Federal Aviation Administration 2012 – Federal Register Recent Federal Regulation Documents

We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737 airplanes. This AD was prompted by a report of a flightcrew not receiving an aural warning during a lack of cabin pressurization event. This AD requires incorporating design changes to improve the reliability of the cabin altitude warning system by installing a redundant cabin altitude pressure switch, replacing the aural warning module (AWM) with a new or reworked AWM, and changing certain wire bundles or connecting certain previously capped and stowed wires as necessary. For certain airplanes, this AD also requires prior or concurrent incorporation of related design changes by modifying the instrument panels, installing light assemblies, modifying the wire bundles, and installing a new circuit breaker, as necessary. We are issuing this AD to prevent the loss of cabin altitude warning, which could delay flightcrew recognition of a lack of cabin pressurization, and could result in incapacitation of the flightcrew due to hypoxia (a lack of oxygen in the body), and consequent loss of control of the airplane.

We are adopting a new airworthiness directive (AD) for certain of The Boeing Company Model 777 airplanes. This AD was prompted by heat damage and cracks at the pivot joint location of the main landing gear (MLG) inner cylinder/truck beam. This AD requires repetitive lubrication of the MLG pivot joints; repetitive detailed inspections of the outer diameter chrome on the center axles of the MLG for chicken- wire cracks, corrosion, and chrome plate distress; repetitive magnetic particle inspections of the outer diameter chrome on the center axles of the MLG for cracks; and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct cracking in the MLG center axle and shock strut inner cylinder lugs (pivot joint), which could result in fracture of the MLG pivot joint components and consequent collapse of the MLG.

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. 14 CFR part 21 prescribes certification standards for aircraft, aircraft engines, propellers appliances and parts. The information collected is used to determine compliance and applicant eligibility. The respondents are aircraft parts designers, manufacturers, and aircraft owners.

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 information collected will be used to evaluate the qualifications of applicants for a variety of positions within the FAA.

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 July 19, 2012, vol. 77, no. 139, page 42547-42548. To obtain type certification of a rotorcraft, applicants must submit substantiating data to show that the rotorcraft complies with specific certification requirements.

We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This proposed AD was prompted by reports of engine fire/overheat detector assemblies advance pneumatic detectors (APDs) failing to reset after activation due to permanent deformation of the detector switch diaphragm after being exposed to high temperatures. This proposed AD would require replacing all three APDs with new detector assemblies. We are proposing this AD to prevent a continued engine fire indication in the cockpit after the actual fire has been extinguished, which is misleading and may influence the pilot to conduct a potentially hazardous ``off-airport'' landing.

We propose to supersede an existing airworthiness directive (AD) that applies to all Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. The existing AD currently requires repetitive inspections to detect discrepancies of the transfer tubes and the collar of the ball nut of the trimmable horizontal stabilizer actuator (THSA), and corrective action if necessary; repetitive inspections for discrepancies of the ball screw assembly, and corrective action if necessary; repetitive greasing of the THSA ball nut, and replacement of the THSA if necessary; and modification or replacement (as applicable) of the ball nut assembly, which would end certain repetitive inspections. Since we issued that AD, we have determined the repetitive inspections of the ball screw assembly (and corrective action if necessary) and repetitive greasing is needed for additional THSA nuts. This proposed AD would remove certain inspections, revise certain actions, and add airplanes to the applicability. We are proposing this AD to prevent degraded operation of the THSA, which could result in reduced controllability of the airplane.

This document announces the availability of and request for comments on the Initial Regulatory Flexibility Analysis for the previously published proposed airworthiness directive (AD) on Cessna Aircraft Company 310, 320, 340, 401, 402, 411, 414, and 421 airplanes regarding the installation of placards requiring flight limitations in icing conditions.

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 are adopting a new airworthiness directive (AD) for certain Airbus Model A340-500 and -600 series airplanes. This AD requires repetitive inspections for corrosion of the drag stay lower arm assembly of the nose landing gear (NLG), and replacement if necessary. This AD also requires eventual replacement of the drag stay lower arm assembly of the NLG with an improved assembly having corrosion protection, which terminates the repetitive inspections required by this AD. This AD was prompted by findings of corrosion traces in the lugs and on the bearing outer surface of the NLG during routine maintenance checks. We are issuing this AD to prevent failure of the drag stay lower arm, which could result in NLG collapse and consequent reduced controllability of the airplane during takeoff.

