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Title 14 published on 2014-01-01
The following are only the Rules published in the Federal Register after the published date of Title 14.
For a complete list of all Rules, Proposed Rules, and Notices view the Rulemaking tab.
We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. This AD requires inspection of the oil feed tube sealing sleeve and removal of those oil feed tube sealing sleeves that are affected by this AD. This AD was prompted by fractures of the high-pressure/intermediate-pressure (HP/IP) turbine support internal oil feed tube. We are issuing this AD to prevent failure of the HP/IP turbine support internal oil feed tube, which could result in uncontained engine failure and damage to the airplane.
We are adopting a new airworthiness directive (AD) for Short Brothers & Harland Ltd. Model SC-7 Series 3 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 fatigue cracking, which could lead to structural failure of the nose landing gear (NLG). We are issuing this AD to require actions to address the unsafe condition on these products.
We are superseding Airworthiness Directive (AD) 2007-22-10 for all Airbus Model A330-200, A330-300, A340-200, A340-300, A340-500, and A340-600 series airplanes. AD 2007-22-10 required repetitive inspections of the left-hand and right-hand wing main landing gear (MLG) rib 6 aft bearing lugs (forward and aft) to detect any cracks on the two lugs, and replacement if necessary. Since we issued AD 2007-22-10, we have received reports of additional cracking of the MLG rib 6 aft bearing forward lug. This new AD expands the applicability and reduces certain compliance times. We are issuing this AD to detect and correct cracking of the MLG rib 6 aft bearing lugs, which could result in collapse of the MLG upon landing.
We are superseding Airworthiness Directive (AD) 2012-09-07 for certain Airbus Model A319-111, -112, and -132 airplanes; Model A320-111, -211, -212, -214, and -232 airplanes; and Model A321-111, -211, -212, and -231 airplanes. AD 2012-09-07 required an electrical bonding test between the gravity fill re-fuel adaptor and the top skin panels on the wings; and, if necessary, an inspection for corrosion of the component interface and adjacent area; and repairing the gravity fuel adaptor if necessary. This new AD adds airplanes to the applicability and requires inspecting those airplanes to determine if a repair was done, and doing the electrical bonding test and corrective action if necessary. This AD was prompted by a determination that more airplanes are subject to the identified unsafe condition. We are issuing this AD to detect and correct corrosion and improper bonding, which, in combination with a lightning strike in this area, could create a source of ignition in a fuel tank, resulting in a fire or explosion and consequent loss of the airplane.
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 reports of fuselage skin cracks at the lower forward corner of the main entry door (MED) 1 cutout. This AD requires repetitive inspections of the fuselage skin of the MED 1 cutout for cracking, and repair if necessary; and also provides an optional terminating modification, including post-repair or post-modification fuselage skin inspections for cracking, and corrective actions if necessary. We are issuing this AD to detect and correct skin cracking, which can become large and could adversely affect the structural integrity of the airplane.
This action amends the legal description of three Jet Routes, one High Altitude Area Navigation (RNAV) Route (Q-route), and five VHF Omnidirectional Range (VOR) Federal Airways in the vicinity of Baton Rouge, LA. The FAA is taking this action because the Baton Rouge VHF Omnidirectional Range/Tactical Air Navigation (VORTAC) navigation aid, included as part of the route structure for the airways, is being renamed the Fighting Tiger VORTAC.
This action amends VHF Omnidirectional Range (VOR) Federal Airway V-330 in the vicinity of Mountain Home, ID. The FAA is taking this action to correct the V-330 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 promotes safety and efficiency within the National Airspace System (NAS).
On June 23, 2014, the FAA published a final rule to extend the requirement for an additional two years for pilots operating civil helicopters under Visual Flight Rules to use the New York North Shore Helicopter Route when operating along the north shore of Long Island, New York. The final rule extended the expiration date to August 6, 2016. However, an error in the final rule resulted in the inadvertent removal of Subpart H of part 93 of Title 14 of the Code of Federal Regulations. This final rule corrects that error and reinstates the provisions of Subpart H.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires replacing a fitting that is part of the refuel control solenoid valve assembly. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
We are adopting a new airworthiness directive (AD) for all Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of dislodged engine fan cowl panels. This AD requires installing additional attaching hardware on the left and right fan cowl access panels and the nacelle attaching structures. We are issuing this AD to prevent damage to the fuselage and flight control surfaces from dislodged engine fan cowl panels.
We are publishing a new airworthiness directive (AD) for Airbus Helicopters (formerly Eurocopter France) Model EC130T2 helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires repetitively inspecting the attachment points where the fan attaches to the main gearbox (MGB) oil cooler hopper (hopper) and replacing any cracked hopper with an airworthy hopper. This AD is prompted by several cases of a cracked hopper. The cracks were found on the hopper at the fan attachment points. These actions are intended to detect a crack in the hopper at a fan attachment point to prevent failure of the fan attachment, interference of the fan with the control rod of the front servo-control or with the flight control bellcrank, and subsequent loss of control of the helicopter.
We are superseding Airworthiness Directive (AD) 2007-03-18, AD 2008-17-02, AD 2012-08-03, and AD 2012-15-14, for certain Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. AD 2007-03-18, AD 2008-17-02, AD 2012-08-03, and AD 2012-15-14 required repetitive inspections of the forward lugs of the aft bearing at rib 5 of the main landing gear (MLG) on the left-hand (LH) and right-hand (RH) wings, and repair if necessary; and installation of new bushes with increased interference fit in the forward lug of the aft bearing at rib 5 of the MLG on the LH and RH wings. This new AD adds airplanes to the applicability; and adds, for certain airplanes, repetitive inspections of the MLG rib 5 aft bearing forward lugs, and repair if necessary. This AD was prompted by reports of cracking in the forward lug of the MLG rib 5 aft bearing attachment. We are issuing this AD to detect and correct cracking of the forward lugs of the aft bearing at rib 5 of the MLG on the LH and RH wings, which could affect the structural integrity of the MLG attachment, resulting in possible MLG collapse during landing or rollout.
We are adopting a new airworthiness directive (AD) for Agusta AB139 and AW139 helicopters to require replacing certain single-braided flexible hydraulic hoses with double-braided flexible hydraulic hoses. This AD was prompted by occurrences of leaking flexible hydraulic hoses. The actions of this AD are intended to prevent loss of hydraulic power and subsequent loss of helicopter control.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-115, A319-133, A320-214, A320-232, and A320-233 airplanes. This AD requires repetitive detailed inspections of the outboard main landing gear (MLG) support rib lower flange fasteners for discrepancies, and corrective actions if necessary. This AD was prompted by reports of failure of certain fasteners on the MLG support rib lower flange. We are issuing this AD to detect and correct discrepancies of the fasteners at the outboard MLG support rib lower flange, which could result in an airplane not meeting its maximum loads expected in service. This condition could result in structural failure.
The FAA is correcting a final rule published on May 28, 2010. In that rule, the FAA amended its regulations by adding equipage requirements and performance standards for Automatic Dependent Surveillance—Broadcast (ADS-B) Out avionics on aircraft operating in Classes A, B, and C airspace, as well as other specified classes of airspace within the U.S. National Airspace System (NAS). This document corrects errors in regulatory provisions addressing ADS-B Out equipment and use.
We are revising Airworthiness Directive (AD) 2014-12-11 for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. AD 2014-12-11 required revising the Rotorcraft Flight Manual (RFM) to include the appropriate operating limitations for performing Class D external load-combination operations. As published, AD 2014-12-11 referenced an incorrect date for Revision No. 12 of Sikorsky RFM SA S92A-RFM-003, Part 1. This AD corrects the error while retaining the requirements of AD 2014-12-11. These actions are intended to require appropriate operating limitations to allow operators to perform Class D external load-combination operations, including human external cargo, in this model helicopter that now meets the Category A performance standard.
We are adopting a new airworthiness directive (AD) for all Quest Aircraft Design, LLC Model KODIAK 100 airplanes. This AD requires inspecting the inboard upper and lower elevator skins for cracking, repairing cracks, and installing doublers. This AD was prompted by a report that fatigue cracks were found in the lower elevator skins. We are issuing this AD to correct the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) airplanes. This AD was prompted by a report that, during a routine inspection, corrosion was discovered on the lower bearing of the rudder upper torque tube. This AD requires applying grease to the bearing; doing a general visual inspection of the expelled old grease for any contaminants, metal wear, and indication of corrosion, and replacing the bearing if necessary; and revising the maintenance or inspection program, as applicable, to incorporate the rudder spring tab operational test and a check of the rudder spring tab operation into the daily inspection. We are issuing this AD to prevent corroded bearings, which could result in a partial or total loss of axial support.
We are adopting a new airworthiness directive (AD) for certain serial number (S/N) Lycoming Engines reciprocating engines. This AD was prompted by propeller governor shaft set screws coming loose due to improper installation. We are issuing this AD to prevent the propeller governor shaft set screw from coming loose, causing damage to the engine and damage to the airplane.
We are superseding airworthiness directive (AD) 2013-15-10 that applies to certain Rolls-Royce plc (RR) RB211 turbofan engines. AD 2013-15-10 required inspecting the intermediate-pressure compressor (IPC) rotor shaft rear balance land for cracks. This AD requires inspecting the IPC rotor shaft rear balance land for cracks, eliminates a terminating action, expands one inspection, and eliminates certain other inspections. We are issuing this AD to detect cracking on the IPC rotor shaft rear balance land, which could lead to uncontained engine failure and damage to the airplane.
We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) AE 2100 series turboprop engines and AE 3007A and 3007C series turbofan engines. This AD was prompted by reports of pitting in the wheel bores and subsequent RRC analysis that concluded that lower life limits are needed for the affected turbine wheels. This AD requires a reduction for the approved life limits of the affected turbine wheels. This AD also requires an eddy current inspection (ECI) of certain RRC engines with affected turbine wheels. We are issuing this AD to prevent uncontained failure of the turbine wheels, damage to the engine, and damage to the airplane.
We are superseding Airworthiness Directive (AD) 95-24-04 for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes; and Model A300 C4-605R Variant F airplanes. AD 95-24-04 required inspections to detect cracks at the aft spar web of the wings, and repair if necessary. This new AD reduces certain compliance times, and expands the applicability. This AD was prompted by a determination that the inspection threshold and interval must be reduced to allow timely detection of cracks and accomplishment of applicable repairs, because of cracking in the rear spar web of the wings between certain ribs due to fatigue-related high shear stress. We are issuing this AD to detect and correct fatigue-related cracking, which could result in reduced structural integrity of the wing.
We are superseding Airworthiness Directive (AD) 2013-24-13 for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, -500, -600, -700, -700C, -800, and -900 series airplanes. AD 2013-24-13 required replacing the pivot link assembly for certain airplanes, replacing the seat track link assemblies or modifying the existing seat track link assembly for certain airplanes, or modifying the existing seat track link assembly fastener for certain other airplanes. AD 2013-24-13 also required inspecting, changing, or repairing the seat track link assembly for certain other airplanes. Since we issued AD 2013-24-13, a certain paragraph reference in that AD was found to be mis-identified; this AD corrects this paragraph reference. We are issuing this AD to prevent seat detachment in an emergency landing, which could cause injury to occupants of the passenger compartment and affect emergency egress.
This action removes the prohibition against certain flights within the territory and airspace of Ethiopia contained in Special Federal Aviation Regulation (SFAR) No. 87 from the Code of Federal Regulations (CFR). The prohibition only applied to flight operations within the territory and airspace of Ethiopia north of 12 degrees north latitude conducted by United States (U.S.) air carriers or commercial operators; persons exercising the privileges of an airman certificate issued by the FAA, unless that person was engaged in the operation of a U.S.-registered aircraft for a foreign air carrier; and operators using an aircraft registered in the United States, except where the operator of such aircraft was a foreign air carrier. The FAA has now determined that the safety and security situation that prompted the above flight prohibition has significantly improved, and that it is safe for U.S. civil flights to be operated within the entire territory and airspace of Ethiopia, subject to the approval of and in accordance with the conditions established by the appropriate authorities of Ethiopia.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, and CL-601-3R Variants) airplanes. This AD requires repetitive inspections for fractured or incorrectly oriented fasteners on the inboard flap hinge-box forward fittings on both wings, and replacement of all fasteners, if necessary. This AD was prompted by several reports of incorrectly oriented and fractured fasteners found on the inboard flap hinge-box forward fitting at wing station (WS) 76.50. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners, which could result in detachment of the flap hinge-box and the flap surface, and consequent reduced controllability of the airplane.
We are superseding airworthiness directive (AD) 2012-14-06 for certain Rolls-Royce Corporation (RRC) 250-C20, -C20B, and -C20R/2 turboshaft engines. AD 2012-14-06 required a one-time visual inspection and fluorescent-penetrant inspection (FPI) on certain 3rd-stage and 4th-stage turbine wheels for cracks in the turbine blades. This new AD replaces the one-time visual inspection and FPI with repetitive visual inspections and FPIs. This AD also adds certain engine models to the applicability. This AD was prompted by the determination that the one-time inspections required by AD 2012-14-06 should be changed to repetitive inspections. We are issuing this AD to prevent failure of 3rd-stage and 4th-stage turbine wheel blades, which could cause engine failure and damage to the aircraft.
We are superseding Airworthiness Directive (AD) 2013-19-19 for certain Eurocopter France Model AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters. AD 2013-19-19 required replacing certain serial-numbered main gearbox (MGB) bevel gear vertical shafts and inspecting and replacing, if necessary, each MGB bevel gear vertical shaft (shaft). This new AD requires the same actions as AD 2013-19-19 but corrects an error in the term used to identify an inspection qualification and updates the type certificate holder's name. This AD is prompted by two incidents of emergency ditching after warning indications of loss of MGB oil pressure . These actions are intended to detect a cracked shaft, which could result in loss of MGB oil pressure, loss of the MGB lubrication system, and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. This AD was prompted by reports of loose, broken, or backed-out spur gear bolts on the horizontal stabilizer trim actuator (HSTA). This AD requires a revision to the airplane flight manual, a revision to the maintenance or inspection program, as applicable, and replacement of HSTAs having certain part numbers. We are issuing this AD to detect and correct loose spur gear bolts on the HSTA, which, if combined with the failure of the primary load path, could lead to failure of the HSTA and subsequent loss of the airplane.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of two in-service incidents where one side of the main landing gear (MLG) did not achieve down-lock. This AD requires doing a detailed inspection of the apex joints of the stabilizer brace lock link in the MLG for clearance; rectifying and repairing the clearance gap, if necessary; and lubricating the apex joints of the stabilizer brace lock link in the MLG. We are issuing this AD to detect and correct insufficiently greased stabilizer brace lock linkage of the MLG and over-torqued lock linkage attachment bolts, which could lead to the failure to extend and down-lock the MLG, and could affect the safe landing of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-201, -202, -203, -301, -302, and -303 airplanes. This AD requires a one-time ultrasonic inspection for fractures of all aft mount-pylon bolts of each engine. This AD was prompted by a report of one bolt on the aft engine mount upper beam found totally broken. We are issuing this AD to detect and correct fracture of the aft mount-pylon bolts, which could result in failure of the engine mount and consequent detachment of the engine.
We are superseding Airworthiness Directive (AD) 2009-06-06 for all Airbus Model A310 and A300-600 series airplanes. AD 2009-06-06 required revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations and maintenance tasks for aging systems maintenance. This new AD requires revising the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. We are issuing this AD to prevent reduced structural integrity and reduced control of these airplanes due to the failure of system components.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-300, A340-200, and A340-300 series airplanes. This AD was prompted by a report of substantial inner skin disbonding damage found on a rudder. This AD requires performing an inspection for damage of certain rudders, and repair if necessary. We are issuing this AD to detect and correct damage of the rudder, which could result in reduced structural integrity of the rudder.
We are adopting a new airworthiness directive (AD) for all Empresa Brasileira de Aeronautica S.A. (Embraer) Model EMB-135ER, -135KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This AD was prompted by a determination of the need to revise the airplane airworthiness limitations related to the pylon yokes I and II, and the skin panel of the windshield pillar. This AD requires revising the maintenance or inspection program, as applicable. We are issuing this AD to prevent fatigue cracking of various structural elements, which could affect the structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model MYSTERE-FALCON 50 airplanes. This AD was prompted by a report of an untimely and intermittent indication of slat activity due to chafing of the electrical wiring under the glare shield and behind the flight deck front panel. This AD requires installing two protective plates between the electrical wiring under the glare shield and the engine fire pull handles. We are issuing this AD to prevent chafing of the electrical wiring, which could result in a short circuit and generation of smoke in the cockpit, potential loss of several functions essential for safe flight, and consequent reduced controllability of the airplane.
