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 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.
This action corrects a final rule; technical amendment, published by the FAA in the Federal Register on October 29, 2012, that adds two waypoints to the description of area navigation (RNAV) route Q-1. This action corrects the spelling of the TOCOS waypoint.
This action amends VHF Omnidirectional Range (VOR) Federal Airway V-8 in the vicinity of Rifle, CO, to correct the description contained in part 71 to ensure it matches the information contained in the FAA's aeronautical database, matches the depiction on the associated charts, and to ensure the safety and efficiency of the National Airspace System (NAS).
This rule establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.
This rule establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System,such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.
This rule establishes, amends, suspends, or revokesStandard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.
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.
This action amends the maintenance regulations by removing from the preventive maintenance category the task of updating databases used in self-contained, front-panel or pedestal-mounted navigation equipment. Further, we are adding text to the maintenance regulations that describes which equipment and, under which conditions, may have aeronautical databases updated by pilots as a non-maintenance function. Equipment which does not meet the criteria outlined in the new regulation will continue to be updated as a maintenance function. This revision will ensure that pilots using specified avionics equipment have the most current and accurate data and thereby increase aviation safety.
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.
This action amends Class E airspace at Anthony, KS. Additional controlled airspace is necessary to accommodate new Area Navigation (RNAV) Standard Instrument Approach Procedures at Anthony Municipal Airport. The FAA is taking this action to enhance the safety and management of Instrument Flight Rule (IFR) operations at the airport.
This action amends Class E airspace at Guthrie, IA. Decommissioning of the Guthrie Center non-directional radio beacon (NDB) at Guthrie County Regional Airport has made reconfiguration necessary for standard instrument approach procedures and for the safety and management of Instrument Flight Rule (IFR) operations at the airport. Geographic coordinates of the airport are also adjusted.
This action amends Class E airspace at Forest City, IA. Additional controlled airspace is necessary to accommodate new Area Navigation (RNAV) Standard Instrument Approach Procedures at Forest City Municipal Airport. The Forest City nondirectional beacon's (NDB) geographic coordinates are also adjusted. The FAA is taking this action to enhance the safety and management of Instrument Flight Rule (IFR) operations at the airport.
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.
This action modifies the Class D and Class E airspace areas at Lewiston, ID, to accommodate aircraft using Area Navigation (RNAV) (GPS) standard instrument approach procedures at Lewiston-Nez Perce County Airport. Also, the geographic coordinates are updated for the airport and navigational aids. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
This action establishes Class E airspace at Coaldale VHF Omni-Directional Radio Range Tactical Air Navigational Aid (VORTAC), Coaldale, NV to facilitate vectoring of Instrument Flight Rules (IFR) aircraft under control of Oakland Air Route Traffic Control Center (ARTCC). This action enhances the safety and management of IFR operations within the National Airspace System.
This action modifies Class E airspace at Pullman/Moscow Regional Airport, Pullman, WA. Controlled airspace is necessary to accommodate aircraft using Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Pullman/Moscow Regional Airport. This action also makes a minor change to the legal description in reference to Class E airspace extending upward from 700 feet above the surface. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
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.
These special conditions are issued for the ATR-GIE Avions de Transport Regional Models ATR42-500 and ATR72-212A airplanes. These airplanes will have novel or unusual design features associated with the architecture and connectivity capabilities of the airplanes' computer systems and networks, which may allow access to or by external computer systems and networks. Connectivity to, or access by, external systems and networks may result in security vulnerabilities to the airplanes' systems. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for these design features. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
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.
These special conditions are issued for the Boeing Model 757 series airplanes. These airplanes as modified by Flight Structures, Inc. will have novel or unusual design features associated with seats that include non-traditional, large, non-metallic panels that would affect survivability during a post-crash fire event. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
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 withdrawing a previously published direct final rule that would have allowed launch operators that conduct certain amateur rocket launches to voluntarily apply for a commercial space transportation license or experimental permit. The FAA is withdrawing this action because of the adverse comments it received.
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.
This action amends Class E airspace at Boone, IA. Decommissioning of the Boone non-directional beacon (NDB) at Boone Municipal Airport has made reconfiguration necessary for standard instrument approach procedures and for the safety and management of Instrument Flight Rule (IFR) operations at the airport.
This action amends Class E airspace at Breckenridge, TX. Additional controlled airspace is necessary to accommodate new Area Navigation (RNAV) Standard Instrument Approach Procedures at Stephens County Airport. The airport's geographic coordinates are also adjusted. The FAA is taking this action to enhance the safety and management of Instrument Flight Rule (IFR) operations at the airport.
This action amends Class E airspace at Perry, IA. Decommissioning of the Perry non-directional beacon (NDB) at Perry Municipal Airport has made reconfiguration necessary for standard instrument approach procedures and for the safety and management of Instrument Flight Rule (IFR) operations at the airport.
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.
This action amends the legal description of area navigation (RNAV) route Q-1 by adding two waypoints along the route. In addition, the route description is amended to match a standardized format by adding the appropriate state name to the waypoints, the name and the state of the Point Reyes, CA, navigation aid, and listing of the points in the proper order.
This action establishes Class E Airspace at La Belle, FL, to accommodate the new Area Navigation (RNAV) Global Positioning System (GPS) Standard Instrument Approach Procedures at La Belle Municipal Airport. This action enhances the safety and airspace management of Instrument Flight Rules (IFR) operations within the National Airspace System.
This action amends the legal description of area navigation (RNAV) route T-240 in Alaska by removing one waypoint that is no longer required and has been deleted from the National Airspace System Resources (NASR) database. In addition, the route description is amended to include the names of the navigation aids that comprise the route. The alignment of T-240 is not affected by this action.
This action amends the legal descriptions of area navigation (RNAV) routes Q-42 and Q-480 by changing the name of one waypoint common to each route. To avoid confusion with a similar sounding waypoint this will enhance safety within the National Airspace System and does not change the alignment or operating requirements of the routes.
This action establishes Class E Airspace at Reidsville, GA. Separation of existing Class E airspace surrounding Swinton Smith Field at Reidsville Municipal Airport, Reidsville, GA, from the Class E airspace of Vidalia Regional Airport, Vidalia, GA, has made this action necessary to enhance the safety and airspace management of Instrument Flight Rules (IFR) operations at the airport. This action also changes the names of both airports and updates the airport's geographic coordinates.
This amendment adopts miscellaneous amendments to the required IFR (instrument flight rules) altitudes and changeover points for certain Federal airways, jet routes, or direct routes for which a minimum or maximum en route authorized IFR altitude is prescribed. This regulatory action is needed because of changes occurring in the National Airspace System. These changes are designed to provide for the safe and efficient use of the navigable airspace under instrument conditions in the affected areas.
This document corrects a direct final rule that made nonsubstantive changes by removing a regulation that is obsolete and no longer used. The revisions to the direct final rule are part of NASA's retrospective plan under Executive Order (EO) 13563 completed in August 2011. NASA's full plan can be accessed on the Agency's open government Web site at http://www.nasa.gov/open/ .
