 29, 2012. The Summary paragraph and the Applicability paragraph list an incorrect engine model for Lycoming Engines. This document corrects those errors. In all other respects, the original document remains the same.
We are superseding an existing airworthiness directive (AD) for all Pratt & Whitney Canada Corp. (P&WC) PW118, PW118A, PW118B, PW119B, PW119C, PW120, PW120A, PW121, PW121A, PW123, PW123B, PW123C, PW123D, PW123E, PW123AF, PW124B, PW125B, PW126A, PW127, PW127E, PW127F, PW127G, and PW127M turboprop engines. That AD currently requires initial and repetitive inspections of certain serial numbers (S/Ns) of propeller shafts for cracks and removal from service if found cracked. This new AD requires the same actions, but requires removal from service of affected propeller shafts as mandatory terminating action to the repetitive inspections. This AD was prompted by reports of two propeller shafts found cracked at time of inspection during maintenance. We are issuing this AD to detect propeller shaft cracks, which could cause failure of the shaft, propeller release, and loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. This AD requires a one-time removal from service of the high-pressure (HP) compressor stages 1 to 6 rotor disc assembly before exceeding certain thresholds. This AD was prompted by a report of silver chloride-induced stress corrosion cracking of the HP compressor stages 1 to 6 rotor disc assembly, identified during overhaul. We are issuing this AD to prevent failure of the HP compressor stages 1 to 6 rotor disc assembly, which could result in uncontained failure of the engine and damage to the airplane.
We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Tay 620-15 turbofan engines. This AD requires a one-time inspection of the low-pressure compressor (LPC) fan blades and if erosion is found their replacement before further flight. This AD was prompted by evidence of excessive leading edge erosion of the LPC fan blades on certain Tay 620-15 engines. We are issuing this AD to prevent failure of the LPC fan blade, which could result in uncontained engine failure and damage to the airplane.
We are adopting a new airworthiness directive (AD) for all Turbomeca S.A. Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, and 1S1 turboshaft engines. This AD requires performing a high gas generator speed (NG) rating vibration check. This AD was prompted by several reports of uncommanded in-flight shutdown on Arriel 1 engines. We are issuing this AD to prevent an uncommanded in-flight shutdown of the engine, which could result in an emergency landing.
We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires revising the airplane flight manual (AFM) to advise the flight crew of emergency procedures for addressing Angle of Attack (AoA) sensor blockage. This AD also provides for optional terminating action for the AFM revision, which involves replacing AoA sensor conic plates with AoA sensor flat plates. This AD was prompted by a report that an airplane equipped with AoA sensors installed with conic plates recently experienced blockage of all sensors during climb, leading to autopilot disconnection and activation of the alpha protection (Alpha Prot) when Mach number was increased. We are issuing this AD to prevent reduced control of the airplane.
We are adopting a new airworthiness directive (AD) for Burkhart GROB Luft- und Raumfahrt GmbH Models GROB G 109 and GROB G 109B sailplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as corrosion and/or cracking of the elevator control rod that could lead to failure of the elevator control rod with consequent loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for all Thielert Aircraft Engines GmbH (TAE) TAE 125-02-99 and TAE 125-02-114 reciprocating engines. This AD requires inspection of the oil filler plug vent hole at the next scheduled maintenance or within 110 flight hours after the effective date of this AD. If chips are found to be blocking the vent hole, additional corrective action is required before next flight. This AD was prompted by an in-flight shutdown of an airplane equipped with a TAE 125-02-99 engine. We are issuing this AD to prevent engine in-flight shutdown or power loss, possibly resulting in reduced control of the airplane.
We are superseding an existing airworthiness directive (AD) for all Thielert Aircraft Engines GmbH models TAE 125-01, TAE 125-02-99, and TAE 125-02-114 reciprocating engines. That AD currently requires installation of full-authority digital electronic control (FADEC) software version 2.91. This new AD requires removing all software mapping versions prior to 292, 301, or 302, applicable to the TAE engine model. This AD was prompted by reports of possible power loss on airplanes equipped with TAE 125 engines. We are issuing this AD to prevent engine power loss or in-flight shutdown, resulting in reduced control of or damage to the airplane.
We are adopting a new airworthiness directive (AD) for the Bell Helicopter Textron Inc. (BHTI) Model 205A, 205A-1, and 205B helicopters with certain starter/generator power cable assemblies (power cable assemblies). This AD requires replacing the power cable assemblies and their associated parts, and performing continuity readings. This AD was prompted by the determination that the power cable assembly connector (connector) can deteriorate, causing a short in the connector that may lead to a fire in the starter/generator, smoke in the cockpit that reduces visibility, and subsequent loss of helicopter control.
We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aerosystems Model SAAB 2000 airplanes. This AD was prompted by reports of chafing on the bottom panel of the center cabin. This AD requires a general visual inspection to determine if certain fasteners are installed, and related investigative and corrective actions. We are issuing this AD to detect and correct any chafing on the bottom panel of the center cabin, which could affect the structural integrity of the affected wing-to-fuselage connection.
We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. air data pressure transducers as installed on various aircraft. This AD requires various tests or checks of equipment having certain air data pressure transducers, and removal of equipment if necessary. As an option to the tests or checks, this AD allows removal of affected equipment having certain air data pressure transducers. This AD was prompted by a report of a pressure measurement error in the pressure transducer used in various air data systems, which translates into air data parameter errors. We are issuing this AD to detect and correct inaccuracies of the pressure sensors, which could result in altitude, computed airspeed, true airspeed, and Mach computation errors. These errors could reduce the ability of the flightcrew to maintain the safe flight of the aircraft and could result in consequent loss of control of the aircraft.
We are adopting a new airworthiness directive (AD) for all Eurocopter France (Eurocopter) Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365C, SA-365C1, SA-365C2, and SA-366G1 helicopters. This AD requires inspecting portions of the main gearbox (MGB) for the presence of sealing compound and corrosion. This AD was prompted by reports of corrosion on the main MGB casing lower area between the two servo-control anchoring fitting attachment ribs. An investigation determined that the corrosion was associated with sealing compound on the lower part of the fitting/casing attachment. The actions in this AD are intended to detect corrosion on the MGB casing, which could lead to a crack, failure of the MGB, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350BA helicopters with certain AERAZUR emergency flotation gear container assemblies installed. This AD requires replacing each affected emergency flotation gear container assembly (container assembly) at specified time limits based on the date of manufacture. This AD was prompted because container assemblies with an intended operating limitation of 10 years may not have been replaced because the limit is no longer recorded in the Maintenance Program. The actions of this AD are intended to prevent failure of the emergency container assembly because of age and subsequent damage to the helicopter and injury to the occupants after an emergency water landing.
We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-524G2-19; RB211-524G2-T-19; RB211-524G3-19; RB211-524G3-T-19; RB211-524H2-19; RB211-524H2-T-19; RB211-524H-36; RB211-524H-T-36; RB211-535E4-37; RB211-535E4-B-37; RB211-535E4-B-75; and RB211-535E4-C-37 turbofan engines. This AD was prompted by an investigation by RR concluding that certain intermediate-pressure (IP) turbine discs produced before 1997 by a certain supplier may contain steel inclusions. This AD requires removal of the affected IP turbine discs to inspect them for steel inclusions, and removal of the affected discs from service if they fail the inspection. This AD also requires removal from service of some IP turbine discs at reduced life limits. We are issuing this AD to prevent uncontained IP turbine disc failure, engine failure, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter series airplanes, Model A330-200 series airplanes, Model A330-300 series airplanes, Model A340-200 series airplanes, and Model A340-300 series airplanes. This AD was prompted by a report of an in-flight turn back after the nose landing gear (NLG) did not retract after take-off. This AD requires repetitive overhaul of the NLG retraction actuator. We are issuing this AD to prevent failure of the retraction actuator, which could cause collapse of the NLG after touchdown and possible injury to flightcrew and passengers.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-202, -203, -223, -243, -302, -323, -342, and -343 airplanes; and Model A340-313 airplanes. This AD was prompted by reports that a specific batch of cargo doors might have deviations in quality related to door structure, such as irregular bore holes, improper application of sealant and paint, or uncleanliness. This AD requires inspecting to identify the part and serial numbers of the forward and aft cargo doors, and replacing the affected cargo doors. We are issuing this AD to prevent the degraded structural capability of the cargo door, a primary structure, from leading to failure of the door, which could lead to a breach through the door or the door detaching from the airplane, resulting in potential rapid decompression.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. That AD currently requires repetitive inspections for cracking of the crown area of the fuselage skin, and corrective actions if necessary. This new AD adds repetitive inspections for cracking using different inspection methods and inspecting additional areas, and corrective actions if necessary. This new AD also requires additional repairs to previously repaired areas and repetitive inspections for loose fasteners and replacement if necessary in certain previously repaired areas. This AD also reduces certain compliance times and extends certain other compliance times. This AD was prompted by additional reports of cracking at the horizontal chem-mill steps away from the lap joints over the entire crown area, and vertical chem-mill cracks adjacent to the butt joints. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin, which could cause the fuselage skin to fracture and fail, and result in rapid decompression of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-300 series airplanes and Model A340-200 and -300 series airplanes. This AD was prompted by reports that, during a flight test, several spoiler servo-controls (SSCs) did not remain locked in the retracted position (hydraulic locking function) after manual depressurization of the corresponding hydraulic circuit. Loss of that locking function—which is ensured by a blocking valve—was caused by an internal leak from a sheared seal on the blocking valve. This AD requires inspecting to determine if certain SSCs are installed, performing an operational test of any affected SSC, and replacing if necessary. We are issuing this AD to prevent loss of the hydraulic locking function during take-off and go-around phases, which, in combination with malfunction of one engine, could result in reduced controllability of the airplane.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of escape slides failing to deploy from the forward and aft right-hand doors during scheduled maintenance slide deployments. This AD requires modifying the escape slide. Also, for certain airplanes, this AD requires modifying or replacing the Vespel piston. For certain other airplanes, this AD requires an additional modification of the escape slide. We are issuing this AD to prevent failure of an escape slide to deploy, which could result in the slide being unusable during an emergency evacuation and increased likelihood of injury to passengers or crewmembers due to the difficulty in evacuating the airplane.
We are revising an existing airworthiness directive (AD) for all GA200 (Pty) Ltd Models GA200 and GA200C airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure of the wing strut bolt through the main spar. We are issuing this AD to require actions to address the unsafe condition on these products.
We are superseding an existing airworthiness directive (AD) for certain Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; and Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, and B4-622R airplanes. That AD currently requires performing a one-time detailed visual inspection of the forward fitting at frame (FR) 40 on both sides of the airplane for cracks, and repair if necessary. This new AD requires repetitive detailed inspections of the forward fitting at FR 40 without nut removal, and a one-time eddy current or liquid penetrant inspection of the forward fitting at FR 40 with nut removal, and repair if necessary. This AD was prompted by reports that new cracks were found in the FR 40 forward fitting. We are issuing this AD to detect and correct cracking of the FR 40 forward fitting, which could result in a deterioration of the structural integrity of the frame.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 and -300 series airplanes. This AD was prompted by a report of a prematurely fractured main landing gear (MLG) bogie beam. This AD requires replacing certain MLG bogie beams before reaching new reduced life limits. We are issuing this AD to prevent fracture of the MLG bogie beam, which, under high speed, could ultimately result in the airplane departing the runway, the bogie beam detaching from the airplane, or collapse of the MLG; and consequent structural damage to the airplane and injury to the occupants.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. That AD currently requires initial and repetitive inspections of the fuselage skin and bear strap at the forward, upper corner of the L1 entry door cutout for cracking, and repair if necessary. That action also provides an optional terminating action for the repetitive inspections. That AD also requires additional inspections for airplanes having repairs or preventative modifications installed and inspections for certain other airplanes. This AD requires the previous actions with additional airplane group configurations added to paragraph (n) of this AD. This AD was prompted by a determination that certain airplane group configurations in paragraph (n) of the existing AD were inadvertently removed in the final rule. We are issuing this AD to detect and correct cracking of the fuselage skin and bear strap at the forward upper corner of the L1 entry door cutout, which could result in reduced structural integrity of the L1 entry door, and consequent rapid decompression of the airplane.
We are adopting a new airworthiness directive (AD) for certain serial numbers (S/Ns) of Rolls-Royce plc (RR) RB211-Trent 768-60, 772-60, and 772B-60 turbofan engines. This AD requires initial and repetitive on-wing or in-shop inspections of the high pressure/intermediate pressure (HP/IP) turbine bearing support oil feed tube outer heat shield. This AD also requires installation of a revised HP/IP turbine bearing support structure as terminating action to the repetitive inspections of the HP/IP turbine bearing support oil feed tube outer heat shield. This AD was prompted by a report of high oil consumption due to an oil leak from the HP/IP turbine bearing support oil feed tube. We are issuing this AD to prevent failure of the HP turbine disc, uncontained engine failure, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GIV-X airplanes. This AD requires performing a modified system power-on self test (SPOST) of the flap/stabilizer electronic control unit (FSECU), and revising the airplane flight manual to incorporate these test procedures into the daily preflight check. This AD was prompted by reports indicating that the FSECU does not detect failures of the brake feature within the horizontal stabilizer electric motor unit (HSEMU), or failures of drive solenoids for hydraulic valves within the flap hydraulic control module (FHCM) during the SPOST. We are issuing this AD to detect and correct such failures, which could result in runaway horizontal stabilizer pitch trim system and consequent loss of pitch control.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400 and -400F series airplanes. This AD was prompted by multiple reports of integrated display unit (IDU) malfunctions and mode control panel (MCP) malfunctions. This AD requires installing new software, replacing the duct assembly with a new duct assembly, making wiring changes, and routing certain wire bundles. We are issuing this AD to prevent IDU malfunctions, which could affect the ability of the flightcrew to read primary displays for airplane attitude, altitude, or airspeed, and consequently reduce the ability of the flightcrew to maintain control of the airplane.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This AD was prompted by a report of in-flight fracture of the right windshield (window 1) on the flight deck and multiple reports of electrical arcs at the terminal blocks of the flight deck windshields resulting in smoke and fire. This AD requires repetitive inspections of electrical heat terminals on the left and right windshields for damage, and corrective actions if necessary. This AD allows replacing an affected windshield with a windshield equipped with different electrical connections, which would terminate the repetitive inspections for that windshield. We are issuing this AD to prevent smoke and fire in the flight deck, which can lead to loss of visibility, and injuries to or incapacitation of the flightcrew.