This rule amends, suspends, or removes 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 for the 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 removes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures (ODPs) 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.
The FAA is correcting the final rule, “Harmonization of Airworthiness Standards—Gust and Maneuver Load Requirements” (79 FR 73462), published December 11, 2014. In the rule, the FAA amended certain airworthiness regulations for transport category airplanes to eliminate regulatory differences between the airworthiness standards of the FAA and European Aviation Safety Agency (EASA). It does not add new requirements beyond what manufacturers currently meet for EASA certification and does not affect current industry design practices. This final rule revises the pitch maneuver design loads criteria; revises the gust and turbulence design loads criteria; revises the application of gust loads to engine mounts, high lift devices, and other control surfaces; adds a “round-the-clock” discrete gust criterion and a multi-axis discrete gust criterion for airplanes equipped with wing-mounted engines; revises the engine torque loads criteria; adds an engine failure dynamic load condition; revises the ground gust design loads criteria; revises the criteria used to establish the rough air design speed; and requires the establishment of a rough air Mach number. This document corrects errors in the rule by ensuring that certain letters in the included equations have the right formatting and therefore the correct meaning.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-601, B4-603, B4-605R, F4-605R, and C4-605R Variant F airplanes. This AD was prompted by reports of cracking found in the pylon box, which was due to the stresses resulting from the pressure applied by the thrust reverser cowl bumpers. This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking; and replacement of all fittings if necessary, which terminates the repetitive HFEC inspections for the modified side only. We are issuing this AD to detect and correct cracks of the pylon rib 5, which could result in reduced structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes. This AD requires revising the electrical emergency configuration procedure in the Emergency Procedures section of the airplane flight manual (AFM) to include procedures for deploying the ram air turbine manually to provide sufficient hydraulic power and avoid constant speed motor/generator (CSM/G) shedding. This AD was prompted by an electrical load analysis that revealed that hydraulic power might not be sufficient to supply the CSM/G during slat/flap extension when only one engine is running. We are issuing this AD to prevent such a condition which, in conjunction with the loss of the main electrical system, could lead to the scenario where the flightcrew is not clearly warned that the electrical system has switched on the battery and thus has a limited duration that would allow a safe landing.
We are superseding airworthiness directive (AD) 2011-23-01 for all Technify Motors GmbH (TMG) models TAE 125-01 and TAE 125-02-99 reciprocating engines with certain part number (P/N) and serial number (S/N) clutch assemblies installed. AD 2011-23-01 required replacement of certain P/N and S/N clutch assemblies. This AD requires the same actions but expands the population of affected P/N and S/N clutch assemblies. This AD was prompted by an additional report of a clutch assembly that malfunctioned due to disk springs that received a nonconforming heat treatment process. We are issuing this AD to prevent failure of the clutch assembly, which could lead to failure of the engine, in-flight shutdown, and 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 found in the engine exhaust pipe. 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 Viking Air Limited Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III 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 failed locknuts on the horizontal stabilizer attach bracket. 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 717-200 airplanes; Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40 and DC-10-40F airplanes; Model MD-10-10F and MD-10-30F airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; Model MD-88 airplanes; and Model MD-90-30 airplanes. This AD was prompted by reports of latent air data transducer degradation. This AD requires revising the maintenance or inspection program, as applicable, to incorporate special compliance items (SCIs). We are issuing this AD to prevent erroneous air data information, which could lead to a mid-air collision within reduced vertical separation minimum (RVSM) airspace.
We are superseding Airworthiness Directive (AD) 2011-13-09 for all Airbus Model A330-200, -200F, and -300 series airplanes. AD 2011-13-09 required revising the maintenance program to incorporate new limitations and maintenance tasks for certain certification management requirements (CMRs). This new AD requires revising the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. We are issuing this AD to prevent safety-significant latent failures that would, in combination with one or more other specific failures or events, result in a hazardous or catastrophic failure condition.
We are superseding Airworthiness Directive (AD) AD 2011-14-06 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2011-14-06 required revising the maintenance program. This new AD requires revising the maintenance program to incorporate new, more restrictive limitations. This AD was prompted by the determination that more restrictive limitations are necessary. We are issuing this AD to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for Pilatus Aircraft Ltd. Model PC-7 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by 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 cracking from stress corrosion on various parts of the airplane structure made of aluminum alloy AA2024-T351. We are issuing this AD to require actions to address the unsafe condition on these products.
This rule establishes, amends, suspends, or removesStandard Instrument Approach Procedures (SIAPs) and associatedTakeoff Minimums and Obstacle Departure Procedures (ODPs) foroperations at certain airports. These regulatory actions areneeded because of the adoption of new or revised criteria, orbecause of changes occurring in the National Airspace System,such as the commissioning of new navigational facilities, addingnew obstacles, or changing air traffic requirements. Thesechanges 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 all Airbus Model A330-200 Freighter, -200, and -300 series airplanes and Model A340-200, -300, -500, and -600 series airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires revising the airplane flight manual to advise the flightcrew of emergency procedures for abnormal Alpha Protection (Alpha Prot). This AD was prompted by a report of Angle of Attack (AoA) probes jamming on an in-service Airbus Model A321 airplane. We are issuing this AD to ensure that the flightcrew has procedures to counteract the pitch down order due to abnormal activation of the Alpha Prot. An abnormal Alpha Prot, if not corrected, could result in loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires revising the airplane flight manual to advise the flightcrew of emergency procedures for abnormal Alpha Protection (Alpha Prot). This AD was prompted by a report of Angle of Attack (AoA) probes jamming on an in-service Airbus Model A321 airplane. Jamming of the two AoA probes during climb is attributed to water freezing under the AoA vane slinger, and led to activation of the Alpha Prot while the Mach number increased, which resulted in an airplane pitch down per design. We are issuing this AD to ensure that the flightcrew has procedures to counteract the pitch down order due to abnormal activation of the Alpha Prot. An abnormal Alpha Prot, if not corrected, could result in loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-115, A319-133, A320-214, A320-232, and A320-233 airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires repetitive detailed visual inspections to detect discrepancies of the wing lower skin surface and inboard main landing gear (MLG) support rib lower flange location fasteners and, depending on findings, accomplishment of applicable corrective action(s). This AD was prompted by reports of failure of certain fasteners located at the wing lower skin surface and inboard MLG support rib lower flange. We are issuing this AD to detect and correct discrepancies of the fasteners at the external surface of the lower wing skin and inboard MLG support rib lower flange, which could result in an airplane not meeting its maximum loads expected in service. This condition could result in structural failure.
We are superseding Airworthiness Directive (AD) 2011-09-11, for certain The Boeing Company Model 777-200 and -300 series airplanes. AD 2011-09-11 required repetitive inspections for hydraulic fluid contamination of the interior of the strut disconnect assembly; repetitive inspections for discrepancies of the interior of the strut disconnect assembly, if necessary; repetitive inspections of the exterior of the strut disconnect assembly for cracks, if necessary; corrective action if necessary; and an optional terminating action for the inspections. This new AD adds, for certain airplanes, an inspection of the side and top cover plates to determine if all cover plate attach fasteners have been installed, and installing any missing fasteners including doing an inspection for damage, and repair if necessary. This AD was prompted by reports of side and top cover plates installed with missing fastener bolts, which results in an unsealed opening on the system disconnect assembly. We are issuing this AD to detect and correct hydraulic fluid contamination, which can cause cracking of titanium parts in the system disconnect assembly; and also to detect and correct missing fasteners, which results in unsealed openings on the system disconnect assembly. Both unsafe conditions can compromise the engine firewall and result in fire hazards for both the engine compartment and the strut.
We are adopting a new airworthiness directive (AD) for certain Mitsubishi Heavy Industries, Ltd. Models MU-2B-30, MU-2B-35, MU-2B-36, MU-2B-36A, and MU-2B-60 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 stress corrosion cracking in the flanges of the airframe at stations 4610 and 5605. We are issuing this AD to require actions to address the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that the maintenance actions for airplane systems susceptible to aging must be mandated. This AD requires revising the maintenance or inspection program to incorporate more restrictive maintenance requirements and airworthiness limitations. We are issuing this AD to mitigate the risks associated with aging effects of airplane systems. Such aging effects could change the characteristics leading to an increased potential for failure, which could result in failure of certain life-limited parts, and could reduce the structural integrity or reduce controllability of the airplane.
We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FAN JET FALCON and FAN JET FALCON SERIES C, D, E, F, and G airplanes. This AD was prompted by our determination of the need for a revision to the airplane airworthiness limitations to introduce changes to the maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to incorporate a new airworthiness limitations section. We are issuing this AD to prevent reduced structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for certain ATR—GIE Avions de Transport Régional Model ATR42-500 airplanes, and Model ATR72-212A airplanes. This AD was prompted by a report that, during an inspection of an airplane on the production line, interference was detected between the electrical harness and a bonding lead due to an incorrect installation of the affected bonding lead. This AD requires a detailed inspection for damage or incorrect routing of the bonding lead routing above the 120VU shelf, and if any damage or incorrect routing is found, repairing damage or modifying the bonding lead routing. We are issuing this AD to detect and correct installation of the bonding lead, which could cause arcing and chafing, and could possibly result in an uncontrolled fire.
We are adopting a new airworthiness directive (AD) for Airbus Helicopters (previously Eurocopter France) Model EC155B1 and AS 365 N3 helicopters with a certain automated flight control system (AFCS) and with a Garmin global positioning system (GPS) installed. This AD requires revising the Rotorcraft Flight Manual (RFM) to prohibit using the autopilot coupled with a Localizer/Instrument Landing System (LOC/ILS) or Very High Frequency Omnidirectional Range (VOR) approach. This AD is prompted by a report of unpredictable and unexpected roll oscillations during coupled LOC or VOR approaches.This condition, if not corrected, could result in loss of helicopter control.
We are superseding Airworthiness Directive (AD) 2014-03-05, for certain Bombardier, Inc. Model BD-700-1A10 airplanes. AD 2014-03-05 required modification of the air data probes and sensors. This new AD continues to require modification of the air data probes and sensors. This new AD also adds airplanes to the applicability. This AD was prompted by a report that the manufacturer has determined that some completion centers used the heater current/brake temperature monitor unit (HBMU) logic circuit to control the line voltage of the drain mast heaters. We are issuing this AD to detect and correct an unannunciated failure of two pitot static probe heaters, which could affect controllability of the airplane in icing conditions.
The FAA is withdrawing a direct final rule regarding aviation training devices published December 3, 2014. That rule would have relieved burdens on pilots seeking to obtain aeronautical experience for an instrument rating by increasing the allowed use of aviation training devices. The FAA received adverse comments to the direct final rule and, thus, is withdrawing the direct final rule.
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 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 final rule requires each air carrier operating under 14 CFR part 121 to develop and implement a safety management system (SMS) to improve the safety of its aviation-related activities. SMS is a comprehensive, process-oriented approach to managing safety throughout an organization. SMS includes an organization-wide safety policy; formal methods for identifying hazards, controlling, and continually assessing risk and safety performance; and promotion of a safety culture. SMS stresses not only compliance with technical standards but also increased emphasis on the overall safety performance of the organization.
We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aerosystems Model 340B airplanes. This AD was prompted by a report that the elevator position quoted in an aircraft maintenance manual is incorrect and a report that the trunnion at the lower part of the control column was installed incorrectly. This AD requires an inspection of the stick pusher rigging and an inspection of the installation of the trunnion and the stick pusher rigging, and corrective actions if necessary. We are issuing this AD to correct the rigging of the elevator position of the stick pusher to reduce the probability of a negative effect on the handling quality during stall, which could result in reduced controllability of the airplane.
We are adopting a new airworthiness directive (AD) for certain GROB-WERKE Models G115EG and G120A airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a defective starter solenoid. 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 Beechcraft Corporation Model G58 airplanes. This AD was prompted by reports of fuel leaks due to fuel cells that did not properly fit in Model G58 airplanes. This AD requires inspecting for and replacing, as necessary, certain fuel cells. This AD also requires inspecting and replacing parts, as necessary, of the left and right fuel system installations and correcting torques on fuel system fittings; and prohibits future installations of certain fuel cells. We are issuing this AD to correct the unsafe condition on these products.
The Department of Transportation is issuing a final rule to implement section 403 of the FAA Modernization and Reform Act of 2012 regarding the carriage of musical instruments as carry-on baggage or checked baggage on commercial passenger flights operated by air carriers. This rule responds to difficulties musicians have encountered when transporting their instruments during air travel.
These special conditions are issued for the Airbus Helicopters Deutschland GmbH Model MBB-BK117 D-2 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 prohibits certain flight operations in the Damascus (OSTT) Flight Information Region (FIR) by all U.S. air carriers; U.S. commercial operators; persons exercising the privileges of a U.S. airman certificate, except when such persons are operating a U.S.-registered aircraft for a foreign air carrier; and operators of U.S.-registered civil aircraft, except when such operators are foreign air carriers. The FAA previously prohibited such flight operations in a Notice to Airmen (NOTAM) 4/4936, which was issued on August 18, 2014, and absent this rule, would have remained in effect until December 31, 2014. This Special Federal Aviation Regulation (SFAR) adopts the prohibitions currently in effect via the NOTAM, and requires compliance with the prohibitions for 2 years from the date of publication of this final rule, unless the FAA determines that it is necessary to amend or rescind this rule based on the situation in the region. The FAA finds that this action is necessary to address a potential hazard to persons and aircraft engaged in such flight operations.
The FAA is correcting a final rule with request for comments, published on December 16, 2014 (79 FR 74607). In that final rule, the FAA amended its regulations to eliminate the requirement for an air traffic control tower operator to hold a control tower operator certificate if the individual also holds a Federal Aviation Administration Credential with a tower rating (FAA Credential). In that document, the FAA inadvertently made an error in the part heading for 14 CFR part 65. This document corrects that error.
This action amends Special Federal Aviation Regulation (SFAR) No. 113, “Prohibition Against Certain Flights in the Simferopol (UKFV) Flight Information Region (FIR),” which prohibited certain flight operations in a portion of the Simferopol (UKFV) FIR by all U.S. air carriers; U.S. commercial operators; persons exercising the privileges of a U.S. airman certificate, except when such persons are operating a U.S.-registered aircraft for a foreign air carrier; and operators of U.S.-registered civil aircraft, except when such operators are foreign air carriers. This action expands the area in which flight operations by persons subject to SFAR No. 113 are prohibited, to include all of the Simferopol (UKFV) FIR, as well as the entire Dnipropetrovsk (UKDV) FIR. The FAA finds this action to be necessary to prevent a potential hazard to persons and aircraft engaged in such flight operations.
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 paint adherence defects inside the engine air intake box and cohesion defects inside the laminated ducting from the filter to the air intake box. We are issuing this AD to require actions to address the unsafe condition on these products.
We are superseding Airworthiness Directive (AD) 97-11-07 and AD 99-18-23, which apply to all The Boeing Company Model MD-90-30 airplanes. AD 97-11-07 and AD 99-18-23 required revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate certain compliance times for principal structural element (PSE) inspections and replacement times for safe-life limited parts. This new AD also requires revising the maintenance or inspection program to incorporate a new PSE requirement for the rear spar caps of the horizontal stabilizer and its associated inspections, which would terminate certain inspections of the horizontal stabilizer rear spar. This AD was prompted by an analysis of data that identified a need to introduce a new PSE requirement for the rear spar caps of the horizontal stabilizer. We are issuing this AD to detect and correct fatigue cracking of PSEs and certain safe-life limited parts, which could adversely affect the structural integrity of the airplane.
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, 747-300, 747-400, 747-400D, and 747SR series airplanes. This AD was prompted by a report of a cracked reveal made from a casting found within a group of airplanes that should have machined reveals made only from 6061 aluminum. This AD requires an inspection to determine the material of the number 3 main entry door (MED) corner reveal, repetitive inspections of certain reveals for cracking, and corrective action if necessary. This AD also requires repetitive inspections for cracking of 6061 machined aluminum one-piece corner reveals, and replacement with 6061 machined aluminum two-piece corner reveals if necessary, which terminates certain repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the lower forward corner reveal of the number 3 MEDs, which could lead to the door escape slide departing the airplane when the door is opened and the slide is deployed, and consequent injuries to passengers and crew using the door escape slide during an emergency evacuation.