This action amends the airspace description for Class D and Class E airspace at Jack Northrop Field/Hawthorne Municipal Airport, Hawthorne, CA. The FAA is taking this action in response to a request from the Southern California Terminal Radar Approach Control to clarify the legal description of the controlled airspace. Some exclusionary language was omitted and the Class E extension was recorded as 1.5 nautical miles and should have been .5 nautical miles. This action enhances the safety and management of aircraft operations for the Hawthorne, CA, area.
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.
This action modifies Class E airspace at Wolf Point, MT. Controlled airspace is necessary to accommodate aircraft using Nondirectional Radio Beacon (NDB) standard instrument approach procedures at L M Clayton Airport, Wolf Point, MT. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
These special conditions are issued for the Airbus Model A318, A319, and A320 series airplanes with modification 160500 and Model A321 series airplanes with modification 160023 (Sharklet). These airplanes will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. These design features include electronic flight controls that affect maneuvering. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
These special conditions are issued for the Airbus Model A318, A319, and A320 series airplanes with modification 160500 and Model A321 series airplanes with modification 160023 (Sharklet). These airplanes will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. The design features are associated with the systems that affect the structural performance of the airplane. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for these design features. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
These special conditions are issued for the Airbus Model A318, A319, and A320 series airplanes with modification 160500 and Model A321 series airplanes with modification 160023 (Sharklet). These airplanes will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. These design features include a high-speed protection system. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
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.
This action amends the FAA's rules for permitting limited use of portable oxygen concentrator systems on board aircraft, to allow for the use of additional portable oxygen concentrator (POC) devices on board aircraft, provided certain conditions in the SFAR are met. This action is necessary to allow all POC devices deemed acceptable by the FAA for use in air commerce to be available to the traveling public in need of oxygen therapy. Passengers will be able to carry these devices on board the aircraft and use them with the approval of the aircraft operator.
This notice concerns a petition for waiver submitted to the FAA by Space Exploration Technologies Corp. (SpaceX) to waive in part the requirement that a launch operator enter into a reciprocal waiver of claims with each customer. The FAA grants the petition.
The FAA is correcting the title of the publication “American Air Almanac” to its current title “Air Almanac”. This document corrects this minor technical error in the codified regulations.
The FAA is correcting a final rule; technical amendment published on December 16, 2011 (76 FR 78141). This final rule; technical amendment was originally published to correct a final rule published on August 21, 2009 (74 FR 42500). In that original final rule, the FAA amended its regulations to revise the training, qualification, certification, and operating requirements for pilots, flight instructors, ground instructors, and pilot schools. A portion of the codified text was inadvertently deleted and this document corrects that error.
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.
This action delays the effective date for a direct final rule that was published on August 22, 2012. In that rule, the FAA amends the scope of its regulations to allow launch operators that conduct certain amateur rocket launches an opportunity to voluntarily apply for a commercial space transportation license or experimental permit. The FAA has received several adverse comments to this rule, and delays the effective date to allow time for adequate analysis and a final determination. This document also corrects the regulatory identification number on the original publication.
This action establishes Class E airspace at Deer Lodge-City-County Airport, Deer Lodge, MT. Controlled airspace is necessary to accommodate aircraft using new Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Deer Lodge-City-County Airport. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
These special conditions amend and supersede those final special conditions No. 29-022-SC, for the ECF model EC225LP helicopter, which were published in the Federal Register on November 6, 2008 (73 FR 65968). A notice proposing this amendment was published December 20, 2010 (75 FR 79312). This amendment modifies the original final special conditions to address comments received and to clarify the intent of some of the requirements. This helicopter, as modified by ECF, will have novel or unusual design features associated with installing an optional SAR AFCS. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for these design features. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
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.
This direct final rule makes nonsubstantive changes by removing a regulation that is obsolete and no longer used. The revision to this rule are part of NASA's retrospective plan under Executive Order (EO) 13563 completed in August 2011. NASA's full plan can be accessed on the Agency's open government Web site at http://www.nasa.gov/open/ .
This rule makes non-substantive changes to NASA rules governing implementation of the Privacy Act by updating statute citations, position titles, terminology, and adjusting appellate responsibility for records held by the NASA Office of the Inspector General. This revision is part of NASA's retrospective plan under EO 13563 completed in August 2011. NASA's full plan can be accessed on the Agency's open Government Web site at http://www.nasa.gov/open/ .
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.
The FAA is correcting a technical amendment published on July 5, 2012 (77 FR 39623). In that technical amendment, the FAA clarified aircraft engine vibration test requirements in the airworthiness standards. The technical amendment was in response to inquiries from applicants requesting FAA engine type certifications and aftermarket certifications, such as supplemental type certificates, parts manufacturing approvals, and repairs. We revised the regulation to clarify that engine surveys require an engine test. Representatives of industry suggested that our technical amendment was in fact, a substantive change in the regulation, not a clarification. The FAA is correcting our prior action in response to that industry claim. This document amends the FAA's regulations to reverse the changes to § 33.83(a) amendment 33-33 and restore § 33.83(a) to its previous amendment 33-17.
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.
These special conditions are issued for the Embraer S.A. Models EMB-135 and EMB-145 series airplanes. These airplanes will have a novel or unusual design feature associated with the airplane seats that have non-traditional, large, non-metallic panels that would affect survivability during a post-crash fire event. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
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.
This action modifies area navigation (RNAV) route Q-62 by extending it further west and incorporating two additional navigation fixes. The route extension links two RNAV Standard Terminal Arrival Routes (STARs) serving the Chicago O'Hare International Airport, IL, terminal area with the high altitude route. The FAA is taking this action to increase National Airspace System (NAS) efficiency and enhance flight safety as aircraft transition from the en route airway structure to the terminal area airspace phase of flight.
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.
This action amends Class E airspace at Kerrville, TX. Additional controlled airspace is necessary to accommodate new Area Navigation (RNAV) Standard Instrument Approach Procedures at Kerrville Municipal Airport/Louis Schreiner Field. The geographic coordinates of the airport also are adjusted. The FAA is taking this action to enhance the safety and management of Instrument Flight Rule (IFR) operations at the airport. Due to subsequent decommissioning, the Shein locator outer marker/nondirectional radio beacon (LOM/NDB) will be removed from the regulatory text.
These special conditions are issued for the Bombardier Model CL-600-2B16 airplanes, including variants CL-601-3A, CL-601-3R and CL-604. This airplane, as modified by Atlantic Aero, Inc., will have a novel or unusual design feature associated with an advanced, enhanced flight vision system (EFVS). The EFVS consists of a head-up display (HUD) system modified to display forward-looking infrared (FLIR) imagery. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
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.
This action amends the Class E airspace areas at Boise Air Terminal (Gowen Field), Boise, ID. This action also adjusts the geographic coordinates of the airport. The Boise VHF Omni-Directional Radio Range Tactical Air Navigational Aid (VORTAC) is no longer needed as a reference. The Donnelly Tactical Air Navigation System (TACAN) has been decommissioned and controlled airspace reconfigured. This action also makes a minor change to the legal description in reference to Class E airspace 9,000 feet Mean Sea Level (MSL). This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
This action amends Class E airspace extending upward from 700 feet above the surface, and adds controlled surface airspace at Dillon, MT, to accommodate aircraft using new Area Navigation (RNAV) Global positioning System (GPS) standard instrument approach procedures at Dillon Airport. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport. The geographic coordinates of the airport also are adjusted.