We are superseding an existing airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. That AD currently requires revising the airworthiness limitations section (AWL) of the Instructions for Continued Airworthiness (ICA) of the Canadair Regional Jet Maintenance Requirements Manual (MRM) by incorporating new procedures for repetitive detailed and special detailed inspections for cracking of the aft pressure bulkhead. This new AD requires revising the maintenance program to incorporate a revised task specified in a certain temporary revision, which requires an improved non-destructive inspection procedure; and adds airplanes to the applicability. This AD was prompted by multiple reports of cracks on the forward face of the rear pressure bulkhead (RPB) web. We are issuing this AD to detect and correct cracking in the RPB, which could result in reduced structural integrity and rapid decompression of the airplane.
We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E and Model A109S helicopters with certain lower semichannel assemblies installed. This AD requires a one-time inspection of the lower semichannel assemblies to determine if metallic spacers are installed. If the metallic spacers are installed, this AD requires an inspection for the correct installation of the metallic spacers on the semichannels and for the correct seating of the gaskets. If the metallic spacers are not installed with rivets, the lower semichannel assemblies must be modified, and the main drive shaft must be inspected for damage. This AD was prompted by reports of damage to the main drive shaft caused by improperly secured metallic spacers on some A109 model helicopters. The actions of this AD are intended to detect missing spacer rivets, which could allow the metallic spacers to rotate and lead to damage and failure of the main drive shaft, and subsequent loss of helicopter control.
We are adopting a new airworthiness directive (AD) for Erickson Air-Crane Incorporated (Erickson) Model S-64F helicopters. This AD requires inspecting for cracking or working rivets in each left and right splice fitting (transition fitting), the pylon bulkhead assembly-canted (bulkhead assembly), and the pylon steel strap (strap). This AD was prompted by several reports of cracking in the transition fittings, the bulkhead assembly, and the pylon. The actions specified by this AD are intended to detect cracking in the rotary rudder boom or pylon due to fatigue, and to prevent failure from static overload and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-Trent 900 series turbofan engines. This AD requires inspection of the low pressure turbine (LPT) bearing housing end cover assembly in certain engines and, if necessary, its replacement. This AD was prompted by a Trent 900 engine experiencing a high intermediate pressure vibration fault, along with other fluctuating engine parameters, while in flight. We are issuing this AD to prevent fracture of the oil transfer tube, which could result in uncontained failure of the engine and damage to the airplane.
We are superseding an existing airworthiness directive (AD) for all Embraer S.A. Model ERJ 190-100 STD, -100 LR, -100 IGW, -200 STD, -200 LR, and -200 IGW airplanes. That AD currently requires revising the maintenance program to incorporate modifications in the Airworthiness Limitation Section (ALS) of the EMBRAER ERJ 190 Maintenance Review Board Report (MRBR). This new AD requires revising the maintenance program to incorporate modifications in the ALS of the EMBRAER ERJ 190 MRBR to include new inspection tasks and their respective thresholds and intervals. This AD was prompted by issuance of new inspection tasks and their respective thresholds and intervals. We are issuing this AD since failure to inspect these structural components according to the new ALS tasks, thresholds, and intervals could prevent a timely detection of fatigue cracking, which if not properly addressed, could result in reduced structural integrity of the airplane.
We are publishing a new airworthiness directive (AD) for Agusta Model AW139 helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires inspecting the pilot's and co-pilot's collective and cyclic control sticks for correctly installed attaching hardware. This AD is prompted by a report of an incorrectly installed pilot's collective stick, pilot's cyclic stick, and co-pilot's cyclic stick. These actions are intended to prevent detachment of the cyclic or collective control stick, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aerosystems Model 340A (SAAB/SF340A) and SAAB 340B airplanes. This AD was prompted by reports of stall events during icing conditions where the natural stall warning (buffet) was not identified. This AD requires replacing the stall warning computer (SWC) with a new SWC, which provides an artificial stall warning in icing conditions, and modifying the airplane for the replacement of the SWC. We are issuing this AD to prevent natural stall events when operating in icing conditions, which, if not corrected, could result in loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of flight crew failure to activate air data probe heat. This AD requires modifying the anti-icing system for the angle of attack sensor, the total air temperature, and the pitot probes. We are issuing this AD to prevent ice from forming on air data system sensors and consequent loss of or misleading airspeed indication on all airspeed indicating systems, which could lead to loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for all Eurocopter Deutschland GmbH (ECD) Model EC135 helicopters, except the EC 135 P2+ and T2+. This AD requires inspecting each upper and lower plain journal bearing (bearing) and replacing the swashplate assembly with an airworthy swashplate assembly if a bearing is not correctly positioned. This AD was prompted by two reports of the bearings moving in relation to the main rotor swashplate sliding sleeve (sliding sleeve). The actions of this AD are intended to detect shifting of the bearing, which could limit the movement of the collective control and result in subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD requires ensuring that lockwire is installed correctly on the engine fuel feed manifold couplings. This AD also requires inspecting the assembly of the engine fuel feed manifold rigid and full flexible couplings. This AD was prompted by reports of fuel leaks due to improperly assembled engine fuel feed manifold couplings. We are issuing this AD to detect and correct improperly assembled couplings, which could result in fuel leaks and consequent fuel exhaustion, engine power loss or shutdown, or leaks on hot engine parts that could lead to a fire.
We are adopting a new airworthiness directive (AD) for Lycoming Engines TSIO-540-AK1A, and Continental Motors, Inc. TSIO-360-MB, TSIO-360-SB, and TSIO-360-RB reciprocating engines, with certain Hartzell Engine Technologies (HET) turbochargers, model TA0411, part number (P/N) 466642-0001; 466642-0002; 466642-0006; 466642-9001; 466642-9002; or 466642-9006, or with certain HET model TA0411 turbochargers overhauled or repaired since August 29, 2012. This AD requires removing the affected turbochargers from service before further flight. This AD was prompted by a report of a turbocharger turbine wheel that failed a static strength test at its manufacturing facility. We are issuing this AD to prevent turbocharger turbine wheel failure, reduction or complete loss of engine power, loss of engine oil, oil fire, and damage to the airplane.
We are superseding an existing airworthiness directive (AD) for all Turbomeca S.A. Arriel 1E2, 1S, and 1S1 turboshaft engines. That AD currently requires a one-time inspection and torque check of the 3-way union plug installed on all fuel control units (FCUs). This new AD requires the same actions. This AD also requires reduction of the applicability to certain FCUs and references an updated service bulletin containing additional detailed information to identify the non-compliant “red disk.” This AD also requires replacement of the plug before further flight if it is found to be non-compliant, and prohibits installation of FCUs that have not passed the 3-way union plug inspection and torque check. This AD was prompted by Turbomeca S.A. informing us that FCUs manufactured, repaired, or overhauled after March 31, 2008, do not require inspection. We are issuing this AD to prevent fuel leaks, which could result in a fire and damage to the helicopter.
We are superseding an existing airworthiness directive (AD) for all Turbomeca S.A. Arriel 1A, 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E, 1E2, 1K, 1K1, 1S, and 1S1 turboshaft engines. That AD currently requires initial and repetitive visual inspections for erosion caused by dust ingestion and, if necessary, cleaning of the gas generator (module M03). This new AD requires determining the engine history; performing a one-time visual inspection of the axial compressor for erosion; performing initial and repetitive cleaning of the gas generator hollow shaft; and replacing the rear bearing if the amount of dust collected during cleaning exceeds 8 grams. This AD also includes an optional terminating action. This AD was prompted by in-service experience which has shown that dust inside the gas generator hollow shaft may be found when the axial compressor wheel has less erosion than initially assessed. We are issuing this AD to prevent an unbalance of the gas generator rotating assembly, which may lead to gas generator rear bearing failure, and uncommanded engine shutdown.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report of a crack found in the fuselage skin under the aft drain mast. This AD requires a detailed inspection for cracking and corrosion of the channel and fillers adjacent to the drain mast bolts, an inspection to determine the location of the bonding strap, a measurement of the washers under the drain mast bolts, and related investigative actions and repair if necessary. We are issuing this AD to detect and correct cracking in the fuselage skin and internal support structure, which could result in uncontrolled decompression of the airplane.
We are adopting a new airworthiness directive (AD) for all Stemme GmbH & Co. KG Models S10, S10-V, and S10-VT powered sailplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as unapproved rubber hoses installed in the engine fuel, oil, and cooling systems, which could lead to a system leak and result in an engine fire. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for GA 8 Airvan (Pty) Ltd Models GA8 and GA8-TC320 Airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as burnt electrical connectors leading to the left-hand wingtip pitot heater, which may result in loss of airspeed indication. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain serial number (S/N) Rolls-Royce Deutschland Ltd & Co KG (RRD) TAY 620-15 turbofan engines. This AD requires initial and repetitive general inspections and ultrasonic inspections (UI) of low-pressure compressor (LPC) fan blades for cracks. If any fan blade is found cracked, this AD requires replacement of the LPC fan blade set and the LPC fan disc. This AD was prompted by a report of an LPC fan blade separation. We are issuing this AD to detect cracks in the LPC fan blades, which could lead to uncontained failure of the LPC fan blades and LPC fan disc, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for Sikorsky Model S-70, S-70A, and S-70C helicopters, which are restricted category helicopters derived from the military Model UH-60 helicopter. This AD would require reducing or establishing life limits for certain listed helicopter parts. This AD is prompted by a review of the United States Army's analysis of their Model UH-60 fleet, which determined it necessary to establish or reduce the life limits of certain parts. The actions are intended to prevent fatigue failure of a part and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by reports of cracks in the main entry door number 1 upper main sill outer chord, along the bend radius of the chord on several airplanes. This AD requires a general visual inspection to identify any existing structural repair manual (SRM) repairs of the upper main sill outer chord of the left and right side main entry door number 1, repetitive detailed inspections for cracks in the upper main sill of the door(s); and related investigative and corrective actions, if necessary. This AD also requires repetitive inspections for airplanes on which a certain repair is done, and corrective actions if necessary, and reduces certain compliance times. We are issuing this AD to detect and correct cracks in the main entry door number 1 upper main sill outer chord, along the bend radius of the chord, which could result in loss of structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by reports of failure of wire support clamps in the forward section of the aft pressure bulkhead. This AD requires a detailed inspection of the clamps on the power feeder cable of the auxiliary power unit (APU) to determine if certain clamps are installed, and related investigative and corrective actions if necessary. We are issuing this AD to prevent failure of the clamp, which could result in wire chafing and potential arcing and consequent fire in section 48 (a flammable fluid leakage zone) or heat damage to the APU power feeder cable, insulation blankets, or pressure bulkhead.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. That AD currently requires replacing the drain tube assemblies and support clamps on the aft fairing of the engine struts. This new AD requires replacing the drain tube assembly of the left and right engine strut aft fairings with a new one, which includes an integral support clamp made of nickel alloy 625. This AD also adds airplanes to the applicability. This AD was prompted by a report of a broken drain tube assembly on the left engine strut at the clamp support location under the aft fairing compartment, inside the heat shield cavity of the aft fairing. There have also been reports of tube wear at this clamp location on additional airplanes. We are issuing this AD to prevent failure of the drain tube assemblies and clamps on the aft fairings of the engine struts. Such failure could allow leaked flammable fluids in the drain systems to discharge onto the heat shields of the aft fairings of the engine struts, which could result in an undetected and uncontrollable fire.
We are adopting a new airworthiness directive (AD) for all Eurocopter France (Eurocopter) Model SA.315B Alouette III, SE.3160 Alouette III, SA.316B Alouette III, SA.316C Alouette III, SA.319B Alouette III, SA 3180-ALOUETTE ASTAZOU, SA 318B-ALOUETTE ASTAZOU, and SA 318 C-ALOUETTE ASTAZOU helicopters. This AD requires inspecting the cage of the free-wheel assembly for the correct alignment of the roller drive pocket recesses and replacing the free-wheel cage with an airworthy free-wheel cage if a defect exists. This AD was prompted by incorrect positioning of the roller drive pocket recesses on the tail rotor drive shaft free-wheel cage, which caused a pilot to experience a heavy jerk in the yaw control during in-flight autorotation training. The requirements of this AD are intended to prevent a loss of tail rotor drive and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports of the escape slide of the raft inflation system not deploying when activated due to the rotation of the cable guide in a direction which resulted in jamming of the inflation control cable. This AD requires modifying the affected slide rafts. We are issuing this AD to prevent non-deployment of the inflation system of the escape slide raft, which could result in delayed evacuation from the airplane during an emergency, and consequent injury to the passengers.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-243, -243F, -341, -342, and -343 airplanes equipped with Rolls-Royce Trent 700 engines. This AD was prompted by reports of extensive damage to engine air intake cowls as a result of acoustic panel collapse. This AD requires repetitive inspections of the three inner acoustic panels of both engine air intake cowls to detect disbonding, and corrective actions if necessary. We are issuing this AD to detect and correct disbonding, which could result in detachment of the engine air intake cowl from the engine leading to ingestion of parts, which could cause failure of the engine, and possible injury to persons on the ground.
