Federal Aviation Administration June 2015 – Federal Register Recent Federal Regulation Documents

We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model EC135P1, EC135T1, EC135P2, EC135T2, EC135P2+, EC135T2+, and MBB-BK 117 C-2 helicopters. This AD requires inspecting certain washers for movement and making appropriate repairs if the washers move. This AD was prompted by play found between the Smart Electro Mechanical Actuator (SEMA) and the control rod during installation work on a helicopter. The actions of this AD are intended to prevent loss of concerned control axis and subsequent loss of control of the helicopter.

We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model and 777 airplanes. This AD was prompted by reports of uncommanded door closure of a large lower lobe cargo door. This AD requires inspecting for part numbers and serial numbers of the rotary actuators of the forward and aft large lower lobe cargo doors, as applicable, and corrective action if necessary. We are issuing this AD to detect and correct rotary actuators made with a material having poor actuator gear wear characteristics, which could result in failure of the rotary actuators for the forward or aft large lower lobe cargo doors and subsequent uncommanded door closure, which could possibly result in fatal injury to people on the ground.

This notice contains a summary of a petition seeking relief from specified requirements of Title 14 of the Code of Federal Regulations. The purpose of this notice is to improve the public's awareness of, and participation in, the FAA's exemption process. 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 propose to adopt a new airworthiness directive (AD) for all General Electric Company (GE) GEnx-1B turbofan engine models. This proposed AD was prompted by reports of GEnx-1B engine oil loss. This proposed AD would require removal and replacement of the non-conforming ball valve in the oil filler cap. We are proposing this AD to prevent loss of engine oil, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane.

This rulemaking proposes to relieve burdens on pilots seeking to obtain aeronautical experience, training, and certification by increasing the allowed use of aviation training devices. These actions are necessary to bring the regulations in line with current needs and activities of the general aviation training community and pilots.

These special conditions are issued for the Honda Aircraft Company model HA-420 airplane. This airplane will have a novel or unusual design feature associated with mounting the engines on the wings in close proximity to the aft fuselage. 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 propose to supersede Airworthiness Directive (AD) 97-02-02, which applies to certain Models SA26-AT, SA26-T, SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), and SA227-TT airplanes. AD 97-02-02 currently requires applying torque to the control column pitch bearing attaching nuts, inspecting the bearing assembly, inspecting the elevator control rod end bearing retainer/dust seals, and replacing or installing new parts as necessary. Since we issued AD 97-02-02, an operator experienced a complete loss of elevator control because of failure of the bolt attaching the elevator control rod to the elevator walking beam under the cockpit floor. This proposed AD would prevent loss of pitch control, which if not corrected, could result in loss of airplane control. We are proposing this AD to correct the unsafe condition on these products.

We are publishing a new airworthiness directive (AD) for Agusta Model A109A and A109A II helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires replacing a certain part-numbered blade with an approved part- numbered blade. This AD is prompted by an error in the Illustrated Parts Catalog (IPC) that incorrectly allows installation of a certain part-numbered blade on the affected helicopters. These actions are intended to prevent blade failure and subsequent loss of control of the helicopter.

We are adopting a new airworthiness directive (AD) for certain Learjet Inc. Model 45 airplanes. This AD was prompted by reports of non-conforming windshield supports (coupe rails). This AD requires a general visual inspection of the coupe rails to detect gouging and scratches, and to determine if a radius has been removed; an ultrasound inspection to measure the dimensions of the lower coupe rails; an eddy current inspection to detect cracks of the lower coupe rails; replacement of the lower coupe rails if necessary; and revision of the maintenance or inspection program, as applicable. We are issuing this AD to detect and correct non-conforming windshield supports, which could result in uncontrolled cabin depressurization and compromise of the capability of the windshield to withstand a bird strike.

This action establishes Class E airspace at the Tucumcari VHF Omni-Directional Radio Range Tactical Air Navigation Aid (VORTAC), Tucumcari, NM, to facilitate vectoring of Instrument Flight Rules (IFR) aircraft under control of Albuquerque Air Route Traffic Control Center (ARTCC). This action enhances the safety and efficiency of aircraft operations within the National Airspace System (NAS).

We are superseding Airworthiness Directive (AD) 2008-06-18 for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A300 series airplanes. AD 2008- 06-18 required repetitive inspections for any cracking of the wing lower skin panel and associated internal support structure, and if necessary, corrective actions such as modifying the lower panel inboard of rib 9 aft of the rear spar and repairing cracks. This new AD continues to require actions required by AD 2008-06-18, and reduces certain compliance times. This AD was prompted by a report that information from an analysis and a fleet survey shows a need for reduced compliance times and intervals. We are issuing this AD to detect and correct cracking, which could lead to reduced structural integrity of the airplane.