This action establishes Class E airspace at Circle Town County Airport, Circle Town, MT to accommodate aircraft using new Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Circle Town County Airport. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
This action establishes Class E airspace at Trinchera Ranch Airstrip Airport, Fort Garland, CO. Controlled airspace is necessary to accommodate aircraft using new Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Trinchera Ranch Airstrip Airport. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
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.
The FAA is correcting a technical amendment published May 24, 2012 to a final rule published November 15, 2010. The final rule required design approval holders of certain existing airplanes and all applicants for type certificates of future transport category airplanes to establish a limit of validity of the engineering data that supports the structural maintenance program (hereinafter referred to as LOV). It also required that operators of any affected airplane incorporate the LOV into the maintenance program for that airplane. The technical amendment to the final rule was issued to correct errors, but within its publication, it contained inadvertent errors due to pagination in two tables. This document corrects the errors in those tables.
This document contains a summary of the agency's decision on a petition for exemption. The purpose of the document is to improve the public's awareness and inform affected operators of the FAA's decision.
This rule amends the requirements for siting explosives under a license to operate a launch site. It increases flexibility for launch site operators in site planning for the storage and handling of energetic liquids and explosives.
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.
This action corrects the geographic coordinates in the airspace description of a final rule, published in the Federal Register on July 10, 2012, amending controlled airspace at Lakehurst Naval Support Activity/Maxfield Field (Joint Base McGuire-Dix-Lakehurst).
This action removes Jet Route J-528 because the route is too short to serve a useful navigation or air traffic control purpose and is causing flight plan rejections in the air traffic control automation system.
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.
This action modifies Class D and Class E airspace at Bozeman Yellowstone International Airport, Bozeman, MT. This action aligns two Class E airspace areas with the Class D airspace area. This action also updates the airport name to Bozeman Yellowstone International Airport. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
This action corrects geographic coordinates that were not adjusted in the airspace description of a final rule, technical amendment published in the Federal Register on July 31, 2012, amending controlled airspace in the Montgomery, AL, area. The corrected coordinates for Maxwell AFB and Wetumpka Municipal Airport, are included in this final.
This action modifies Class E airspace at Lewistown Municipal Airport, Lewistown, MT. Controlled airspace is necessary to accommodate aircraft using Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Lewistown Municipal Airport. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
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.
This action amends Class E Airspace in Augusta, GA. The Bushe Non-Directional Beacon (NDB) and the Burke County NDB have been decommissioned and new Standard Instrument Approach Procedures have been developed at Augusta Regional Airport at Bush Field, Augusta, GA, and Burke County Airport, Waynesboro, GA, respectively. Airspace reconfiguration is necessary for the continued safety and management of instrument flight rules (IFR) operations within the Augusta, GA, airspace area. This action also updates the geographic coordinates of Burke County Airport.
This action amends Title 14 Code of Federal Regulations (14 CFR) part 71 relating to airspace designations to reflect the approval by the Director of the Federal Register of the incorporation by reference of FAA Order 7400.9W, Airspace Designations and Reporting Points. This action also explains the procedures the FAA will use to amend the listings of Class A, B, C, D, and E airspace areas; air traffic service routes; and reporting points incorporated by reference.
This document notifies the public of the Office of Management and Budget's (OMB's) approval of the information collection requirement contained in the FAA's final rule, “Fatigue Tolerance Evaluation of Metallic Structures,” which was published on December 2, 2011.
This document notifies the public of the Office of Management and Budget's (OMB's) approval of the information collection requirement contained in the FAA's final rule, “Damage Tolerance and Fatigue Evaluation of Composite Rotorcraft Structures,” which was published on December 1, 2011.
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.
The FAA is amending the scope of its regulations to allow launch operators that conduct certain amateur rocket launches an opportunity to voluntarily apply for a commercial space transportation license or experimental permit.
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.
This action modifies the Salt Lake City, UT, Class B airspace to contain aircraft conducting Instrument Flight Rules (IFR) instrument approach procedures to Salt Lake City International Airport (SLC), Salt Lake City, UT. The FAA is taking this action to improve the flow of air traffic, enhance safety, and reduce the potential for midair collision, while accommodating the concerns of airspace users. Further, this effort supports the FAA's national airspace redesign goal of optimizing terminal and en route airspace to reduce aircraft delays and improve system capacity. Minor corrections have been made to the geographic coordinates of the affected legal descriptions, as well as editorial corrections.
This action amends Class D airspace at Sault Ste Marie, ON. Additional controlled airspace is necessary to coincide with the Canadian control zone over Sault Ste Marie Airport. The FAA is taking this action to enhance the safety and management of Instrument Flight Rule (IFR) operations at the airport.
This action establishes Class E airspace at Chenega Bay, AK, to accommodate aircraft using a new Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Chenega Bay Airport. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
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.
These special conditions are issued for the Eurocopter France Model EC130T2 helicopter. This model helicopter will have the novel or unusual design feature of a 30-minute power rating, generally intended to be used for hovering at increased power for search and rescue missions. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
This action establishes Class E airspace at Fort Morgan, CO, to accommodate aircraft using a new Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Fort Morgan Municipal Airport. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
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.
This action amends Class E airspace at Sweetwater, TX. Additional controlled airspace is necessary to accommodate new Area Navigation (RNAV) Standard Instrument Approach Procedures at Avenger Field Airport. The airport's geographic coordinates are adjusted and the airport name changed. The FAA is taking this action to enhance the safety and management of Instrument Flight Rule (IFR) operations at the airport.
This action amends Class E airspace at Battle Creek, MI. Additional controlled airspace is necessary to accommodate new Area Navigation (RNAV) Standard Instrument Approach Procedures at W.K. Kellogg Airport. The airport's geographic coordinates also are adjusted. The FAA is taking this action to enhance the safety and management of Instrument Flight Rule (IFR) operations at the airport.
This action amends Class E airspace at Lemmon, SD. Additional controlled airspace is necessary to accommodate new Area Navigation (RNAV) Standard Instrument Approach Procedures at Lemmon Municipal Airport. The airport's geographic coordinates also are adjusted. The FAA is taking this action to enhance the safety and management of Instrument Flight Rule (IFR) operations at the airport.
This notice of policy announces Alaskan fuel hauling as a restricted category special purpose operation under Title 14 of the Code of Federal Regulations (14 CFR) 21.25(b)(7), for aircraft type-certificated under 14 CFR 21.25(a)(1), for operations within the State of Alaska, to provide bulk fuel to isolated individuals or locations in the State of Alaska.
This action amends Class D and E Airspace at Fort Rucker, AL, by updating the geographic coordinates of Cairns Army Air Field to aid in the navigation of our National Airspace System. This action is necessary for the continued safety and management of instrument flight rules (IFR) operations within the Fort Rucker, AL airspace area.
This action amends Class E Airspace in the Montgomery, AL area, by recognizing the name change of Prattville-Grouby Field Airport, formerly called Autauga Airport, and adjusts the geographic coordinates. This action does not change the boundaries or operating requirements of the airspace.