We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model DC-10-10, DC-10-10F, DC-10-15, DC- 10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F airplanes. That AD currently requires installing or replacing with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane; and for certain airplanes, repositioning or replacing two bonding straps, doing a bonding-resistance check and an inspection to determine correct installation of certain bonding straps, and applicable corrective actions. This new AD adds airplanes to the applicability and, depending on the airplane configuration, requires installing new braided bonding straps, inspecting to determine if a certain strap is installed and replacing with or installing a braided bonding strap if necessary, measuring the electrical resistance of the bonding straps, verifying that brackets have an acceptable fillet seal, and doing corrective actions if necessary. This AD was prompted by fuel system reviews conducted by the manufacturer, and our determination that additional actions are necessary to address the identified unsafe condition. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks in the event of a severe lightning strike, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.

This supplemental notice of proposed rulemaking would rename the city designator listed under the title in the preamble and regulatory text for Tri-Cities Regional Airport, and establish Class E airspace extending upward from 700 feet above the surface at Hawkins County Airport, Rogersville, TN, and Virginia Highlands Airport, Abington, VA. The Tri-Cities Class D airspace description would be amended to better describe the controlled airspace area. In an NPRM published in the Federal Register on April 10, 2012, the FAA proposed to amend existing controlled airspace extending upward from 700 feet above the surface at Tri-Cities Airport, Blountville, TN, that included the airports mentioned above. The FAA has reassessed the proposal and finds that separation of existing Class E airspace surrounding Virginia Highlands Airport, Abingdon, VA, and Hawkins County Airport, Rogersville, TN, from the Class E airspace area of Tri-Cities Regional Airport, Tri-Cities, TN, is necessary to further the safety and management of Instrument Flight Rules (IFR) operations in the Tri- Cities, TN area.

This notice announces a public meeting of the FAA's Aviation Rulemaking Advisory Committee (ARAC) to discuss transport airplane and engine (TAE) issues.

We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called A300-600 series airplanes); and Model A310 series airplanes. This proposed AD was prompted by reports of cracking through the honeycomb core closed with phenolic resin. This condition could result in extended debonding and could adversely affect the structural integrity of the rudder. This proposed AD would require inspecting to determine the serial number of a certain rudder and replacing the rudder with a new or serviceable rudder if necessary. We are proposing this AD to prevent extended de-bonding, which could result in loss of the rudder and consequent reduced controllability of the airplane.

This action proposes special conditions for the Embraer Model EMB-550 airplane. This airplane will have a novel or unusual design feature associated with the effects of sudden engine stoppage upon the airframe. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. 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.

We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B, EC155B1, SA-365N1, AS- 365N2 and AS 365 N3 helicopters to require visually inspecting the tail rotor hub (TRH) for a crack and removing the TRH if a crack exists. This AD is prompted by reports of cracks on two TRHs. These actions are intended to prevent the tail rotor from jamming, which could lead to reduced or loss of control of the helicopter.

We propose to adopt a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (Bell), Model 412 and 412EP helicopters. This proposed AD is prompted by reports of cracking in the swashplate outer ring assemblies (outer ring). This AD would establish a lower life limit on certain outer rings, requiring a revision of the retirement life on the components' history card or equivalent record, and a revision of the maintenance manual or Instructions for Continued Airworthiness (ICA). This proposal also would prohibit installing these outer rings on any helicopter. The proposed actions are intended to prevent failure of an outer ring because of cracking, which could lead to the loss of main rotor (M/R) blade pitch control and subsequent loss of helicopter control.

We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This proposed AD was prompted by a new revision to the airworthiness limitations of the maintenance planning data document. This proposed AD would require revising the maintenance program to update inspection requirements to detect fatigue cracking of principal structural elements (PSEs). We are proposing this AD to detect and correct fatigue cracking of various PSEs, which could adversely affect the structural integrity of these airplanes.