We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Models 172R and 172S airplanes. This AD was prompted by reports of chafed fuel return line assemblies, which were caused by the fuel return line assembly rubbing against the right steering tube assembly during full rudder pedal actuation. This AD requires you to inspect the fuel return line assembly for chafing; replace the fuel return line assembly if chafing is found; inspect the clearance between the fuel return line assembly and both the right steering tube assembly and the airplane structure; and adjust as necessary. We are issuing this AD to correct the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200 and -300 series airplanes. This AD was prompted by reports of cracks in the inner chords at both left-side and right-side stations 859.5, 883.5, and 903.5. This AD requires repetitive inspections of the frame inner chord transition radius for cracks, and related investigative and corrective actions if necessary. We are issuing this AD to prevent large cracks in the frames and adjacent structure that can adversely affect the structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, -400D, and -400F series airplanes. This AD was prompted by reports of crown frame web cracking at left buttock line (LBL) 15.0, station (STA) 320. This AD requires measuring the web at STA 320 and, depending on findings, various inspections for cracks and missing fasteners, web and fastener replacement, and related investigative and corrective actions if necessary. We are issuing this AD to prevent complete fracture of the crown frame assembly, and consequent damage to the skin and in-flight decompression of the airplane.
We are adopting a new airworthiness directive (AD) for all Cessna Aircraft Company (Cessna) Model 402C airplanes modified by Supplemental Type Certificate (STC) SA927NW and Model 414A airplanes modified by STC SA892NW. This AD was prompted by report of a Cessna Model 414A airplane modified by STC SA892NW that experienced an asymmetrical flap condition causing an uncommanded roll when the pilot set the flaps to the approach position. We are issuing this AD to prevent failure of the flap system, which could result in an asymmetrical flap condition. This condition could result in loss of control.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 737-100 and -200 series airplanes. The existing AD currently requires various inspections for cracks in the outboard chord of the frame at body station (BS) 727 and in the outboard chord of stringer (S) 18A, and repair or replacement of cracked parts. This new AD adds airplanes to the applicability statement in the existing AD and adds inspections for cracks in the BS 727 frame outboard chords and the radius of the auxiliary chord, for certain airplanes. This new AD also removes the inspections of the outboard chord of S-18A required by the existing AD. This AD was prompted by several reports of fatigue cracking in the frame outboard chord at BS 727 and in the radius of the auxiliary chord on airplanes that were not affected by the existing AD. We are issuing this AD to detect and correct fatigue cracking of the outboard and auxiliary chords, which could result in reduced structural integrity of the outboard chord and consequent rapid decompression of the airplane.
We are adopting a new airworthiness directive (AD) for all Eurocopter Deutschland GmbH (ECD) Model MBB-BK117 C-2 helicopters with certain Generator Control Units (GCU) installed. This AD requires replacing the GCUs. This AD was prompted by reports of internal short circuits in certain GCUs. These actions are intended to prevent a short circuit, which could result in a loss of electrical generating power, loss of systems required for continued safe flight and landing, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model EC135 P1, EC135 P2, EC135 P2+, EC135 T1, EC135 T2, and EC135 T2+ helicopters. This is the Federal Register publication of an Emergency AD (EAD) that was previously sent to all known owners and operators of these helicopters. That EAD superseded an earlier related EAD. This AD requires, before further flight and at specified intervals, checking and inspecting the upper and lower main rotor hub (MRH) shaft flanges for a crack, and inspecting the lower hub-shaft flange bolt attachment areas for a crack. This AD is prompted by three reported incidents of cracking on the lower hub-shaft flanges of EC135 model helicopters. These actions are intended to detect a crack on the hub-shaft flange, which if not corrected could result in failure of the MRH and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600 and A300 B4-600R, Model A300, and Model A310 series airplanes. This AD was prompted by reports of fatigue cracking in the crossbeams at the junction of the actuator beam of the lower deck cargo door. This AD requires repetitive inspections of the crossbeams of certain fuselage frames, and repair if necessary. We are issuing this AD to detect and correct cracking of the crossbeams at the junction of the actuator beam of the lower deck cargo door, which could result in failure to withstand ultimate load conditions, and consequent reduced structural integrity of the airplane.
We are superseding an existing airworthiness directive (AD) for certain Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. That AD currently requires performing a detailed visual inspection for cracks of the pistons on the main landing gear (MLG), and replacing the affected pistons if necessary. This new AD also requires modifying the MLG by installing a piston containing a certain part number, and revising the airplane maintenance program. This AD was prompted by a new modification developed to safeguard the integrity of the MLG assembly and improve surface protection of the affected area of the MLG piston. We are issuing this AD to prevent MLG failure, possibly resulting in loss of control of the airplane during the landing roll-out.
We are superseding an existing airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. That AD currently requires revising the airworthiness limitations section (ALS) of the instructions for continued airworthiness for certain airplanes, and the FAA-approved maintenance program for certain other airplanes, to incorporate new limitations. This new AD requires revising the maintenance program to incorporate the limitations, tasks, thresholds, and intervals specified in certain revised Fokker maintenance review board (MRB) documents. This AD was prompted by a revised Fokker 70/100 MRB document with revised limitations, tasks, thresholds, and intervals. We are issuing this AD to reduce the potential of structural failures or of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron (BHT) Model 412, 412EP, and 412CF helicopters. This AD requires a repetitive inspection of the collective lever for a crack, and if there is a crack, before further flight, replacing the collective lever with an airworthy collective lever. This AD was prompted by a reported failure of a collective lever. The actions are intended to detect a crack in the collective lever, which could lead to failure of the collective lever and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for the Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires inspecting the tail rotor (T/R) pylon for a loose or missing fastener, a crack, damage, or corrosion and adding an internal doubler to the aft shear deck tunnel assembly. This AD was prompted by the discovery of cracks in T/R pylons. The actions are intended to detect a loose or missing fastener, a crack, damage, or corrosion on the T/R pylon and, if present, to repair the T/R pylon and install a doubler on the aft shear deck tunnel assembly or to replace the T/R pylon and install a doubler on the aft shear deck tunnel assembly. The actions are intended to prevent failure of the T/R pylon or other T/R components, which could lead to the loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Sikorsky Aircraft Corporation (Sikorsky) Model S-76C helicopters. This AD requires installing an improved throttle stop and a wider trigger on the engine control levers (ECL). This AD was prompted by a bird-strike to the windshield that resulted in unintended movement of the engine control levers from the forward position and towards the flight-idle position, which reduced power on both engines. These actions are intended to prevent unintended movement of the ECLs, resulting in main rotor speed decay and subsequent loss of control of the aircraft.
We are superseding an existing Emergency airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-70, S-70A, S-70C, S-70C(M), and S-70C(M1) helicopters with a certain part-numbered intermediate gearbox (IGB). The existing Emergency AD requires a one-time inspection of the internal oil passages of the IGB for an obstruction. That Emergency AD was prompted by an accident that resulted from blockage of oil in the IGB by a plug that was inadvertently left in the IGB during the coating of the IGB housing. We are issuing this supersedure to that Emergency AD to include two additional part numbers of affected IGBs and identify a specific date since new or overhaul of the affected IGBs. The actions specified by this AD are intended to detect a plug in the IGB and prevent overheating and seizing of the IGB, failure of the tail rotor drive output shaft, loss of tail rotor drive, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for all Pratt & Whitney Division PW4050, PW4052, PW4056, PW4060, PW4060A, PW4060C, PW4062, PW4062A, PW4152, PW4156, PW4156A, PW4158, PW4160, PW4460, PW4462, and PW4650 turbofan engines, including models with any dash number suffix. This AD was prompted by 16 reports of damaged or failed 3rd stage low-pressure turbine (LPT) duct segments. This AD requires removing from service certain part numbers (P/Ns) of 3rd stage LPT duct segments. We are issuing this AD to prevent failure of the 3rd stage LPT duct segments, which could lead to LPT rotor damage, uncontained engine failure, and damage to the airplane.
We are revising an existing airworthiness directive (AD) for certain Piaggio Aero Industries S.p.A. Model P-180 airplanes. That AD currently requires replacement of any firewall shutoff or crossfeed valve with a serial number in a certain range even if it has been previously modified. The way the applicability was written includes valves that should not be affected and are not included in the referenced service information. This AD requires the same actions as the current AD, but only affects those firewall shutoff valves referenced in the referenced service information. We are issuing this AD to clarify the affected parts required to correct the unsafe condition on these products.
We are revising an existing airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes; all Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes; all Model CL-600-2D15 (Regional Jet Series 705) airplanes; and all Model CL-600-2D24 (Regional Jet Series 900) airplanes. That AD currently requires replacing certain water accumulator assemblies having a certain part installed on the pitot and static lines of the air data computer (ADC). This new AD corrects an erroneous service document number and removes the other erroneously cited service document from that AD. This new AD was prompted by an error that was discovered in one service document number, and a determination that credit for accomplishing actions in another erroneously cited service document should be removed from that AD. We are issuing this AD to prevent pitot-static tubing from becoming partially or completely blocked by water, which could result in erroneous airspeed and altitude indications and consequent loss of control of the airplane.
The FAA is correcting an airworthiness directive (AD) that published in the Federal Register . That AD applies to certain Univair Aircraft Corporation Models (ERCO) 415-C, 415-CD, 415-D, E, G; (Forney) F-1 and F-1A; (Alon) A-2 and A2-A; and (Mooney) M10 airplanes. All references to Ercoupe Service Memorandum No. 20, Revision A, dated September 1, 2008, in the non-regulatory preamble and the regulatory text of the AD are incorrect because it is a service bulletin instead of a memorandum. This document corrects these errors. In all other respects, the original document remains the same.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. This AD was prompted by reports of an in-service incident where the propeller de-icing system became unavailable due to burnt/chafed wires within the alternating current contactor box (ACCB). This AD requires inspection for chafing, damage, and loose wiring within an ACCB and repair if necessary; and requires rework and re-identification of the wiring installation within each ACCB. We are issuing this AD to detect and correct damaged, chafed, or loose wiring within an ACCB, which could affect the operation of the windshield heater, ice detector, angle of attack (AOA) vane heater, pilot probe heater, engine intake heater, or propeller de-icing system, and subsequently adversely affect the airplane's flight characteristics in icing conditions.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a report that certain wing-to-fuselage attachment nuts do not conform to the certification design requirements for dual locking features. This AD requires repetitive inspections to determine that cotter pins are installed at affected wing-to-fuselage attachment joints and replacement if necessary. We are issuing this AD to prevent loss of wing-to-fuselage attachment joints, which could result in the loss of the wing.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-243, -243F, -341, -342, and -343 airplanes. This AD was prompted by reports of cracking of air intake cowls on Rolls-Royce Trent engines, worn and detached attachment links, and fractured thermal anti-ice (TAI) piccolo tubes. This AD requires inspecting piccolo tubes, piccolo tube mount links, the aft side of the forward bulkhead, and outer boundary angles (OBA) for cracks, fractures, and broken links, and corrective actions if necessary. We are issuing this AD to prevent degraded structural integrity of the engine nose cowl in case of forward bulkhead damage in conjunction with a broken piccolo tube, and damage to the engine due to operation in icing conditions with reduced TAI performance.
We are adopting a new airworthiness directive (AD) for all 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); and Model A310 series airplanes. This AD was prompted by events of excessive rudder pedal inputs and consequent high loads on the vertical stabilizer on several airplanes. This AD requires either incorporating a design change to the rudder control system and/or other systems, or installing a stop rudder inputs warning (SRIW) modification. We are issuing this AD to prevent loads on the vertical stabilizer that exceed ultimate design loads, which could cause failure of the vertical stabilizer and consequent reduced controllability of the airplane.
We are adopting a new airworthiness directive (AD) for Aeronautical Accessories, Inc. (AAI) high landing gear forward crosstube assemblies (crosstubes) installed on Agusta S.p.A. (Agusta) Model AB412 and AB412EP; and Bell Helicopter Textron, Inc. (Bell) Model 205A, 205A-1, 205B, 212, 412, 412CF, and 412EP helicopters during production or based on a supplemental type certificate (STC). This AD requires counting and recording the total number of landings for the crosstubes, and inspecting the crosstubes and replacing them if a crack or other damage exists. This AD was prompted by two reports from the field of failed crosstubes. The actions are intended to prevent failure of a crosstube, collapse of the landing gear, and subsequent loss of control of the helicopter.
The FAA is correcting an airworthiness directive (AD) that was published in the Federal Register . That AD applies to BRP-Powertrain GmbH & Co KG Rotax 912 F2; 912 F3; 912 F4; 912 S2; 912 S3; and 912 S4 reciprocating engines. The word “not” was improperly omitted from the Installation Prohibition section of the AD, thereby changing the prohibition in the AD. This correction reinserts “not” into the paragraph to correct the omission. In all other respects, the original document remains the same.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 freighter series airplanes, Model A330-200 and -300 series airplanes, and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports of the ram air turbine (RAT) not deploying when tested. This AD requires identification of the supplier, part number, and serial number of the installed RAT actuator, and re-identification of the actuator and RAT, or replacement of the RAT actuator with a serviceable unit and re-identification of the RAT, if necessary. We are issuing this AD to prevent non-deployment of the RAT, which if occurred following a total engine flame-out, or during a total loss of normal electrical power generation, could result in reduced control of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 freighter series airplanes; Model A330-200 and -300 series airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by reports of ram air turbine (RAT) pump failure. This AD requires inspecting the RAT pump anti-stall valve for correct setting, re-identifying the RAT pump, performing a functional ground test of the RAT, and replacing the RAT pump or the RAT assembly with a serviceable part if necessary. We are issuing this AD to detect and correct malfunction of the RAT pump, which could lead to in-flight loss of the RAT-pump pressurization, possibly resulting in reduced control of the airplane.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A320-214 and -232 airplanes. This AD was prompted by reports that medium-head fasteners were installed in lieu of shear-head fasteners on a certain upper panel, which manufacturer fatigue and damage tolerance analyses demonstrated could have an effect on panel fatigue life. This AD requires repetitive inspections for cracking of certain fasteners, and repairs if necessary. We are issuing this AD to detect and correct such cracking, which could result in the loss of structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for certain BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. This AD was prompted by hydraulic pipe ruptures in the center of the cabin resulting in passengers being contaminated with hydraulic fluid. This AD requires installing a hydraulic fluid containment system. We are issuing this AD to prevent harmful or hazardous concentrations of hydraulic fluid or hydraulic vapor from entering the passenger compartment, possibly resulting in injury to the passengers.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model MD-90-30 airplanes. This AD was prompted by reports of fatigue cracks found in Stringer 11 at the outboard flap, inboard drive hinge at Station Xrs=164.000. This AD requires repetitive inspections for cracks in Stringer 11, and a splice repair if necessary; and repetitive post-repair inspections, and repair if necessary. We are issuing this AD to detect and correct such cracking, which could result in the wing structure not supporting the limit load condition, which could lead to loss of the structural integrity of the wing.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model MD-90-30 airplanes. This AD was prompted by reports of cracks of the wing rear spar lower cap at the outboard flap, inboard drive hinge at station Xrs=164.000. This AD requires repetitive eddy current high frequency (ETHF) inspections for cracking on the aft side of the left and right wing rear spar lower caps at station Xrs=164.000, further ETHF inspections if cracks are found, and repair if necessary; and repetitive post-repair inspections, and repair if necessary. We are issuing this AD to detect and correct cracking of the left and right rear spar lower caps, which could result in fuel leaks and damage to the wing skin or other structure, and consequent loss of the structural integrity of the wing.