We are revising an earlier proposed airworthiness directive (AD) for Bell Helicopter Textron Canada (Bell) Model 222, 222B, 222U, 230, and 430 helicopters, which proposed to require replacing certain servo actuators before further flight. The NPRM was prompted by a collective servo actuator malfunction. This action revises the NPRM by adding new actions. Since these actions impose an additional burden over that proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these proposed changes.

This action reopens the comment period for the regulatory evaluation associated with the FAA's January 13, 2015 Notice of Proposed Rulemaking (NPRM), Reciprocal Waivers of Claims for Licensed or Permitted Launch and Reentry Activities. The FAA has discovered that this regulatory evaluation was not posted to the docket prior to the close of the NPRM's comment period. Therefore, the FAA is reopening the comment period to allow the public the opportunity to adequately analyze the full regulatory evaluation for the NPRM. The FAA will accept comment on the regulatory evaluation only, and not on the regulatory changes proposed in the NPRM.

This notice contains a summary of a petition seeking relief from specified requirements of Title 14 of the Code of Federal Regulations. The purpose of this notice is to improve the public's awareness of, and participation in, the FAA's exemption process. 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.

This action withdraws the NPRM published in the Federal Register on May 6, 2014, proposing to amend Class E airspace in the State of South Dakota. The FAA has determined that withdrawal of the NPRM is warranted as additional analysis is needed.

We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This proposed AD was prompted by reports of fatigue cracking of a certain chord of the pivot bulkhead. This proposed AD would require repetitive inspections for cracking of the left side and right side forward outer chords of the pivot bulkhead, and related investigative and corrective actions if necessary. This proposed AD provides a modification of the pivot bulkhead, which would terminate the repetitive inspections. We are proposing this AD to detect and correct fatigue cracking of the outer flanges of the left and right side forward outer chords of the pivot bulkhead, which could result in a severed forward outer chord and consequent loss of horizontal stabilizer control.

We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, and A340-300 series airplanes. This proposed AD was prompted by reports that the inner bore of some main landing gear (MLG) unit bogie beams were insufficiently re-protected against corrosion after inspection or maintenance actions were accomplished. This proposed AD would require, for certain MLG units, determining which revision of the component maintenance manual (CMM) was used to accomplish the most recent MLG unit overhaul; a detailed inspection for missing or damaged paint, and if necessary, a detailed inspection of the cadmium plating for discrepancies, measurement of the depth of the cadmium plating, a general visual inspection of the base metal for corrosion or damage, a detailed inspection of repaired areas for cracking or corrosion; and corrective actions if necessary. We are proposing this AD to detect and correct corrosion in the bore of each MLG unit bogie beam, which could result in collapse of a MLG unit, and subsequent damage to the airplane and injury to occupants.

This action establishes Class E airspace at Tribune, KS. Controlled airspace is necessary to accommodate new Standard Instrument Approach Procedures (SIAPs) at Tribune Municipal Airport. The FAA is taking this action to enhance the safety and management of Instrument Flight Rules (IFR) operations for SIAPs at the airport.

The FAA is issuing this notice to advise the public that an Environmental Impact Statement (EIS) will be prepared for proposed improvements to the Norfolk International Airport (ORF). In October 2008, the Norfolk Airport Authority (NAA), owner and operator of ORF, prepared a Master Plan Update (MPU) to document changes occurring ``in Airport facilities and activity that have taken place since the 1995 Master Plan Update,'' to ``provide the Authority with a development plan for the Airport through 2024,'' and to address compliance shortfalls with published safety standards. Following the MPU, NAA prepared technical documents that focused on the potential construction of a replacement secondary runway. The first was the December 2008 Supplemental Technical Analyses for the Proposed Secondary Runway at Norfolk International Airport and the second was the December 2009 Justification for Proposed Runway 5R/23L. In 2008 NAA also developed an Airport Layout Plan (ALP) that evaluated and noted future development needs at ORF. The ALP included a Capital Improvement Program (CIP) for the Airport to address Federal Aviation Administration (FAA) design standards for the Airport's existing crosswind Runway 14/32. During its planning process, NAA explored a number of alternatives to meet FAA design standards while also providing the flexibility needed to operate without interruption during various conditions. These alternatives included the potential construction of a replacement secondary runway as well as improvements to the existing crosswind Runway 14/32. The FAA will evaluate and consider the Airport's MPU, ALP, and associated planning efforts when considering reasonable and feasible alternatives for the ORF EIS. Based on these previous planning efforts, the primary components of NAA's proposed project at ORF include: Decommissioning and demolition of Runway 14/32 Constructing a relocated secondary runway parallel to and separated by 876 feet from the existing Runway 5/23. The proposed Runway 5R/23L would be 6,500 feet long by 150 feet wide. The purpose of the proposed project is: To meet relevant FAA airfield safety standards and enhance airfield safety without reducing runway availability. Relevant airfield safety standards include: [cir] Runway Safety Area, which is designed to provide additional safety in the event an aircraft leaves the runway; [cir] Runway Protection Zone, which is area at ground level prior to the threshold or beyond the runway end to enhance the safety and protection of people and property on the ground; and [cir] Runway Object Free Area, which is designed to provide an area clear of objects surrounding a runway. To enhance operational efficiency and maintain airfield utility while considering surrounding airspace and ORF's critical design aircraft. To provide a safe, efficient southern vehicular access, on Airport property, to the Airport's terminal area. The proposed project is needed to address the following four primary areas of deficiency at ORF: Runway 14/32 does not meet the FAA design standards discussed above for several reasons, including, but not limited to, the location of Robin Hood Road and Lake Whitehurst near the Runway 14 end. The current airfield configuration limits operational efficiency, safety and flexibility due to secondary runway length and challenges in taxiing from the airfield layout. Provide a flexible two-runway airfield system for aircraft operators and air traffic controllers. Incremental changes over time have severely decreased ORF's ability to remain flexible with increasing airspace conflicts from surrounding military facilities. Robin Hood Road, the secondary (southern) access to the Airport, has safety and functional deficiencies. Specifically, several curves in the on-airport section of Robin Hood Road can be improved through a redesign of the roadway.

