Federal Aviation Administration July 2014 – Federal Register Recent Federal Regulation Documents

The FAA hereby provides notice of intent to release approximately 1.166 acres of airport property at Venice Municipal Airport, Venice, FL, from the conditions, reservations, and restrictions as contained in a Quitclaim Deed agreement between the FAA and the City of Venice, FL, dated June 10, 1947. The release of property will allow the City of Venice to dispose of the property for other than aeronautical purposes. The property is located at 1600 Harbor Drive South. The parcel is currently designated as non- aeronautical land use. The property will be released of its federal obligations for commercial land use. The fair market value of this parcel has been determined to be $2,200,000.

The FAA proposes to amend the collective risk limits for commercial launches and reentries. Under this proposal, the FAA would separate its expected-number-of-casualties (Ec) limits for launches and reentries. For commercial launches, the FAA proposes to aggregate the Ec posed by the following hazards: Impacting inert and explosive debris, toxic release, and far field blast overpressure. The FAA proposes to limit the aggregate Ec for these three hazards to 1 x 10-\4\. For commercial reentries, the FAA proposes to aggregate the Ec posed by debris and toxic release, and set that Ec under an aggregate limit of 1 x 10-\4\. Under the FAA's proposal, the aggregate Ec limit for both launch and reentry would be expressed using only one significant digit. The FAA also proposes to clarify the regulatory requirements concerning hazard areas for ships and aircraft. The proposed rule would require a launch operator to establish a hazard area where the probability of impact does not exceed: 0.000001 (1 x 10-\6\) for an aircraft; and 0.00001 (1 x 10-\5\) for a water-borne- vessel.

We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This proposed AD was prompted by a determination that more restrictive airworthiness limitations are necessary. This proposed AD would require revising the maintenance or inspection program as applicable. We are proposing 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 propose to adopt 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 proposed 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 proposed AD would require 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 proposing 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.

This action establishes Class E airspace at the Truth or Consequences VHF Omni-Directional Radio Range Tactical Air Navigation Aid (VORTAC), Truth or Consequences, 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.

We propose to adopt a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This proposed AD was prompted by a report of several cracks found on the forward passenger airstair door step assembly. This proposed AD would require an inspection to determine the serial number of the airstair step assembly, and if necessary, an electronic tap test, re-identification of the airstair step assembly, and replacement of the airstair step assembly. We are proposing this AD to detect and correct cracks in the forward passenger airstair door step assembly, which could propagate and result in the structural failure of the steps and impede the evacuation of passengers in the event of an emergency egress situation.

In accordance with the Paperwork Reduction Act of 1995, FAA invites public comments about our intention to request the Office of Management and Budget (OMB) approval to renew an information collection. The Federal Register Notice with a 60-day comment period soliciting comments on the following collection of information was published on May 2, 2014, vol. 79, no. 85, page 25172. 14 CFR part 17 sets forth procedures for filing solicitation protests and contract claims in the FAA's Office of Dispute Resolution for Acquisition. The regulations seek factual and legal information from protesters or claimants primarily through written submissions.

The Federal Aviation Administration (FAA) is issuing this notice to advise the public of the availability of the Final Written Reevaluation and Record of Decision for a minor adjustment to a project evaluated in FAA's 2005 Final Environmental Impact Statement (FEIS) for the LAX Master Plan is available for public inspection. The Final Written Reevaluation and Record of Decision was prepared for the construction and operation of the proposed West Aircraft Maintenance Area (WAMA) west of Taxiway AA in the southwest quadrant of Los Angeles International Airport, Los Angeles, California. FAA is making the Final Written Reevaluation and Record of Decision available for public inspection.

We propose to adopt 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 proposed AD was prompted by a report of early ruptures on the levers of the nose landing gear (NLG) sequence valve. This proposed AD would require 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 proposing 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 propose to supersede airworthiness directive (AD) 2013-18- 01 for Eurocopter France Model EC 155B, EC155B1, SA-365N, SA-365N1, AS- 365N2, AS-365-N3, and SA-366G1 helicopters. AD 2013-18-01 currently requires inspecting the collective pitch lever for correct locking and unlocking conditions. As published, AD 2013-18-01 contains certain errors. This proposed AD would retain the requirements of AD 2013-18- 01, correct these errors, and update the type certificate holder's name. The proposed actions are intended to detect an incorrectly adjusted collective pitch lever, which could result in loss of control of the helicopter.