We are superseding an existing airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. That AD currently 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. The existing AD also requires corrective and related actions if necessary. This new AD requires repetitive detailed inspections for corrosion and damage of the MLG side-brace fitting, and replacing the side-brace fitting shaft with the re-designed side-brace fitting shaft of the MLG if necessary. This AD also requires eventual replacement of certain side-brace fitting shafts with the re-designed part. Replacement with a re-designed side-brace fitting shaft of the MLG is terminating action for the repetitive inspections. This AD was prompted by reports of failure of the side-brace fitting shaft of the main landing gear (MLG) due to corrosion. We are issuing this AD to prevent fractures of the side-brace fitting shafts of the MLG, and possible collapse of the MLG.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This AD was prompted by reports of fatigue cracks found in Stringer 11 at the outboard flap, inboard drive hinge at Station Xrs=164.000. This AD requires repetitive inspections for cracks in Stringer 11, and a splice repair if necessary; and repetitive post-repair inspections, and repair if necessary. We are issuing this AD to detect and correct such cracking, which could result in the wing structure not supporting the limit load condition, which could lead to loss of structural integrity of the wing.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200LR and -300ER series airplanes. This AD requires reviewing the airplane's maintenance records for each rudder power control unit (PCU) to identify the condition of its related reaction link assembly, and replacing the rudder PCU and its related reaction link assembly if necessary. This AD was prompted by a report of an abnormal airframe vibration in the aft fuselage during flight. We are issuing this AD to prevent excessive freeplay in the rudder control surface, which could cause rudder vibration, and result in structural damage severe enough to prevent continued safe flight and landing.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by reports of deformation at the neck of the pressure regulator body on the oxygen cylinder and regulator assemblies (CRAs), and an electrical wiring harness in the area of the oxygen cylinder with no protective conduit sleeving. This AD requires inspecting to determine if certain oxygen pressure regulators are installed and replacing oxygen CRAs containing pressure regulators that do not meet the required material properties. This AD also requires inspecting for damaged wiring, and repairing or replacing wiring if necessary. We are issuing this AD to prevent rupture of the oxygen cylinder, which in the case of cabin depressurization, would lead to oxygen not being available when required; and to detect and correct unprotected wiring that could chafe against the oxygen system components or surrounding structure in the area, and lead to electrical arcing and an oxygen-fed fire.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by cases of on-ground failure of the screw cap or end cap of hydraulic accumulators on other airplane models, resulting in high-energy impact damage to adjacent systems and structure. This AD requires inspecting for a part number and replacing the affected parking brake hydraulic accumulator, and relocating the parking brake accumulator, on the subject airplanes. We are issuing this AD to prevent failure of the screw caps and/or end caps of the parking brake hydraulic accumulator, which could result in damage to the airplane's primary structures, with potential adverse effect on the airplane's controllability.
We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Model G58 airplanes. This AD was prompted by notification from Hawker Beechcraft Corporation that certain affected aircraft were produced with the incorrect gauge wiring installed. This AD requires replacement of the incorrect gauge wiring with the correct wiring required by type design and the aircraft's circuit protection. We are issuing this AD to correct the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Model C90GTi (King Air) airplanes. This AD was prompted by reports of incorrect gauge wires used in certain wiring bundles for the cockpit electrical power for backlighting and instrument panel components. This AD requires replacing incorrect gauge wires in certain electrical power wiring bundles, inspecting associated wiring bundles and components for heat damage, and taking all necessary corrective actions. We are issuing this AD to correct the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by a design review following a ground fire incident and reports of flammable fluid leaks from the wing leading edge area onto the engine exhaust area. This AD requires modification of the fluid drain path in the leading edge area of the wing. We are issuing this AD to prevent flammable fluid from leaking onto the engine exhaust nozzle, which could result in a fire.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. This AD was prompted by reports of two in-service occurrences on Model 737-400 airplanes of total loss of boost pump pressure of the fuel feed system, followed by loss of fuel system suction feed capability on one engine, and in-flight shutdown of the engine. This AD requires repetitive operational tests, and corrective actions if necessary. We are issuing this AD to detect and correct loss of the engine fuel suction feed capability of the fuel system, which, in the event of total loss of the fuel boost pumps, could result in dual engine flameout, inability to restart the engines, and consequent forced landing of the airplane.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. That AD currently requires installing and testing an updated version of the operational program software (OPS) of the flight control computers (FCCs). This new AD requires an inspection for part numbers of the operational program software of the flight control computers, and corrective actions if necessary. This AD was prompted by reports of undetected erroneous output from a single radio altimeter channel, which resulted in premature autothrottle retard during approach. We are issuing this AD to detect and correct an unsafe condition associated with erroneous output from a radio altimeter channel, which could result in premature autothrottle landing flare retard and the loss of automatic speed control, and consequent loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109S helicopters to require modifying the electrical power distribution system to carry a higher electrical load. This AD was prompted by an electrical failure on an Agusta Model A109E helicopter that resulted from “inadequate functioning of the 35 amperes (amps) BATT BUS circuit breaker.” The actions of this AD are intended to require modifying the electrical power distribution system to prevent failure of the circuit breaker, loss of electrical power to instruments powered by the “BATT BUS” system, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Model A310 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by reports of cracked fuel pump canister hoods located in fuel tanks. This AD requires replacing any cracked hood halves of fuel pump canisters. We are issuing this AD to prevent any detached canister hood fragments/debris from being ingested into the fuel feed system, and becoming a potential source of ignition with consequent fire or explosion.
We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC225 helicopters with certain epicyclic modules installed. This AD requires inspecting the epicyclic module for the presence of a through-hole upstream of the magnetic plug. This AD is prompted by a report of a missing through-hole between the integrated collector and the magnetic plug, which would prevent the flow of chips from the integrated collector to the magnetic plug. This could result in the chip-detector system failing to detect deterioration of the main rotor mast lift bearing (lift bearing). These actions are intended to detect a missing through-hole and prevent lift bearing failure and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) to supersede an existing airworthiness directive for MD Helicopters, Inc. (MDHI), Model MD900 helicopters. The existing AD requires a visual inspection, and if necessary, an eddy current inspection of the main rotor lower hub assembly (lower hub) for a crack. If a crack exists, the AD requires replacing the lower hub with an airworthy lower hub before further flight. Because that AD was immediately effective, we declined to require certain long-term actions prior to public comment. This superseding AD will require the same inspections as the existing AD but will also require long-term recurring inspections and replacing the lower hub with an airworthy lower hub. We are issuing this AD to detect a crack in the lower hub and prevent failure of the lower hub and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of alternating current (AC) generator failures in-service due to incomplete fusion in the weld joint of the rotor band assembly. This AD requires inspecting the AC generator to determine the part number, and replacing the AC generator if necessary. We are issuing this AD to prevent rotor windings from coming in contact with the generator housing, which could result in debris contaminating and potentially blocking the engine oil scavenge system, leading to loss of oil pressure and an in-flight shutdown of the engine.
We are rescinding an airworthiness directive (AD) for all Piaggio Aero Industries S.p.A Model P-180 airplanes. That AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. We issued that AD to prevent the brake hydraulic fluid from leaking because of the brake assembly rods contacting the brake valve tubing, which could result in the inability to adequately stop the airplane during ground operations. Since we issued that AD, we have determined this is no longer an unsafe condition and that regularly scheduled annual inspections address this subject.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-200 and -200C series airplanes. This AD was prompted by a report of elevator vibration and bearing swage failures. This AD requires, for certain airplanes, repetitive inspections for any discrepancies (such as a gap or a loose spacer) of the aft attach lugs for the elevator tab control mechanism, and replacement if necessary; and, for other airplanes, contacting the FAA for inspection or repair instructions and doing the work specified in those instructions. We are issuing this AD to detect and correct discrepancies in the aft attach lugs for the elevator tab control mechanism, which could result in elevator and tab vibration. Consequent structural failure of the elevator or horizontal stabilizer could result in loss of structural integrity and loss of airplane control.
We are superseding an existing airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; and all Model A319, A320, and A321 series airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This new AD requires revising the maintenance program to incorporate revised fuel maintenance and inspection tasks, and adds airplanes to the applicability. This AD was prompted by Airbus issuing more restrictive maintenance requirements and/or airworthiness limitations. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
We are superseding an existing airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. That AD currently requires a modification to trim the edge of the bumper plate, including performing an inspection for damage or cracks of the bumper plate and base fitting, and replacing any damaged or cracked part. That AD also currently requires, for certain airplanes, reidentifying the bumper plate. This new AD requires, for airplanes on which the reidentification is done, an operational check of the alternate extension system of the main landing gear (MLG), and repair if necessary. This AD was prompted by the determination that an operational check must be done after reidentifying the bumper plate to ensure the identified unsafe condition is addressed. We are issuing this AD to detect and correct failure of the MLG to extend and lock, which could adversely affect the safe landing of the airplane.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of chafing between the wire harness along the wing leading edge and the inboard end rib of the wing leading edge due to insufficient clearance. This AD requires inspecting the wire harness along the leading edge for chafing damage, and repair if necessary; and relocating and installing new anchor nuts. We are issuing this AD to detect and correct chafing damage to the wire harness along the wing leading edge, which if not corrected, could lead to the loss of the airframe de-icing system, and could become a possible ignition source causing fire.
We are adopting a new airworthiness directive (AD) for Alpha Aviation Concept Limited Model R2160 Airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as possible installation of non-conforming air filter elements that are not fitted with metallic mesh and could internally collapse resulting in disruption of the powerplant operation. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, and -200C series airplanes. This AD was prompted by a report of a severed upper butt strap, and cracks in the forward skin and bonded doubler, on one airplane. This AD requires repetitive inspections for cracks and a chemical spot test in the area of station (STA) 908, and related investigative and corrective actions, if necessary. For certain airplanes, this AD requires an inspection and modification. We are issuing this AD to prevent cracks at the adjacent mating skins (forward and aft), which could initiate just above stringers S-4R and S-4L; and could grow and result in a decompression event.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 747 airplanes. That AD currently requires repetitive visual inspections around the bushings of the wing landing gear (WLG) beam outboard end fittings for corrosion, and rework if necessary; and ultrasonic inspections for cracks of the outboard end fittings of the WLG support beams, and rework if necessary. This new AD adds airplanes and adds repetitive inspections of the outboard end fitting of the left and right WLG support beams for cracks and corrosion, and corrective actions if necessary. This AD was prompted by new reports of corrosion damage to the end fittings of the WLG support beams, and one report of subsequent cracking in the end fittings. We are issuing this AD to detect and correct corrosion and subsequent cracking in the outboard end fittings, which could result in separation of the fitting and damage to adjacent flight control cables and hydraulic systems and consequent reduced controllability of the airplane.
We are adopting a new airworthiness directive (AD) for certain of The Boeing Company Model 777 airplanes. This AD was prompted by heat damage and cracks at the pivot joint location of the main landing gear (MLG) inner cylinder/truck beam. This AD requires repetitive lubrication of the MLG pivot joints; repetitive detailed inspections of the outer diameter chrome on the center axles of the MLG for chicken-wire cracks, corrosion, and chrome plate distress; repetitive magnetic particle inspections of the outer diameter chrome on the center axles of the MLG for cracks; and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct cracking in the MLG center axle and shock strut inner cylinder lugs (pivot joint), which could result in fracture of the MLG pivot joint components and consequent collapse of the MLG.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737 airplanes. This AD was prompted by a report of a flightcrew not receiving an aural warning during a lack of cabin pressurization event. This AD requires incorporating design changes to improve the reliability of the cabin altitude warning system by installing a redundant cabin altitude pressure switch, replacing the aural warning module (AWM) with a new or reworked AWM, and changing certain wire bundles or connecting certain previously capped and stowed wires as necessary. For certain airplanes, this AD also requires prior or concurrent incorporation of related design changes by modifying the instrument panels, installing light assemblies, modifying the wire bundles, and installing a new circuit breaker, as necessary. We are issuing this AD to prevent the loss of cabin altitude warning, which could delay flightcrew recognition of a lack of cabin pressurization, and could result in incapacitation of the flightcrew due to hypoxia (a lack of oxygen in the body), and consequent loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for certain P&W PW4000 series turbofan engines. This AD was prompted by reports of 3rd and 4th stage vane fractures in the low-pressure turbine (LPT) of certain PW4000-94” and PW4000-100” turbofan engines. This AD requires dimensional inspections of LPT 3rd stage vanes and the rear turbine case, inspection of LPT 4th stage vanes at the next LPT overhaul and removal of vanes with non-conforming airfoil fillet radii and vanes with more than one strip and recoat repair. This AD also requires disassembly and reassembly of the 2nd stage high-pressure turbine (HPT) rotor and 3rd stage LPT rotor at the next HPT and LPT overhauls. We are issuing this AD to prevent 3rd and 4th stage vane fractures in the LPT, damage to the LPT rotor, uncontained engine failure, and damage to the airplane.
