Federal Aviation Administration June 2006 – Federal Register Recent Federal Regulation Documents

This action proposes special conditions for the Boeing Model 777-200 series airplanes. These airplanes, modified by Aerocon Engineering Company (AEC), will have a novel or unusual design feature associated with a forward lower lobe crew rest compartment (CRC). 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.

This final rule changes the airman medical certification standards to disqualify an airman based on an alcohol test result of 0.04 or greater breath alcohol concentration (BAC) or a refusal to take a drug or alcohol test required by the Department of Transportation (DOT) or a DOT agency. Further, this rulemaking standardizes the time period for reporting refusals and certain test results to the FAA, and requires employers to report pre-employment and return-to-duty test refusals. It also amends the airman medical certification requirements to allow suspension or revocation of airman medical certificates for pre-employment and return-to-duty test refusals. Finally, we have updated the regulations to recognize current breath alcohol testing technology. These amendments are necessary to ensure that persons who engage in substance abuse do not operate aircraft or perform contract air traffic control duties until it is determined that these individuals can safely exercise the privileges of their certificates.

The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model MD-11 and -11F airplanes. The existing AD currently requires an initial general visual inspection of the power feeder cables of the integrated drive generator (IDG) and the fuel feed lines of engine pylons No. 1 and No. 3 on the wings for proper clearance and damage; corrective actions if necessary; and repetitive general visual inspections and a terminating action for the repetitive inspections. This proposed AD would continue to require the existing actions, and for certain airplanes, this proposed AD would require installation of new clamps on the power feeder cables of the IDG of engine pylons No. 1 and No. 3. This proposed AD results from reports of IDG power feeder cables riding against structure and fuel lines in the No. 1 and No. 3 pylons. We are proposing this AD to prevent potential chafing of the power feeder cables of the IDG in engine pylons No. 1 and No. 3 on the wings, and consequent arcing on the fuel lines in the engine pylons and possible fuel fire.

The FAA proposes to adopt a new airworthiness directive (AD) for all Fokker Model F27 Mark 500 airplanes. This proposed AD would require an inspection to determine whether certain main landing gear (MLG) drag stay units (DSUs) are installed. This proposed AD would also require an ultrasonic inspection to determine if certain tubes are installed in the affected DSUs of the MLG, and related investigative/ corrective actions if necessary. This proposed AD results from a report that, due to fatigue cracking from an improperly machined radius of the inner tube, a drag stay broke, and, consequently, led to the collapse of the MLG during landing. We are proposing this AD to prevent such fatigue cracking, which could result in reduced structural integrity or collapse of the MLG.

We are adopting a new airworthiness directive (AD) to revise AD 68-17-03, which applies to all Pilatus Aircraft Ltd. (Pilatus) PC-6 series airplanes. AD 68-17-03 requires you to repetitively inspect the rudder end rib for cracks and replace the rudder end rib with a modified rudder end rib when you find cracks. Installing the modified rudder end rib terminates the repetitive inspection requirements of AD 68-17-03. Under a licensing agreement with Pilatus, Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation) produced Model PC-6 series airplanes (manufacturer serial numbers 2001 through 2092) in the United States. AD 68-17-03 was intended to apply to all affected serial numbers of Model PC-6 series airplanes listed on Type Certificate Data Sheet (TCDS) No. 7A15, including the Fairchild-produced airplanes. Consequently, this AD clarifies that all models of the PC-6 airplane on TCDS No. 7A15 (including those models produced under the licensing agreement by Fairchild Republic Company) are included in the applicability. We are issuing this AD to detect and correct cracks in the rudder end rib, which could result in failure of the rudder end rib. This failure could result in loss of rudder control.