The FAA is correcting an airworthiness directive (AD) that published in the Federal Register . That AD applies to all Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engine models with certain second-stage high-pressure turbine (HPT) air seals installed. The time required to perform the initial eddy current inspection (ECI) in the Compliance section is incorrect. This document corrects that error. In all other respects, the original document remains the same.
This joint interim final rule implements for all Federal award-making agencies the final guidance Uniform Administrative Requirements, Cost Principles, and Audit Requirements for Federal Awards (Uniform Guidance) published by the Office of Management and Budget (OMB) on December 26, 2013. This rule is necessary in order to incorporate into regulation and thus bring into effect the Uniform Guidance as required by OMB. Implementation of this guidance will reduce administrative burden and risk of waste, fraud, and abuse for the approximately $600 billion per year awarded in Federal financial assistance. The result will be more Federal dollars reprogrammed to support the mission, new entities able to compete and win awards, and ultimately a stronger framework to provide key services to American citizens and support the basic research that underpins the United States economy.
These special conditions are issued for the Sikorsky Model S-76D helicopter. This model of helicopter, as modified by Sikorsky, 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 Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes. This AD was prompted by a report of cracking at the splice plate of the frame (FR) 47 butt joint crossing area found during full-scale fatigue testing. This AD requires repetitive inspections for cracking of both sides of the splice plate of that frame butt joint crossing area, and corrective action if necessary. This AD also provides for an optional modification, which terminates the repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the splice plate of the FR 47 butt joint crossing area, which could result in reduced structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Airbus Model A310 series airplanes. This AD was prompted by a report of early ruptures on the levers of the nose landing gear (NLG) sequence valve. This AD requires a one-time inspection for damage of the landing gear sequence valve levers and pin shearing indicating areas on the NLG and the main landing gears (MLGs); and depending on findings, replacing the sequence valve and lever, or doing a one-time inspection to detect interference between control rods and sequence valves and corrective actions if necessary. We are issuing this AD to detect and correct interference between a landing gear leg and door, which could result in failure of that landing gear to extend and could damage the airplane and injure occupants.
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 reports of fatigue cracking in the skin assembly and bear strap of the aft lower corner of the forward airstair stowage doorway. This AD requires repetitive inspections for cracking of the skin assembly and bear strap of the forward airstair stowage doorway; post-repair and post-modification inspections for certain airplanes; and related investigative and corrective actions, if necessary. This AD also provides optional terminating actions for certain inspections. We are issuing this AD to detect and correct fatigue cracking, which could result in rapid loss of cabin pressure.
We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 2000 and FALCON 2000EX airplanes. This AD was prompted by a design review, which revealed that the forward servicing compartment (FSC) is configured with tie-down points. This AD requires inspecting the FSC for installed tie-down points, and removing those tie-down points. We are issuing this AD to detect and correct installed tie-down points, which could lead to inadvertent use of the FSC as a cargo compartment, which could result in damage to the structure of the airplane or potential risk of fire.
This rulemaking eliminates the requirement for an air traffic control tower operator to hold a control tower operator certificate if the individual also holds a Federal Aviation Administration Credential with a tower rating (FAA Credential). The requirement to hold both the control tower operator certificate and the FAA Credential is redundant since the underlying requirements for the FAA Credential encompass those of the control tower operator certificate. This action will reduce the FAA's burden of administering redundant programs for those individuals who hold an FAA Credential.
This action makes minor adjustments to the boundary descriptions of restricted areas R-2932, R-2933, R-2934 and R-2935 at Cape Canaveral, FL. The changes are required based on more accurate digital plotting of points that revealed minor mismatches between adjacent boundaries. The R-2933 description is also amended to remove exclusionary wording that no longer applies.
We are revising Airworthiness Directive (AD) 2008-14-02 for Agusta Model AB139 and AW139 helicopters. AD 2008-14-02 required inspecting the fuselage frame to detect fatigue cracks which could lead to structural failure and subsequent loss of control of the helicopter. Since we issued AD 2008-14-02, Agusta developed a frame reinforcement modification, which supports extending the interval for inspecting the fuselage frame for a fatigue crack. This new AD requires inspecting the fuselage frame for a crack and reduces the applicability from AD 2008-14-02 to exclude helicopters with the frame reinforcement modification. The actions of this AD are intended to detect a fatigue crack that could result in failure of the fuselage frame and subsequent loss of control of the helicopter.
We are superseding an airworthiness directive (AD) 2013-11-08 for Pilatus Aircraft Limited Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a need to incorporate new revisions into the aircraft maintenance manual or in the limitations document of the FAA-approved maintenance program. 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 777 airplanes. This AD was prompted by reports of corroded, migrated, or broken spring pins of the girt bar floor fitting; in one case the broken pins prevented a door escape slide from deploying during a maintenance test. This AD requires replacing the existing spring pins at each passenger entry door at both girt bar floor fittings with new spring pins. We are issuing this AD to prevent broken or migrated spring pins of the girt bar floor fittings, which could result in improper deployment of the escape slide/raft and consequent delay and injury during evacuation of passengers and crew from the cabin in the event of an emergency.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports from multiple operators that have found fatigue cracking in the corners of the forward galley service doorway. This AD requires repetitive inspections for any cracking of the skin and bear strap doublers in the corners of the forward galley service doorway, and corrective action if necessary. This AD also provides optional terminating actions for certain repetitive inspections. We are issuing this AD to detect and correct fatigue cracking, which could result in rapid loss of cabin pressure.
We are superseding Airworthiness Directive (AD) 2010-13-04 for certain Bombardier, Inc. Model DHC-8-400 series airplanes. AD 2010-13-04 required modifying the nose landing gear (NLG) trailing arm. This new AD requires installing a new pivot pin retention mechanism. This new AD also adds airplanes to the applicability. This AD was prompted by a report of several missing or damaged pivot pin retention bolts. We are issuing this AD to prevent failure of the pivot pin retention bolt, which could result in a loss of directional control or loss of a NLG tire during take-off or landing.
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 issuance of revised certification maintenance requirements for the horizontal stabilizer trim actuator (HSTA). This AD requires revising the maintenance or inspection program. We are issuing this AD to detect and correct premature wear and cracking of the HSTAs, which could result in reduced structural integrity and reduced control of the airplane due to the failure of system components.
This final rule amends certain airworthiness regulations for transport category airplanes, based on recommendations from the FAA-sponsored Aviation Rulemaking Advisory Committee (ARAC). This amendment eliminates regulatory differences between the airworthiness standards of the FAA and European Aviation Safety Agency (EASA). It does not add new requirements beyond what manufacturers currently meet for EASA certification and does not affect current industry design practices. This final rule revises the pitch maneuver design loads criteria; revises the gust and turbulence design loads criteria; revises the application of gust loads to engine mounts, high lift devices, and other control surfaces; adds a “round-the-clock” discrete gust criterion and a multi-axis discrete gust criterion for airplanes equipped with wing-mounted engines; revises the engine torque loads criteria; adds an engine failure dynamic load condition; revises the ground gust design loads criteria; revises the criteria used to establish the rough air design speed; and requires the establishment of a rough air Mach number.
These special conditions are issued for the Boeing 757-200 series airplane. This airplane, as modified by AAR Engineering Services, will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport-category airplanes. This design feature includes seats with non-traditional, large, non-metallic panels on Boeing 757-200 series airplanes. 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 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.
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 emanating from the aft-most barrel nut holes of the left and right upper rear spar caps of the horizontal stabilizer. This AD requires repetitive high frequency eddy current (ETHF) inspections for cracks in the areas around the two aft-most barrel nut holes of the upper rear spar caps, and corrective action if necessary; and repetitive ETHF inspections for cracks in the areas around the two aft-most barrel nut holes of any repaired or replaced upper rear spar cap, and corrective actions if necessary. We are issuing this AD to detect and correct such cracks, which could propagate until the upper rear spar cap severs, and result in failure of the horizontal stabilizer upper center or aft skin panel and adversely affect the structural integrity of the airplane.
The FAA is issuing a Final Supplemental Regulatory Impact Analysis (Final SRIA) of its final rule that amended its existing flight, duty and rest regulations applicable to certain certificate holders and their flightcrew members. A copy of the Final SRIA may be found in the docket for the rulemaking. The Final SRIA responds to comments that were made in response to the Initial Supplemental Regulatory Impact Analysis, and, where appropriate, incorporates new information provided by the commenters. In addition, the Final SRIA makes adjustments to the methodology used to estimate the costs and benefits of applying the final flight, duty, and rest rule to cargo-only operations, and includes additional sensitivity analyses. The results of the Final SRIA concludes that the base-case benefits of applying the flight, duty, and rest rule to cargo-only operations would be about $3 million, and the high-case benefits of doing so would be about $10 million. Conversely, the costs of applying the flight, duty, and rest rule to cargo-only operations would be about $452 million. Because the results of the analysis continue to indicate that the costs of mandating all-cargo operation compliance with the new flight, duty, and rest rule significantly outweigh the benefits, the FAA has determined that no revisions to the final rule are warranted.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by failure during testing of the anchor attachment on the occupant restraint system on the standard attendant seat due to an understrength attachment fitting. This AD requires replacing the existing restraint attachment fitting on the standard attendant seat with a new, improved attachment fitting. We are issuing this AD to prevent failure of the restraint attachment fitting of the attendant seat during an emergency landing, which could cause injury to the cabin crew and passengers and could impede a rapid evacuation.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report of a crack found in the fuselage during a fatigue test campaign. This AD requires repetitive rototest inspections for cracking; corrective actions if necessary; and modification of the torsion box, which would terminate the repetitive inspections. We are issuing this AD to prevent cracking in the side box beam flange of the fuselage, which could affect the structural integrity of the airplane.
We are superseding Airworthiness Directive (AD) 2000-12-12, for certain Airbus Model A300, A300-600, and A310 series airplanes. AD 2000-12-12 required inspecting to detect cracks in the lower spar axis of the nacelle pylon between ribs 9 and 10, and repair if necessary. AD 2000-12-12 also provided for optional modification of the pylon, which terminated the inspections for Model A300 series airplanes. This new AD reduces the initial and repetitive inspection compliance times. This AD was prompted by reports of cracking of the lower pylon spar after accomplishing the existing modification. We are issuing this AD to detect and correct fatigue cracking, which could result in reduced structural integrity of the lower spar of the nacelle pylon.
We are superseding Airworthiness Directive (AD) 2011-12-10 for Robinson Helicopter Company (Robinson) Model R22, R22 Alpha, R22 Beta, R22 Mariner, R44, and R44 II helicopters with certain main rotor blades (blade) installed. AD 2011-12-10 required inspecting each blade at the skin-to-spar line for debonding, corrosion, a separation, a gap, or a dent and replacing any damaged blade with an airworthy blade. This new AD also requires a terminating action for those inspection requirements. These actions are intended to detect debonding of the blade skin, which could result in blade failure and subsequent loss of control of the helicopter, and to correct the unsafe condition by replacing the main rotor blades with new blades that do not require the AD inspection.
This action amends multiple high altitude Area Navigation (RNAV) routes (Q-routes) in the north central and northeast United States (U.S.) to change 13 fixes identified in the Q-routes to match waypoint (WP) characterizations contained in the FAA and Canadian aeronautical database information establishing the WPs. This action also amends the route termination point and geographic latitude/longitude position in RNAV route Q-822 to reflect changes made by Canada as part of its Windsor-Toronto-Montreal (WTM) airspace redesign effort.
This rulemaking relieves burdens on pilots seeking to obtain aeronautical experience, training, and certification by increasing the allowed use of aviation training devices. These training devices have proven to be an effective, safe, and affordable means of obtaining pilot experience. These actions are necessary to bring the regulations in line with current needs and activities of the general aviation training community and pilots.
We are superseding Airworthiness Directive (AD) 2008-17-03 for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2008-17-03 required repetitive inspections to detect fuselage frame cracking, and corrective action if necessary. AD 2008-17-03 also provided for optional terminating action (repair/preventive change) for the repetitive inspections. This new AD adds airplanes to the applicability, but does not provide terminating action for the newly added airplanes. This AD was prompted by reports of cracks found at the cutout in the web of body station frame 303.9 inboard of stringer 16L, as well as a new report of cracking found on an airplane not identified in the applicability of AD 2008-17-03. We are issuing this AD to detect and correct fuselage frame cracking, which could prevent the left forward entry door from sealing correctly, and could cause in-flight decompression of the airplane.
We are revising airworthiness directive (AD) 2010-17-11R1, which applies to all Dowty Propellers R408/6-123-F/17 model propellers. AD 2010-17-11R1 required initial application of sealant between the bus bar assembly and the backplate assembly of certain line-replaceable units (LRUs) and repetitive re-applications of sealant on all R408/6-123-F/17 model propellers. AD 2010-17-11R1 also provided an optional terminating action to the repetitive re-application of sealant. This AD increases the interval allowed between the required re-application of sealant, and specifies an additional acceptable sealant. This AD was prompted by failure of the propeller de-ice bus bar due to friction or contact between the bus bar and the backplate assembly, consequent intermittent short circuit, and possible double generator failure. We are issuing this AD to prevent an in-flight double generator failure, which could result in reduced control of the airplane.
We are adopting a new airworthiness directive (AD) for all Harry E. Williams de Havilland Model DH 82A airplanes, all Cliff Robertson de Havilland Model DH 82A airplanes, and all de Havilland Model DH 83 airplanes. This AD was prompted by reports of structural failure of the attachment of the wing to the fuselage that resulted from failed lateral fuselage tie rods. This AD requires inspecting the aircraft maintenance records to determine the date of installation or the date of last replacement of the lateral fuselage tie rods. This AD also requires repetitively replacing all lateral fuselage tie rods and attaching nuts at a specified life limit interval. We are issuing this AD to correct the unsafe condition on these products.
We are superseding Airworthiness Directive (AD) 2013-20-06 for all Airbus Model A340-211, -212, -213, -311, -312, -313, -541, and -642 airplanes. AD 2013-20-06 required revising the maintenance program to incorporate certain maintenance requirements and airworthiness limitations. This new AD requires revising the maintenance or inspection program to incorporate certain other maintenance requirements and airworthiness limitations. This AD was prompted by a determination that existing maintenance requirements are not adequate to address the aging effects of aircraft systems. We are issuing this AD to address the aging effects of aircraft systems. Such aging effects could change the characteristics of systems' life-limited components leading to an increased potential for failure, which, in isolation or in combination with one or more other specific failures or events, could result in failure of certain life limited parts, which could reduce the structural integrity or the controllability of the airplane.
We are superseding airworthiness directive (AD) 98-07-07 for all Rolls-Royce plc (RR) RB211-535E4 and RB211-535E4-B turbofan engines. AD 98-07-07 required removing certain part number (P/N) low-pressure (LP) fuel filter-to-high-pressure (HP) fuel pump tube assemblies and installing flexible LP fuel filter-to-HP fuel pump tube assemblies. This AD expands the applicability of AD 98-07-07 to include the RB211-535E4-C-37 turbofan engine and requires removal from service of additional P/N LP fuel filter-to-high-pressure HP fuel pump tube assemblies. This AD was prompted by reports of fuel leaks that have resulted in a number of engine in-flight shutdowns. We are issuing this AD to prevent loss of fuel supply to the engine, which could lead to an in-flight shutdown of one or more engines, loss of thrust control, and damage to the airplane.
This action amends Class D Airspace at MacDill AFB, FL, by adding the words “to but not including 1,200 feet MSL,” further clarifying the ceiling in the descriptor of the Class D airspace. This action does not change the boundaries or operating requirements of the airspace.
This action establishes Class D airspace and Class E airspace designated as an extension, at Hammond, LA. The establishment of an air traffic control tower has made this action necessary for the safety and management of Instrument Flight Rules (IFR) operations within the airspace at Hammond Northshore Regional Airport. This action also amends the airport name and adjusts the geographic coordinates for the current Class E airspace area.
This action amends Class E Airspace at Apalachicola, FL, as Apalachicola Municipal Airport has been renamed Apalachicola Regional Airport. This action also updates the geographic coordinates of the airport.