This action proposes special conditions 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 associated with the 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 proposed 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 Embraer S.A. Model EMB-550 airplanes. This airplane will have a novel or unusual design feature associated with electrical and electronic systems that perform critical functions, the loss of which could be catastrophic to the airplane. 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.

In accordance with National Environmental Policy Act of 1969, as amended (NEPA; 42 United States Code 4321 et seq.), Council on Environmental Quality NEPA implementing regulations (40 Code of Federal Regulations parts 1500 to 1508), and FAA Order 1050.1E, Change 1, Environmental Impacts: Policies and Procedures, the FAA is announcing the availability of the ROD for the SpaceX Texas Launch Site, Cameron County, Texas. The ROD provides the FAA's final environmental determination and approval to support the issuance of launch licenses and/or experimental permits that would allow Space Exploration Technologies Corp. (SpaceX) to launch the Falcon 9 and Falcon Heavy orbital vertical launch vehicles and a variety of reusable suborbital launch vehicles from a launch site on privately owned property in Cameron County, Texas, as proposed in the Final Environmental Impact Statement (EIS) published in May 2014. The ROD provides a description of the applicant's Proposed Action and reasonable alternatives, and identifies the FAA's preferred and the environmentally preferred alternative. It includes a discussion of environmental impacts associated with the Proposed Action in each resource area, as analyzed in the Final EIS. The ROD summarizes the mitigation and enforcement actions that would be made the subject of the terms and conditions of the launch licenses and/or experimental permits issued to SpaceX, as well as other conservation and enhancement measures described in the Final EIS and presented for consideration. The Final EIS, prepared by the FAA for the SpaceX Texas Launch Site, serves as the primary reference and basis for preparation of the ROD. The Final EIS documents the analysis of environmental consequences associated with the construction and operation of the SpaceX Texas Launch Site and the No Action Alternative. The FAA is the lead Federal agency responsible for preparation of the EIS and ROD. Cooperating agencies include the National Aeronautics and Space Administration, National Park Service (NPS), U.S. Army White Sands Missile Range, and U.S. Army Corps of Engineers (USACE). The EIS and ROD were prepared pursuant to the requirements of NEPA, the CEQ Regulations for Implementing the Procedural Provisions of NEPA, and FAA Order 1050.1E, Change 1, Environmental Impacts: Policies and Procedures. The FAA has posted the ROD on the FAA Web site at https:// www.faa.gov/about/officeorg/headquartersoffices/ast/environme ntal/ nepadocs/review/documentsprogress/spacextexaslaunchsite environmentalimpactstatement/.

We propose to adopt 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 proposed 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 proposed AD would require 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; 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 proposing this AD to prevent corroded bearings, which could result in a partial or total loss of axial support.

This notice contains a summary of a petition seeking relief from specified requirements of 14 CFR. The purpose of this notice is to improve the public's awareness of, and participation in, this aspect of FAA's regulatory activities. Neither publication of this notice nor the inclusion or omission of information in the summary is intended to affect the legal status of the petition or its final disposition.

We are publishing a new airworthiness directive (AD) for Airbus Helicopters Model MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B- 1, and MBB-BK 117 C-2 helicopters with a certain Metro Aviation, Inc. (Metro), vapor-cycle air conditioning kit pulley (pulley) installed, which was sent previously to all known U.S. owners and operators of these helicopters. This AD supersedes AD 2013-12-06, which required inspecting the pulley for looseness and properly installed lockwire and re-installing the pulley. Since we issued AD 2013-12-06, we received a report of a possible design and manufacturing deficiency in some pulleys wherein they did not have sufficient thread depth, allowing the pulley to detach from the rotor brake disc. This AD requires inspecting each pulley attaching bolt hole to determine if there is sufficient depth of the threads and either removing the pulley if the depth is insufficient or installing dual locking tabs under each pulley attaching bolt if the depth is sufficient. These actions are intended to prevent the pulley from detaching, resulting in damage to the tail rotor (T/R) driveshaft, and subsequent loss of control of the helicopter.