This action amends the Class E airspace area at Bar Harbor, ME, as the Surry Non-Directional Radio Beacon (NDB) has been decommissioned and new Standard Instrument Approach Procedures have been developed at Hancock County-Bar Harbor Airport. This action enhances the safety and airspace management of Instrument Flight Rules (IFR) operations within the National Airspace System. This action also makes a minor adjustment to the geographic coordinates of the airport.
This action establishes Class E Airspace at Arcadia, FL, to accommodate the new Area Navigation (RNAV) Global Positioning System (GPS) Standard Instrument Approach Procedures at Arcadia Municipal Airport. This action enhances the safety and airspace management of Instrument Flight Rules (IFR) operations within the National Airspace System.
This action establishes Class E Airspace at Quakertown, PA, to accommodate the new Area Navigation (RNAV) Global Positioning System (GPS) Standard Instrument Approach Procedures at Quakertown Airport. This action enhances the safety and airspace management of Instrument Flight Rules (IFR) operations within the National Airspace System.
This action establishes Class E Airspace at Apopka, FL, to accommodate the new Area Navigation (RNAV) Global Positioning System (GPS) Standard Instrument Approach Procedures at Orlando Apopka Airport. This action enhances the safety and airspace management of Instrument Flight Rules (IFR) operations within the National Airspace 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.
The NASA Research Misconduct rule describes procedures to be used by NASA for the handling of allegations of research misconduct. This direct final rule makes non-substantive changes to the policy governing the handling of allegations of research misconduct and updates to reflect organizational changes that have occurred in the Agency. The revisions to this rule are part of NASA's retrospective plan under EO 13563 completed in August 2011. NASA's full plan can be accessed at: http://www.nasa.gov/open/.
These special conditions are issued for the Agusta S.p.A. (Agusta) Model AW139 and AB139 helicopters. These model helicopters, as modified by Agusta, will have novel or unusual design features associated with installing an optional SAR AFCS. The applicable airworthiness standards do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards the Administrator considers necessary to show a level of safety equivalent to that established by the existing airworthiness standards.
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.
This action establishes Class E airspace at Roundup Airport, Roundup, MT, to accommodate aircraft using new Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Roundup Airport. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
These special conditions are issued for the Tamarack Aerospace Group's modification to the Cirrus SR22 airplane. This airplane as modified by Tamarack will have a novel or unusual design feature(s) associated with Tamarack Aerospace Group's modification. The design change will install winglets and an Active Technology Load Alleviation system (ATLAS). The addition of the ATLAS mitigates the negative effects of the winglets by effectively aerodynamically turning off the winglet under limit gust and maneuver loads. This is accomplished by measuring the aircraft loading and moving a small aileron-like device called a Tamarack Active Control Surface (TACS). The TACS movement reduces lift at the tip of the wing, resulting in the wing center of pressure moving inboard, thus reducing bending stresses along the wing span. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
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.
This action modifies three VHF Omnidirectional Range (VOR) Federal airways V-10, V-12, and V-508 in the vicinity of Olathe, KS. The FAA is taking this action to adjust the airway route structure due to the planned decommissioning of the Johnson County VOR navigation aid located on Johnson County Executive Airport, Olathe, KS. The establishment of the WETZL fix is canceled due to lack of extended service volume, and replaced with the existing DODSN fix, thereby making a one-degree correction to the Napoleon, MO, radial in the V-10 and V-12 airway descriptions. This action also removes the reference to the decommissioning of the Distance Measuring Equipment (DME) portion of the Johnson County VOR/DME navigation aid, as it remains in service.
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.
This action amends the legal descriptions of Jet Routes J-45 and J-79, and VHF omnidirectional range (VOR) Federal airways V-3, V-51, V-159, V-225, V-295 and V-537, in the vicinity of Vero Beach, FL. The FAA is taking this action because the name of the Vero Beach, FL, VOR Tactical Air Navigation (VORTAC) facility, which is included in the descriptions of the above routes, is being changed to the Treasure VORTAC.
This action amends Class E airspace at Grinnell Regional Airport, Grinnell, IA, by removing reference to the Grinnell NDB from the legal description, and amends the geographic coordinates of the airport. The Grinnell NDB has been decommissioned and is not needed as part of the airspace description. This action does not change the boundaries or operating requirements of the airspace.
This action amends the descriptions of 14 Jet Routes and 9 VOR Federal airways in the northeastern United States to reflect route changes made in Canadian airspace as part of Canada's Windsor-Toronto-Montreal airway project.
This action establishes Class E airspace at West Memphis, AR. Separation of existing Class E airspace surrounding West Memphis Municipal Airport from the Class E airspace of Memphis International Airport, Memphis, TN, has made this action necessary to enhance the safety and management of Instrument Flight Rules (IFR) operations at the airport.
This action removes Class E airspace listed at Lloydsville, PA, for Latrobe Hospital Heliport (old name), and incorporates Excela Health Latrobe Hospital Heliport (new name) onto Class E airspace at Latrobe, PA. Also, this action amends Class D and E airspace at Latrobe, PA, as new Standard Instrument Approach Procedures have been developed at Arnold Palmer Regional Airport. The geographic coordinates for both the heliport and the airport are updated. This action enhances the safety and airspace management of Instrument Flight Rules (IFR) operations in the Latrobe, PA, area. This action also recognizes the airport name change to Arnold Palmer Regional Airport.
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.
This rule establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures foroperations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports.
This action modifies Class E airspace at Plentywood Sher-Wood Airport, Plentywood, MT. Controlled airspace is necessary to accommodate aircraft using Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Plentywood Sher-Wood Airport. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport. This action also makes a minor adjustment to the geographic coordinates of the airport.
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.
This document notifies the public of the Office of Management and Budget's (OMB's) approval of the information collection requirement contained in the FAA's final rule, “Flightcrew Member Duty and Rest Requirements,” which was published on January 4, 2012.
This action confirms the effective date of the direct final rule published on February 16, 2012 (77 FR 9163), and responds to the comments received on that direct final rule. In that document, the FAA proposed to remove the definitions of Category IIIa, IIIb, and IIIc operations because the definitions are outdated and no longer used for aircraft certification or operational authorization.
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.
This action changes the name of the airport associated with the Class D and Class E airspace at Lakehurst, NJ. The airport's name is being changed to Lakehurst Naval Support Activity/Maxfield Field (Joint Base McGuire-Dix-Lakehurst). The FAAs Aeronautical Products office requested the change to reflect the current airport name.
This action amends Class E Airspace at Memphis, TN area, as the West Memphis Non-Directional Beacon (NDB) has been decommissioned and new Standard Instrument Approach Procedures have been developed at Memphis International Airport. This action also removes West Memphis Municipal Airport, West Memphis, from the existing airspace surrounding Memphis International Airport, Memphis, TN. This action enhances the safety and airspace management of Instrument Flight Rules (IFR) operations at the airport. This action also makes a minor adjustment to the geographic coordinates of General DeWitt Spain Airport and makes a minor correction to the regulatory text.
This action corrects a final rule published in the Federal Register on June 14, 2012, that establishes two RNAV routes in the southwest United States. This action corrects the latitude/longitude coordinates for the NOCHI waypoint (WP) as appears in the description of RNAV route T-310.