This action amends Class E Airspace at Roanoke Rapids, NC, as Halifax County Airport has been abandoned, no longer requiring controlled airspace.
We are superseding Airworthiness Directive (AD) 2014-07-51 for AgustaWestland S.p.A. Model AB139 and AW139 helicopters with certain main rotor (M/R) rotating scissors installed. AD 2014-07-51 required repetitively inspecting theM/R rotating scissors for play of the lower half scissor spherical bearing (bearing) and removing the bearing if there was play beyond allowable limits. AD 2014-07-51 also required removing all affected bearings. AD 2014-07-51 was prompted by reports of certain bearings dislodging from certain M/R rotating scissors. This new AD retains the requirements of AD 2014-07-51, expands the applicability, and requires installing a special nut. These actions are intended to detect excessive play of the bearing and prevent failure of the M/R rotating scissors and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-8-55, DC-8F-54, and DC-8F-55 airplanes, Model DC-8-60 series airplanes, Model DC-8-60F series airplanes, Model DC-8-70 series airplanes, and Model DC-8-70F series airplanes. This AD was prompted by multiple reports of cracking of the upper aft skin panel of the fuselage. An evaluation by the design approval holder (DAH) indicates that the upper aft skin panel of the fuselage is subject to widespread fatigue damage (WFD). This AD requires removing any previously installed local repairs; installing a full-length improvement modification with or without finger doublers, or a full-length repair with or without finger doublers, as applicable; and doing repetitive inspections for cracking of the doublers, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the upper aft skin panel of the fuselage, which could result in loss of structural integrity and consequent rapid decompression of the airplane.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of swing arm assemblies of engine fuel feed ejector pumps detaching from the outlet port of the engine fuel feed ejector pump and partially blocking the engine fuel feed line. This AD requires installing a restrictor into the engine fuel feed line. We are issuing this AD to prevent blocked engine fuel flow and possible engine flameout.
We are superseding Airworthiness Directive (AD) 2005-13-05, which applied to certain Boeing Model 747-400F series airplanes. AD 2005-13-05 required inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, and repair of any cracking. AD 2005-13-05 also required a preventive modification of the upper deck floor beams, and repetitive inspections for cracking after accomplishing the modification. This new AD retains these actions and requires a second modification, repetitive inspections for cracking, and repair if necessary. This AD was prompted by a determination that the upper chords of the upper deck floor beams at certain stations are structures that are susceptible to widespread fatigue damage, and that certain airplanes with an initial modification require a second modification for the airplane to meet its limit of validity (LOV). We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam, which could result in reduced structural integrity of the airplane and rapid decompression or reduced controllability of the airplane.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report indicating that, on a different Boeing airplane model, there was an oxygen-fed fire, which caused extensive damage to the flight deck. This AD requires replacing the low-pressure oxygen hoses with non-conductive hoses in the crew oxygen system. We are issuing this AD to prevent inadvertent electrical current from passing through an internal, anti-collapse spring of the low pressure oxygen hose, which can cause the low-pressure oxygen hose to melt or burn, leading to an oxygen-fed fire and/or smoke beneath the flight deck in the forward electronics equipment bay.
We are superseding Airworthiness Directive (AD) 2004-16-01 for certain Airbus Model A330-200 and -300 series airplanes and Model A340-200 and -300 series airplanes. AD 2004-16-01 required repetitive inspections for cracking of the chromed area of the left and right piston rods for the main landing gear (MLG) retraction actuators, and related investigative and corrective actions if necessary. This new AD requires repetitive draining of any fluid from the retraction actuator piston rod internal volume and sealing of the vent hole; repetitive ultrasonic inspections of the upper end of the piston rods, and corrective actions if necessary; a one-time ultrasonic inspection (longitudinal and circumferential) of the full length of the piston rod, and corrective actions if necessary; and a terminating modification of the left-hand and right-hand MLG retraction actuators. This AD was prompted by reports of the piston rods for the MLG retraction actuators rupturing during flight. We are issuing this AD to prevent cracking of the piston rods for the MLG retraction actuators, which could result in rupture of a piston rod, non-damped extension of the MLG, high loads on the fully extended MLG, and consequent reduced structural integrity of the MLG.
We are superseding Airworthiness Directive (AD) 2012-06-19 for certain Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-200 and -300 series airplanes. AD 2012-06-19 required repetitive inspections of the main fitting and sliding tube of the nose landing gear (NLG) for defects, damage, and cracks; and corrective actions if necessary. This new AD requires an inspection of the part number and serial number of the NLG main fitting and NLG sliding tube; for affected parts, this new AD requires a magnetic particle inspection (MPI) for cracks, and flap peening and replacement if necessary. This new AD also requires, for certain parts, additional inspections for damage and cracking. This new AD also adds airplanes to the applicability. This AD was prompted by reports of a cracked main fitting and sliding tube during NLG overhaul. We are issuing this AD to detect and correct cracks, defects, or damage of the main fitting or sliding tube, which could result in consequent NLG collapse.
We are superseding Airworthiness Directive (AD) 2000-17-03 for all Fokker Services B.V. Model F.28 Mark 0100 airplanes. AD 2000-17- 03 required inspections of the nose landing gear (NLG) main fitting to detect cracking of the NLG main fitting subassembly, and corrective actions if necessary. This new AD retains the requirements of AD 2000-17-03, requires installing a new part number NLG unit that terminates the repetitive inspections, and adds airplanes to the applicability. This AD was prompted by a report of an NLG main fitting failure. We are issuing this AD to prevent cracking of the NLG main fitting, which could lead to collapse of the NLG during takeoff and landing, and possible injury to the flight crew and passengers.
We are superseding airworthiness directive (AD) 2013-15-09 for all Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engine models with certain second-stage high-pressure turbine (HPT) air seals installed. AD 2013-15-09 required initial and repetitive inspections for cracks in second-stage HPT air seals. This new AD expands the applicability of AD 2013-15-09 to include additional part numbers (P/Ns), requires removal of the mating hardware if the second-stage HPT air seal is found with a through-crack, and adds a mandatory terminating action. This AD was prompted by reports of cracking in the original location on two additional P/Ns and reports of through-cracks in a new location in the second-stage HPT air seal. We are issuing this AD to prevent failure of the second-stage HPT air seal, which could lead to uncontained engine failure and damage to the airplane.
This action amends Class E airspace at Lakeport, CA. Controlled airspace is necessary to accommodate Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures at Lampson Field. The FAA is taking this action to enhance the safety and management of instrument flight rules (IFR) operations at the airport.
We are adopting a new airworthiness directive (AD) for all Airbus Model A318 series airplanes, Model A319 series airplanes, Model A320-211, -212, -214, -231, -232, and -233 airplanes, and Model A321 series airplanes. This AD was prompted by a report of a circumferential crack at the gland retaining-ring groove of certain retraction actuators on the main landing gear (MLG). This AD requires an inspection to identify the part numbers of MLG retraction actuators and replacement of certain MLG retraction actuators. We are issuing this AD to prevent MLG retraction actuator failure that could prevent the full extension and/or down-locking of the MLG, possibly resulting in MLG collapse during landing or rollout, and consequent damage to the airplane and injury to the occupants.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200LR, -300, -300ER, and 777F series airplanes. This AD was prompted by reports of dual pitch rate sensor (PRS) failures causing the primary flight computers to transition from primary mode to secondary mode, resulting in autopilot disconnects. This AD requires an inspection to determine the PRS part number, and replacement if necessary. We are issuing this AD to prevent a dual PRS failure that could cause an automatic disengagement of the autopilot and autoland, which may prevent continued safe flight and landing if disengagement occurs at low altitude and the flight crew is unable to safely assume control and execute a go-around or manual landing.
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 indicating that inboard and outboard hydraulic lines of the brakes were found connected to the incorrect ports on the swivel assembly of the main landing gear (MLG). This AD requires modifying the MLG by installing a new bracket on the left and right lower aft-wing planks. We are issuing this AD to prevent incorrect installation of the brake hydraulic lines, which could cause the brakes and the anti-skid system to operate incorrectly, and consequent catastrophic failure of the airplane during a high-speed rejected takeoff.
We are adopting a new airworthiness directive (AD) for certain Agusta Model A109E, A109K2, A119, and AW119 MKII helicopters. This AD requires repetitively performing a magnetic particle inspection of the Gleason crown for a crack. This AD was prompted by a report of a crack that was found on a Gleason crown, which if not detected, could cause damage to or loss of the main rotor drive and subsequent loss of control of the helicopter.
These special conditions are issued for Dassault Model Falcon 900EX airplanes. These airplanes will have a novel or unusual design feature associated with electronic system-security protection from unauthorized external access. 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 Airworthiness Directive (AD) 2012-14-11 for Arrow Falcon Exporters, Inc. (AFE), Rotorcraft Development Corporation (RDC), and San Joaquin Helicopters (SJH) Model OH-58A, OH-58A+, and OH-58C helicopters. AD 2012-14-11 required inspecting the main rotor mast (mast) for a crack. This new AD expands the mast inspection area, changes the inspection to a repetitive inspection, and removes the reporting requirement. The actions in this AD are intended to prevent failure of the mast and subsequent loss of control of the helicopter.
This action incorporates certain amendments into FAA Order 7400.9Y, dated August 6, 2014, and effective September 15, 2014, for incorporation by reference in 14 CFR § 71.1.
We are superseding Airworthiness Directive (AD) 76-06-09 for certain Piper Aircraft, Inc. Model PA-31P airplanes. AD 76-06-09 required repetitive inspection of certain exhaust system parts with replacement of parts mating with the turbocharger, as necessary, and allowed installation of a certain tailpipe v-band coupling as terminating action. This new AD requires the use of new service information and expands the scope of the inspections of the turbocharger exhaust system. This AD was prompted by reports of exhaust system failures, new service information, and the tailpipe v-band coupling used for terminating action is obsolete. We are issuing this AD to correct the unsafe condition on these products.
We are superseding Airworthiness Directive (AD) 2012-26-16 for all PILATUS AIRCRAFT LTD. Models PC-12, PC-12/45, PC-12/47, and PC-12/47E airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a need to incorporate new revisions into the Limitations section, Chapter 4, of the FAA-approved maintenance program (e.g., maintenance manual). We are issuing this AD to require actions to address the unsafe condition on these products.
This document notifies the public of the Federal Aviation Administration's policy regarding enforcement of the pilot pairing requirement in the “Part 121 Pilot Age Limit” final rule. Currently, while the International Civil Aviation Organization (ICAO) standards allow a person between the age of 60 and 65 to serve as pilot in command (PIC) of an airplane with two or more pilots, in international commercial air transport operations, the PIC must be paired with a pilot younger than 60 years of age. Parts 61 and 121 of title 14, of the Code of Federal Regulations contain similar limitations. However, a recent amendment to the ICAO standards would remove this pilot pairing requirement. Instead, all pilots serving on airplanes in international commercial air transport operations with more than one pilot may serve beyond 60 years of age (until age 65) without being paired with a pilot under 60 years of age. This ICAO amendment triggers the sunset of the statutory authority that provides the basis for the crew pairing limitations in title 14.
NASA is revising the NASA Grant & Cooperative Agreement Handbook to clarify that NASA does not pay profit or fee on Federal Financial Assistance awards, i.e. grants and cooperative agreements, to non-profit organizations. This rule makes changes to NASA regulations to reflect that revision.
We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that more restrictive airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program as applicable. We are issuing this AD to prevent a safety-significant latent failure (which is not annunciated) which, in combination with one or more other specific failures or events, would result in a hazardous or catastrophic failure condition.
We are superseding Airworthiness Directive (AD) 2005-07-12, which applies to certain the Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2005-07-12 required detailed and eddy current inspections to detect cracking of the frame web around the cutout for the doorstop intercostal strap at the aft side of the station (STA) 291.5 frame at stringer 16R, and corrective action if necessary. Since we issued AD 2005-07-12, we received reports of new findings of cracking at various locations of the STA 277 to STA 291.5 frames and intercostals, including webs, chords, clips, and shear ties, between stringers 7R and 17R. This new AD requires inspections for cracking at the forward galley door cutout, and corrective actions if necessary. This new AD also reduces a certain inspection threshold required by AD 2005-07-12. We are issuing this AD to detect and correct fatigue cracking of the aft frame and frame support structure of the forward galley door, which could result in a severed fuselage frame web, rapid decompression of the airplane, and possible loss of the forward galley door.
We are adopting a new airworthiness directive (AD) for all the Boeing Company Model 767 airplanes. This AD was prompted by a report of a rotary actuator for the trailing edge (TE) flap that had slipped relative to its mating reaction ring, which is attached to the flap support rib. This AD requires repetitive inspections for corrosion of the fixed ring gear and reaction ring splines of the rotary actuator assembly for each support position, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct flap rotary actuator gear disengagement from its mating reaction ring. This disengagement with flaps extended could cause an uncommanded roll due to flap blowback, overload, or flap departure from the airplane, which could compromise safe flight and landing of the airplane.
We are superseding Airworthiness Directive (AD) 2012-13-08 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. AD 2012-13-08 required inspections of tension ties and surrounding structure for cracking, and related investigative and corrective actions if necessary; modification of tension tie structure or tension tie and frame structure at specified stations; and post-modification inspections of some modified and unmodified areas, and repair if necessary. This new AD adds inspections in unmodified center section tension ties, and repair if necessary; post-modification inspections of modified and unmodified areas, and repair if necessary; a new modification of tension tie and frame structures; and inspections of tension ties and surrounding structure, and related investigative and corrective actions if necessary. This new AD reduces an inspection interval. This AD was prompted by widespread fatigue damage analysis that resulted in a determination that more inspections are necessary. We are issuing this AD to prevent tension ties from becoming severed or disconnected from the frames, which could lead to reduced structural integrity and sudden decompression of the airplane in flight.
The FAA is correcting a final rule published in the Federal Register on January 15, 2002 (67 FR 2110). In that rule, the FAA amended its regulations to require that all persons who remove any life-limited aircraft part safely control that part, to deter the installation of that part after it has reached its life limit. The rule reduced the risk of life-limited parts being used beyond their life limits. The rule also required that type certificate and design approval holders of life-limited parts provide instructions on how to mark a part indicating its current status, when requested by persons removing such a part. This document corrects error in the codified text of that document.
The Federal Aviation Administration (FAA) is correcting a final rule published in the Federal Register on August 12, 2014, (79 FR 46974). In that rule, the FAA removed a word to address what the agency perceived to be a previous oversight. After publication, and based on information in a petition for rulemaking, the FAA realized that the word should remain. Since the final rule's changes do not become effective until November 10, 2014, this correction will ensure that the word remains in the regulation.
We are superseding Airworthiness Directive (AD) 2013-16-08 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. AD 2013-16-08 required inspection of the main landing gear (MLG) retraction actuator components; corrective actions if necessary; and, for certain retraction actuators, installation of a new jam nut. This new AD continues to require those actions. This AD was prompted by a determination that a certain part was incorrectly identified in a certain section of AD 2013-16-08. We are issuing this AD to prevent disconnection of the MLG retraction actuator, which could result in extension of the MLG without damping, and consequent structural damage and collapse of the MLG during landing.
We are superseding Airworthiness Directive (AD) 2013-10-06, for all Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, A340-300, A340-500, and A340-600 series airplanes. AD 2013-10-06 required an inspection to identify the installed windshields, and replacement of any affected windshield. This new AD requires expanding the inspection area to 15 additional windshields' serial numbers. This AD was prompted by several reports of a burning smell and/or smoke in the cockpit during cruise phase, leading in some cases, to diversion to alternate airports. We are issuing this AD to prevent significantly increased workload for the flightcrew, which could, under some flight phases and/or circumstances, constitute an unsafe condition.
This document corrects errors that appeared in final special conditions docket no. FAA-2013-0894, which was published in the Federal Register on December 20, 2013 (78 FR 76980). The errors are in the document's special conditions stage (notice vs. final) and special conditions number.