We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-102, -103, and -106 airplanes; and DHC-8- 200 and DHC-8-300 series airplanes. This AD was prompted by a report of a beta warning horn (BWH) system failing to activate when the beta mode was triggered. This AD requires modifying the BWH microswitch installation. We are issuing this AD to prevent the inadvertent activation of ground beta mode during flight, which could lead to engine overspeed, engine damage or failure, and consequent reduced controllability 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), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by the finding of an uncertified main landing gear (MLG) inboard retraction actuator bracket pin installed on an in- service airplane. This AD requires inspection of the MLG inboard retraction actuator bracket for a part number, and replacement if necessary. We are issuing this AD to detect and correct uncertified pins in the MLG inboard retraction actuator bracket, which could result in pin failure, leading to an MLG extension without damping, and a potential for MLG structural damage and possible collapse during landing.

We are superseding Airworthiness Directive (AD) 2008-08-09 for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2008-08-09 required revising the airworthiness limitations (AWL) section of the Instructions for Continued Airworthiness by incorporating procedures for repetitive functional tests of the pilot input lever of the pitch feel simulator (PFS) units and corrective actions if necessary. This new AD requires replacing certain PFS units with new redesigned PFS units, which would terminate the repetitive functional tests; and both adding and removing certain airplanes from the applicability. This AD was prompted by reports that the shear pin in the input lever of several PFS units failed due to fatigue; and by the development of a re-designed PFS unit, which eliminates the need for repetitive functional tests. We are issuing this AD to prevent undetected failure of the shear pins of both PFS units simultaneously, which could result in loss of pitch feel forces and consequent reduced control of the airplane.

We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. This AD was prompted by reports of scribe-line-related fatigue cracks on Model 727 airplanes, which are similar in design to Model 707 airplanes, and Model 720 and 720B series airplanes. This AD requires inspections for scribe lines in the skin lap joints, external approved repairs, external features, skin butt joints, and decals; and related investigative and corrective actions if necessary. This AD also requires surface finish restoration. We are issuing this AD to detect and correct scribe lines, which can develop into fatigue cracks in the skin and cause rapid decompression of the airplane.

We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by reports of severe corrosion on bonding jumpers installed on the flight control surfaces. This AD requires repetitive bonding jumper inspections for corrosion, sealant disbond, and insufficient sealant coverage; and corrective actions if necessary. This AD also specifies an optional inspection for corrosion damage of the bonding brackets, and corrective actions if necessary, which would terminate the repetitive inspections. For certain airplanes, this AD requires installing certain bonding jumpers, and replacing single-tabbed brackets with two-tabbed brackets. We are issuing this AD to detect and correct corrosion on bonding jumpers installed on the flight control surfaces, which, in the event of a lightning strike, could damage the actuator control electronics (ACEs) and result in the loss of the ability to command individual flight control surfaces or cause uncommanded motion of individual flight control surfaces.

We are adopting a new airworthiness directive (AD) for certain Learjet Inc. Model 45 airplanes. This AD was prompted by a report of two cases of premature corrosion found on the structural support flange for the engine thrust reverser. This AD requires inspecting for any corrosion, and damage to the sealant; installing sealants and gaskets; and related investigative and corrective actions as necessary. We are issuing this AD to prevent failure of the thrust reverser structural support, which could result in departure of the thrust reverser from the engine that could subsequently result in damage to the adjacent support structure and engine controls, airframe structure, and control surfaces. Departing thrust reversers could also result in injury to persons on the ground.

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.

We propose to adopt a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211 Trent 875-17, 877-17, 884-17, 884B-17, 892- 17, 892B-17, and 895-17 turbofan engines. This proposed AD was prompted by failure of the intermediate pressure (IP) turbine disk drive arm on an RR RB211 Trent turbofan engine. This proposed AD would require modification of the engine by removing any electronic engine control (EEC) that incorporates EEC software standard prior to version B7.2 and installing an EEC eligible for installation. We are proposing this AD to prevent overspeed failure of the turbine blades or the IP turbine disk, which could lead to uncontained blade or disk release, damage to the engine, and damage to the airplane.

We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) PW120, PW121, PW121A, PW124B, PW127, PW127E, PW127F, PW127G, and PW127M turboprop engines. This AD requires removal of the O-ring seal from the fuel manifold fitting. This AD was prompted by reports of fuel leaks at the interface between the fuel manifold and the fuel nozzle that resulted in engine fire. We are issuing this AD to prevent in-flight fuel leakage, which could lead to engine fire, damage to the engine, and damage to the airplane.