This action removes eighteen Domestic and Alaskan compulsory reporting points defined by navigation aids previously decommissioned, removed, or shutdown and taken out of the FAA aeronautical database as compulsory reporting points. Additionally, this action also requires changes to the name of four navigation aids that define associated compulsory reporting points. The FAA is removing the outdated Part 71 compulsory reporting points since they are no longer valid, and amending those Part 71 compulsory reporting points that require name changes, to be consistent with the FAA's aeronautical database.
This action removes Class D Airspace at Andalusia, AL, as the Air Traffic Control Tower at South Alabama Regional Airport at Bill Benton Field has closed, and amends Class E Airspace at Fort Rucker, AL, by recognizing the airport's name change to South Alabama Regional Airport at Bill Benton Field. This action also updates the geographic coordinates of the three listed Class E airports. This action enhances the safety and management of Instrument Flight Rules (IFR) operations at the airport.
This document notifies the public of the Office of Management and Budget's (OMB's) approval of the information collection requirement contained in the FAA's final rule, “Operations Specifications,” which was published on February 10, 2011.
These special conditions are issued for the Boeing Model 737-800 airplane. This airplane as modified by Lufthansa Technik will have a novel or unusual design feature associated with the installation of large non-structural glass items in the cabin area of an executive interior occupied by passengers and crew. The installation of these items in a passenger compartment, which can be occupied during taxi, takeoff, and landing, is a novel or unusual design feature with respect to the material used. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
This action requires helicopter pilots to use the New York North Shore Helicopter Route when operating along the north shore of Long Island, New York. The North Shore Helicopter Route was added to the New York Helicopter Route Chart in 2008 and prior to this action, its use has been voluntary. The purpose of this rule is to protect and enhance public welfare by maximizing utilization of the existing route flown by helicopter traffic one mile off the north shore of Long Island and thereby reducing helicopter overflights and attendant noise disturbance over nearby communities. This rule will lapse in 2 years unless the FAA determines that a permanent rule is merited.
This amendment clarifies aircraft engine vibration test requirements in the airworthiness standards. The clarification is in response to inquiries from applicants requesting FAA engine type certifications and aftermarket certifications, such as supplemental type certificates, parts manufacturing approvals, and repairs. We are revising the regulations to clarify that “engine surveys” require an engine test. The change is not substantive in nature, and will not impose any additional burden on any person.
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.
This action confirms the effective date of the direct final rule published on March 22, 2012. The rule removes a regulatory provision under Federal Aviation Administration (FAA) medical certification standards that requires individuals granted the Special Issuance of a Medical Certificate (Authorization) to have their letter of Authorization in their physical possession or readily accessible on the aircraft while exercising pilot privileges.
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.
Based upon its assessment of the special light-sport aircraft (SLSA) manufacturing industry, the FAA is issuing this notice of policy to inform the public of its policy for assessing the accuracy of declarations made in Statements of Compliance issued for aircraft intended for airworthiness certification as SLSA and to ensure that SLSA conform to identified consensus standards. Additionally, in response to findings noted in its assessment of the SLSA manufacturing industry, the FAA is reiterating its policy regarding the airworthiness certification of SLSA manufactured outside the United States.
These special conditions are issued for the Gulfstream Aerospace LP, Model Gulfstream G280 airplane. This airplane will have novel or unusual design features associated with connectivity of the passenger service computer systems to the airplane critical systems and data networks. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for these design features. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
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.
This action amends Class D airspace within the Pontiac, MI, area by changing the name of the airport from Oakland-Pontiac Airport to Oakland County International Airport and updating the geographic coordinates. This action does not change the boundaries or operating requirements of the airspace.
This action amends Class E airspace at Travis Air Force Base (AFB), Fairfield, CA. The projected decommissioning of the Travis VHF Omni-Directional Radio Range (VOR) has made this action necessary for the safety and management of Instrument Flight Rules (IFR) operations at the airport.
This action amends Class E airspace at Livingston, Mission Field Airport, Livingston, MT. Decommissioning of the Livingston Tactical Air Navigation System (TACAN) has made this action necessary for the safety and management of Instrument Flight Rules (IFR) operations at the airport. Also, the geographic coordinates of the airport are updated at the request of National Aeronautical Navigation Services.
This action amends Class E airspace at Watts-Woodland Airport, Woodland, CA. The projected decommissioning of the Travis VHF Omni-Directional Radio Range (VOR) has made this action necessary for the safety and management of Instrument Flight Rules (IFR) operations at the airport. This action also makes a minor adjustment to the geographic coordinates of the airport.
This action establishes Class E airspace at Eureka, NV, to accommodate aircraft using a new Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Eureka Airport, Eureka, NV. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
This amendment adopts miscellaneous amendments to the required IFR (instrument flight rules) altitudes and changeover points for certain Federal airways, jet routes, or direct routes for which a minimum or maximum en route authorized IFR altitude is prescribed. This regulatory action is needed because of changes occurring in the NationalAirspace System. These changes are designed to provide for the safe and efficient use of the navigable airspace under instrument conditions in the affected areas.
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 supplemental oxygen supply.
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 cracking of certain fuel access panels of the outer wing. This AD requires an external inspection, and if necessary an internal inspection, to determine if certain fuel access panels are installed, and replacement if necessary; optional repetitive inspections for cracking of the fuel access panels, and replacement if necessary, would defer the internal inspection; and eventual replacement of affected fuel access panels with new panels. We are issuing this AD to prevent cracking of fuel access panels, which could result in arcing and ignition of fuel vapor in the outer wing fuel tank during a lightning strike.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes. This AD was prompted by reports of deformation found at the neck of the pressure regulator body on the oxygen cylinder and regulator assembly (CRA). This AD requires an inspection to determine if a certain oxygen CRA is installed and the replacement of affected oxygen CRAs. We are issuing this AD to prevent elongation of the pressure regulator neck, which could result in rupture of the oxygen cylinder, and, in the case of cabin depressurization, oxygen not being available when required.
We are adopting a new airworthiness directive (AD) for the Aeronautical Accessories, Inc. (AAI), High Landing Gear Aft Crosstube Assembly (aft crosstube) installed on certain Bell Helicopter Textron, Inc. (Bell) and Agusta S.p.A. (Agusta) model helicopters as an approved Bell part installed during production or based on a Supplemental Type Certificate (STC). This AD requires certain recurring visual, dimensional, and fluorescent penetrant inspections of each aft crosstube, and replacing any cracked crosstube. This AD also requires establishing a life limit and creating a component history card or equivalent record for one of the affected part-numbered aft crosstubes. This AD was prompted by three reports of failed crosstubes because of cracks. 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 certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of cracked retract actuator fuse pins that can fail earlier than the previously determined safe life limit of the pins. A fractured retract actuator fuse pin can cause the main landing gear to extend without restriction and attempt to lock into position under high dynamic loads. This AD requires an inspection for the part number of the fuse pin, and replacement of the pin if necessary. We are issuing this AD to prevent structural damage to the side and drag brace lock assemblies, which could result in landing gear collapse during touchdown, rollout, or taxi.