We are superseding Airworthiness Directive (AD) 2005-23-08 for certain Airbus Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R airplanes; and Model A300 C4-605R Variant F airplanes. AD 2005-23-08 required repetitive inspections to detect cracks of certain attachment holes, installation of new fasteners, follow-on inspections or repair if necessary, and modification of the angle fittings of fuselage frame FR47. This new AD adds new repetitive ultrasonic inspections for cracks of the center wing box lower panel; and repair if necessary. This new AD also removes certain airplanes from the applicability. This AD was prompted by reports of cracks found on the horizontal flange of the Frame 47 internal corner angle fitting while accomplishing the modification required by AD 2005-23-08. We are issuing this AD to detect and correct fatigue cracking of the forward fitting of fuselage frame FR47, which could result in reduced structural integrity of the frame.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-9-10, DC-9-20, and DC-9-30 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the improved (shot-peened) aft fuselage non-ventral pressure bulkhead tee is subject to widespread fatigue damage (WFD). This AD requires repetitive inspections for cracking of the improved (shot-peened) non-ventral aft pressure bulkhead tees, and replacement if necessary. We are issuing this AD to detect and correct fatigue cracking of the improved (shot-peened) non-ventral aft pressure bulkhead tees connecting the bulkhead web to the fuselage, which could result in reduced structural integrity and rapid decompression of the airplane.
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. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the bulkhead dome tees, which connect the bulkhead web to the fuselage, are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the improved ventral aft pressure bulkhead tees, and replacement if necessary. We are issuing this AD to detect and correct fatigue cracking of the bulkhead dome tees, which could result in reduced structural integrity and rapid decompression of the airplane.
This action establishes Class E airspace and modifies Class D and E airspace at Charles M. Schulz-Sonoma County Airport, Santa Rosa, CA. This action, initiated by the FAAs biennial review of the airspace area, enhances the safety and management of instrument flight rules (IFR) operations at the airport. Class D and E airspace is amended to reflect the airport's name change. Also, a minor adjustment is made to the geographic coordinates of the airport.
These special conditions are issued for Airbus Model A350-900 series airplanes. These airplanes will have novel or unusual design features, associated with flight-envelope protection in icing and non-icing conditions, that use low-speed incidence protection and an alpha-floor function that automatically advances throttles whenever the airplane angle of attack reaches a predetermined value. 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.
The Federal Aviation Administration is amending the airworthiness standards applicable to certain transport category airplanes certified for flight in icing conditions and the icing airworthiness standards applicable to certain aircraft engines. The regulations will improve safety by addressing supercooled large drop icing conditions for transport category airplanes most affected by these icing conditions; mixed phase and ice crystal conditions for all transport category airplanes; and supercooled large drop, mixed phase, and ice crystal icing conditions for all turbojet, turbofan, and turboprop engines.
This action confirms the effective date of the direct final rule published on July 28, 2014, and responds to the comments received on that direct final rule. The rule permits the pilot in command of a helicopter air ambulance to assess the weather at a departure point where current weather observations are not available and allows the pilot to depart if the observed ceiling and visibility is greater than certain weather minimums. This action will allow a pilot to utilize the minimum takeoff visibilities depicted in a published obstacle departure procedure, or in the absence of such a procedure, when the pilot observed ceiling and visibility is greater than the minimum ceiling and visibility limitations required by specific helicopter air ambulance rules. This change to the current regulation will permit helicopter air ambulance flights to enter the National Airspace System (NAS) under Instrument Flight Rules (IFR) when visibilities and ceilings are below Visual Flight Rules (VFR), thus increasing the safety of the flight.
These final special conditions are issued for the SNECMA, Silvercrest-2 SC-2D engine model. This engine will have a novel or unusual design feature—an additional takeoff rating that increases the exhaust gas temperature (EGT) limit to maintain takeoff thrust in certain high ambient temperature conditions with one engine inoperative (OEI) for a maximum of 10 minutes. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These final 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 all Rolls-Royce plc (RR) Trent 1000-A, 1000-C, 1000-D, 1000-E, 1000-G, and 1000-H turbofan engines. This AD requires removing engine electronic controller (EEC) software earlier than standard MB6.15 and replacing with a software standard eligible for installation. This AD was prompted by a finding that an intermediate pressure (IP) shaft failure may not be detected by EEC software earlier than standard MB6.15. We are issuing this AD to detect IP shaft failure and prevent IP compressor turbine burst, uncontained engine failure, and damage to the airplane.
We are removing Airworthiness Directive (AD) 2012-26-15, which applied to certain Honeywell International Inc. air data pressure transducers as installed on various aircraft. AD 2012-26-15 required doing various tests or checks of equipment having certain air data pressure transducers, removing equipment if necessary, and reporting the results of the tests or checks. As an option to the tests or checks, AD 2012-26-15 allowed removal of affected equipment having certain air data pressure transducers. We issued AD 2012-26-15 to detect and correct inaccuracies of the pressure sensors, which could result in altitude, computed airspeed, true airspeed, and Mach computation errors. AD 2012-26-15 reported that these errors could reduce the ability of the flightcrew to maintain the safe flight of the aircraft and could result in consequent loss of control of the aircraft. Since we issued AD 2012-26-15, we have received new data indicating that the safety risk is lower than originally estimated.
We are superseding Airworthiness Directive (AD) 2005-14-07 for certain The Boeing Company Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F series airplanes. AD 2005-14-07 required repetitive inspections of the carriage attach fittings on the inboard and outboard foreflaps of each wing for cracking and other discrepancies, and corrective actions if necessary. This new AD requires reducing certain repetitive inspection intervals for the inboard and outboard carriage attach fittings for the outboard foreflaps, requires previously optional terminating actions which install improved outboard foreflap carriage attach fittings, and adds new initial and repetitive inspections of those fittings and corrective actions if necessary. This AD was prompted by a report of broken inboard and outboard carriage attach fittings of the outboard foreflaps found during an inspection. We are issuing this AD to detect and correct fatigue cracking of the attach fittings of the foreflap carriage of the wings, which could result in partial or complete loss of the foreflap and consequent loss of controllability of the airplane.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-10-10, DC-10-10F, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, MD-10-10F, and MD-10-30F airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the forward cargo compartment frames are subject to widespread fatigue damage (WFD). This AD requires an inspection of the attachment holes at the forward cargo compartment frames and the cargo liner for cracking, and repair if necessary. This AD would also require installing new oversized fasteners in the forward cargo compartment frames. We are issuing this AD to prevent fatigue cracking of the forward cargo compartment frames, which could result in loss of the fail-safe structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This AD was prompted by reports of cracks emanating from the aft-most barrel nut holes of the left and right upper rear spar caps of the horizontal stabilizer. This AD requires repetitive high frequency eddy current (ETHF) inspections for cracks in the areas around the two aft-most barrel nut holes of the upper rear spar caps, and corrective actions if necessary; and repetitive ETHF inspections for cracks in the areas around the two aft-most barrel nut holes of any repaired or replaced upper rear spar cap, and corrective actions if necessary. We are issuing this AD to detect and correct cracks in the horizontal stabilizer, which could propagate until an upper rear spar cap severs, and result in failure of the horizontal stabilizer upper center or aft skin panel and adversely affect the structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires inspecting the inboard flap fasteners of the hinge-box forward fitting at Wing Station (WS) 76.50 and WS 127.25 to determine the orientation and condition of the fasteners, as applicable, and replacement or repetitive inspections of the fasteners if necessary. This AD also provides for optional terminating action for the requirements of the AD. This AD was prompted by reports of fractured fastener heads on the inboard flap hinge-box forward fitting at WS 76.50 due to incorrect installation. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners, which could result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting. Failure of the fasteners could lead to the detachment of the flap hinge box and the flap surface, and consequent loss of control of the airplane.
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-600-2D24 (Regional Jet Series 900) airplanes, and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a report that certain parts of the aft baggage door did not conform to the design specifications and were of degraded strength. This AD requires repetitive inspections for cracking and deformations of certain stop fittings and striker plates of the aft baggage bay door; and replacement, which would terminate the repetitive inspections. We are issuing this AD to prevent cracking and deformations of certain stop fittings and striker plates, which could result in the opening of the aft baggage bay door and rapid decompression or reduced controllability of the airplane.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-700-1A11 airplanes. This AD was prompted by a report that certain lanyards for the passenger oxygen masks are longer than the specified length, possibly leading to inactive oxygen masks in an emergency. This AD requires replacement of certain oxygen mask lanyards. We are issuing this AD to detect and correct lanyards of incorrect length, which might not activate the flow of oxygen in an emergency, resulting in injury to passengers.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. This AD was prompted by a report of contact between certain electrical harnesses and the hatrack rod that could cause chafing between the harnesses and surrounding structure. This AD requires modifying the routing of certain electrical harnesses. We are issuing this AD to prevent chafing and possible short circuit of two oxygen chemical generator containers in different wiring routes, which could result in malfunction of the electrical opening of all the containers connected to these routes. Such conditions, during a sudden depressurization event, could result in lack of oxygen and consequent injuries to airplane occupants.
We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332L2 helicopters with a certain yaw control damper support (support) installed. This AD requires repetitively inspecting the support attachment points for a crack. This AD is prompted by a report that the front attachment points of several supports were found to have cracks. These actions are intended to detect a crack in a support, which could result in failure of the support, separation of the yaw damper unit, blocking of the yaw flight control channel, and reduced control of the helicopter.
We are adopting a new airworthiness directive (AD) for Fiberglas-Technik Rudolf Lindner GmbH & Co. KG (type certificates formerly held by GROB-WERKE GMBH & CO KG and BURKHART GROB LUFT- UND RAUMFAHRT GmbH & CO KG) Models G102 STANDARD ASTIR III, G102 CLUB ASTIR III, G102 CLUB ASTIR IIIb, G103 TWIN II, G103A TWIN II ACRO, G103C TWIN III ACRO, and G 103 C Twin III SL gliders. This AD revises AD 2014-15-02, which required inspection of the rudder control unit for installation of plastic cable pulleys and replacement of plastic cable pulleys with aluminum cable pulleys. This AD retains the actions of AD 2014-15-02 but clarifies the suffixes of serial numbers (S/Ns) in paragraph (c) Applicability. This AD was prompted by reports of plastic control cable pulleys developing cracks due to aging, which could lead to breaking of the pulley and potentially jamming the rudder control unit, possibly resulting in loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
This document corrects two errors that appeared in Docket No. FAA-2014-0698, Special Conditions No. 25-567-SC, which was published in the Federal Register on September 12, 2014 (79 FR 54574). There is an error in the header information and in one instance of one of the airplane model numbers in the publication.
These special conditions are issued for the Bombardier Aerospace, Models BD-500-1A10 and BD-500-1A11 series airplanes. 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 are composite materials used in the construction of the fuel tank skin and structure, which may behave differently in a post-crash fire than traditional aluminum construction. 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 document corrects two errors that appeared in Docket No. FAA-2014-0666, Special Conditions No. 25-566-SC, which was published in the Federal Register on September 12, 2014 (79 FR 54572). There is an error in the header information and in one instance of one of the airplane model numbers in the publication.
These special conditions are issued for the Boeing Model 767-2C airplane. This airplane 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 the addition of four body fuel tanks and a modified fuel management system that, directly or as a result of failure or malfunction, could affect the airplane's structural performance. 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 Pacific Aerospace Limited Model FU24-954 and FU24A-954 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracking of the control column at the wiring access hole, which could lead to loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
We are superseding airworthiness directives (ADs) 90-26-01, 91-20-02, and 2009-05-02 for all General Electric Company (GE) CF6-80C2 and CF6-80E1 series turbofan engines. This AD retains the requirements of those ADs and requires removal of additional fuel manifold part numbers (P/Ns), additional repetitive inspections, replacement as required of certain fuel manifold P/Ns and tube (block) clamps, and replacement of loop clamps. This AD was prompted by a report of an under-cowl fire caused by a manifold high-pressure fuel leak, and several additional reports of fuel leaks. We are issuing this AD to prevent failure of the fuel manifold, which could lead to uncontrolled engine fire, engine damage, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for certain Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation) Model 400, 400A, 400T, and MU-300 airplanes. This AD was prompted by a report of a failure of the Acme nut threads in a pitch trim actuator (PTA). This AD requires an inspection to determine if PTAs having a certain serial number and part number are installed, and replacement if they are installed. This AD also requires repetitive replacements of PTAs with new PTAs or certain overhauled PTAs. We are issuing this AD to prevent failure of the Acme nut threads in the PTA, which could lead to loss of control of pitch trim and reduced controllability of the airplane.
On September 22, 2014, the National Aeronautics and Space Administration (NASA) published a direct final rule which rearranged existing drug-free workplace requirements for financial assistance in the Code of Federal Regulations (CFR). The action was consistent with the Office of Management and Budget's (OMB) guidance on drug-free workplace requirements for financial assistance. This rule makes amendments for editorial purposes.
This action establishes Class E airspace at Thomas, OK. Controlled airspace is necessary to accommodate new Area Navigation (RNAV) Standard Instrument Approach Procedures at Thomas Muni Airport. The FAA is taking this action to enhance the safety and management of Instrument Flight Rules (IFR) operations at the airport.
This action removes restricted areas R-4105A and R-4105B, No Man's Land Island, MA. The Air National Guard and U.S. Air Force informed the FAA that they no longer have a requirement for these areas. Management of the land has been transferred to the U.S. Fish and Wildlife Service.
This final rule is the second mandatory inflation-based adjustment to the maximum civil penalty authorized for violations of the Commercial Space Launch Act of 1984, as amended. This adjustment is done to bring the authorized penalty for violations into compliance with the requirements of the Federal Civil Penalties Inflation Adjustment Act of 1990, as amended by the Debt Collection Improvement Act of 1996.
On August 12, 2014, the FAA published an immediate final rule (79 FR 46964) entitled “Orders of Compliance, Cease and Desist Orders, Orders of Denial, and Other Orders.” This action confirms the effective date of the immediate final rule and responds to the comments received on that immediate final rule.
This notice of enforcement policy announces how the Department of Transportation (DOT or Department) will enforce compliance with the requirements of the Department of Transportation and Related Agencies Appropriations Act, 2000, which prohibits the Department from subsidizing Essential Air Service (EAS) to communities located within the 48 contiguous States receiving per passenger subsidy amounts exceeding $200, unless the communities are located more than 210 miles from the nearest large or medium hub airport. All communities receiving subsidized EAS have until September 30, 2015, based on data from October 1, 2014 through September 30, 2015, to ensure compliance with the $200 subsidy cap or face termination of subsidy eligibility. After September 30, 2015, the Department will enforce the $200 subsidy cap on an annual basis based on data compiled at the end of every fiscal year. Consistent with established procedures, DOT will issue a show-cause order to each EAS community that has been identified as failing to meet the $200 per passenger subsidy requirement. Each such community will have a fair and reasonable opportunity to demonstrate compliance with the $200 subsidy cap prior to a final decision by DOT. In addition, any community that is deemed ineligible under the $200 subsidy cap provision may petition the Secretary for a waiver. After receiving a community's petition for a waiver, the Secretary may waive the subsidy cap for a limited period of time, on a case-by-case basis, and subject to the availability of funds. To provide the Department with sufficient time to evaluate the FY 2015 data for potentially affected communities, DOT does not intend to issue any show-cause orders concerning compliance with the $200 subsidy cap until 2016.
These special conditions are issued for the Hawker Beechcraft Model No. 400A airplane as modified by Nextant Aerospace. This modification will have a novel or unusual design feature associated with an installed emergency power supply and standby attitude module that use rechargeable lithium batteries and battery systems. 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 Airworthiness Directive (AD) 2011-07-05 for certain Sicma Aero Seat 9140, 9166, 9173, 9174, 9184, 9188, 9196, 91B7, 91B8, 91C0, 91C2, 91C4, 91C5, and 9301 series passenger seat assemblies; and Sicma Aero Seat 9501311-05, 9501301-06, 9501311-15, 9501301-16, 9501441-30, 9501441-33, 9501311-55, 9501301-56, 9501441-83, 9501441-95, 9501311-97, and 9501301-98 passenger seat assemblies. AD 2011-07-05 required a general visual inspection for cracking of backrest links, replacement with new links if cracking is found, and eventual replacement of all links with new links. This new AD requires a new general visual inspection for cracking of backrest links, which includes new seat backrest links; replacement with new links if cracking is found; and eventual replacement of all links with new links. This AD was prompted by a report that new seat backrest links could be affected by cracks similar to those identified on the backrest links with the previous design. We are issuing this AD to detect and correct cracks in the backrest links, which could affect the structural integrity of seat backrests. Failure of the backrest links could result in injury to an occupant during emergency landing conditions.
