Federal Aviation Administration August 26, 2005 – Federal Register Recent Federal Regulation Documents

Airworthiness Directives; GROB-WERKE Model G120A Airplanes
Document Number: 05-16986
Type: Proposed Rule
Date: 2005-08-26
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to adopt a new airworthiness directive (AD) for all GROB-WERKE Model G120A airplanes. This proposed AD would require you to inspect for signs of any chafing damage to the attachment cables of the switch panels below the left-hand instrument panel, any damaged switch below the switch panels of the left-hand instrument panel, any damaged (that is, sharp) edge of the support tray for the attachment cables of the switch panels below the left-hand instrument panel; correct any damage found during the inspection; and apply a layer of anti-rub (protective padding) strips to the edge of the support tray. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this proposed AD to detect, correct, and prevent chafing of the cables against the rear lip of the tray that holds the switch panels. Chafing of the electrical cables could result in smoke or fire in the cockpit.
Notice of Intent To Rule on Request To Release Airport Land at March Inland Port, Riverside, CA
Document Number: 05-16970
Type: Notice
Date: 2005-08-26
Agency: Federal Aviation Administration, Department of Transportation
The Federal Aviation Administration (FAA) proposes to rule and invites public comment on the release of two parcels comprised of approximately 184.70 acres of airport property at March Inland Port, Riverside, California, from all restrictions of the surplus property agreement since the land is not needed for airport purposes. Reuse of the land for commercial/light industrial and environmental mitigation purposes represents a compatible land use. Disposal of the property will provide income for investment in airport improvements and development in accordance with the FAA Policy and Procedures Concerning the Use of Airport Revenue.
Noise Exposure Map Notice for Fresno Yosemite International Airport, Fresno, CA
Document Number: 05-16969
Type: Notice
Date: 2005-08-26
Agency: Federal Aviation Administration, Department of Transportation
The Federal Aviation Administration (FAA) announces its determination that the noise exposure maps submitted by the City of Fresno for Fresno Yosemite 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.
Airworthiness Directives; Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 Turbofan Engines
Document Number: 05-16903
Type: Rule
Date: 2005-08-26
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 turbofan engines. This AD requires removing affected rotating parts overhauled by a certain repair vendor, and inspecting the parts as applicable. This AD results from reports that certain JT8D critical life-limited rotating parts have been returned to service with cracks, corrosion pitting, or dimensions outside of manual limits. We are issuing this AD to prevent failure of critical life-limited rotating engine parts which could result in an uncontained engine failure and damage to the airplane.
Airworthiness Directives; Turbomeca Arrius 2F Turboshaft Engines
Document Number: 05-16902
Type: Rule
Date: 2005-08-26
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for Turbomeca Arrius 2F turboshaft engines. This AD requires a one-time removal and inspection of the fuel filter-holder assembly to determine that the fuel control unit (FCU) filter is dimensionally correct. The AD also requires updating the Engine Maintenance Manuals to include a dimensional check of the fuel filter-holder assembly every time the FCU filter element is removed from the fuel filter-holder assembly. This AD results from reports of restricted fuel flow caused by a dimensionally incorrect FCU filter. Ground run testing may not detect the fuel flow limitation. We are issuing this AD to detect a dimensionally incorrect FCU filter that could lead to an undetected limitation of fuel flow, limiting the maximum power available in-flight, which could result in the inability to continue safe flight, avoid obstacles or land safely.
Airworthiness Directives; Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes; and Model A340-541 and -642 Airplanes
Document Number: 05-16896
Type: Rule
Date: 2005-08-26
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes; and Model A340-541 and -642 airplanes. This AD requires repetitively resetting the display units (DUs) for the electronic instrument system (EIS) either by switching them off and back on again or by performing a complete electrical shutdown of the airplane. This AD results from an incident in which all of the DUs for the EIS went blank simultaneously during flight. We are issuing this AD to prevent automatic reset of the DUs for the EIS during flight and consequent loss of data from the DUs, which could reduce the ability of the flightcrew to control the airplane during adverse flight conditions.