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 fatigue cracking on the lower main sill inner chord of the hatch opening of the overwing emergency exit. This AD requires repetitive inspections for cracking, corrosion damage, and any other irregularity of the lower main sill inner chord and surrounding structure, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking on the lower main sill inner chord of the hatch opening of the overwing emergency exit, which could result in reduced structural integrity of the hatch opening of the overwing emergency exit and consequent rapid decompression of the airplane.
We are adopting a new airworthiness directive (AD) for certain the Boeing Company Model 777-200, -200LR, and -300ER series airplanes. This AD was prompted by a report from the manufacturer indicating that the lowered ceiling support structure of Section 41, in airplanes incorporating the overhead space utilization (OSU) option, was found to be under-strength when subjected to a 9.0 g forward load. This AD requires installing new structural members, tie rod(s), and attach fittings on the left and right sides of the lowered ceiling support structure. We are issuing this AD to prevent the forward lowered ceiling panels and support structure from becoming dislodged during a 9.0 g forward load and consequent injury to personnel or interference with an emergency evacuation.
We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. This AD was prompted by reports of baggage bay fire bottles that can be misassembled such that two squib electrical connectors can be cross-connected. This AD requires a general visual inspection of certain baggage bay fire bottles for correct connection and for the length of the wiring loom, modification of the wiring loom to certain squib connectors, and corrective actions if necessary. We are issuing this AD to detect and correct excessive wiring loom length and improper connection of the squib connecters, which in conjunction with a fire in one of the baggage bays, could result in the fire extinguishing agent being discharged into a wrong compartment and consequent damage to the airplane.
We are adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. This AD was prompted by a report of a crack found on the left-hand sidewall well on the nose landing gear (NLG). This AD requires performing a repetitive high frequency eddy current inspection of the stiffeners on the left-hand sidewall on the NLG bay for cracks, and repair or replace the sidewall if necessary. We are issuing this AD to detect and correct failure of the sidewall, which could result in consequent in-flight rapid decompression of the cabin and injury to the passengers.
We are adopting a new airworthiness directive (AD) that supersedes an existing Emergency Airworthiness Directive (EAD) for certain Eurocopter Deutschland GmbH (ECD) Model EC135 helicopters. The existing EAD, which was previously sent to all known U.S. owners and operators of ECD Model EC135 helicopters and not made generally effective by publication in the Federal Register , currently requires inspecting the ring frame between the rear structure tube (tailboom) and the tail rotor fenestron housing (fenestron housing) for a crack before the first flight of each day and replacing any cracked ring frame with an airworthy ring frame. Since we issued that EAD, we have determined that a pre-flight pilot check in conjunction with a recurring 25-hour inspection is sufficient for determining the airworthiness of the ring frame. Additionally, ECD has developed a modification that is terminating action for the requirements of that EAD. This superseding AD revises the inspection requirements of the EAD to allow an owner/operator to perform the pre-flight pilot check, adds a recurring inspection of the ring frame, and allows for installation of a ring frame reinforcement as an optional terminating action for the AD requirements. The actions are intended to detect a crack in the ring frame which could result in loss of the fenestron structure and subsequent loss of control of the helicopter.
We are superseding an existing airworthiness directive (AD) for all Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 C-2 helicopters. That AD currently requires revising the “Emergency and Malfunction Procedures” and “Performance Data” sections of the Rotorcraft Flight Manual (RFM) by inserting three temporary pages into the RFM to alert pilots to monitor the power display when a generator is deactivated and provides procedures to prevent failure of the remaining generator. Before we issued that AD, the manufacturer developed a procedure to modify the two “After Junction Boxes” by removing a diode from each box, which provides terminating action for our AD requirements. These actions are intended to require implementing this terminating action to prevent an electrical power system failure and subsequent loss of control of the helicopter and revising the RFM accordingly, by removing the temporary pages inserted to comply with the superseded AD.
We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters with a certain generator control unit (GCU), to require replacing each affected GCU with an airworthy GCU. This AD was prompted by laboratory tests which revealed a potential fault in the overvoltage protection on a certain part-numbered GCU. The actions are intended to prevent failure of the overvoltage protection of the GCU, degraded performance of the electrical power generation and distribution systems, a fire, and subsequent loss of control of the helicopter.
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 cracks underneath the passenger door in a butt-joint on the forward fuselage of a Model F.28 Mark 0100 airplane. This AD requires repetitive low frequency eddy current inspections of the forward fuselage butt-joints for cracks, and if necessary, a temporary repair followed by a permanent repair. We are issuing this AD to detect and correct cracking of the butt-joint on the forward fuselage, which could result in explosive decompression and consequent loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by a design review which revealed the absence of electrical insulation material between a wing or integral center wing tank (ICWT) fuel quantity indication system (FQIS) probe and the bottom of the tank structure. This AD requires for all airplanes, applying sealant below the FQIS probes in the wing tanks; and for certain airplanes, applying sealant below the FQIS probes in the ICWT. This AD also requires revising the aircraft maintenance program by revising the fuel airworthiness limitations and incorporating critical design configuration control limitations (CDCCLs). We are issuing this AD to prevent an ignition source in the tank vapor space, which could result in a fuel tank explosion and consequent loss of the airplane.
We are superseding an existing airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. That AD currently requires revising the Abnormal Procedures and Limitations sections of the Dassault F7X Airplane Flight Manual. This new AD requires a test of the power distribution control units (PDCU) cards and generator control units (GCU) cards to detect faulty components, and if any faulty components are found, replacing any affected PDCU or GCU card. This AD was prompted by a determination that additional actions are necessary to address the identified unsafe condition. We are issuing this AD to detect and correct a leakage failure mode of transient voltage suppression (TVS) diodes used on PDCU cards or GCU cards in the primary power distribution boxes (PPDB), which, in combination with other system failures, could lead to loss of controllability of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 series airplanes; Airbus Model A330-200 Freighter series airplanes; Airbus Model A330-300 series airplanes; Airbus Model A340-200 series airplanes; and Airbus Model A340-300 series airplanes. This AD was prompted by reports of sheared fasteners located on the outside skin of the forward cargo door and cracks on the frame fork ends, as well as cracks of the aft cargo door frame 64A. This AD requires performing a detailed inspection of the outer skin rivets at the frame fork ends of the forward and aft cargo door for sheared, loose, and missing rivets; repairing the outer skin rivets, if necessary; and performing repetitive inspections. We are issuing this AD to detect and correct sheared, loose, or missing fasteners on the forward and aft cargo door frame, which could result in the loss of structural integrity of the forward and aft cargo door.
This action establishes Class D airspace and amends existing Class E airspace at East Hampton, NY, to accommodate the new mobile airport traffic control tower (ATCT) at East Hampton Airport. Controlled airspace enhances the safety and management of Instrument Flight Rules (IFR) operations at the airport. This action also updates the geographic coordinates of the airport's existing Class E airspace and eliminates Class E extensions that are no longer required.