We are adopting a new airworthiness directive (AD) for Empresa Brasileira de Aeronautica S. A. (EMBRAER) Models EMB-110P1 and EMB-110P2 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 corrosion and cracking on the rudder trim tab actuator terminal. We are issuing this AD to require actions to address the unsafe condition on these products.
We are superseding Airworthiness Directive (AD) 75-20-06 for certain Alexandria Aircraft LLC (type certificate previously held by Bellanca Aircraft Corp., Viking Aviation, Inc., and Bellanca, Inc.) Models 14-19-3A, 17-30, 17-30A, 17-31, 17-31A, 17-31ATC, and 17-31TC airplanes. AD 75-20-06 required repetitively inspecting the aft fuselage structure near the top of the vertical side tubing, which connects the horizontal stabilizer carry-through to the upper fuselage longeron, for cracks and installing the manufacturer's service repair kit as a terminating action for the repetitive inspections to repair any cracks found. Since we issued AD 75-20-06, we have determined that installing the service kit has not prevented cracks from occurring. We have also determined that all affected airplane serial numbers should be included in the Applicability section. This AD requires continued repetitive inspections of the aft fuselage structure near the top of the vertical side tubing for cracks and making all necessary replacements of cracked parts. This AD also adds additional serial number airplanes to the Applicability section. We are issuing this AD to correct the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model 750XL airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure of the fin forward pickup due to possible fatigue cracks. We are issuing this AD to require actions to address the unsafe condition on these products.
We are superseding Airworthiness Directive (AD) 2014-04-03 for all Pacific Aerospace Limited Model 750XL 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 broken control column attachment bolts failing in service. We are issuing this AD to require actions to address the unsafe condition on these products.
We are superseding Airworthiness Directive (AD) 2013-11-14 for certain The Boeing Company Model 777-200 and -300 series airplanes. AD 2013-11-14 required repetitive general visual inspections of the strut forward dry bay for the presence of hydraulic fluid, and related investigative and corrective actions (including checking drain lines for blockage due to hydraulic fluid coking, and cleaning or replacing drain lines to allow drainage) if necessary. This AD adds airplanes to the applicability. This AD was prompted by reports of hydraulic fluid contamination (including contamination caused by hydraulic fluid in its liquid, vapor, and/or solid (coked) form) found in the strut forward dry bay. We are issuing this AD to detect and correct hydraulic fluid contamination of the strut forward dry bay, which could result in hydrogen embrittlement of the titanium forward engine mount bulkhead fittings, and consequent inability of the fittings to carry engine loads, resulting in engine separation. Hydrogen embrittlement also could cause a through-crack formation across the fittings through which an engine fire could breach into the strut, resulting in an uncontained strut fire.
We are superseding airworthiness directive (AD) 2012-02-13 for certain Airbus Helicopters, Inc. (Airbus Helicopters) Model EC130B4 helicopters. AD 2012-02-13 required inspecting certain areas of the tailboom/Fenestron junction frame (junction frame) for a crack. This AD retains the requirements of AD 2012-02-13, expands the inspection area of the junction frame, and reduces the repetitive inspection interval. These actions are intended to detect a crack in the junction frame, which could result in detachment of the Fenestron and subsequent loss of control of the helicopter.
We are adopting a new airworthiness directive (AD) for Brantly International, Inc. (Brantly) Model B-2, Model B-2A, and Model B-2B helicopters with certain main rotor blades. This AD requires inspecting each main rotor (M/R) blade for a crack or delamination and removing the blade if a crack exists or if the delamination exceeds certain thresholds. This AD was prompted by multiple reports of M/R blade cracks and an incident in which a crack that originated near the M/R blade trailing edge resulted in the loss of a large section of the M/R blade. The actions of this AD are intended to prevent loss of the M/R blade and subsequent loss of control of the helicopter.
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 requires repetitive inspections for any fuel leak in the right-hand landing lights compartment, and related investigative and corrective actions if necessary. This AD also provides for an optional replacement of the connector of the fuel boost pump canister of the auxiliary power unit (APU), which terminates the repetitive inspections. This AD was prompted by a report of fuel leaks in the connector cavity of the APU fuel boost pump canister and at the electrical conduit connection of the APU fuel boost pump in the right-hand landing lights compartment. We are issuing this AD to detect and correct fuel leaks in the right-hand landing lights compartment, which, in combination with the heat generated by the taxi lights and landing lights on the ground reaching the auto-ignition temperature of the fuel, could result in ignition of any fuel or fumes present in the right-hand landing lights compartment.
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 missing clamps that are required to provide positive separation between the alternating current (AC) feeder cables and the hydraulic line of the landing gear alternate extension. This AD requires an inspection for missing clamps that are required to provide positive separation between the AC feeder cables and the hydraulic line of the landing gear alternate extension, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct chafing of the AC feeder cable. A chafed and arcing AC feeder cable could puncture the adjacent hydraulic line, which, in combination with the use of the alternate extension system, could result in an in-flight fire.
We are superseding Airworthiness Directive (AD) 2010-03-05 for all the Boeing Company Model 747-200C and -200F series airplanes. AD 2010-03-05 required, for the upper chords of the upper deck floor beam of section 41, an inspection for cracking of certain fastener holes, and corrective action if necessary; and repetitive replacements of the upper chords, straps (or angles), and radius fillers of certain upper deck floor beams and, for any replacement that is done, inspections for cracking, and corrective actions if necessary. This new AD adds repetitive inspections of the upper chords of the upper deck floor beam of Section 42, repetitive replacements of the upper chords, post-replacement inspections, and corrective actions if necessary. This new AD also adds post-replacement inspections for section 41 and reduces certain compliance times. This AD was prompted by a determination that the upper deck floor beams are subject to widespread fatigue damage (WFD), the existing inspection program is not sufficient to maintain an acceptable level of safety, and the upper chords of the upper deck floor beam of section 42 are subject to the unsafe condition. We are issuing this AD to detect and correct cracking of the upper chords and straps (or angles) of the floor beams, which could lead to failure of the floor beams and consequent loss of controllability, rapid decompression, and loss of structural integrity of the airplane.
We are superseding Airworthiness Directive (AD) 94-12-03 for certain Airbus Model A320 series airplanes. AD 94-12-03 required modification of the belly fairing structure. This new AD requires repetitive inspections for cracking of the four titanium angles between the belly fairing and the keel beam side panel, an inspection for cracking of the open holes if any cracking is found in the titanium angles, and repair or replacement if necessary; this new AD also expands the applicability of AD 94-12-03. This AD was prompted by reports of cracks at the lower riveting of the four titanium angles that connect the belly fairing to the keel beam side panels on both sides of the fuselage. We are issuing this AD to detect and correct cracking of the titanium angles that connect the belly fairing to the keel beam side panels on both sides of the fuselage, which could affect the structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011 series airplanes. This AD was prompted by reports of cracked rib cap castellations. This AD requires repetitive inspections for castellation and skin clips cracked or damaged between stringers and cracked stringer clips of the wing box pylon back-up structure, and front spar to rear spar; repetitive inspections for cracking, damage, or failure of the pylon back-up torque box structure; repetitive inspections for cracking or damage of the wing box external areas at the drag brace aft wing fitting; repetitive inspections of the outer surface of the wing upper and lower skins for cracks or damage along the rib attachment at the fastener holes and between the two rows of attachment; and corrective actions if necessary. We are issuing this AD to detect and correct cracked or damaged rib cap castellations, which could degrade the structural capabilities of the airplane.
This action updates the name of the controlling agency for restricted areas R-2502N Fort Irwin, CA; R-2505 China Lake, CA; R-2506 China Lake South, CA; R-2508 Complex, CA; R-2515 Muroc Lake, CA and R-2524 Trona, CA to read “FAA, Joshua Control Facility, Edwards AFB, CA.” This is an administrative change only as there are no changes to the dimensions, time of designation or activities conducted within the affected restricted areas.
This final rule amends certain airworthiness regulations for transport category airplanes, based on recommendations from the FAA-sponsored Aviation Rulemaking Advisory Committee (ARAC). This amendment eliminates regulatory differences between the airworthiness standards of the FAA and the European Aviation Safety Agency (EASA). This final rule does not add new requirements beyond what manufacturers currently meet for EASA certification and does not affect current industry design practices. This final rule revises the structural test requirements necessary when analysis has not been found reliable; clarifies the quality control, inspection, and testing requirements for critical and non-critical castings; adds control system requirements that consider structural deflection and vibration loads; expands the fuel tank structural and system requirements regarding emergency landing conditions and landing gear failure conditions; adds a requirement that engine mount failure due to overload must not cause hazardous fuel spillage; and revises the inertia forces requirements for cargo compartments by removing the exclusion of compartments located below or forward of all occupants in the airplane.
We are adopting a new airworthiness directive (AD) for all Turbomeca S.A. Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, 1S1, 2B, 2B1, 2C, 2C1, 2C2, 2S1, and 2S2 turboshaft engines. This AD requires an initial one-time vibration check of the engine accessory gearbox (AGB) on certain higher risk Arriel 1 and Arriel 2 model engines. This AD also requires repetitive vibration checks of the engine AGB for all Arriel 1 and Arriel 2 engines at every engine shop visit. This AD was prompted by reports of uncommanded in-flight shutdowns on Turbomeca S.A. Arriel 1 and Arriel 2 engines following rupture of the 41-tooth gear forming part of the 41/23-tooth bevel gear located in the engine AGB. We are issuing this AD to prevent failure of the engine AGB, which could lead to in-flight shutdown and damage to the engine, which may result in damage to the aircraft.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of an incorrectly assembled check tee fitting used in fire extinguishing (FIREEX) distribution lines. This AD requires inspecting to determine the part number and for all affected check tee fittings measuring for correct depth, and replacing if necessary. We are issuing this AD to detect and correct faulty check tee fittings, which will reduce fire extinguishing protection.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, -300F, and -400ER airplanes. This AD was prompted by reports indicating that a standard access door was located where an impact-resistant access door was required, and stencils were missing from some impact-resistant access doors. This AD requires an inspection of the wing fuel tank access doors to determine whether impact-resistant access doors are installed in the correct locations, and to replace incorrectly installed doors with impact-resistant access doors. This AD also requires an inspection for stencils and index markers on impact-resistant access doors, and application of new stencils or index markers if necessary. In addition, this AD requires revising the maintenance program to incorporate changes to the airworthiness limitations section. We are issuing this AD to correct the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes, and Model 777 airplanes. This AD was prompted by testing reports on certain Honeywell phase 3 display units (DUs). These DUs exhibited susceptibility to radio frequency emissions in WiFi frequency bands at radiated power levels below the levels that the displays are required to tolerate for certification of WiFi system installations. The phase 3 DUs provide primary flight information including airspeed, altitude, pitch and roll attitude, heading, and navigation information to the flightcrew. This AD requires replacing the existing phase 3 DUs with phase 1, phase 2, or phase 3A DUs, and for certain replacement DUs, installing new DU database software. We are issuing this AD to prevent loss of flight-critical information displayed to the flightcrew during a critical phase of flight, such as an approach or takeoff, which could result in loss of airplane control at an altitude insufficient for recovery, or controlled flight into terrain.
This document provides clarification of the intent of the Approach/Departure IFR Transitions regulation contained in the Helicopter Air Ambulance, Commercial Helicopter, and Part 91 Helicopter Operations final rule, published on February 22, 2014. After publication, the FAA received comments and questions from intended users and industry advocacy groups about the clarity of terms used in this regulation, specifically, regarding the use of published instrument approaches and departures and the visibility limitations and differences between the terms “proceed visually” and “proceed VFR”. The FAA is clarifying the terms and intent of this regulation in order to increase situational awareness and enhance Helicopter Air Ambulance safety. This clarification is intended for Part 135 air carriers engaged in helicopter air ambulance operations, and Principal Inspectors with oversight responsibility for helicopter air ambulance operations.
These special conditions are issued for the Boeing, Model 767-200/-300 series airplanes. These airplanes, as modified by Avionics Support Group, will have a novel or unusual design feature when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. This design feature is an ePhone handset for use with the ICS SATCOM System that will use rechargeable lithium batteries and battery systems. 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 The Boeing Company Model 747-8 and 747-8F series airplanes. This AD was prompted by an analysis by the manufacturer, which revealed that certain fuse pins for the strut-to-wing attachment of the outboard aft upper spar are susceptible to migration in the event of a failed fuse pin through bolt. This AD requires replacing the fuse pins for the strut-to-wing attachment of the outboard aft upper spar with new fuse pins, and replacing the access cover assemblies with new access cover assemblies. We are issuing this AD to prevent migration of these fuse pins, which could result in the complete disconnect and loss of the strut-to-wing attachment load path for the outboard aft upper spar. The complete loss of an outboard aft upper spar strut-to-wing attachment load path could result in divergent flutter in certain parts of the flight envelope, which could result in loss of control of the airplane.
We are superseding Airworthiness Directive (AD) 2004-03-19, which applies to certain Airbus Model A320-111, -211 and -231 series airplanes. AD 2004-03-19 required repetitive inspections for cracking in the transition and pick-up angles in the lower part of the center fuselage area, and corrective action if necessary. AD 2004-03-19 also provided for an optional terminating modification for the repetitive inspection requirements. This new AD requires accomplishing the modification by installing washers between the transition pick-up angle and the pin nuts, and doing related investigative and corrective actions if necessary. This new AD also adds airplanes to the applicability of AD 2004-03-19. This AD was prompted by a determination that the optional terminating modification must be required in order to address the unsafe condition. We are issuing this AD to prevent fatigue cracking in the transition and pick-up angles of the lower part of the center fuselage, which could result in reduced structural integrity of the wing-fuselage support and fuselage pressure vessel.
This action amends the description of Area D of the Washington Tri-Area Class B airspace area to include exclusion of restricted area R-4001C from the Class B airspace when the restricted area is active. The remainder of the Class B description is not affected by this change.
This action amends, removes, and establishes multiple jet routes, high altitude and low altitude Area Navigation (RNAV) routes (Q- and T-routes), and VHF Omnidirectional Range (VOR) Federal airways in the north central and northeast United States (U.S.) to reflect and accommodate route changes being made in Canadian airspace as part of Canada's Winsor-Toronto-Montreal (WTM) airspace redesign project. This action also amends or removes ATS routes with minimal or no use. This action also corrects a publishing error in the NPRM regulatory text for Q-71, reverses the order of points published for RNAV route Q-844, changes an airway point in RNAV route Q-937, refines the geographic latitude/longitude position information for one waypoint (CLNTN), and corrects the state and country identifiers for three waypoints (KARIT, ATENE, and REVEN).
These special conditions are issued for Boeing Model 777-300ER airplanes with single-occupant, oblique (side-facing) seats equipped with inflatable lapbelts. This installation is novel or unusual, and the applicable airworthiness regulations do not contain adequate or appropriate safety standards for occupants of seats installed at an oblique angle of 30 degrees to the centerline of the airplane or for inflatable restraint systems. 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 amends the Appendix listing airports/locations with special operating restrictions in FAA's general operating and flight rules. Specifically, this action adds an additional entry for Houston, TX (William P. Hobby Airport), and San Diego, CA (Marine Corps Air Station Miramar), to the Appendix, which lists the airports where aircraft operating within 30 nautical miles (NM) of the listed airports, from the surface upward to 10,000 feet mean sea level (MSL) must be equipped with an altitude encoding transponder. The FAA is taking this action to correctly identify applicable airports under the appropriate sections in the Appendix.
This rule establishes, amends, suspends, or revokesStandard Instrument Approach Procedures (SIAPs) and associatedTakeoff Minimums and Obstacle Departure Procedures foroperations at certain airports. These regulatory actions areneeded because of the adoption of new or revised criteria, orbecause of changes occurring in the National Airspace System,such as the commissioning of new navigational facilities, addingnew obstacles, or changing air traffic requirements. Thesechanges 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 amends Class D airspace at Wichita, McConnell AFB, KS. The closure of nearby Derby, Hamilton Field has necessitated the need to amend Class D airspace at McConnell AFB. This action enhances the safety and management of aircraft operations at the airport.
These special conditions are issued for Airbus Model A350-900 airplanes. These airplanes will have a novel or unusual design feature associated with general limiting requirements of its flight-envelope protection features. 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.