We are superseding two existing airworthiness directives (ADs) for certain Fokker Services B.V. Model F.28 Mark 0100 airplanes. The first existing AD currently requires removing the actuator from the fuel-balance transfer-valve (FBTV) and installing a locking device on the FBTV. The second existing AD currently requires inspecting to verify that the position indicator of the FBTV is in the closed position and deactivating the fuel-balance transfer-system. This new AD requires installing an FBTV locking device. This AD was prompted by reports that the FBTV was inadvertently reactivated after required de-activation measures were undone. We are issuing this AD to prevent fuel starvation and a consequent double-engine flameout, possibly resulting in a forced landing, damage to the airplane, and injury to occupants.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F airplanes. That AD currently requires installing or replacing with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane; and for certain airplanes, repositioning or replacing two bonding straps, doing a bonding-resistance check and an inspection to determine correct installation of certain bonding straps, and applicable corrective actions. This new AD adds airplanes to the applicability and, depending on the airplane configuration, requires installing new braided bonding straps, inspecting to determine if a certain strap is installed and replacing with or installing a braided bonding strap if necessary, measuring the electrical resistance of the bonding straps, verifying that brackets have an acceptable fillet seal, and doing corrective actions if necessary. This AD was prompted by fuel system reviews conducted by the manufacturer, and our determination that additional actions are necessary to address the identified unsafe condition. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks in the event of a severe lightning strike, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A340-500 and -600 series airplanes. This AD requires repetitive inspections for corrosion of the drag stay lower arm assembly of the nose landing gear (NLG), and replacement if necessary. This AD also requires eventual replacement of the drag stay lower arm assembly of the NLG with an improved assembly having corrosion protection, which terminates the repetitive inspections required by this AD. This AD was prompted by findings of corrosion traces in the lugs and on the bearing outer surface of the NLG during routine maintenance checks. We are issuing this AD to prevent failure of the drag stay lower arm, which could result in NLG collapse and consequent reduced controllability of the airplane during takeoff.
We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B, EC155B1, SA-365N1, AS-365N2 and AS 365 N3 helicopters to require visually inspecting the tail rotor hub (TRH) for a crack and removing the TRH if a crack exists. This AD is prompted by reports of cracks on two TRHs. These actions are intended to prevent the tail rotor from jamming, which could lead to reduced or loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 airplanes, and Model EMB-145, -145ER, -145MR, -145LR, -145MP, and -145EP airplanes. This AD was prompted by a report of a lightning strike hitting an airplane tail boom causing certain rear bulkhead parts to jam an elevator control rod. This AD requires installing or reworking, as applicable, metallic diverters and aluminum sheets; modifying the light assembly on the tail boom rear movable fairing; and replacing the hood assembly with a new hood assembly and rerouting its electrical harness. We are issuing this AD to prevent lightning strikes from causing certain parts to contact the airplane pitch control system, which could reduce airplane controllability.
We are superseding an existing airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections (UIs) of certain low-pressure (LP) compressor blades identified by serial number (S/N). This new AD requires the same actions but expands the population of blades. This AD was prompted by the need to add the inspections of the LP compressor blades listed by S/N in Appendices 3H through 3L of RR plc Alert Service Bulletin (ASB) No. RB.211-72-AG244, Revision 4, dated December 22, 2011. We are issuing this AD to prevent multiple LP compressor blades from failing due to blade root cracks, which could lead to uncontained engine failure and damage to the airplane.
We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by reports of burned contacts in a certain production break plug and its corresponding receptacle. This AD requires modifying galley power supply wiring by disconnecting it from the affected plug/receptacle and reconnecting the power supply wiring through splices. We are issuing this AD to prevent a high electrical load, which might lead to overheating of the galley power supply wiring and/or the electrical connector and consequent smoke or fire in the galley area, which could result in damage to the airplane and injury to occupants.
We are adopting a new airworthiness directive (AD) for General Electric Company GEnx-1B54, GEnx-1B58, GEnx-1B64, GEnx-1B67, GEnx-1B70, GEnx-1B54/P1, GEnx-1B58/P1, GEnx-1B64/P1, GEnx-1B67/P1, GEnx-1B70/P1, GEnx-1B70/72/P1, GEnx-1B70/75/P1, GEnx-1B74/75/P1, GEnx-1B75/P1, GEnx-2B67, and GEnx-2B67B turbofan engines. This AD requires initial and repetitive ultrasonic inspections (UI) of certain part number (P/N) fan mid shafts (FMS) for cracks. This AD was prompted by a report of an FMS failure and a report of a crack found in another FMS. We are issuing this AD to prevent failure of the FMS resulting in one or more engine failure(s) and possible loss of the airplane.
We are superseding an existing airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. That AD currently requires repetitive inspections to detect cracking in the web of the aft pressure bulkhead at body station 1016 at the aft fastener row attachment to the “Y” chord, and corrective actions if necessary. This new AD adds various inspections for discrepancies at the aft pressure bulkhead, and related investigative and corrective actions if necessary. This AD was prompted by several reports of fatigue cracking at that location. We are issuing this AD to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage.
We are adopting a new airworthiness directive (AD) for certain The Cessna Aircraft Company Model 750 airplanes. This AD was prompted by reports of direct current (DC) generator overvoltage events. This AD requires replacing the auxiliary power unit (APU) generator control unit (GCU). We are issuing this AD to prevent DC generator overvoltage events, which could result in smoke in the cockpit and loss of avionics and electrical systems.
We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model SA330F, SA330G, SA330J, AS332C, AS332L, AS332L1, and AS332L2 helicopters to require cleaning, inspecting, and lubricating each tangential gearbox (gearbox) and adjusting, as necessary, the fuel shut-off control lever. This AD was prompted by the jamming of one of two fuel shut-off control levers because of solidified grease in the gearbox. A companion gearbox had extensive corrosion. In case of an emergency, pilots may need to use the control levers to shut off fuel going into the engine and to shut off the helicopter's electrical power system. The jamming of the levers prevents the shut off of the engine fuel and prevents the parallel-mounted micro switches from switching off the electrical power system. These actions are intended to prevent the jamming of the control levers, which could prevent shut-off of the engine fuel and electrical power system during an emergency shutdown.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by reports of failures of a hydraulic accumulator's screw-cap/end cap while on the ground that resulted in loss of use of that hydraulic system, and in high-energy impact damage to adjacent systems and structures. This AD requires an inspection for part numbers; repetitive inspections for any cracking of certain hydraulic system accumulators, and replacement, if necessary; and revising the maintenance program to include a life limit for certain hydraulic system accumulators. We are issuing this AD to prevent loss of use of a hydraulic system, which could result in reduced controllability of the airplane.
We are superseding an existing airworthiness directive (AD) for certain Turbomeca S.A. Arriel 2B and 2B1 turboshaft engines. That AD currently requires accomplishment of the TU166 modification. This new AD requires adding the Arriel 2S2 and 2C2 engines to the applicability of engines requiring the TU166 modification with different compliance times. This AD was prompted by reports of an accident involving a twin-engine helicopter powered by two Arriel 2S2 engines. We are issuing this AD to prevent rupture of a gas generator (GG) turbine blade, which could result in an uncommanded in-flight shutdown and a forced landing or accident.
We are superseding an existing 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. That AD currently requires replacing certain crankshafts in the affected engines. This AD continues to require replacing certain crankshafts, corrects the start date of affected engine models in Lycoming Mandatory Service Bulletin (MSB) No. 569A to the start date in Supplement No. 1 to Lycoming MSB No. 569A, dated May 27, 2009, and includes additional (formerly experimental) IO-390, AEIO-390, and AEIO-580 series engine models having affected crankshafts. This AD was prompted by Lycoming Engines discovering that the start date of affected engine models in MSB No. 569A is incorrect and the need to include additional engine models having the affected crankshafts. 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.
We are superseding an existing airworthiness directive (AD) for all Airbus Model A330-243, -341, -342 and -343 airplanes. That AD currently requires modifying certain cowl assemblies of the left- and right-hand thrust reversers. This new AD requires removing certain C-duct assemblies of the left- and right-hand thrust reversers from service at certain designated life limits, and also adds airplanes to the applicability. This AD was prompted by new life limits on certain thrust reverser C-duct assemblies. We are issuing this AD to prevent fatigue cracking of the hinges integrated into the 12 o'clock beam of the thrust reversers, which could result in separation of a thrust reverser from the airplane, and consequent reduced controllability of the airplane.
We are adopting a new airworthiness directive (AD) for Piaggio Aero Industries S.p.A. Model P-180 Airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as jamming of the external bearing of the screwjack drive gear, which resulted in failure of the main wing outboard flap external actuator. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Bombardier Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports that the automatic de-icing mode became unavailable due to a failure of the timer and monitor unit (TMU). This AD requires replacing the TMU. We are issuing this AD to prevent loss of the automatic de-icing mode and consequent increased workload for the flightcrew, which, depending on additional failures, could lead to loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for Costruzioni Aeronautiche Tecnam srl Model P2006T airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracking, bulging, deformation, or oil leakage in the lower lid of the landing gear emergency accumulator, which could result in decreasing the airplane's structural integrity and jeopardizing the landing gear emergency extension in case of system failure in normal mode. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-24, PA-24-250, and PA-24-260 airplanes. This AD was prompted by reports of cracks developing in the stabilator horn assembly. This AD requires replacement of the stabilator horn assembly and/or repetitive inspections of the stabilator horn assembly for corrosion or cracks, as applicable. Corrosion or cracks could lead to failure of the stabilator horn. Consequently, failure of the stabilator horn could lead to a loss of pitch control in flight. We are issuing this AD to correct the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain serial numbers of Pratt & Whitney Canada (P&WC) PW901A auxiliary power units (APUs) approved under Technical Standard Order TSO-C77A and installed on, but not limited to, Boeing 747-400 series airplanes. This AD requires modifications of the rear gas generator case, exhaust duct support, and turbine exhaust duct flanges. This AD was prompted by several events of high-pressure turbine blade fracture leading to separation of the rear gas generator case and release of high energy debris. We are issuing this AD to prevent separation of the rear gas generator case and release of high energy debris, which could result in injury and damage to the airplane.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by a report of a torn out aspirator due to the aspirator interfering with the extrusion lip of the off-wing escape slide (OWS) enclosure during the initial stage of the deployment sequence. This AD requires modifying the OWS enclosures on both sides. We are issuing this AD to prevent both off-wing exits from being inoperative, which, during an emergency, would impair the safe evacuation of occupants, possibly resulting in personal injuries.
We are adopting a new airworthiness directive (AD) for the Bell Helicopter Textron Canada Limited (BHTC) Model 407 helicopters. This AD requires you to replace tailboom-attachment hardware (attachment hardware), and perform initial and recurring determinations of the torque on the nuts of the tailboom-attachment bolts (bolts) at all four attachment locations. This AD was prompted by a review of the tailboom-attachment installation, which revealed that the torque value of the bolts specified in the BHTC Model 407 Maintenance Manual and applied during manufacturing was incorrect and exceeded the torque range recommended for the bolts. The actions required by this AD are intended to prevent an over-torque of a bolt, bolt failure, loss of the tailboom, and subsequent loss of control of the helicopter.
We are superseding an existing airworthiness directive (AD) for all Pratt & Whitney Division (Pratt & Whitney) PW4052, PW4056, PW4060, PW4062, PW4062A, PW4074, PW4077, PW4077D, PW4084D, PW4090, PW4090-3, PW4152, PW4156A, PW4158, PW4164, PW4168, PW4168A, PW4460, and PW4462 turbofan engines. That AD currently requires initial and repetitive fluorescent penetrant inspections (FPI) for cracks in the blade loading and locking slots of the high-pressure compressor (HPC) drum rotor disk assembly rear drum. This new AD requires the same actions, requires replacement of the 13th, 14th, and 15th stage HPC seals with redesigned HPC seals as an additional action, and adds an optional terminating action to the repetitive inspection requirements by allowing replacement of the entire HPC drum rotor disk assembly with a redesigned HPC drum rotor disk assembly. This AD was prompted by Pratt & Whitney developing a redesigned HPC drum rotor disk assembly for certain affected engine models. We are issuing this AD to prevent failure of the HPC drum rotor disk assembly, which could lead to an uncontained engine failure, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for Eurocopter France Model SA341G helicopters. This AD requires replacing any rotating star with more than 12,000 hours TIS. This AD was prompted by an analysis and tests performed by the manufacturer that indicate that the life limit of the rotating star should be 12,000 hours time-in-service (TIS). The actions of this AD are intended to prevent failure of the rotating star and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. This AD was prompted by the discovery of a manufacturing defect on certain part number (P/N) and serial number (S/N) low-pressure (LP) compressor booster rotors. This AD requires initial and repetitive fluorescent penetrant inspections of certain P/N and S/N LP compressor booster rotors and rework or replacement of them as terminating action to the repetitive inspections. We are issuing this AD to prevent failure of the LP compressor booster rotor, uncontained engine failure, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-Trent 800 series turbofan engines. This AD requires removing from service certain intermediate pressure (IP) turbine discs that have a serial number listed in this AD. This AD was prompted by RR performing an evaluation that determined that the current lives for certain IP turbine discs with a steel inclusion may fail before they reach their current mandatory life limits. We are issuing this AD to prevent failure of the IP turbine disc, which could result in uncontained failure of the engine and damage to the airplane.