We are adopting a new airworthiness directive (AD) for Turbomeca S.A. Arriel 2C1, 2C2, and 2S2 turboshaft engines. This AD requires replacement of affected digital engine control units (DECUs). This AD was prompted by a report of a helicopter experiencing a DECU malfunction during flight. We are issuing this AD to prevent loss of automatic control on one or both engines installed on the same helicopter, which could result in an uncommanded in-flight engine shutdown, forced autorotation landing, or accident.
This action establishes restricted area airspace within the Devils Lake Military Operations Area (MOA), overlying Camp Grafton Range, in the vicinity of Devils Lake, ND. The new restricted areas permit realistic training in modern tactics to be conducted at Camp Grafton Range while ensuring the safe and efficient use of the National Airspace System (NAS) in the Devils Lake, ND, area. Unlike restricted areas which are designated under Title 14 Code of Federal Regulations (14 CFR) part 73, MOAs are not regulatory airspace. However, since the restricted areas overlap the Devils Lake East MOA, the FAA is including a description of the Devils Lake East MOA change in this rule. The MOA change described herein will be published in the National Flight Data Digest (NFDD).
We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada (Bell) Model 206, 206A, 206A-1, 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4 helicopters, with Aviation Specialties Unlimited, Inc. (ASU), Night Vision Imaging System (NVIS) lighting modified by Supplemental Type Certificate SR01383SE (STC). This AD requires determining the date of STC installation, determining if the aircraft has an unfiltered turbine outlet temperature (TOT) internal over-temperature warning light, and based on those findings, installing an NVIS filter. This AD was prompted by the finding that an unfiltered TOT indicator over-temperature warning light, when illuminated, created glare and reflections that could degrade the pilot's view while using night vision goggles thereby creating an unsafe condition. The actions of this AD are intended to modify any unfiltered TOT indicator unit over-temperature warning light by installing a filter to prevent degradation of the pilot's vision while using night vision goggles and to prevent subsequent loss of control of the helicopter.
These special conditions are issued for the Gulfstream Aerospace LP, Model Gulfstream G280 airplane. This airplane will have novel or unusual design features associated with the architecture and connectivity capabilities of the airplane's computer systems and networks, which may allow access to or by external computer systems and networks. Connectivity to, or access by, external systems and networks may result in security vulnerabilities to the airplane's systems. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for these design features. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
We are adopting a new airworthiness directive (AD) for SOCATA Model TBM 700 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 incorrect part number during overhaul of the nose landing gear. 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 of cracking found in the wing rear spar. This AD requires a one-time detailed inspection for cracks, corrosion, and other defects of the rear face of the wing rear spar, and repair if necessary. We are issuing this AD to detect and correct cracking in the rear spar, which could propagate to a critical length, possibly affecting the structural integrity of the area and resulting in a fuel tank rupture, with consequent damage to the airplane and possible injury to its occupants.
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, and Model CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by reports of a bleed air leak from the high pressure ducts which was not immediately detected by the bleed leak detection system. This AD requires installing new sensing elements in the main landing gear wheel well and the overwing area, protective blankets on the upper surface of the wing box and fuel tubes, and protective shields on the rudder quadrant support-beam in the aft equipment compartment. We are issuing this AD to prevent an undetected bleed air leak which can cause loss of rudder control, can lead to degradation of structural integrity, and could be a potential heat source that can lead to fuel being ignited.
We are superseding an existing airworthiness directive (AD) for Enstrom Helicopter Corporation (Enstrom) Model F-28C, F-28C-2, F-28F, 280C, 280F, 280FX, TH-28, 480, and 480B helicopters to add another trim relay to the applicability and to revise the modification instructions. This AD is prompted by the discovery that another part-numbered trim relay, inadvertently omitted from the current AD, may contain the same unsafe condition. These actions are intended to prevent failure of the cyclic trim system and subsequent loss of control of the helicopter.
We are superseding two existing airworthiness directives (ADs) for certain Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The first existing AD currently requires, for certain airplanes, repetitive inspections of the Station (STA) 348.2 frame to detect cracking under the stop fittings and intercostal flanges at stringers S-14L, S-15L, and S-16L, and corrective action if necessary. The second existing AD currently requires repetitive inspections to detect cracking of the intercostal webs, attachment clips, and stringer splice channels, and corrective action if necessary. This new AD requires that the inspection for cracking under the stop fittings be done on additional airplanes; extends the repetitive interval for certain airplanes; adds a one-time inspection to detect missing fasteners; and updates or adds certain inspection and repair instructions. This new AD also requires, for certain airplanes, repetitive inspections of the cargo barrier net fitting for cracking, and repair if necessary. This new AD also adds, for certain airplanes, repetitive inspections for cracking of the stringer S-15L aft intercostal, and repair if necessary. This AD was prompted by reports of cracking of the STA 348.2 frame above the two outboard fasteners attaching the frame inner chord and door stop fittings, and in the outboard chord at stringer S-16L. We have also received reports of missing fasteners in the STA 348.2 frame inner chord. We are issuing this AD to detect and correct fatigue cracking of the intercostals on the forward and aft sides of the forward entry door cutout, which could result in loss of the forward entry door and rapid decompression of the airplane.
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 external detailed inspections or non-destructive inspections to detect cracks in the fuselage skin along the chem-mill steps at stringers S-1 and S-2R, between station (STA) 400 and STA 460, and repair if necessary. This new AD adds inspections for cracking in additional fuselage skin locations, and repair if necessary. This new AD also reduces the inspection thresholds and repetitive intervals for certain airplanes. This AD was prompted by reports of additional crack findings of the fuselage skin at the chem-mill steps. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin panels at the chem-mill steps, which could result in sudden fracture and failure of the fuselage skin panels, and consequent rapid decompression of the airplane.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes. This AD was prompted by reports of cracks found on the center section ribs of the horizontal stabilizers. This AD requires repetitive inspections for cracking of the aft face of the left and right rib hinge bearing lugs of the center section of the horizontal stabilizer; and crack measurement, repairs, post-repair repetitive inspections, and installation of a new center section rib if necessary. We are issuing this AD to detect and correct cracking in the left and right bearing lugs of the rib hinge spreading at the same time, which could result in failure of both hinge bearing lugs. Failure of the hinge bearing lugs could result in the inability of the horizontal stabilizer to sustain flight loads and thereby reduce the controllability of the airplane.
We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AW139 helicopters to determine if the hardware that attaches the upper end of collective control rod C2 to torque tube C3 is properly installed. This AD is prompted by the discovery of an incorrectly-attached collective control rod. These actions are intended to prevent separation of the collective control rod from the torque tube, loss of control of the collective pitch, and subsequent loss of control of the helicopter.
We are superseding an existing airworthiness directive (AD) for all Airbus Model A300 B4-600, B4-600R and A300 F4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and Model A310 series airplanes. That AD currently requires modifying the wiring in the right-hand electronics rack. This new AD requires replacing the cockpit multi-tank indicators (MTI), and for certain airplanes, replacing high-level, low-level, and overflow sensors and their harness connectors, and re-instating the low-level warning indication to the cockpit MTI. This AD was prompted by reports of failures of four fuel level sensor-amplifier and MTI units. This AD also adds Model A310 series airplanes to the applicability. We are issuing this AD to prevent degradation of the electrical insulation sleeves of the low-level indication lamps on the MTI, which could cause a short circuit that might result in high voltage being conveyed to the high- andlow-level sensors in the wing tanks. This condition could cause the level sensor to heat above acceptable limits, possibly resulting in a fuel tank explosion, and consequent loss of the airplane.