The National Aeronautics and Space Administration (NASA) is deleting existing drug-free workplace requirements for financial assistance in one Title of the Code of Federal Regulations (CFR), and moving it to another Title, consistent with the Office of Management and Budget's (OMB) guidance on drug-free workplace requirements for financial assistance. Further, NASA is implementing, and thereby giving regulatory effect to, the OMB guidance on drug-free workplace requirements for financial assistance.
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 rudder bearings falling out of the fore rudder hinge bracket during assembly. This AD requires a proof load test and detailed inspections; and installation of a new bearing, reaming, or repair of the bearing if necessary. We are issuing this AD to detect and correct improper bearing installation, which could result in abnormal wear and potential increased freeplay in the rudder system, and resultant airframe vibration, leading to compromise of the flutter margins of the airplane.
This action modifies VOR Federal airway V-298 in the vicinity of Pasco, WA. The FAA is taking this action due to the Pasco, WA (PSC), VHF Omnidirectional Range (VOR)/Distance Measuring Equipment (DME) facility that provides navigation aid (NAVAID) guidance for a portion of V-298, being relocated. This action will ensure the safety and efficient management of aircraft operating within the National Airspace System.
This action amends 5 VHF Omnidirectional Range (VOR) Federal airways (V-6, V-30, V-126, V-133, and V-416) and removes 1 VOR Federal airway (V-65) in the vicinity of Sandusky, OH. The FAA is taking this action due to the scheduled decommissioning of the Sandusky, OH, VOR/Distance Measuring Equipment (VOR/DME) facility that provides navigation guidance for a portion of the airways listed.
We are superseding an airworthiness directive (AD) 2013-22-20 for Embraer S.A. 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 cracks beyond acceptable limits in the carbon discs of the left hand (LH) and right hand (RH) brake assemblies. We are issuing this AD to require actions to address the unsafe condition on these products.
This action makes minor adjustments to the latitude/longitude positions of two points in the descriptions of restricted areas R-2901A, B, G, H, J, K, L and N at the Avon Park Air Force Range, FL. The corrections are the result of more accurate digital plotting of the points.
This action establishes Class D airspace and amends Class E airspace at Blackstone, VA, to accommodate the new air traffic control tower at Allen C Perkinson Blackstone Army Airfield. Controlled airspace is necessary for the safety and management of instrument flight rules (IFR) operations at the airfield. This action updates the geographic coordinates of the airfield's Class E airspace, and adds exclusion of Restricted area airspace in Class D airspace.
This action establishes Class E airspace at Pine Knot, KY, to accommodate a new Area Navigation (RNAV) Global Positioning System (GPS) Standard Instrument Approach Procedure (SIAP) serving Mc Creary County Airport. This action enhances the safety and management of Instrument Flight Rules (IFR) operations at the airport.
This action establishes Class E Airspace at Cynthiana, KY, to accommodate a new Area Navigation (RNAV) Global Positioning System (GPS) Standard Instrument Approach Procedures (SIAP) serving Cynthiana-Harrison County Airport. This action enhances the safety and management of Instrument Flight Rules (IFR) operations at the airport.
This action modifies three RNAV Q-routes and establishes five Q-routes originating in Oakland Air Route Traffic Control Center's (ARTCC) airspace. The routes promote operational efficiencies for users and provide connectivity to current and proposed RNAV en route and terminal procedures. Also, two waypoints and a fix name is changed for Q-120, and Q-128, as the proposed names already were in use.
These special conditions are issued for the AgustaWestland Model AW189 helicopter. This model helicopter will have the novel or unusual design feature of a 30-minute all engines operating (AEO) 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.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, -106, -201, -202, -301, -311, and --315 airplanes. This AD was prompted by reports of dual alternating current (AC) generator failure during flight. The failure was attributed to wire chafing along the wing lower flap shroud. This AD requires revising the maintenance program to incorporate certain tasks for the electrical wiring interconnection system inspection program. We are issuing this AD to prevent failure of both AC generators due to wire chafing, which could result in loss of power to the anti-icing heaters for the elevator horn, engine inlet, and propeller, and consequent ice accumulation in these areas, which could adversely affect the controllability of the airplane.
The FAA is revising airworthiness directive (AD) 2014-07-04 that published in the Federal Register to correct certain errors. AD 2014-07-04 applied to certain Sikorsky Model S-92A helicopters. The range of serial numbers in the Applicability section and a reference to the service information in the Required Actions section of the regulatory text are incorrect. This document corrects those errors. In all other respects, the original document remains the same.
We are revising an airworthiness directive (AD) 2013-22-14 for any DG Flugzeugbau GmbH Model DG-1000T glider equipped with a Solo Kleinmotoren Model 2350 C engine. 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 engine shaft failure and consequent propeller detachment. 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 Dassault Aviation Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes; Model MYSTERE-FALCON 200 airplanes; and Model MYSTERE-FALCON 20-C5, 20-D5, 20-E5, and 20-F5 airplanes. This AD was prompted by reports of a manufacturing defect in the charge indicator on fire extinguisher bottles. This AD requires repetitive weighing of fire extinguisher bottles having a certain part number, and eventual replacement of those bottles to terminate the repetitive weighing. We are issuing this AD to detect and correct a dormant failure in the fire suppression system, which could result in the inability to put out a fire in an engine, auxiliary power unit, or rear compartment.
This action modifies VOR Federal airways V-93, V-314, and V-471; and RNAV route T-295 in northeastern Maine due to the scheduled decommissioning of the Princeton, ME, VOR facility. In addition, an analysis of the airway structure in that area found that some segments of the affected routes are rarely utilized and are therefore being removed.
NASA is amending its regulations by adding a subpart for traffic enforcement regulations, authorities, and procedures at all NASA Centers and component facilities. Changes are being made to align this part with NASA objectives in the protection of its people and property. Establishing a traffic safety program is essential for the protection and security of NASA bases, stations, facilities laboratories and of its aircraft, spacecraft, missiles and similar vehicles and of its real and personal property, including property in the custody of NASA contractors and subcontractors.
These special conditions are issued for the Bombardier Aerospace Models BD-500-1A10 and BD-500-1A11 series airplanes. These airplanes will have a novel or unusual design feature associated with a reduced margin between design cruising speed, V C /M C , and design diving speed, V D /M D , based on the incorporation of a high-speed protection system that limits nose down pilot authority at speeds above V D /M D . 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 Bombardier Aerospace Models BD-500-1A10 and BD-500-1A11 series airplanes. These airplanes will have novel or unusual design features, specifically, digital systems architecture composed of several connected data networks that will have the capability to allow 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 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 Bombardier Aerospace Models BD-500-1A10 and BD-500-1A11 series airplanes. These airplanes will have novel or unusual design features, specifically, digital systems architecture composed of several connected networks that may allow access to or by external computer systems and networks and 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.
These special conditions are issued for the Bombardier Aerospace, Models BD-500-1A10 and BD-500-1A11 series airplanes. These airplanes will have a novel or unusual design feature associated with the use of carbon fiber reinforced plastic (CFRP) for most of the wing fuel tank structure, which, when impacted by tire debris, may resist penetration or rupture differently from aluminum wing skins. 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 APEX Aircraft Model R 3000/160 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 small pieces of paint from the engine air intake box blocking the engine carburetor. We are issuing this AD to require actions to address the unsafe condition on these products.
We are superseding Airworthiness Directive (AD) 2007-18-09 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2007-18-09 required repetitive inspections of the upper support of the nose landing gear (NLG), and related investigative and corrective actions if necessary; and also provided an optional terminating action for the repetitive inspections. This new AD adds installation of a new enhanced manufacturing and maintainability (EMM) braking and steering control unit (BSCU) standard, and adds airplanes to the applicability. This AD was prompted by a determination that previously allowed terminating actions no longer address the unsafe condition and that a new terminating action is necessary. We are issuing this AD to prevent landings with the NLG turned 90 degrees from centerline, which could result in reduced controllability of the airplane.
This action modifies two jet routes and three VOR Federal airways and removes three jet routes in the north central United States. The FAA is taking this action due to the scheduled decommissioning of the Peck, MI, VHF Omnidirectional Range (VOR) navigation aid (NAVAID), which provides navigation guidance for portions of the affected routes. The amendments for one jet route (J-38) and one VOR Federal airway (V-337) that were addressed in the notice of proposed rulemaking (NPRM) are withdrawn from this final rule as they are being amended in a separate rulemaking action. This action promotes flight safety and the efficient management of aircraft operating within the National Airspace System (NAS).
These special conditions are issued for Airbus Model A350-900 airplanes. These airplanes will have a novel or unusual design feature associated with electronic system-security protection from unauthorized external access. 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 Airbus Model A350-900 airplanes. These airplanes will have a novel or unusual design feature that will incorporate a nitrogen generation system (NGS) for all fuel tanks, to actively reduce flammability exposure within the fuel tanks significantly below that required by the fuel-tank flammability regulations. Among other benefits, the NGS significantly reduces the potential for fuel-vapor ignition caused by lightning strikes. 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 Airworthiness Directive (AD) 2014-05-02 for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2014-05-02 required repetitive inspections for cracking and corrosion of the aft pressure bulkhead, repetitive inspections of the frame chord drain path for debris, and corrective actions if necessary; and, for certain airplanes, enlargement of frame chord drain holes. This AD requires the same actions as AD 2014-05-02, but revises a certain repetitive inspection interval to avoid a misunderstanding of the repetitive inspection interval for the aft pressure bulkhead. This AD was prompted by reports from operators expressing confusion regarding a certain repetitive inspection interval for the aft pressure bulkhead. We are issuing this AD to detect and correct corrosion or cracking of the aft pressure bulkhead, which could result in loss of the aft pressure bulkhead web and stiffeners, and consequent rapid decompression of the airplane.
This action establishes Class E airspace at the Flagstaff VHF Omni-Directional Radio Range/Distance Measuring Equipment (VOR/DME) navigation aid, Flagstaff, AZ, to facilitate vectoring of Instrument Flight Rules (IFR) aircraft under control of Albuquerque Air Route Traffic Control Center (ARTCC). This improves the safety and management of IFR operations within the National Airspace System.
We are superseding Airworthiness Directive (AD) 2011-16-01 for all Dassault Aviation Model FALCON 7X airplanes. AD 2011-16-01 required adding an automatic reversion logic and a means for the pilot to override pitch trim control normal modes, and installing placards in the cockpit; replacing the frame of the emergency switch box; replacing certain horizontal stabilizer electronic control units (HSECU); revising the Limitations section of the airplane flight manual (AFM); and revising the maintenance program to incorporate a certain task. This new AD requires modifying the fly-by-wire (FBW) standard; and operational testing of the electric motors reversion relays and trim emergency command of the horizontal stabilizer trim system (HSTS), and repairs if necessary. This AD was prompted by an uncontrolled pitch trim runaway during descent. We are issuing this AD to prevent an uncontrolled pitch trim runaway, which could result in loss of control of the airplane.
These special conditions are issued for the Embraer S.A. Model EMB-550 airplane. This airplane will have a novel or unusual design feature when compared to the state of technology and design envisioned in the airworthiness standards for transport category airplanes. This design feature is a high incidence protection system that limits the angle of attack at which the airplane can be flown during normal low speed operation. 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 Gulfstream Aerospace Corporation Model GVI airplane. This airplane, as modified by Gulfstream Aerospace Corporation, will have novel or unusual design features associated with the installation of electro-hydraulically operated seats with a backup power supply (BPS) and hydraulic reservoir, pump, and actuators, as well as massage and heating functions. 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 all Pratt & Whitney Canada Corp. (P&WC) PT6A-114 and PT6A-114A turboprop engines. This AD requires initial and repetitive borescope inspection (BSI) of compressor turbine (CT) blades, and the removal from service of blades that fail inspection. This AD was prompted by several incidents of CT blade failure, causing power loss, and engine failure. We are issuing this AD to prevent failure of CT blades, which could result in damage to the engine and damage to the airplane.
We are superseding Airworthiness Directive (AD) 2007-06-12 for certain Airbus Model A330-200 and A330-300 airplanes. This new AD reduces the compliance times for reinforcing the structure of the center fuselage. This AD was prompted by a new fatigue and damage tolerance evaluation that revealed the compliance time for an existing reinforcement of the fuselage has to be reduced. We are issuing this AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage.
We are superseding Airworthiness Directive (AD) 2011-17-08 for all Airbus Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330-300 series airplanes. AD 2011-17-08 required revising the maintenance program by incorporating certain Airworthiness Limitation Items (ALIs). This new AD requires a revision to the maintenance or inspection program, as applicable, to incorporate new or revised structural inspection requirements. This AD was prompted by a revision of certain airworthiness limitations items (ALI) documents, which specifies more restrictive instructions and/or airworthiness limitations. We are issuing this AD to detect and correct fatigue cracking, damage, and corrosion in certain structure, which could result in reduced structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes; Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of rupture of the uplock springs of the nose landing gear (NLG) and main landing gear (MLG) doors and legs. This AD requires repetitive inspections of the uplock springs of the NLG and MLG doors and legs for broken and damaged springs, and corrective actions if necessary. We are issuing this AD to detect and correct improper free fall extension of the MLG or NLG, which could lead to possible loss of control of the airplane on the ground, and consequent damage to the airplane and injury to occupants.
We are adopting a new airworthiness directive (AD) for all Harry E. Williams de Havilland Model DH 82A airplanes, all Cliff Robertson de Havilland Model DH 82A airplanes, and all de Havilland Model DH 83 airplanes. This AD requires inspecting the aircraft maintenance records and/or the installed lateral fuselage tie rods and attaching nuts to determine the origin of manufacture. This AD also requires immediately replacing lateral fuselage tie rods and attaching nuts produced by a specific manufacturer. This AD was prompted by reports of structural failure of the attachment of the wing to the fuselage that resulted from failed lateral fuselage tie rods. We are issuing this AD to correct the unsafe condition on these products.
We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 2000EX airplanes. This AD was prompted by a revision to the airplane airworthiness limitations to introduce a corrosion prevention control program, among other changes, to the maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program to include the maintenance tasks and airworthiness limitations specified in the airworthiness limitations section of the airplane maintenance manual. We are issuing this AD to prevent reduced structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-400ER series airplanes. This AD was prompted by reports of turbine wheel bursts in the air driven pump (ADP) turbine gearbox assembly (TGA), which resulted in the release of high energy fragments. This AD requires replacing the existing ADP TGA with an improved ADP TGA. We are issuing this AD to prevent fragments from an uncontained turbine wheel burst penetrating the fuselage and striking passengers, or penetrating the wing-to-body fairing and striking ground handling or maintenance personnel, causing serious injury.
This action establishes Class E airspace at the Albuquerque VHF Omni-Directional Radio Range Tactical Air Navigation Aid (VORTAC), Albuquerque, NM, to facilitate vectoring of Instrument Flight Rules (IFR) aircraft under control of Albuquerque Air Route Traffic Control Center (ARTCC). This improves the safety and management of IFR operations within the National Airspace System.
This action modifies Class E airspace at Hulett Municipal Airport, Hulett, WY, to accommodate aircraft using the Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach procedures. This action enhances the safety and management of aircraft operations at the 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 7400.9Y, 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.
We are adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 airplanes. This AD was prompted by reports of “BLEED 1(2) LEAK” messages displayed on the engine indication and crew alert system (EICAS), and indirect damage to components of the electrical wiring interconnection system (EWIS) in the engine pylon area. This AD requires inspecting the EWIS components for damage, and repair if necessary. This AD also requires installing pre-cooler deflectors on the left- and right-hand pylons, and applying silicone sealant. We are issuing this AD to prevent indirect damage to EWIS components near the engine bleed air pre-coolers, which could result in a dual engine roll back to idle and consequent dual engine power loss and reduced controllability of the airplane.
We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by reports that the pintle pins installed on a certain number of airplanes may be incorrectly protected against corrosion. This AD requires replacing certain pintle pins on the left- and right-hand main landing gear (MLG) with a serviceable part. We are issuing this AD to detect and correct pintle pins that have been incorrectly corrosion-protected, which could cause the pintle pins to shear under normal load and lead to the collapse of the MLG during take-off or landing.
We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. This AD was prompted by reports of cracking of the main fitting of the nose landing gear (NLG). This AD requires revising the maintenance program by incorporating a new safe-life limitation for the NLG main fitting. We are issuing this AD to prevent collapse of the NLG, which could lead to degradation of direction control on the ground or an un-commanded turn to the left, and a consequent loss of control of the airplane on the ground, possibly resulting in damage to the airplane and injury to occupants.
