Federal Aviation Administration 2005 – Federal Register Recent Federal Regulation Documents

The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 875, 877, 884, 892, 892B, and 895 series turbofan engines with certain part number (P/N) low pressure compressor (LPC) fan blades installed. That AD currently requires initial and repetitive ultrasonic inspections of the fan blade dovetail roots. This AD requires the same actions except at reduced compliance times for certain blades, defines a specific terminating action to the repetitive blade inspection requirements, and adds the 884B series to the applicability. This AD results from a report of a cracked fan blade found before the blade reached the initial inspection threshold of AD 2002-11-08. This AD also results from the need to reduce a repetitive inspection compliance time due to potential breakdown of blade coating and lubrication on certain blades. We are issuing this AD to prevent multiple LPC fan blade failures due to cracks, which could result in uncontained engine failure and possible damage to the airplane.

The FAA proposes to adopt a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This proposed AD would require doing repetitive detailed inspections for accumulation of debris (blockage) of the drain holes of the pitot tubes, and cleaning if any evidence of debris is found. This proposed AD is prompted by reports of blocked drain holes of the pitot tubes. We are proposing this AD to prevent blocked drain holes of the pitot tubes, which could result in the accumulation of water in the pitot- static system and consequent failure of that system. Failure of the pitot-static system could result in erroneous airspeed indications in the cockpit and consequent loss of airspeed control.

This action withdraws a notice of proposed rulemaking (NPRM) that proposed a new airworthiness directive (AD), applicable to certain McDonnell Douglas 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. That action would have required installing shield assemblies for power feeder cables in the forward and aft lower cargo compartments, and installing an additional shield for the power feeder cable of the auxiliary power unit in the aft lower cargo compartment. Since the issuance of the NPRM, the Federal Aviation Administration (FAA) has determined that the proposed requirements are included in the requirements of another existing AD; the NPRM does not contain any new requirements beyond those of the existing AD. Accordingly, the proposed rule is withdrawn.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Eagle Aircraft (Malaysia) Sdn. Bhd. Model Eagle 150B airplanes. This proposed AD would require you to modify or replace the co-pilot rudder pedal assembly. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Malaysia. We are issuing this proposed AD to prevent binding of the co-pilot rudder pedal assembly due to premature wear of the bushing, which could result in loss of co-pilot rudder and brake control. This failure could result in loss of control of the airplane.

These special conditions are issued for Learjet Model 35, 35A, 36, and 36A airplanes modified by ARINC, Inc. These modified airplanes will have a novel or unusual design feature when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. The modification is the installation of a Thommen AD32 Air Data Display Unit (ADDU) which incorporates a digital air data computer and altimeter. This equipment will perform critical functions. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for the protection of these systems from the effects of high-intensity radiated fields (HIRF). 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 (FAA) announces its determination that the noise exposure maps (NEM) submitted by the airport director for King County International Airport under the provisions of 49 U.S.C. 47501 et seq. (Aviation Safety and Noise Abatement Act) and 14 CFR part 150 are in compliance with applicable requirements. The FAA also announces that it is reviewing a proposed noise compatibility program that was submitted for King County International Airport under part 150 in conjunction with the noise exposure map, and that this program will be approved or disapproved on or before June 21, 2005.

This document corrects an error that appears in the Code of Federal Regulations (CFR), title 14, as of January 1, 2004. The regulation relates to attitude-indicating instruments that are required to be installed on transport category rotorcraft.

Pursuant to FAA's rulemaking provisions governing the application, processing, and disposition of petitions for exemption, part 11 of Title 14, Code of Federal Regulations (14 CFR), this notice contains a summary of certain petitions 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 any petition or its final disposition.

The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Boeing Model 707 airplanes and Model 720 and 720B series airplanes. The existing AD currently requires a preventive modification of the front spar fitting on the outboard engine nacelle. This proposed AD would remove the requirement to do this preventive modification, and would require repetitive inspections for cracking of the front spar fitting of the inboard and outboard nacelle struts, and replacement of any cracked fitting with a new fitting. The proposed AD would also apply to more airplanes. This proposed AD is prompted by a report indicating that a crack was found in a front spar fitting that had been replaced as part of the modification required by the existing AD. We are proposing this AD to detect and correct this cracking, which could result in reduced structural integrity of the engine nacelle, and consequent separation of an engine from the airplane.

The FAA is superseding an existing airworthiness directive (AD) for Bombardier-Rotax GmbH Type 912 F, 912 S, and 914 F series reciprocating engines. That AD currently requires venting of the lubrication system and inspection of the valve train on all engines. That AD also requires venting of the lubrication system of all engines on which the lubrication system has been opened, and any engine on which the propeller has been rotated one full turn in the wrong direction. This AD requires similar actions, and also requires removing the existing part number oil dipstick from service and installing a new oil dipstick. This AD results from the need to clarify the mandated procedures for inspections and venting. This AD also results from the manufacturer discovering that under certain circumstances, the oil level in the oil tank can fall below the minimum level required to sustain proper engine lubrication. We are issuing this AD to prevent damage to the engine valve train due to inadequate venting of the lubrication system, which can result in an in-flight engine failure and forced landing.

This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200, -200PF, and -200CB series airplanes, that requires an inspection of certain ballscrews of the trailing edge flap system to find their part numbers, and replacement of the ballscrews with new, serviceable, or modified ballscrews if necessary. This action is necessary to prevent a flap skew due to insufficient secondary load path of the ballscrew of the trailing edge flaps in the event that the primary load path fails, which could result in possible loss of a flap and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.

This notice proposes to create a Class E surface area at Ames, IA. It also proposes to modify the Class E5 airspace at Ames, IA.

This document confirms the effective date of the direct final rule which revises Class E airspace at Lexington, MO.