This action modifies Jet Route J-2, and VOR Federal airways V-16, V-66 and V-202 in southern Arizona and New Mexico due to the scheduled decommissioning of the Cochise, AZ, VHF Omnidirectional Range Tactical Air Navigation (VORTAC) which currently is used to define segments of the routes.
This action modifies the Colorado Springs, CO, Class C airspace area by amending the legal description to reflect the current airport reference point (ARP) information for the City of Colorado Springs Municipal Airport. The operating requirements remain the same.
This action establishes two new low-altitude RNAV routes, designated T-306 and T-310, in the southwestern United States. The new routes expand the availability of RNAV within the National Airspace System (NAS) and provide substitute route segments for portions of VOR Federal airways V-16 and V-202.
The “FAA Modernization and Reform Act of 2012,” enacted on February 14, 2012, in Section 305 of the Act, removed the line check performance evaluation requirements for pilots over 60 years of age that applied to air carriers engaged in part 121 operations. This technical amendment conforms to the FAA's regulations as a result of the Act.
We are adopting a new airworthiness directive (AD) for Cessna 206, 207, and 210 airplanes with Hartzell Engine Technologies (HET) turbochargers, part numbers (P/Ns) 406610-0005 and 406610-9005, installed. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires removing the affected turbochargers from service before further flight. This AD was prompted by a report of an HET turbocharger causing an engine in-flight power rollback. We are issuing this AD to prevent turbocharger bearing seizure, failed turbocharger components, and damage to the airplane.
This action amends Class D and Class E airspace at Leesburg, FL, changing the airport's name to Leesburg International Airport. The FAAs Aeronautical Products office requested the change to reflect the airport's current name.
This action amends Class E Airspace in the Tallahassee, FL area. Tallahassee Commercial Airport has been abandoned and controlled airspace is no longer needed. Airspace reconfiguration is necessary for the continued safety and management of instrument flight rules (IFR) operations within the Tallahassee, FL airspace area.
This action amends Class E Airspace at Orlando, FL, as new Standard Instrument Approach Procedures have been developed at Orlando Executive Airport. This action enhances the safety and airspace management of Instrument Flight Rules (IFR) operations within the National Airspace System. This action also makes a minor adjustment to the geographic coordinates of Orlando Executive Airport, Orlando International Airport, and Kissimmee Municipal Airport.
This action amends seventeen Domestic, Alaskan, and Hawaiian compulsory reporting points previously updated in the FAA aeronautical database without accompanying regulatory action being taken. The FAA is taking this action to correct the compulsory reporting point information contained in part 71 to ensure it matches the information contained in the FAA's aeronautical database and to ensure the safety and efficiency of the National Airspace System (NAS).
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, and -400ER series airplanes. That AD currently requires replacing the separation link assembly on the applicable entry and service doors with an improved separation link assembly, and doing related investigative and corrective actions if necessary. This new AD adds an airplane to the applicability and removes certain other airplanes. This AD was prompted by a report that an additional airplane is subject to the unsafe condition. We are issuing this AD to prevent failure of an entry or service door to open fully in the event of an emergency evacuation, which could impede exit from the airplane. This condition could result in injury to passengers or crewmembers.
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 oil lines fitted to affected aircraft are not fire resistant. 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 WACO Classic Aircraft Corporation Models 2T-1A, 2T-1A-1, and 2T-1A-2 airplanes. This AD requires inspection of the front and rear horizontal stabilizer spar assemblies with replacement of parts as necessary. This AD was prompted by cracking of the horizontal stabilizer spars, which could lead to failure of the horizontal spars with consequent loss of control. We are issuing this AD to correct the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GMBH (ECD) Model MBB-BK 117 C-1 and C-2 helicopters. This AD requires installing a placard that corresponds to the maximum permissible flight altitude, amending the Rotorcraft Flight Manual (RFM) to revise the maximum permissible operating altitude, and inserting revised performance charts into the RFM. This AD also requires a repetitive maintenance “MAX N1 CHECK” to determine the appropriate maximum altitudes. This AD also requires, if the engine or a Fuel Control Unit (FCU) or module 2 or 3 is replaced, repeating the maintenance “MAX N1 CHECK.” Finally, this AD specifies that modifying both engines would provide terminating action for the AD requirements. This AD was prompted by the failure of a “few” engines to reach the specified one-engine-inoperative (OEI) rating at altitudes above 10,000 feet. The actions of this AD are intended to prevent flights at altitudes where the full OEI engine power cannot be reached and subsequent loss of control of the helicopter if an OEI operation is required.
We are adopting a new airworthiness directive (AD) for all Burkhart GROB Luft- und Raumfahrt GmbH Models GROB G 109 and GROB G 109B 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 excessive corrosion on the nose plate in the vertical stabilizer, which could cause the vertical stabilizer nose plate to fail. 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 The Boeing Company Model 777 airplanes. This AD was prompted by four reports of retaining cross bolt hardware not fully engaged into the fuse pins of the forward trunnion lower housing of the main landing gear (MLG), which could result in an incorrect MLG emergency landing break-away sequence. This AD requires a detailed inspection of the fuse pin cross bolts and fuse pins of the left and right MLG forward trunnion lower housing to verify that the cross bolts are correctly installed and that there are no missing fuse pins, and replacement of the fuse pins if necessary. We are issuing this AD to prevent an incorrect emergency landing MLG break-away sequence, which could result in puncturing of the wing box and consequent fuel leaks and an airplane fire. Failure of the fuse pins could also result in a possible landing gear collapse causing a runway excursion during take-off or landing.
We are superseding an existing airworthiness directive (AD) for certain Bombardier Inc. Model CL-215-1A10 and CL-215-6B11 (CL-215T Variant) airplanes. That AD currently requires repetitive inspections to detect cracking of the lower cap of the wing front and rear spars at wing station (WS) 51.00, and the wing lower skin. Additional actions, if cracking is found, include reworking the lower cap of the front or rear spar, inspecting for cracking, and repairing any cracking. The existing AD also requires reporting inspection results. This new AD requires extending the inspection area of the rear spar lower cap from WS 51.00 to WS 49.50 and modifying the ultrasonic inspection calibration procedure. This AD was prompted by reports of cracking found outside the inspection area. We are issuing this AD to detect and correct cracking of the lower caps of the wing front and rear spars, and lower wing skin, which could result in reduced structural integrity of the airplane.
This action modifies Class D and Class E airspace at Bellingham, WA, to accommodate aircraft departing and arriving under Instrument Flight Rules (IFR) at Bellingham International Airport. This action, initiated by the biennial review of the Bellingham airspace area, enhances the safety and management of aircraft operations at the airport.
This action modifies Class E airspace at Billings Logan International Airport, Billings, MT. Controlled airspace is necessary to accommodate aircraft using Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Billings Logan International Airport. This action will also make a minor adjustment to the geographic coordinates of the airport. This improves the safety and management of Instrument Flight Rules (IFR) operations at the airport.