Airworthiness Directives; Turbomeca S.A. Arrius 2F Turboshaft Engines
Document Number: 05-16834
Type: Rule
Date: 2005-08-26
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for Turbomeca S.A. Arrius 2F turboshaft engines. This AD requires replacing certain O-rings on the check valve piston in the lubrication unit. This AD results from a report of a forced landing of a Eurocopter EC120B helicopter. We are issuing this AD to prevent an uncommanded in-flight shutdown of the engine, which could result in a forced autorotation landing and damage to the helicopter.
Child Restraint Systems
Document Number: 05-16783
Type: Proposed Rule
Date: 2005-08-26
Agency: Federal Aviation Administration, Department of Transportation
The FAA is withdrawing a previously published Advance Notice of Proposed Rulemaking that sought public comment on issues about the use of child restraint systems (CRSs) in aircraft. Specifically, we sought crash performance and ease-of-use information about existing and new automotive CRSs, when used in aircraft. We also sought information about the development of any new or improved CRSs designed exclusively for aircraft use. We are withdrawing the document to pursue other options that will mitigate the risk of child injuries and fatalities in aircraft.
FAA-Approved Child Restraint Systems
Document Number: 05-16782
Type: Rule
Date: 2005-08-26
Agency: Federal Aviation Administration, Department of Transportation
The Federal Aviation Administration (FAA) is amending its operating regulations to allow the use, on board aircraft, of Child Restraint Systems (CRSs) that are approved by the FAA through a Type Certificate, Supplemental Type Certificate, or Technical Standard Order. Current FAA regulations do not allow the use of CRSs other than those that meet specific standards for the automobile environment. The intended effect of this regulation is to reduce the regulatory burden to industry while maintaining or increasing safety.
Airworthiness Directives; Short Brothers Model SD3-60 Airplanes
Document Number: 05-16750
Type: Rule
Date: 2005-08-26
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for all Short Brothers Model SD3-60 airplanes. This AD requires an inspection of the rudder for damage, an inspection of the balance weight attachment for discrepancies, an inspection of the rudder horn spar and cleats for cracking and corrosion, and corrective action if necessary. This AD results from events in which fatigue cracking was found on the rudder horn spar. We are issuing this AD to detect and correct cracking and corrosion of the rudder horn spar, which could lead to detachment of the mass balance weight of the rudder. The detachment of the mass balance weight could jam or restrict the movement of the rudder, which could result in reduced controllability of the airplane. Loss of a mass balance weight could also damage other parts of the airplane, which could result in reduced controllability of the airplane, or could result in an injury to a person or damage to property on the ground.
Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes; 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 A310-200 and -300 Series Airplanes
Document Number: 05-16749
Type: Rule
Date: 2005-08-26
Agency: Federal Aviation Administration, Department of Transportation
The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 B2 and B4 series airplanes; Model A300-600 series airplanes; and Model A310-200 and -300 series airplanes. That AD currently requires, among other actions, repetitive tests to detect desynchronization of the rudder servo actuators, and adjustment or replacement of the spring rods of the rudder servo actuators, if necessary. This new AD requires new repetitive tests/inspections/analyses of the rudder servo actuators, and related investigative/corrective actions if necessary. Accomplishment of the new actions ends the existing repetitive requirements. This AD is prompted by new reports of desynchronization of the rudder servo actuators. We are issuing this AD to prevent desynchronization of one of the three rudder servo actuators, which, if combined with an engine failure, could result in the loss of the related hydraulic system and could cause the loss of one of the two synchronized actuators. This condition could create additional fatigue loading and possible cracking on the attachment fittings and could result in the inability of the remaining synchronized actuator to maintain the commanded rudder deflection, which could result in reduced controllability of the airplane.