We are adopting a new airworthiness directive (AD) that supersedes AD 2005-26-53, which applies to certain Pacific Aerospace Corporation Ltd. (PAC) 750XL airplanes. AD 2005-26-53 currently requires you to insert text into the Limitations Section of the Airplane Flight Manual (AFM) that reduces the maximum takeoff weight from 7,500 pounds to 7,125 pounds. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for New Zealand and the FAA's decision that the actions correct an unsafe condition. Consequently, this AD would require you to remove rivets that have not been fully age hardened and replace them with bolts, washers, and nuts in specific locations where reduction in rivet strength affects overall structural capability. This AD retains the actions of the previous AD until the rivets are replaced with the bolts, washers, and nuts. We are issuing this AD so that wing ultimate load requirements are met. If wing ultimate load requirements are not met, wing failure could result with consequent loss of control of the airplane.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Model A310-300 airplanes. This proposed AD would require replacing the existing non-return valve (NRV) of the auxiliary center tanks (ACTs) of the fuel system with a new, improved NRV. This proposed AD results from a report that it was not possible to transfer fuel from ACTs 1 and 2 during flight, and no electronic centralized aircraft monitor warnings were triggered. Investigation revealed a faulty static inverter and blown fuse, resulting in failure of certain fueling bus bars and subsequent failure of the automatic ACT fuel transfer. We are proposing this AD to prevent these failures, combined with failure of the NRV to close. If the NRV is open during flight, the fuel supply to the engines may be reduced during cross-feed operation to the extent that fuel starvation could occur and result in engine flameout.

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 is adopting a new airworthiness directive (AD) for certain EMBRAER Model ERJ 170 airplanes. This AD requires inspecting for excess sealant applied to the attachment bolts of the negative pressure relief valve, and performing corrective actions if necessary. This AD results from reports that excess sealant was applied to the attachment bolts of the negative pressure relief valve, which interfered with the valve's movable diaphragm. We are issuing this AD to prevent incorrect operation of the negative pressure relief valve, which could result in negative pressures that exceed the structural strength limits of the airframe and lead to reduced structural integrity of the airplane.

These special conditions are issued to Sagem Avionics, Inc., 16923 Meridian East, Puyallup, WA 98375, for a Supplemental Type Certificate for the Cessna C-180 airplane. This airplane will have novel and unusual design features when compared to the state of technology envisaged in the applicable airworthiness standards. This novel and unusual design feature will include the installation of a two panel electronic display system, or Electronic Flight Instrument System (EFIS), manufactured by Sagem. The installation also includes components associated with this display system. 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.

We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The proposed AD would require actions that are intended to address an unsafe condition described in the MCAI.

The Federal Aviation Administration (FAA) announces its findings on the noise compatibility program submitted by the City of Scottsdale, Arizona under the provisions of Title I of the Aviation Safety and Noise Abatement Act, as amended, (Public Law 96-193) (hereinafter referred to as ``the Act'') and 14 CFR part 150. These findings are made in recognition of the description of Federal and nonfederal responsibilities in Senate Report No. 96-52 (1980). On January 21, 2005, the FAA determined that the noise exposure maps submitted by the City of Scottsdale under Part 150 were in compliance with applicable requirements.

This action corrects an error in the airspace description contained in a Final Rule that was published in the Federal Register on Monday, April 24, 2006 (71 FR 20871). Airspace Docket No. 06-AAL-06.

We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

These final special conditions are issued to Aero Propulsion, Inc., for Piper Model PA28-236 airplanes with a Societe de Motorisation Aeronautiques (SMA) Model SR305-230 ADE. The supplemental type certificate for these airplanes will have a novel or unusual design feature associated with the installation of an aircraft diesel engine that uses an electronic engine control system instead of a mechanical control system. 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.

This action proposes to establish 16 VOR Federal Airways (V- 65, V-176, V-383, V-396, V-406, V-410, V-414, V-416, V-418, V-426, V- 467, V-486, V-542, V-584, V-586, and V-609); modify 13 VOR Federal Airways (V-14, V-26, V-40, V-72, V-75, V-90, V-96, V-103, V-116, V-133, V-297, V-435, and V-526); and revoke one VOR Federal Airway (V-42) over the East Central United States in support of the Midwest Airspace Enhancement Plan (MASE). The FAA is proposing this action to enhance safety and to improve the efficient use of the navigable airspace assigned to the Chicago, Cleveland, and Indianapolis Air Route Traffic Control Centers (ARTCC).

The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 208, Aeronautical Mobile Satellite Services.