We propose to supersede an existing airworthiness directive (AD) that applies to 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. The existing AD currently requires repetitive inspections of the rudder travel limiter (RTL) return springs and primary actuator, and corrective actions if necessary. Since we issued that AD, terminating action has been developed which eliminates the need for the repetitive inspections. This proposed AD would require replacing certain RTL return springs, including doing related investigative and corrective actions, if necessary; and would also revise the applicability. We are proposing this AD to prevent failure of the RTL, which would permit an increase of rudder authority beyond normal structural limits and consequently affect the controllability of the airplane.

We are adopting a new airworthiness directive (AD) all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 airplanes, and Model EMB-145, -145ER, -145MR, -145LR, -145MP, and -145EP airplanes. This AD was prompted by a report of a lightning strike hitting an airplane tail boom causing certain rear bulkhead parts to jam an elevator control rod. This AD requires installing or reworking, as applicable, metallic diverters and aluminum sheets; modifying the light assembly on the tail boom rear movable fairing; and replacing the hood assembly with a new hood assembly and rerouting its electrical harness. We are issuing this AD to prevent lightning strikes from causing certain parts to contact the airplane pitch control system, which could reduce airplane controllability.

We are adopting a new airworthiness directive (AD) for General Electric Company GEnx-1B54, GEnx-1B58, GEnx-1B64, GEnx-1B67, GEnx-1B70, GEnx-1B54/P1, GEnx-1B58/P1, GEnx-1B64/P1, GEnx-1B67/P1, GEnx-1B70/P1, GEnx-1B70/72/P1, GEnx-1B70/75/P1, GEnx-1B74/75/P1, GEnx-1B75/P1, GEnx- 2B67, and GEnx-2B67B turbofan engines. This AD requires initial and repetitive ultrasonic inspections (UI) of certain part number (P/N) fan mid shafts (FMS) for cracks. This AD was prompted by a report of an FMS failure and a report of a crack found in another FMS. We are issuing this AD to prevent failure of the FMS resulting in one or more engine failure(s) and possible loss of the airplane.

Under this notice, the FAA announces the submission deadline of October 11, 2012, for Summer 2013 flight schedules at Chicago's O'Hare International Airport (ORD), San Francisco International Airport (SFO), New York's John F. Kennedy International Airport (JFK), and Newark Liberty International Airport (EWR) in accordance with the International Air Transport Association (IATA) Worldwide Slot Guidelines. The deadline coincides with the schedule submission deadline for the IATA Slots Conference for the Summer 2013 scheduling season.

We propose to supersede an existing airworthiness directive (AD) that applies to all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. The existing AD currently requires repetitive inspections of the aft attach lugs of the elevator tab control mechanisms, and replacement of any discrepant elevator tab control mechanism. Since we issued that AD, Boeing has developed a modification of the aft attach lugs of the elevator tab control mechanisms, which will adequately address the unsafe condition. This proposed AD would require replacing the left and right elevator tab control mechanisms with elevator tab control mechanisms that have the modified attach lugs, which would terminate the existing requirements. We are proposing this AD to prevent discrepancies in the aft attach lugs of the elevator tab control mechanism, which could result in severe elevator and tab vibration. Consequent structural failure of the elevator or horizontal stabilizer could result in loss of structural integrity and aircraft control.

We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, 737-400, 737-500, and 757-200 series airplanes. This proposed AD was prompted by a report of damage caused by electrical arcing to the wires that connect seat electronics boxes (SEBs). This proposed AD would require installing a new relay and doing certain wiring changes of the entertainment control switch if necessary. We are proposing this AD to prevent power from being supplied to passenger seats when the entertainment control switch is in the OFF position, which could cause an electrical shock hazard resulting in serious or fatal injury to maintenance personnel.

We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This proposed AD was prompted by a report of chafing damage to a wire bundle that was arcing to hydraulic tubing and caused by insufficient separation between the wire bundle and the hydraulic tubing in the main landing gear (MLG) wheel well. This proposed AD would require an inspection for damage of wire bundles and hydraulic tubing on the right side of the forward bulkhead of the MLG wheel well; installation of new clamps; and corrective actions, as applicable. We are proposing this AD to detect and correct possible damage caused by insufficient separation between the wire bundles and hydraulic tubing to prevent electrical arcing in a flammable fluid leakage zone, which could lead to a wheel well fire.