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

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.

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.

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

We propose to supersede airworthiness directive (AD) 2014-04- 14 for AgustaWestland Model A109S, AW109SP, A119, and AW119 MKII helicopters. AD 2014-04-14 currently requires removing certain rod end assemblies from service because of reports of fractures. Since we issued AD 2014-04-14, additional fractured rod end assemblies have been reported. This proposed AD would retain the requirements of AD 2014-04- 14 but expand the scope of applicable rod end assemblies. These proposed actions are intended to prevent failure of a rod end assembly, which could result in damage to the main rotor assembly and loss of control of the helicopter.

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 propose to adopt a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R[eacute]gional Model ATR42 and ATR72 airplanes. This proposed AD was prompted by reports of fuel quantity indication malfunctions caused by fuel probe failure. This proposed AD would require identifying the part number and serial number of the fuel probes and replacing if necessary. We are proposing this AD to prevent fuel probe failure, which could lead to undetected fuel starvation and consequent dual engine in-flight flame-out.

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 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.

This action would amend certain airworthiness regulations for transport category airplanes to require fuel tank designs that prevent a fuel tank explosion caused by flame propagation through the fuel tank vents from external fires. This action would add a new requirement for fuel tank vent fire protection and would increase the time available for passenger evacuation and emergency response. This proposed amendment would apply to applications for new type certificates and certain applications for amended or supplemental type certificates. It would also require certain airplanes produced in the future and operated by air carriers to meet the new standards.

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 propose to adopt a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 2000 and FALCON 2000EX airplanes. This proposed AD was prompted by a design review, which revealed that the forward servicing compartment (FSC) is configured with tie-down points. This proposed AD would require inspecting the FSC for installed tie-down points, and removing those tie-down points. We are proposing 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.

We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This proposed AD was prompted by issuance of revised certification maintenance requirements (CMR) for the horizontal stabilizer trim actuator (HSTA). This proposed AD would require revising the maintenance or inspection program. We are proposing 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 action amends the legal descriptions of Jet Route J-34 and VHF omnidirectional range (VOR) Federal airways V-274, V-285, and V-510, in the vicinity of Grand Rapids, MI. The FAA is taking this action because the name of the Grand Rapids, MI, VOR/Distance Measure Equipment (VOR/DME) facility, which is included in the descriptions of the above routes, is being changed to the Victory VOR/DME.

The Federal Aviation Administration (FAA) announced its findings on the noise compatibility program submitted by the Seattle- Tacoma International Airport under the provisions of 49 U.S.C. (the Aviation Safety and Noise Abatement Act, hereinafter referred to as ``the Act'') and 14 CFR Part 150 on May 29, 2014. These findings were made in recognition of the description of Federal and nonfederal responsibilities in Senate Report No. 96-52 (1980). On December 13, 2013, the FAA determined that the noise exposure maps submitted by the Seattle-Tacoma International Airport under Part 150 were in compliance with applicable requirements. On May 29, 2014, the FAA approved the Seattle-Tacoma International Airport Noise Compatibility Program in a Record of Approval (ROA), which was published in the Federal Register on June 12, 2014. Subsequent to the Federal Register publication, FAA recognized that a measure was inadvertently omitted from the ROA. This measure has been added via an errata sheet. Measure M-14Sound insulate eligible owner- occupied multi-family (condominiums) within the modified noise remedy boundary was included in the Noise Compatibility Program and vetted with the public through the Part 150 process. As stated in the errata sheet, FAA has approved this measure.

This action modifies jet routes J-64 and J-80, and removes jet route J-77, in the northeastern United States. The FAA is taking this action to remove segments that are receiving minimal to no usage due to other more efficient routes in the area. This action eliminates the unneeded route segments, reduces aeronautical chart clutter and improves chart readability.

We propose to supersede Airworthiness Directive (AD) 2011-13- 11 and AD 2013-16-09, for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2011-13-11 currently requires an amendment of the airplane flight manual (AFM), repetitive checks of specific centralized fault display system (CFDS) messages, an inspection of the opening sequence of the main landing gear (MLG) door actuator for discrepancies if certain messages are found, and corrective actions if necessary. AD 2013-16-09 currently requires an inspection to determine airplane configuration and part numbers of the landing gear control interface unit and MLG door actuators; and, for affected airplanes, repetitive inspections of the opening sequence of the MLG door actuator, and replacement of the MLG door actuator if necessary; and provides optional terminating action for the repetitive inspections. Since we issued AD 2011-13-11 and AD 2013-16-09, we have determined that the interval of the MLG door opening sequence inspection must be reduced. This proposed AD would reduce the interval of the MLG door opening sequence inspection. This proposed AD would also require replacing or modifying certain MLG door actuators. We are proposing this AD to detect and correct deterioration of the damping ring and associated retaining ring of the MLG door actuator, which can sufficiently increase the friction inside the actuator to restrict opening of the MLG door by gravity, during operation of the landing gear alternate (free-fall) extension system. This condition could prevent the full extension and/or down-locking of the MLG, possibly resulting in MLG collapse during landing and consequent damage to the airplane and injury to occupants.

We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A330-300 and A340-200 and -300 series airplanes. This proposed AD was prompted by a report of substantial inner skin disbonding damage found on a rudder. This proposed AD would require performing an inspection for damage of certain rudders, and repair if necessary. We are proposing this AD to detect and correct damage of the rudder, which could result in reduced structural integrity of the rudder.

The Federal Aviation Administration (FAA) announces its determination that the noise exposure maps for Portsmouth International Airport at Pease, as submitted by the Pease Development Authority under the provisions of Title I of the Aviation Safety and Noise Abatement Act of 1979 (Pub. L. 96-193) and 14 CFR Part 150, are in compliance with applicable requirements.

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 the maintenance actions for airplane systems susceptible to aging must be mandated. This proposed AD would require revising the maintenance or inspection program to incorporate more restrictive maintenance requirements and airworthiness limitations. We are proposing 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.

This rule amends the FAA's repair station regulations to allow the FAA to deny an application for a new repair station certificate if the applicant or certain associated key individuals had materially contributed to the circumstances that caused a previous repair station certificate revocation action. The rule also adds a new section prohibiting fraudulent or intentionally false entries or omissions of material facts in any application, record, or report made under the repair station rules, and provides that making the fraudulent or intentionally false entry or omitting or concealing the material fact is grounds for imposing a civil penalty and for suspending or revoking any certificate, approval, or authorization issued by the FAA to the person who made or caused the entry or omission. These changes are necessary because the repair station rules do not presently provide these safeguards as do other parts of the FAA's regulations. Both of these changes will enhance safety by reducing the number of individuals in the repair station industry who commit intentional and serious violations of the regulations or who demonstrate they are otherwise unqualified to hold repair stations certificates.

This rulemaking provides the opportunity for an informal conference with an FAA attorney before an order is issued under the FAA's regulation covering orders other than certificate action and civil penalty orders. This change is necessary to provide additional fairness and process to those persons who are subject to such an order, and is consistent with the process available in other enforcement actions. These conferences may result in either a resolution of the matter or a narrowing of the issues, thereby conserving resources for respondents and the FAA.