The FAA adopts a new airworthiness directive (AD) for General MachineDiecron, Inc. (GMD) actuator nut assembly, part number (P/N) GMD115-810029-17 and P/N GMD115-810029-23, that are installed on certain Raytheon Aircraft Company (Raytheon) (formerly Beech) airplanes that are not equipped with a hydraulic main landing gear (MLG) or modified to a hydraulic MLG. This AD requires you to determine by maintenance records check and/or inspection whether any actuator nut assembly, P/N GMD115-810029-17 or P/N GMD115-810029-23, is installed on the right main MLG actuator, and, if installed, requires you to replace it with a new actuator nut assembly, P/N GMD115-810029-23B or FAA- approved equivalent P/N. This AD results from several reports of failures of the actuator nut assembly, P/N GMD115-810029-17 and P/N GMD115-810029-23. We are issuing this AD to prevent failure of the actuator nut assembly for the right MLG actuator, which could result in failure of the MLG. This failure could prevent the extension or retraction of the MLG.

This document makes a correction to Airworthiness Directive (AD) 2006-10-21. That AD applies to Engine Components Incorporated (ECi) reciprocating engine connecting rods. We published AD 2006-10-21 in the Federal Register on May 18, 2006, (71 FR 28769). An incorrect amendment number exists under the Sec. 39.13 amended heading. This document corrects the amendment number. In all other respects, the original document remains the same.

The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 airplanes. This AD requires inspecting to determine the part number and serial number of the fuel tank boost pumps and, for airplanes with affected pumps, revising the Airplane Flight Manual (AFM) and the FAA-approved maintenance program. This AD also provides for optional terminating action for compliance with the revisions to the AFM and the maintenance program. This AD results from a report that a fuel tank boost pump failed in service, due to a detached screw of the boost pump housing that created a short circuit between the stator and rotor of the boost pump motor and tripped a circuit breaker. We are issuing this AD to ensure that the flightcrew is aware of procedures to prevent the presence of a combustible air-fuel mixture in the fuel tank boost pump, which, in the event of electrical arcing in the pump motor, could result in an explosion and loss of the airplane.

The FAA is adopting a new airworthiness directive (AD) for all Raytheon Model BAe.125 series 800A (including variants C-29A and U- 125), 800B, 1000A, and 1000B airplanes and Model Hawker 800 (including variant U-125A) and 1000 airplanes; and for certain Raytheon Model HS.125 series 700A and 700B airplanes and Model Hawker 800XP airplanes. This AD requires measuring the resistance of the current limiters for the PE, PS1, and PS2 busses, and replacing a current limiter with a new part if necessary. This AD also requires reporting certain information to the airplane manufacturer. This AD allows a records review for determining if suspect current limiters were installed, which may exempt airplanes from the required measurement. This AD results from reports that certain current limiters have opened within two to four hours after installation. We are issuing this AD to prevent loss of all primary electrical power, which could result in the airplane operating only under emergency power.

The FAA is adopting a new airworthiness directive (AD) for all Short Brothers Model SD3 airplanes. This AD requires installing additional fuel tank bonding jumpers, performing an in-place resistance check of the float switches, inspecting certain internal components of the fuel tanks, and performing related corrective actions if necessary. This AD also requires revisions to the Airworthiness Limitations section of the Instructions for Continued Airworthiness, and to the airplane flight manual procedures for operation during icing conditions and fuel system failures. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent ignition sources inside the fuel tanks, which could lead to fire or explosion.

This proposes special conditions for the Cessna Models 182Q and 182R airplanes with a Societe de Motorisation Aeronautiques (SMA) Model SR305-230 aircraft diesel engine (ADE). The supplemental type certificate for these airplanes will have a novel or unusual design feature associated with the installation of an aircraft diesel engine that uses an electronic engine control system instead of a mechanical control system. 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.

These special conditions are issued to Thielert Aircraft Engines, GmbH, Lichtenstein, Germany for a supplemental type certificate for the Piper PA 28-161 Cadet, Warrior II and Warrior III series airplanes. The supplemental type certificate for these airplanes will have a novel or unusual design feature associated with the installation of an aircraft diesel engine that uses an electronic engine control system instead of a mechanical control system. 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.

These special conditions are issued for the installation of an AmSafe, Inc., Inflatable Two-, Three-, Four- or Five-Point Restraint Safety Belt with an Integrated Airbag Device on various airplane models. These airplanes, as modified by AmSafe, Inc., will have a novel or unusual design feature(s) associated with the lap belt or shoulder harness portion of the safety belt, which contains an integrated airbag device. 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.