These special conditions are issued for the CFM International (CFM), LEAP-1A and -1C engine models. These engine models will have a novel or unusual design feature associated with the engine fan blades new woven composite fan blades. 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 propose to adopt a new airworthiness directive (AD) for British Aerospace Regional Aircraft Jetstream Series 3101 and Jetsream Model 3201 airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated 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 missing countersunk washers under the head of the main landing gear trunnion cap tension bolts that could cause fatigue in the bolt shanks. We are issuing this proposed AD to require actions to address the unsafe condition on these products.

We are adopting a new airworthiness directive (AD) for certain Bell Helicopter Textron Canada Limited (Bell) Model 206L-1, 206L-3, and 206L-4 helicopters. This AD requires installing a placard and revising the limitations section of the rotorcraft flight manual (RFM). This AD was prompted by several incidents of third stage engine turbine wheel failures caused by excessive vibrations at certain engine speeds during steady-state operations. The actions of this AD are intended to prevent turbine failure, engine power loss, and subsequent loss of control of the helicopter.

We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (type certificate previously held by Schweizer Aircraft Corporation) (Sikorsky) Model 269D and Model 269D Configuration A helicopters. This AD requires reducing the life limit of the ring gear carrier assembly. This AD was prompted by cracks in the ring gear carrier assembly. The actions are intended to reduce the life of the ring gear carrier assembly to prevent failure of the main rotor transmission, loss of engine power to the main rotor, and subsequent loss of control of the helicopter.

We are adopting a new airworthiness directive (AD) for Sikorsky Model S-92A helicopters. This AD requires installing a main gearbox (MGB) failed pump sensor and vacuum switch wiring, installing an MGB oil auto bypass system, activating Aircraft Management System (AMS) 7.1 software to show a new visual warning, and installing updated enhanced ground proximity warning system (EGPWS) software that includes an aural annunciation of a complete oil pressure loss condition. This AD also requires inserting a Rotorcraft Flight Manual (RFM) Supplement into the applicable RFM. This AD was prompted by investigation results of in- service oil leakage incidents. The actions are intended to alert and prevent MGB oil loss, which could lead to failure of the MGB and subsequent loss of control of the helicopter.

We are superseding Airworthiness Directive (AD) 95-26-11 for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011 series airplanes. AD 95-26-11 required repetitive inspections to detect cracking of the fittings that attach the aft pressure bulkhead to the fuselage stringers, repetitive inspections to detect cracking of the fittings and of the splice tab of the aft pressure bulkhead, and corrective actions if necessary. This new AD requires repetitive inspections to detect cracking of the fittings that attach the aft pressure bulkhead to the fuselage stringers, repetitive inspections to detect cracking of the fittings and of the splice tab of the aft pressure bulkhead, repetitive inspections for cracking of certain aft fuselage skin panels, a structural modification, a post- modification inspection program, and corrective actions if necessary. This AD was prompted by a determination that the fittings at stringer attachments to the upper region of the aft pressure bulkhead are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent simultaneous failure of multiple stringer end fittings through fatigue cracking at the aft pressure bulkhead, which could lead to rapid decompression of the airplane.