We are adopting a new airworthiness directive (AD) for various restricted category Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F,UH-1H, UH-1L, and UH-1P helicopters with certain main rotor (M/R) blade assemblies installed, to require inspecting the grip plates, doublers, and upper and lower surfaces of the M/R blades in the area between blade stations 24.5 and 40 for an edge void, corrosion, or a crack. This AD is prompted by several reports of fatigue cracks on M/R blades installed on Bell Helicopter Textron, Inc. (Bell) Model 212 helicopters. These same part-numbered M/R blades may also be installed on certain FAA-approved modified restricted category helicopters. These actions are intended to detect an edge void, corrosion, or a crack on an M/R blade, which could lead to loss of the M/R blade and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 707-100 long body, -200, -100B long body, and -100B short body series airplanes; Model 707-300, -300B, -300C, and -400 series airplanes; and Model 720 and 720B series airplanes. This AD was prompted by reports of stress corrosion cracking in the chord segments made from 7079 aluminum in the horizontal stabilizer rear spar, and potential early fatigue cracking in the chord segments made from 7075 aluminum. For certain airplanes, this AD requires using redefined flight cycle counts, determining the type of material of the horizontal stabilizer, rear spar, and upper and lower chords on the inboard and outboard ends of the rear spar; repetitively inspecting for cracking of the horizontal stabilizer components; and repairing or replacing the chord, or modifying chord segments made from 7079 aluminum, if necessary. For all airplanes, this AD requires inspecting certain structurally significant items, and repairing discrepancies if necessary. We are issuing this AD to detect and correct stress corrosion and/or potential early fatigue cracking in the horizontal stabilizer, which could compromise the structural integrity of the stabilizer.
We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 and AB412 EP helicopters with certain hoist hook assemblies (hook) installed. This AD requires inspecting the hook for correct assembly of the nut and body. This AD is prompted by a report that a hook separated from the cable of a helicopter. These actions are intended to prevent detachment of the hook from the helicopter and subsequent loss of an external load, possibly resulting in personal injury.
We are adopting a new airworthiness directive (AD) for GA200 (Pty) Ltd Models GA200 and GA200C airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure of the strut bolt through the main spar. We are issuing this AD to require actions to address the unsafe condition on these products.
We are revising an existing airworthiness directive (AD) for Glasflugel Models Standard Libelle-201B, Club Libelle 205, Mosquito, and Kestrel gliders. That AD currently requires actions to address the unsafe condition on these products. This new AD includes clarification that the replacement control rod has an additional drain hole at the rod bottom between the forks and is the acceptable configuration for compliance. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as corrosion damage to the elevator control rod that could lead to failure of the elevator control rod, possibly resulting in loss of control of the glider. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for all M7 Aerospace LLC Models SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), SA227-AT, and SA227-TT airplanes. This AD requires repetitively inspecting the left and right forward (main) and aft spar wing-to-fuselage attach fittings for cracks and replacing any cracked fitting. This AD also requires reporting certain inspection results to the FAA. This AD was prompted by reports of fatigue cracking in the left and right forward (main) spar wing-to-fuselage attach fittings. We are issuing this AD to correct the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Division PW4000-94″ and PW4000-100″ turbofan engines having a 1st stage high-pressure turbine (HPT) seal support, part number (P/N) 55K601 (contained within assembly P/N 55K602-01) or P/N 50K532 (contained within assembly P/N 50K530-01), installed. This AD was prompted by 58 reports of cracked 1st stage HPT air seal rings, including 15 in-flight engine shutdowns. This AD requires removal and replacement of the 1st stage HPT seal support and inspection of the 1st stage HPT air seal ring. We are issuing this AD to prevent failure of the 1st stage HPT air seal ring, which could lead to an internal oil fire, uncontained engine failure, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400 series airplanes. This AD was prompted by reports of water leaking into electrical and electronic equipment in the main equipment center (MEC). This AD requires modifying the floor panels; removing drains; installing floor supports, floor drain trough doublers, drain troughs, and drains; and sealing and taping the floor panels. We are issuing this AD to prevent water from entering the MEC, which could result in an electrical short and potential loss of several functions essential for safe flight.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes; and Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88, and MD-90-30 airplanes; equipped with center wing fuel tank and Boeing original equipment manufacturer-installed auxiliary fuel tanks. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
We are adopting a new airworthiness directive (AD) for certain Eurocopter France Model AS350 helicopters. This AD requires installing protection sleeves over certain forward (pitch) servo-control hydraulic hoses. This AD was prompted by an in-flight fire caused by the ignition of hydraulic fluid leaking from a damaged forward servo-control hydraulic hose. This AD's actions are intended to prevent the forward servo-control hydraulic hoses from becoming damaged and leaking hydraulic fluid that could ignite in flight, which could result in loss of main rotor (M/R) control, power loss, structural damage, propagation of fire, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH Models DA 42, DA 42 NG, and DA 42 M-NG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as excessive voids in the adhesive joint between the center wing spars and the upper center wing skins. This condition could cause the wing to fail, which could result in loss of control of the airplane. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for all BAE SYSTEMS (Operations) Limited Model 4101 airplanes. This AD was prompted by reports that the fire extinguisher in the toilet vanity unit needs to be mounted vertically rather than horizontally. This AD requires inspecting to determine if a certain fire extinguisher bottle is installed, and repositioning the affected fire extinguisher bottle to the vertical position. We are issuing this AD to detect and correct the orientation of the fire extinguisher bottle in the toilet vanity unit to the vertical position, which if not corrected, could result in a toilet waste bin fire spreading, and consequent damage to the airplane and injury to its occupants.
We are adopting a new airworthiness directive (AD) for all Eurocopter France (EC) Model SA-365N, SA-365N1, SA-366G1, AS-365N2, AS 365 N3, EC 155B, and EC155B1 helicopters. This AD was prompted by the discovery of a cracked main rotor mast nut. This condition, if not corrected, could lead to complete failure of the mast nut, resulting in failure of the rotor mast and loss of control of the helicopter. This AD will require replacing the main rotor mast nut with an airworthy main rotor mast nut to prevent this scenario.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Rolls-Royce RB211 Trent 800 engines. This AD was prompted by reports of events related to thermal damage of the thrust reverser (T/R) inner wall on Rolls-Royce RB211 Trent 800 engines. This AD requires replacing the bleed valve parts and tubing with new parts and tubing on the left and right engines; and installing Aero-Engine database (AEDB) software in the airplane information management system (AIMS) hardware. We are issuing this AD to prevent T/R thermal damage caused by excessive heat downstream of the 8th stage IP8 exhaust ports, which could result in T/R structural failure. This failure could result in large pieces of the T/R or adjacent components departing the airplane. A separated T/R piece could result in a rejected takeoff and cause asymmetric thrust and consequent loss of control of the airplane during reverse thrust operations. Separated components could also cause structural damage to the airplane, damage to other airplanes due to debris left on the runway, or injury to people on the ground.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. That AD currently requires initial and repetitive inspections of the fuselage skin and bear strap at the forward, upper corner of the L1 entry door cutout for cracking, and repair if necessary. That action also provides an optional terminating action for the repetitive inspections. This new AD requires additional inspections for airplanes having repairs or preventative modifications installed and inspections for certain other airplanes. This AD also adds airplanes to the applicability. This AD was prompted by reports of additional cracking in the fuselage skin. We are issuing this AD to detect and correct cracking of the fuselage skin and bear strap at the forward upper corner of the L1 entry door cutout, which could result in reduced structural integrity of the L1 entry door, and consequent rapid decompression of the airplane.
We are adopting a new airworthiness directive (AD) for Goodyear Aviation Tires, part number 299K63-1 (Brazilian made new tires only), installed on various transport category airplanes, including but not limited to Bombardier, Inc. Model CL-600-2B19 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as tire tread separations and tread-area bulges on the main landing gear tires due to low adhesion in the tread shoulder area. The unsafe condition is specific to Brazilian produced new tires, size H29x9.0-15, only; retread tires are not affected by this AD. This condition, if not detected and corrected, could cause the main landing gear tires to fail during takeoff or landing. The failure may cause damage to the airplane structure, flaps, engine, and wheel well and result in reduced controllability of the airplane. We are issuing this AD to require actions to address the unsafe condition on these products.
We are superseding an existing airworthiness directive (AD) for certain Univair Aircraft Corporation Models (ERCO) 415-C, 415-CD, 415-D, E, G; (Forney) F-1 and F-1A; (Alon) A-2 and A2-A; and (Mooney) M10 airplanes. That AD currently requires an inspection of the aileron balance assembly and ailerons for cracks and excessive looseness of associated parts with the required repair or replacement of defective parts as necessary. This new AD would add airplanes to the Applicability section; require inspections of the ailerons, aileron balance assembly, and aileron rigging for looseness or wear, require repair or replacement of parts as necessary; and require a report of the inspection results. This new AD was prompted by a report of a Univair Aircraft Corporation Model ERCO 415-D Ercoupe that crashed after an in-flight breakup due to possible aileron flutter. We are issuing this AD to correct the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. models TFE731-4, -4R, -5, -5R, -5AR, and -5BR series turbofan engines. This AD was prompted by a report of a rim/web separation of a first stage low-pressure turbine (LPT1) rotor assembly. This AD requires replacing affected LPT1 rotor assemblies with assemblies eligible for installation. We are issuing this AD to prevent uncontained disk separation, engine failure, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for all Honeywell International Inc. TFE731-20R, -20AR, -20BR, -40, -40AR, -40R, -50R, and -60 turbofan engines. This AD was prompted by a report of a quality escape of about 8,000 2nd stage low-pressure turbine (LPT2) rotor blades, manufactured by Honeywell Chihuahua Manufacturing Operation since 2009. This AD requires removing and inspecting certain LPT2 rotor blades. We are issuing this AD to correct an unsafe condition caused by these blades installed on these engines.
We are adopting a new airworthiness directive (AD) for Pratt & Whitney Division PW4052, PW4152, PW4056, PW4156A, PW4060, PW4060A, PW4060C, PW4062, PW4062A, PW4158, PW4460, PW4462, PW4164, PW4164C, PW4164C/B, PW4168, and PW4168A turbofan engines with certain high-pressure turbine (HPT) stage 1 front hubs installed. This AD was prompted by Pratt & Whitney's updated low-cycle-fatigue analysis that indicated certain HPT stage 1 front hubs could initiate a crack prior to the published life limit. This AD requires removing the affected HPT stage 1 front hubs from service using a drawdown plan. We are issuing this AD to prevent failure of the HPT stage 1 front hub, which could lead to an uncontained engine failure and damage to the airplane.
We are adopting a new airworthiness directive (AD) for BRP-Powertrain GmbH & Co KG Rotax 912 F2; 912 F3; 912 F4; 912 S2; 912 S3; and 912 S4 reciprocating engines. This AD requires replacing the pressure side fuel hose on certain fuel pumps and inspecting the carburetors connected to those fuel pumps for contamination within 5 flight hours after the effective date of this AD. This AD was prompted by reports of fuel pumps having pressure side fuel hoses not meeting the design specification. We are issuing this AD to prevent pressure side fuel hose deterioration and contamination of the carburetor, which could result in an in-flight engine shutdown, forced landing and damage to the airplane.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD was prompted by a report of extensive corrosion of the ballscrew of the drive mechanism of the horizontal stabilizer trim actuator. This AD requires repetitive detailed inspections for discrepancies of the horizontal stabilizer ballscrew assembly; repetitive lubrication of the horizontal stabilizer trim control system; repetitive measurements for discrepancies of the ballscrew to ballnut freeplay; and corrective actions, if necessary. We are issuing this AD to prevent undetected failure of the primary and secondary load paths for the ballscrew in the horizontal stabilizer, which could lead to loss of control of the horizontal stabilizer and consequent loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for Eurocopter France Model EC155B and EC155B1 helicopters with a VIP 4-seat bench to require revising the Limitations section of the Rotorcraft Flight Manual (RFM) and converting the VIP 4-seat bench into a 3-seat configuration. This AD was prompted by the determination that the load strength of the seat attachment hardware of the seat installation does not meet certification specifications. The required actions are intended to prevent overloading of the seat structure at the attachment point during a hard landing or emergency landing, which could result in the VIP 4-seat bench detaching from the floor and subsequent injury to the seat occupants.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of jamming/malfunctioning of the left-hand engine thrust control mechanism. This AD requires modifying the left-hand engine upper core-cowl. We are issuing this AD to prevent jamming/malfunctioning of the left-hand engine thrust control mechanism, which could lead to loss of control of the airplane.
We are superseding two existing airworthiness directives (AD) for all Embraer S.A. Model ERJ 170 and ERJ 190 airplanes. Those ADs currently require revising the airplane flight manual (AFM) to introduce limitations for the use of auxiliary power unit (APU) bleed and to prohibit dispatch with a failed air management system (AMS) controller card. This new AD requires replacing the AMS controller processor module with one containing new software, and a new AFM revision. This AD was prompted by reports of the possible loss of automatic activation of the engine inlet ice protection system. We are issuing this AD to prevent the possibility of a right-hand (RH) engine compressor stall after the APU becomes the active bleed source for the left side, which may result in an engine failure; and to prevent the intermittent communication failure between the AMS controller cards and both secondary power distribution assemblies (SPDAs), which could lead to the loss of automatic activation of the engine inlet ice protection system when flying in icing conditions, which could result in ice accretion in the engine inlet and subsequent dual engine failure.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 and -121 airplanes; Model A319-111, -112, -115, -132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, -213, and -231 airplanes. This AD was prompted by reports that some nuts installed on the wing, including on primary structural elements, were found cracked. This AD requires inspecting to determine if certain nuts are installed or cracked, and replacing the affected nuts if necessary. We are issuing this AD to detect and correct missing and cracked nuts, which could result in the structural integrity of the airplane wings being impaired.
The FAA is correcting an airworthiness directive (AD) that was published in the Federal Register. That AD applies to Eurocopter Deutschland GmbH Model MBB-BK 117 C-2 helicopters. A page reference of the rotorcraft flight manual in the Required Actions section, paragraph (e)(1)(i), is incorrect. This document corrects that error. In all other respects, the original document remains the same.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. This AD was prompted by reports of cracking of the midspar fittings, and of the engine and nacelle strut separating from the airplane. This AD requires performing a detailed inspection of the midspar fittings of the nacelle strut to confirm that the correct part number is installed, and installing the correct part number if necessary; performing repetitive high frequency eddy current (HFEC) inspections of the midspar fittings of the nacelle strut for cracks, and repair if necessary; and performing repetitive general visual inspections of the nacelle struts to verify that the nacelle strut has not drooped below its normal position, applying the droop stripe to the nacelle strut and sailboat fairing if necessary, and performing repair if necessary. We are issuing this AD to detect and correct cracking of the midspar fitting, which could result in separation of the nacelle strut and engine from the airplane while in flight, and consequent loss of controllability of the airplane.