This document confirms the effective date of the direct final rule which revises Class E airspace at Sedalia, MO.

These special conditions are issued to The New Piper Aircraft, Inc.; Vero Beach, Florida, for a type design change for the PA-46-350P and PA-46-500TP model airplanes. These airplanes will have novel and unusual design features when compared to the state of technology envisaged in the applicable airworthiness standards. These novel and unusual design features include the installation of electronic flight instrument system (EFIS) displays Model 700-00006-003 Entegra, manufactured by Avidyne Corporation, Inc., for which the applicable regulations do not contain adequate or appropriate airworthiness standards for the protection of these systems from the effects of high intensity radiated fields (HIRF). These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to the airworthiness standards applicable to these airplanes.

This final rule establishes procedures and some standards by which an air traffic controller in a flight service station, en route or terminal facility, or at the David J. Hurley Air Traffic Control System Command Center may request a waiver of the mandatory separation age. By taking this action, the Secretary of the Department of Transportation (DOT) implements congressional authority to issue such exemptions.

The FAA adopts a new airworthiness directive (AD) that supersedes Airworthiness Directive (AD) 74-06-01, which applies to certain The New Piper Aircraft, Inc. (Piper) Models PA-23-235, PA-23- 250, and PA-E23-250 airplanes equipped with Garrett Aviation Services (Garrett) (formerly AiResearch) turbosuperchargers installed under supplemental type certificate (STC) SA852WE, SA909WE, or SA978WE; or installed under Piper Aircraft Drawing Number 32016. AD 74-06-01 currently requires you to replace turbosupercharger oil tanks, install fire shrouds, seal all openings in the fire shrouds, and add drainage provisions in the oil tank fairings for airplane serial numbers 27-1 through 27-2504; and add drainage provisions in the air scoops on serial numbers 27-2505 and higher. This AD requires you to replace the oil reservoir and related hoses with a fireproof oil tank and fire- shielded hoses. This AD results from a report of a fatal accident related to the breakdown of the turbocharger oil reservoir following a fire in the engine nacelle. We are issuing this AD to prevent turbosupercharger oil reservoirs with inadequate fire resistance from failing when exposed to flame or exhaust gases. This failure could lead to an in-flight fire within the nacelle area penetrating the firewall and subsequent failure of the wing spar.

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100 and -200B series airplanes. This AD requires installing bonding clips and bonding jumpers from the housing of each fuel pump to airplane structure outside the fuel tanks. This AD is prompted by the results of fuel system reviews conducted by the manufacturer. We are issuing this AD to ensure adequate electrical bonding between the housing of each fuel pump and airplane structure outside the fuel tanks. Inadequate electrical bonding, in the event of a lightning strike or pump electrical fault, could cause electrical arcing and ignition of fuel vapor in the wing fuel tank, which could result in a fuel tank explosion.

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747 series airplanes. This AD requires a one-time inspection for discrepancies of the frame web and inner chords on the forward edge frame of the number 5 main entry door cutout, and related corrective action. This AD is prompted by a report of cracking of the frame web and inner chords on the forward edge frame of the number 5 main entry door. We are issuing this AD to find and fix discrepancies of the frame web and inner chords, which could result in cracking, subsequent severing of the frame, and consequent rapid depressurization of the airplane.

The FAA is adopting a new airworthiness directive (AD) to supersede (AD) 98-15-13, which applies to certain Raytheon Aircraft Company 90, 100, 200, and 300 series airplanes. This AD adds the Raytheon Beech 99 series to the applicability listed in AD 98-15-13. The compliance actions remain the same for those aircraft originally affected by AD 98-15-13. AD 98-15-13 currently requires you to check the airplane maintenance records from January 1, 1994, up to and including the effective date of that AD, for any MIL-H-6000B fuel hose replacements on the affected airplanes; inspecting any replaced rubber fuel hose for a spiral or diagonal external wrap with a red or orange- red stripe along the length of the hose with 94519 printed along the stripe; and replacing any MIL-H-6000B rubber fuel hose matching this description with an FAA-approved hose having a criss-cross or braided external wrap. We are issuing this AD to prevent fuel flow interruption, which could lead to uncommanded loss of engine power and loss of control of the airplane.

The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP Model Gulfstream 100 airplanes; and Model Astra SPX and 1125 Westwind Astra series airplanes. This AD requires adjusting the ground contact switches of the main landing gear. This AD is prompted by two occurrences of uncommanded deployments of the ground airbrakes during descent. We are issuing this AD to prevent a false ``Ground'' position signal, which could result in deployment of the ground airbrakes and reduced controllability of the airplane.

The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A320 series airplanes. That AD currently requires repetitive inspections to detect fatigue cracking in certain areas of the fuselage, and corrective action if necessary. That AD also provides for an optional terminating action for the repetitive inspections. This new AD reduces the compliance threshold and repetitive intervals for the inspections required by the existing AD. This AD is prompted by a full-scale fatigue survey on the Model A320 fleet. We are issuing this AD to detect and correct fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane.

The FAA is issuing this notice to advise the public that a meeting of the Federal Aviation Air Traffic Procedures Advisory Committee (ATPAC) will be held to review present air traffic control procedures and practices for standardization, clarification, and upgrading of terminology and procedures.

These special conditions are issued for a Dassault-Breguet Model Falcon 10 airplane modified by Long Beach Avionics of Long Beach, California. The modified airplane will have novel and unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. The modification incorporates the installation of a Collins Model ALI-80 Altimeter and Model MSI-80 Mach Airspeed Indicator. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for the protection of these systems from the effects of high- intensity radiated fields (HIRF). These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that provided by the existing airworthiness standards.

This amendment establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) 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, addition of new obstacles, or changes in 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.