We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD requires repetitive on-ground power cycles (resets) of the Transponder, Terrain and Traffic Collision Avoidance System (T3CAS). This AD was prompted by reports of spurious terrain ahead warning system (TAWS) alerts during approach and takeoff. We are issuing this AD to prevent spurious TAWS alerts, which could increase flightcrew workload during critical landing or takeoff phases, and result in reduced control of the airplane.
We are adopting a new airworthiness directive (AD) for certain Technify Motors GmbH (type certificate previously held by Thielert Aircraft Engines GmbH) TAE 125-02-99 and TAE 125-02-114 reciprocating engines. This AD requires removal of each high-pressure (HP) fuel pump before 300 flight hours (FHs) in service or within 55 FHs after the effective date of the AD, whichever occurs later. This AD was prompted by in-flight shutdowns on airplanes with TAE 125-02 engines. We are issuing this AD to prevent failure of the HP fuel pump, which could result in damage to the engine and damage to the airplane.
We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 900EX airplanes. This AD was prompted by our determination of the need for a revision to the airplane airworthiness limitations to introduce a corrosion prevention control program, among other changes, to the maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to include the maintenance tasks and airworthiness limitations specified in the Airworthiness Limitations section of the airplane maintenance manual. We are issuing this AD to prevent reduced structural integrity of the airplane, and prevent reduced controllability of the airplane.
We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 900EX airplanes. This AD was prompted by our determination to introduce a corrosion prevention control program, among other changes, to the maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to include the maintenance tasks and airworthiness limitations specified in the Airworthiness Limitations section of the airplane maintenance manual. We are issuing this AD to prevent reduced structural integrity and reduced controllability of the airplane.
We are adopting a new airworthiness directive (AD) for certain Empresa Brasileira de Aeronautica S.A. (Embraer) Model EMB-135BJ airplanes. This AD was prompted by reports of failure of the bolts that connect the cockpit windshield center-post to the forward fuselage. This AD requires repetitive detailed inspections to detect discrepancies on the attaching parts of the cockpit windshield center-post; checking whether the bolts are tightened, if applicable; and modifying parts, including inspecting for and repairing damage. We are issuing this AD to prevent failed bolts and failed attaching parts of the cockpit windshield center-post, which could lead to loss of structural integrity of the airplane.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports that elevator power control unit (PCU) shear pins may fail prematurely. This AD requires repetitive replacement of the elevator PCU shear pins. We are issuing this AD to prevent premature elevator PCU shear pin failure. If all pins fail on one elevator, the elevator surface would become inoperative, which could reduce the controllability of the airplane and could result in a loss of redundancy for flutter prevention.
We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This AD was prompted by our determination of the need to incorporate new life limits for the main landing gear (MLG) barrel assembly, retraction actuator assembly linkage, and flange duct. This AD requires revising the maintenance or inspection program, as applicable, to include the new life limits. We are issuing this AD to prevent reduced structural integrity of the airplane and possible loss of controllability of the airplane.
We are adopting a new airworthiness directive (AD) for Viking Air Limited Model DHC-3 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 looseness of the horizontal stabilizer actuator mounting block in the forward-aft and side-to-side directions. We are issuing this AD to require actions to address the unsafe condition on these products.
We are superseding Airworthiness Directive (AD) 2013-18-09 for certain Honeywell ASCa Inc. emergency locator transmitters (ELTs) installed on various transport category airplanes. AD 2013-18-09 required various one-time general visual inspections of the ELT transmitter units (TUs), and corrective actions if necessary. This new AD corrects the manufacturer's name in the AD applicability and adds a source of approval for an installation. AD 2013-18-09 was prompted by a fire on a parked and unoccupied airplane; preliminary information indicated combustion in the area of the ELT TU. This new AD was prompted by the identification of an error in the applicability of AD 2013-18-09. We are issuing this AD to detect and correct discrepancies of the battery wiring installation inside the TU, which could result in an electrical short and possible ignition source.
We are superseding Airworthiness Directive (AD) 2010-17-18 R1, which applies to certain Air Tractor, Inc. Models AT-802 and AT-802A airplanes. AD 2010-17-18 R1 required repetitively inspecting (using the eddy current method) the two outboard fastener holes in both of the wing main spar lower caps at the center splice joint for cracks; repairing or replacing any cracked spar; changing the safe life for certain serial number ranges; and sending the inspection results, only if cracks are found, to the FAA. This new AD retains all actions of AD 2010-17-18 R1 and expands the applicability to include all serial numbers regardless of configuration or operational use. This AD was prompted by our determination that the safe life for the wing main spar lower caps should apply to all Models AT-802 and AT-802A airplanes regardless of configuration or operational use. We are issuing this AD to correct the unsafe condition on these products.
These special conditions are issued for Airbus Model A350-900 airplanes. This airplane will have a novel or unusual design feature associated with permanently installed rechargeable lithium-ion batteries and battery systems. These batteries have certain failure, operational, and maintenance characteristics that differ significantly from those of the nickel-cadmium and lead-acid rechargeable batteries currently approved for installation on large transport-category airplanes. 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 Airbus Model A350-900 series airplanes. These airplanes will have a novel or unusual design feature associated with high speed limiting. 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 Airbus Model A350-900 airplanes. These airplanes will have a novel or unusual design feature associated with a high-speed protection system that limits nose-down pilot authority at speeds above V C /M C , and prevents the airplane from performing the maneuver required under the Code of Federal Regulations. 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 Airbus Model A350-900 series airplanes. These airplanes will have a novel or unusual design feature associated with the post-crash fire survivability of composite fuel tanks. 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 Airworthiness Directives (AD) 2006-21-08, AD 2007-14-01, AD 2008-25-02, AD 2010-04-09, AD 2011-01-02, and AD 2012-16-05, for certain Airbus Model A330 and A340 series airplanes. AD 2006-21-08, AD 2007-14-01, AD 2008-25-02, AD 2010-04-09, AD 2011-01-02, and AD 2012-16-05 required revising the maintenance program or inspection program to incorporate certain maintenance requirements and airworthiness limitations for fuel tank systems. This new AD requires a new maintenance or inspection program revision. This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This AD was prompted by an analysis of the impacts of extended service goal activities on Airbus Model A300 series airplanes. This AD requires revising the maintenance or inspection program. We are issuing this AD to prevent failure of flight critical systems.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, A330-200, A330-300, and A340-200, A340-300, A340-500, and A340-600 series airplanes. This AD was prompted by a determination that the service life limits of the cabin pressure control system (CPCS) safety valves installed on the aft pressure bulkhead were being exceeded. This AD requires repetitive replacement of the CPCS safety valves with serviceable valves. We are issuing this AD to prevent exceeding the service life limits of the CPCS safety valves, which, in the event of a failure, could result in excessive positive or negative differential pressure in the fuselage and consequent incapacitation or injuries to airplane occupants.
We are superseding Airworthiness Directive (AD) 2005-15-04 for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. AD 2005-15-04 required operators to assign serial numbers or part numbers to certain landing gear parts; establish the number of landings on the parts, if necessary; and revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) to reflect the new life limits of the landing gear parts. This new AD adds airplanes to the applicability, requires operators to assign serial numbers or part numbers to certain additional landing gear parts to establish the number of landings on the parts if necessary, and requires operators to record in all required airplane technical records and manuals the new part numbers, serial numbers, and landings assigned to these parts. This AD was prompted by reports that landing gear parts that have safe-life limits but do not have serial numbers or part numbers can be removed from one landing gear and re-installed on another, making tracking difficult. We are issuing this AD to prevent life-limited landing gear parts from being used beyond their safe-life limits, which could lead to collapse of the landing gear.
We are adopting a new airworthiness directive (AD) for certain Embraer S.A. Model EMB-500 airplanes. This AD was sent previously to all known U.S. owners and operators of these airplanes as an emergency AD. This AD requires an inspection and replacement as necessary of the barrel nuts at the horizontal stabilizer to vertical stabilizer attachment joint. This AD was prompted by 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 cracking of the barrel nuts at the horizontal stabilizer to vertical stabilizer attachment joint. We are issuing this AD to correct the unsafe condition on these products.
We are superseding Airworthiness Directive (AD) 2012-10-53 for Eurocopter Deutschland GmbH (ECD) (now Airbus Helicopters) Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters. AD 2012-10-53 required, 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. Since we issued AD 2012-10-53, it has been determined that it is safe to increase the visual inspection intervals of the MRH shaft flanges from 10 hours time-in-service (TIS) to 50 hours TIS and remove the inspection of the lower MRH shaft flange bolt attachment areas. This new AD continues to require checking and inspecting the upper and lower MRH shaft flanges for a crack. These actions are intended to detect a crack on the MRH shaft flange, which if not corrected, could result in failure of the MRH and subsequent loss of control of the helicopter.
These special conditions are issued for the modification of the Robinson Helicopter Company Model R66 helicopter. This model helicopter will have a novel or unusual design feature after installation of the HeliSAS helicopter autopilot/stabilization augmentation system (AP/SAS) that has potential failure conditions with more severe adverse consequences than those envisioned by the existing applicable airworthiness regulations. These special conditions contain the added safety standards the Administrator considers necessary to ensure the failures and their effects are sufficiently analyzed and contained.
These special conditions are issued for the modification of the Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model EC135 series helicopters. These model helicopters will have a novel or unusual design feature after installation of the S-TEC Corporation (S-TEC) HeliSAS helicopter autopilot/stabilization augmentation system (AP/SAS) that has potential failure conditions with more severe adverse consequences than those envisioned by the existing applicable airworthiness regulations. These special conditions contain the added safety standards the Administrator considers necessary to ensure the failures and their effects are sufficiently analyzed and contained.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 707 airplanes, Model 720 and 720B series airplanes, Model 727 airplanes, and Model 737-100, -200, and -200C series airplanes. This AD was prompted by a report of a fire that originated near the first officer's area and caused extensive damage to the flight deck on a different airplane model. 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 inadvertently passing through an internal, anti-collapse spring of the low-pressure oxygen hose, which can cause the low-pressure oxygen hose to melt or burn, leading to an oxygen-fed fire and/or smoke in the flight deck.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 series airplanes. This AD was prompted by reports of smoke or flames in the passenger cabin of various transport category airplanes related to the wiring for the passenger cabin in-flight entertainment (IFE) system, cabin lighting, and passenger seats. This AD requires, for certain airplanes, doing an inspection of the electrical power control panel for a certain part number, and corrective action if necessary; and, for certain other airplanes, installing a new electrical power control panel, and making changes to the wiring and certain electrical load management system (ELMS) panels. We are issuing this AD to ensure that the flightcrew is able to turn off electrical power to the IFE systems and other non-essential electrical systems through one or two switches in the flight deck in the event of smoke or flames. In the event of smoke or flames in the airplane flight deck or passenger cabin, the flightcrew's inability to turn off electrical power to the IFE system and other non-essential electrical systems could result in the inability to control smoke or flames in the airplane flight deck or passenger cabin during a non-normal or emergency situation, and consequent loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD was prompted by reports in which a single, undetected, erroneous radio altimeter output caused the autothrottle to enter landing flare retard mode prematurely on approach. This AD requires removing certain autothrottle computers and installing a new or reworked autothrottle computer. We are issuing this AD to prevent a single, undetected, erroneous radio altimeter output from causing premature autothrottle landing flare retard and subsequent loss of automatic speed control, which could result in loss of control of the airplane.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) airplanes. This AD was prompted by several reports indicating that shorter nacelle strut bushings were inadvertently installed on certain airplanes. This AD requires a general visual inspection of the left and right nacelle upper strut bushings; installation of the bolts and preload indicating (PLI) washers, if necessary; and replacement of the bushing or repair of the bushing installation, if necessary. We are issuing this AD to detect and correct inadequate nacelle strut bushings, which provide insufficient engagement in the strut fork end, and could deform under the bearing load and lead to the failure of the joint.
We are superseding Airworthiness Directive (AD) 2011-15-09 for certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. AD 2011-15-09 required repetitive inspections for proper operation of the main landing gear (MLG) alternate extension system (AES), and corrective actions if necessary. This new AD requires, for certain airplanes, new repetitive inspections for proper operation of the MLG AES, and corrective actions if necessary. This new AD also requires eventually replacing the MLG AES cam mechanism assembly with a new assembly, which terminates the repetitive inspections for those airplanes. This AD was prompted by a determination that, for certain airplanes not affected by AD 2011-15-09, a different MLG AES cam mechanism assembly was installed, resulting in input lever fractures and inability to open the MLG door; those assemblies could be subject to the same unsafe condition in AD 2011-15-09. We are issuing this AD to prevent improper operation of the cam mechanism or rupture of the door release cable, which could result in loss of control of the airplane during landing.
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. This AD was prompted by reports of in-flight uncommanded rudder movements. This AD requires revising the airplane flight manual (AFM) to incorporate an uncommanded yaw motion procedure. We are issuing this AD to prevent in-flight uncommanded rudder movements, which could lead to structural failure and subsequent loss of the airplane.
We are adopting a new airworthiness directive (AD) for all Airbus 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 A300-600 series airplanes). This AD was prompted by the revision of certain airworthiness limitation items (ALI) documents, which require more restrictive maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program to incorporate the limitations section. We are issuing this AD to prevent fatigue cracking, damage, or corrosion in principal structural elements, which could result in reduced structural integrity of the airplane.
We are superseding airworthiness directive (AD) 2013-12-01 for all Rolls-Royce plc (RR) model RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. AD 2013-12-01 required a one-time ultrasonic inspection (UI) of low-pressure (LP) compressor blades with more than 2,500 flight cycles since new or last inspection. This AD requires initial and repetitive UIs of the affected LP compressor blades. This AD was prompted by LP compressor blade partial airfoil release events. We are issuing this AD to prevent LP compressor blade airfoil separations, damage to the engine, and damage to the airplane.
We are adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190-100 STD, -100 LR, -100 ECJ, -100 IGW, -200 STD, -200 LR, and -200 IGW airplanes. This AD requires, for certain airplanes, retorquing and replacing the pylon outboard and inboard lower link fittings. For all airplanes, this AD requires repetitive retorquing of the pylon outboard and inboard lower link fittings. This AD was prompted by a report of a loose lower link assembly on the left and right pylons. We are issuing this AD to prevent loss of a shear pin on the pylon outboard and inboard lower link fittings, which could result in failure of the fitting and consequent separation of the engine from the wing.
We are superseding Airworthiness Directive (AD) 2008-14-17 for certain Airbus Model A330-200 and A340-300 series airplanes. AD 2008-14-17 required a high frequency eddy current (HFEC) inspection, corrective actions if necessary, and modifications. This new AD requires the same actions as those required by AD 2008-14-17, but with a reduced compliance time. This AD was prompted by a determination from a fatigue and damage tolerance evaluation that the compliance time needs to be revised. We are issuing this AD to detect and correct damage of the upper shell structure at the skin and frame interface, which could result in reduced structural integrity of the airframe.
We are superseding Airworthiness Directive (AD) 2006-26-06 for certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Rolls-Royce engines. AD 2006-26-06 required repetitive inspections to detect cracks of the outer V-blades of the thrust reverser, and corrective action if necessary. AD 2006-26-06 also provided for an optional terminating action for the repetitive inspections. This new AD adds, for airplanes on which the optional terminating action is done, repetitive inspections for cracking in the outer V-blade fittings of the hinge beam and latch beam ends of each thrust reverser half, and replacement of an affected thrust reverser half if necessary. This new AD also adds airplanes to the applicability. This AD was prompted by reports of cracked outer V-blade fittings at the hinge beam end of Rolls-Royce engine thrust reversers, on airplanes on which the optional terminating action was done. We are issuing this AD to prevent separation of a thrust reverser from the airplane during normal reverse thrust or during a refused takeoff, which could result in unexpected thrust asymmetry and a possible runway excursion.
We are adopting a new airworthiness directive (AD) for certain Turbomeca S.A. Makila 2A and Makila 2A1 turboshaft engines. This AD requires initial and repetitive visual inspections, and replacement of the splines of the high-pressure (HP) fuel pump/metering valve and the module M01 drive gear, if necessary. This AD was prompted by the failure of two HP fuel pumps that resulted in engine in-flight shutdowns. We are issuing this AD to prevent failure of the HP fuel pump, which could lead to an in-flight shutdown, damage to the engine, and forced landing or accident.