We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76A helicopters to require modifying the electric rotor brake (ERB) and inserting changes into the “Normal Procedures” and “Emergency Procedures” sections of the Rotorcraft Flight Manual (RFM). This AD was prompted by a fire in the main gearbox area as a result of a hot electric rotor brake (ERB). The actions are intended to prevent overheating of the ERB, ignition of the ERB hydraulic fluid, a fire in the main gearbox area, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by chafing on high pressure fuel lines due to improper installation of an expandable pin on the lower cowl assembly. This AD requires installing spring clips and repositioning the lanyard attachment points at the forward end and the forward firefloor of the lower cowl. We are issuing this AD to prevent chafing of the high pressure fuel lines, which if not corrected, could cause fuel leakage in a fire zone.
We are adopting a new airworthiness directive (AD) for certain BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 and Avro 146-RJ series airplanes. This AD was prompted by reports of cracking and surface anomalies of the fuselage skin at the water trap/air dryer unit of the forward discharge valve due to corrosion. This AD requires repetitive detailed inspections for bulging, surface anomalies, and cracking of the fuselage skin adjacent to the discharge valves, repair if necessary, and application of additional sealant in the affected area if necessary. We are issuing this AD to detect and correct bulging, surface anomalies, and cracking that could propagate towards the forward discharge valve outlet, which could result in the failure of the fuselage skin, leading to a possible sudden loss of cabin pressure.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-500 series airplanes. This AD was prompted by reports of chem-mill step cracking on the aft lower lobe fuselage skins. This AD requires inspections of the fuselage skin at the chem-mill steps, and repair if necessary. We are issuing this AD to detect and correct cracking on the aft lower lobe fuselage skins, which could result in decompression of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600 series airplanes and Model A310-203, -204, -221, and -222 airplanes. This AD was prompted by a report of a capacitive density condensator (cadensicon) coil overheating during testing. This AD requires an inspection to determine if a certain fuel quantity indication computer (FQIC) is installed, replacement of identified FQICs, and modification of the associated wiring. We are issuing this AD to detect and correct potential overheating of the cadensicon coil, which could create an ignition source inside a fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -200 freighter series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires modification of the control circuit for the fuel pumps for the center fuel tanks for certain airplanes, and center and rear fuel tanks for certain other airplanes. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
We are superseding an existing airworthiness directive (AD) for all Model 747-100B SUD, 747-300, 747-400, and 747-400D series airplanes; and Model 747-200B series airplanes having a stretched upper deck. The existing AD currently requires repetitively inspecting for cracking or discrepancies of the fasteners in the tension ties, shear webs, and frames at body stations 1120 through 1220; and related investigative and corrective actions if necessary. That AD requires modifying the frame-to-tension-tie joints at body stations 1120 through 1220 (including related investigative actions and corrective actions if necessary), which provides a terminating action for the repetitive inspections. That AD also requires new repetitive inspections after the modification, corrective actions if necessary, and additional modification requirements at a specified time after the first modification. That AD also removed certain airplanes from the applicability. That AD was prompted by reports of cracked and severed tension ties, broken fasteners, and cracks in the frame, shear web, and shear ties adjacent to tension ties for the upper deck. This AD revises the existing AD by adding repetitive open hole high frequency eddy current (HFEC) inspections for cracking in the forward and aft tension tie channels, and repair if necessary. For certain airplanes, this AD also requires a one-time angle inspection to determine if the angle is installed correctly, and re-installation if necessary; and a one-time open hole HFEC inspection at the fastener locations where the tension tie previously attached to the frame prior to certain modifications, and repair if necessary. This AD also, for the Stage 2 inspections, reduces the initial compliance times for those inspections. We are issuing this AD to detect and correct cracking of the tension ties, shear webs, and frames of the upper deck, which could result in rapid decompression and reduced structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-603, B4-605R, and B4-622R airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4-600R series airplanes. This AD was prompted by a report that chafing was detected between the autopilot electrical wiring conduit and the wing bottom skin. This AD requires modifying the wiring installation on the right-hand wing. We are issuing this AD to prevent sparking due to electrical chafing when flammable vapors are present in the area, which could cause an uncontrolled fire.
We are adopting a new airworthiness directive (AD) for all HPH s. r.o. Models 304C, 304CZ, and 304CZ-17 sailplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as the lack of a drain hole in the elevator control rod, which may allow water to accumulate in the control rod and lead to possible corrosion. This condition could cause the elevator control rod to fail, which could result in loss of control of the sailplane. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8 series airplanes. This AD was prompted by reports that various pushrods had been manufactured with tubes having the incorrect heat treatment. This AD requires replacing the affected pushrod assembly. We are issuing this AD to prevent loss of rudder control, reduced directional control of the airplane on the ground, or a jammed nose landing gear (NLG) door that could prevent the NLG from retracting or extending.
We are adopting a new airworthiness directive (AD) certain Airbus Model A310-203, -221, and -222 airplanes. This AD was prompted by the manufacturer re-classifying slat extension eccentric bolts as principal structural elements with replacement due at or before their calculated fatigue lives. This AD replaces certain slat extension eccentric bolts with new bolts. We are issuing this AD to prevent fatigue cracking, which could result in the loss of structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-103, B4-203, and B4-2C airplanes, and 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). This AD was prompted by reports of cracking in the forward lug of the main landing gear (MLG) rib 5 aft bearing attachment. This AD requires repetitive inspections for cracking of the left-hand (LH) and right-hand (RH) wing MLG rib 5 aft bearing forward lugs, and repair if necessary. We are issuing this AD to detect and correct cracking of the LH and RH wing MLG rib 5 aft bearing forward lugs, which could affect the structural integrity of the MLG attachment, resulting in MLG collapse during landing or rollout with consequent damage to the airplane and injury to occupants.
We are revising an existing airworthiness directive (AD) that applies to all Airbus Model A318, A319, A320, and A321 series airplanes. The existing AD currently requires revising the airplane flight manual (AFM) to include a procedure intended to address the unsafe condition, an inspection of the firewall connector for signs of arcing if an integrated drive generator (IDG) (or generator (GEN)) was shut down in-flight automatically or using the AFM procedure, and corrective action if necessary; and provides an optional terminating action for certain AFM revision and inspections. This AD was prompted by the potential for an inadvertent error by flightcrew to use the IDG switch instead of the GEN switch when doing the AFM display unit failure procedure required by the existing AD. This AD retains the actions required by the existing AD and clarifies certain terminology. We are issuing this AD to prevent transient loss of certain systems, which could result in the reduced ability of the flightcrew to cope with adverse flight conditions.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767 airplanes. This AD was prompted by reports of cracks of the underwing longeron fittings in the wing center section. This AD requires repetitive inspections of the underwing longeron fitting for cracking, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct such cracking, which could result in loss of the primary load path between the fuselage and the wing box, and consequent catastrophic damage to the wing box and failure of the wing.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400 and 747-400D series airplanes. This AD was prompted by a report of an in-flight multi-power system loss of the #1, #2, and #3 alternating current electrical power systems located in the main equipment center (MEC). This AD requires installing aluminum gutter reinforcing brackets to the forward and aft drip shield gutters of the MEC; and adding a reinforcing fiberglass overcoat to the top surface of the MEC drip shield, including an inspection for cracking and holes in the MEC drip shield, and corrective actions if necessary. This AD also provides for an option to install an MEC drip shield drain system, which, if accomplished, would extend the compliance time for adding the reinforcing fiberglass overcoat to the top surface of the MEC drip shield. We are issuing this AD to prevent water penetration into the MEC, which could result in the loss of flight critical systems.
We are adopting a new airworthiness directive (AD) for Glasflugel Models Standard Libelle-201B, Club Libelle 205, Mosquito, and Kestrel gliders. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as corrosion damage to the elevator control rod that could lead to failure of the elevator control rod, possibly resulting in loss of control of the glider. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report that a passenger oxygen pipe at frame 10 was chafing against the forward lavatory rear structure, raising the risk of the oxygen pipe developing a crack. This AD requires modifying the routing of and, if necessary, replacing, the oxygen pipe. We are issuing this AD to prevent rupture of the oxygen pipe which, in case of a cabin depressurization, would impair operation of the passenger oxygen distribution system.
We are adopting a new airworthiness directive (AD) for various aircraft equipped with Rotax Aircraft Engines 912 A series engine. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a deviation in the manufacturing process of fuel hoses installed on the pressure side of part number 893114 fuel pumps. The fuel hoses may not be fuel resistant, which could lead to detachment of particles from the fuel hose and cause irregularities in the carburetor function and possibly result in rough engine operation, engine misfire, in-flight engine shutdown, and forced landing. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP (Type Certificate previously held by Israel Aircraft Industries, Ltd.) Model Astra SPX, 1125 Westwind Astra, and Gulfstream 100 airplanes. This AD was prompted by a report indicating that sponge rubber padding was found between wheel well fuel lines and electrical harnesses. This AD requires inspecting for the presence of sponge rubber padding and for proper separation of the fuel lines and electrical harnesses in the wheel well area, and corrective actions if necessary. We are issuing this AD to detect and correct corrosion or chafing of the fuel lines, which could result in fuel leakage and possible fire in the wheel well area.
We are adopting a new airworthiness directive (AD) for Arrow Falcon Exporters, Inc. (previously Utah State University); Firefly Aviation Helicopter Services (previously Erickson Air-Crane Co.); California Department of Forestry; Garlick Helicopters, Inc.; Global Helicopter Technology, Inc.; Hagglund Helicopters, LLC (previously Western International Aviation, Inc.); International Helicopters, Inc.; Precision Helicopters, LLC; Robinson Air Crane, Inc.; San Joaquin Helicopters (previously Hawkins and Powers Aviation, Inc.); S.M.&T. Aircraft (previously US Helicopters, Inc., UNC Helicopter, Inc., Southern Aero Corporation, and Wilco Aviation); Smith Helicopters; Southern Helicopter, Inc.; Southwest Florida Aviation International, Inc. (previously Jamie R. Hill and Southwest Florida Aviation); Tamarack Helicopters, Inc. (previously Ranger Helicopter Services, Inc.); US Helicopter, Inc. (previously UNC Helicopter, Inc.); West Coast Fabrication; and Williams Helicopter Corporation (previously Scott Paper Co.) Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P Helicopters; and Southwest Florida Aviation Model UH-1B (SW204 and SW204HP) and UH-1H (SW205) Helicopters. This AD requires inspecting each affected tail rotor blade (blade) forward tip weight retention block (tip block) and the aft tip closure (tip closure) for adhesive bond voids and removing any blade with an excessive void from service. This AD also requires modifying certain blades by installing shear pins and tip closure rivets. This AD was prompted by reports of missing tip blocks or tip closures, resulting in minor to substantial damage to blades installed on Bell Model 212 and 412 helicopters. The actions are intended to prevent loss of a tip block or tip closure, loss of a blade, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190 airplanes. This AD was prompted by a report of damage on the rod end of the retracting actuator rod of the main landing gear (MLG). This AD requires performing a one-time general visual inspection to determine if a certain part number is installed on the MLG retraction actuator; if necessary, performing a general visual inspection for discrepancies between the actuator rod end and shock strut lug of the MLG retraction actuator; and corrective actions if necessary. We are issuing this AD to detect and correct breakage of the MLG retracting actuator rod, which may result in MLG extension with no hydraulic damping and consequent damage to the locking mechanism and collapse of the MLG.
We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP (Type Certificate previously held by Israel Aircraft Industries, Ltd.) Model Gulfstream G150 airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires a one-time detailed or borescope inspection of the left- and right-hand inboard vent holes for debris or obstructions, and repair if necessary. This AD was prompted by a report indicating that an inboard vent tube hole was completely covered with sealant, which blocked airflow through the vent. Under these conditions, the rise of internal pressure during pressure fueling or due to thermal expansion is sufficient to damage the wing. We are issuing this AD to detect and correct compromised integrity of the wing structure.
We are adopting a new airworthiness directive (AD) for all Eurocopter Deutschland GmbH (ECD) MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK B-1, MBB-BK 117 B-2, and MBB-BK C-1 helicopters equipped with a certain external-hoist system (hoist system). This AD requires deactivating the entire hoist system or deactivating the hoist system cable cutter function on the hoist system operator control handle (operator handle). This AD was prompted by an uncommanded activation of the hoist cable cutter function on an MBB-BK117 C-1 helicopter. The actions of this AD are intended to prevent uncommanded cutting of the hoist cable and subsequent injury to persons being lifted by the hoist.
We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC155B1 helicopters with a certain automated flight control system installed. This AD requires changing the minimum required crew for instrument flight rules (IFR) operations from one pilot to two. This AD is prompted by a report that an EC155B1 helicopter experienced significant intermittent roll oscillations while coupled to the autopilot. These actions are intended to decrease the pilot's workload while experiencing any oscillations during landing, which could result in possible loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 and -121 airplanes; Model A319-111, -112, -115, -132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, -213, and -231 airplanes. This AD was prompted by reports of some fuselage nuts found cracked. This AD requires an inspection to determine if certain fuselage nuts are installed, a detailed inspection for cracking of fuselage nuts having a certain part number, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct fuselage nuts found cracked, which could result in reduced structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for CHI Model 107-II and Kawasaki Model KV107-II and KV107-IIA helicopters. This AD requires, before further flight, replacing certain upper collective pitch control yoke bolts. This AD is prompted by three failures of the affected bolts. These actions are intended to prevent failure of an upper collective pitch control yoke bolt (bolt), excessive vibration, migration of the shafts, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-100, DHC-8-200, and DHC-8-300 series airplanes. This AD was prompted by reports of hydraulic accumulator screw cap or end cap failure. This AD requires replacing the affected parking brake accumulator. We are issuing this AD to prevent failure of the parking brake accumulator screw caps or end caps, which could result in loss of the number 2 hydraulic system and damage to airplane structures, and could potentially have an adverse effect on the controllability of the airplane.
We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 (all versions) and BO-105LS A-3 helicopters. This AD requires inspecting the tail rotor pitch link spherical bearing for proper swaging. This AD is prompted by a report of a tail rotor pitch link with a spherical bearing that had migrated out of the bearing bore. The actions specified by this AD are intended to prevent failure of the tail rotor pitch link and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of fatigue cracks in the lap joints, which initiated at scribe lines that were made during production when maskant was removed from the affected skin panels during the chemical milling process. This AD requires repetitive external phased-array ultrasonic inspections to detect cracks of the affected fuselage skin lap splices in Sections 41, 43, and 44, as applicable, and repair if necessary. We are issuing this AD to detect and correct such fatigue cracking, which could grow large and cause sudden decompression and the inability to sustain limit flight and pressure loads.
We are superseding an existing airworthiness directive (AD) for The Boeing Company Model 757 Airplanes. That AD currently requires revising the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness by incorporating new limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. That AD also requires the initial inspection of certain repetitive AWL inspections to phase-in those inspections, and repair if necessary. This new AD requires actions that were provided previously as optional actions, and would require a certain initial inspection to be accomplished for a revised AWL. This AD was prompted by a report that an AWL required by the existing AD must be revised. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
We are adopting a new airworthiness directive (AD) for Arrow Falcon Exporters, Inc. (AFE), Rotorcraft Development Corporation (RDC), and San Joaquin Helicopters (SJH) Model OH-58A, OH-58A+, and OH-58C helicopters to require inspecting the main rotor mast (mast) for a crack. This AD is prompted by two reported failures of the mast from corrosion-initiated fatigue cracking. The actions specified by this AD are intended to prevent failure of the mast and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain aircraft equipped with Honeywell International, Inc. Model KGS200 Mercury 2 wide area augmentation system (WAAS) global navigation satellite sensor units (GNSSU). This AD requires you cease all localizer performance (LP), localizer performance with vertical guidance (LPV), and satellite based augmentation system (SBAS) lateral navigation/vertical navigation (LNAV/VNAV) approaches until a software problem is corrected. This AD was prompted by a report and follow-up investigation of a software problem that occurred during flight test trials of SBAS-capable aircraft using a similar Honeywell global positioning system (GPS) sensor and the same software as the Model KGS200 Mercury 2 GNSSU. A software problem occurred that could result in misleading information during LP, LPV, or SBAS LNAV/VNAV approaches. We are issuing this AD to correct the unsafe condition on these products.
We are adopting an airworthiness directive (AD) superseding an existing airworthiness directive for Bell Helicopter Textron Canada (Bell) Model 407 and 427 helicopters. The existing AD requires inspecting certain hydraulic servo actuators (servo) to determine whether the shaft turns independently of the nut or the clevis assembly, and additional actions based upon the inspection's outcome. The AD also requires reidentifying the servo. Since we issued that AD, Bell has learned that additional servos may need repair or removal. This AD expands the scope of the current AD to include inspections for all servos, and requires that servos meeting inspection requirements be marked with the letter “V” after the part number on the data plate. The actions are intended to detect any loose or misaligned parts in the servo that could lead to failure of the servo and subsequent loss of helicopter control.
We are superseding an existing airworthiness directive (AD) for all Pratt & Whitney Division PW4074 and PW4077 turbofan engines. That AD currently requires removing the 15th stage high-pressure compressor (HPC) disk within 12,000 cycles since new (CSN) or using a drawdown removal plan for disks that exceed 12,000 CSN. This new AD requires the same actions and clarifies that 15th stage HPC disks that have accumulated more than 9,865 CSN require a borescope inspection (BSI) or eddy current inspection (ECI) of the disk outer rim front rail for cracks prior to accumulating 12,000 CSN. This AD was prompted by a request from an operator that we clarify our inspection schedule for 15th stage HPC disks that have accumulated more than 9,865, but less than 12,000 CSN, on the effective date of the AD. We are issuing this AD to prevent cracks from propagating into the disk bolt holes, which could result in a failure of the 15th stage HPC disk, uncontained engine failure, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by reports of unsuccessful slide deployments during scheduled deployment tests, and failed functional tests of the release travel of the slide release mechanism. This AD requires inspecting the off-wing slide release cables on the left- and right-hand sides to determine whether a certain part number is installed, and replacement if necessary. We are issuing this AD to prevent non-availability of left- or right-hand off-wing exit slides that could impair emergency evacuation of the passengers and flightcrew, and could result in personal injuries.
We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires inspecting the main gearbox (MGB) for a crack. This AD is prompted by a crack in the cored passage of the MGB housing, which may be indicated by oil on the housing. These actions are intended to detect a crack in the MGB housing, which could result in loss of oil, failure of the MGB, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model G-IV, GIV-X, GV, and GV-SP airplanes. This AD requires measuring to determine paint thickness on the flight control surfaces and corrective actions if necessary, and revising the Airplane Flight Manual (AFM). This AD was prompted by reports of failure to inspect or document the paint thickness on flight controls (ailerons, rudder, elevator), potentially having a negative impact on the flutter characteristics of the airplane. We are issuing this AD to detect and correct paint thickness on flight controls, which could result in loss of control of the airplane due to flutter.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 767-200 and -300 series airplanes. That AD currently requires replacement of the existing deactivation pin, aft cascade pin bushing, and pin insert on each thrust reverser half with new, improved components. This new AD requires a dye penetrant inspection for cracking of the rivet holes of the bushing plate and repair or replacement, if necessary; and for certain airplanes, replacing the existing bushing with a new bushing and deactivation pin, and installing a new or serviceable stowage bracket for the deactivation pins on all airplanes powered by Pratt & Whitney JT9D series engines. This AD was prompted by reports that certain airplanes require installation of a new bushing and deactivation pin with increased load carrying capability and all airplanes powered by Pratt & Whitney JT9D series engines require installation of a new bracket for stowing the deactivation pin. We are issuing this AD to prevent failure of the thrust reverser deactivation pins, which could fail to prevent a deployment of a deactivated thrust reverser in flight and consequent reduced controllability of the airplane.
We are adopting a new airworthiness directive (AD) for the PZL Swidnik S.A. (PZL) Model PZL W-3A helicopter with a certain generator air outlet collector (collector) installed. This AD requires modifying the generator air outlet collector attachments (collector attachments). This AD is prompted by an incident where cyclic control stick movement was restricted due to rotation of a loose collector, resulting in locking of the longitudinal control system hydraulic actuator fork end. These actions are intended to prevent rotation of the collector, which could lead to restricted cyclic control stick movement, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series airplanes. This AD was prompted by a report indicating that a fire originated near the first officer's area, which caused extensive damage to the flight deck. This AD requires replacing the low-pressure oxygen hoses with non-conductive low-pressure oxygen hoses in the flight compartment. We are issuing this AD to prevent electrical current from passing through the low-pressure oxygen hose internal anti-collapse spring, which can cause the low-pressure oxygen hose to melt or burn, and a consequent oxygen-fed fire in the flight compartment.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by several reports of electrical arcs at terminal “A” of the electrically heated flight deck window 1. This AD requires repetitive inspections for damage of the electrical connections at terminal “A” of the left and right flight deck window 1, and corrective actions if necessary. This AD also allows for replacing a flight deck window 1 with a new improved flight deck window 1 equipped with different electrical connections, which would terminate the repetitive inspections for that window. We are issuing this AD to prevent smoke and fire in the cockpit, which could lead to loss of visibility, and injuries to or incapacitation of the flight crew.
We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) 250-C20, -C20B, and -C20R/2 turboshaft engines. This AD was prompted by seven cases reported of released turbine blades and shrouds, which led to loss of power and engine in-flight shutdowns (IFSDs). This AD requires a one-time visual inspection and fluorescent penetrant inspection (FPI) on certain 3rd and 4th stage turbine wheels for cracks in the turbine blades. We are issuing this AD to prevent failure of 3rd or 4th stage turbine wheel blades which could cause engine failure and damage to the airplane.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-400F, 747SR, and 747SP series airplanes, without a stretched upper deck or stretched upper deck modification. That AD currently requires repetitive inspections for cracks of each affected tension tie and of the surrounding structure, and related investigative and corrective actions if necessary. This new AD requires, for certain airplanes, modifying the tension tie structure or tension tie and frame structure at certain stations; and a post-modification inspection of the modified area and post-modification repetitive inspections of the unmodified area, and repair if necessary. Doing the modification would terminate the repetitive inspection requirements in the existing AD. This AD reduces the compliance time and adds inspections for certain airplanes. This AD was prompted by reports that certain airplanes have tension ties that are susceptible to widespread fatigue damage. This AD also results from reports of cracks on the forward and aft tension tie channels at station (STA) 740 and STA 760, and a determination that initial inspection intervals need to be reduced. We are issuing this AD to prevent tension ties from becoming severed or disconnected from the frames, which could lead to rapid in-flight decompression.
We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; all Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model 300 C4-605R Variant F airplanes (collectively called A300-600 series airplanes). This AD was prompted by reports of an inoperative fire shut-off valve (FSOV) as a result of damage due to over-length of the bonding lead. This AD requires a one-time detailed inspection for length of the FSOV bonding leads and for contact or chafing of the wires, and corrective actions, if necessary. We are issuing this AD to detect and correct contact or chafing of wires and bonding leads which, if not detected could be a source of sparks in the wing trailing edge, and could lead to an uncontrolled engine fire.
We are adopting a new airworthiness directive (AD) for all Pratt & Whitney Canada (P&WC) PW118, PW118A, PW118B, PW119B, PW119C, PW120, PW120A, PW121, PW121A, PW123, PW123B, PW123C, PW123D, PW123E, PW123AF, PW124B, PW125B, PW126A, PW127, PW127E, PW127F, PW127G, and PW127M turboprop engines. This AD requires initial and repetitive inspections of certain serial numbers (S/Ns) of propeller shafts for cracks and removal from service if found cracked. This AD was prompted by reports of two propeller shafts found cracked at time of inspection during maintenance. We are issuing this AD to detect propeller shaft cracks, which could cause failure of the shaft, propeller release, and loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires inspecting parts or doing a records review to determine if certain trailing edge flap carriages are installed, doing repetitive inspections for corrosion, and flaking or missing thermal coating on suspect carriage spindles, and related investigative and corrective actions, if necessary; this AD also provides optional terminating action for the repetitive inspections. This AD was prompted by reports of corrosion found on carriage that are located on the outboard flaps. We are issuing this AD to detect and correct corrosion of the carriage spindle, which could result in a fracture; fracture of both the inboard and outboard carriage spindles, at the forward ends through the large diameters, on a single flap assembly, could adversely affect the continued safe flight and landing of the airplane.
We are rescinding an airworthiness directive (AD) for RRD BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. The existing AD resulted from the need to reduce the published life limits of high-pressure (HP) turbine stage 1 discs, part numbers (P/Ns) BRH20130 and BRH20131, and HP turbine stage 2 discs, P/Ns BRH19423 and BRH19427. We are rescinding the existing AD because RRD has revised the approved published life limits of these parts to the same or higher limits as originally certified.
We are superseding an existing airworthiness directive (AD) for all Rolls-Royce plc (RR) models RB211-Trent 970-84, 970B-84, 972-84, 972B-84, 977-84, 977B-84, and 980-84 turbofan engines. That AD currently requires inspecting the intermediate-pressure (IP) shaft rigid coupling splines for wear resulting in rearward movement of the IP turbine. This AD requires the same inspections, and new inspections based on possible changes in wear rate. This AD was prompted by RR identifying wear beyond engine manual limits on the abutment faces of the splines. RR also determined that an additional IP shaft rigid coupling configuration requires inspection. We are issuing this AD to detect wear on the abutment faces of the splines, which could result in loss of disc integrity, an uncontained failure of the engine, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for certain Empresa Brasileria de Aeronáutica S.A. (EMBRAER) Model EMB-505 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as an inadequate amount of drain holes in the primary control surfaces (rudder, elevator, and aileron) and their tab surfaces, which may allow water to accumulate in the control surfaces. This condition could cause unbalanced flight control surfaces and reduced flutter margins, which could result in loss of control of the airplane. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a report of a ground fire which was fed by oxygen escaping from a damaged third crew person oxygen line and had started in the vicinity of an electrical panel. This AD requires replacing and changing the routing of the flexible oxygen hose of the third crew person oxygen line and modifying the entrance compartment assembly. We are issuing this AD to prevent the possibility of damage to the third crew person oxygen line and of an oxygen-fed fire in the airplane.
We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aerosystems Model 340A (SAAB/SF340A) and SAAB 340B airplanes. This AD was prompted by reports indicating that wear of the elevator pushrods has occurred on some airplanes after extended time in service. This AD requires determining if a certain part number is installed, performing a detailed inspection for individual play between the elevator pushrod assembly and degradation of elevator pushrod assembly, and replacing the affected elevator pushrod assembly with a new elevator pushrod assembly if necessary. We are issuing this AD to prevent a free elevator from affecting the pitch control authority, which may result in reduced controllability of the airplane.
We are superseding an existing airworthiness directive (AD) for certain transport category airplanes. That AD currently requires either activating all chemical oxygen generators in the lavatories until the generator oxygen supply is expended, or removing the oxygen generator(s); and, for each chemical oxygen generator, after the generator is expended (or removed), removing or restowing the oxygen masks and closing the mask dispenser door. This new AD requires installing a supplemental oxygen system in affected lavatories, which terminates the requirements of the existing AD. This AD was prompted by reports that the current design of the oxygen generators presents a hazard that could jeopardize flight safety. We are issuing this AD to eliminate a hazard that could jeopardize flight safety, and to ensure that all lavatories have a supple