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

Results 51 - 100 of 183
Airworthiness Directives; Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes; and Model A340-541 and A340-642 Airplanes
Document Number: 06-5548
Type: Rule
Date: 2006-06-22
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes; and Model A340-541 and A340-642 airplanes. This AD requires an inspection for anti-fretting material contamination of the Halon filters and plumbing parts of the flow metering system (FMS) and flow metering compact unit (FMCU) in the lower deck cargo compartment (LDCC) and bulk crew rest compartment (BCRC), as applicable; other specified actions; and corrective actions if necessary. This AD results from a report that the FMS and FMCU of the fire extinguishing system may be blocked by anti-fretting material contamination. We are issuing this AD to prevent such anti-fretting material contamination, which could reduce the effectiveness of the fire extinguisher system to discharge fire extinguishing agents and to lower the concentration of Halon gas in the LDCC or BCRC in a timely manner. An ineffective fire extinguisher system in the event of a fire could result in an uncontrollable fire in the LDCC or BCRC.
Special Conditions: Boeing Model 777-200 Series Airplanes; Forward Lower Lobe Crew Rest Compartment (CRC)
Document Number: E6-9819
Type: Proposed Rule
Date: 2006-06-21
Agency: Federal Aviation Administration, Department of Transportation
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.
Special Conditions; Rickenbacker Avionics, EFS-50 EFIS Installation in Rockwell Twin Commander Model 690B; Protection of Systems From High Intensity Radiated Fields (HIRF)
Document Number: E6-9818
Type: Rule
Date: 2006-06-21
Agency: Federal Aviation Administration, Department of Transportation
These special conditions are issued to Rickenbacker Avionics, 2820 Bobmeyer Road, Hangar C-6, Hamilton, OH 45015, for a Supplemental Type Certificate for the Rockwell Twin Commander Model 690B 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-tube Bendix/King EFS-50 Electronic Flight Instrument System (EFIS). 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 that established by the existing the airworthiness standards applicable to these airplanes.
Disqualification for Airman and Airman Medical Certificate Holders Based on Alcohol Violations or Refusals To Submit to Drug and Alcohol Testing
Document Number: E6-9814
Type: Rule
Date: 2006-06-21
Agency: Federal Aviation Administration, Department of Transportation
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.
Airworthiness Directives; Boeing Model 747 Airplanes
Document Number: E6-9721
Type: Proposed Rule
Date: 2006-06-21
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Boeing Model 747 airplanes. The existing AD currently requires a one-time inspection to determine whether the outer cylinder of the wing landing gear has certain part numbers (P/Ns), and replacement of the outer cylinder of the wing landing gear with a new, improved, or reworked part if necessary. The existing AD also requires removal of the load evening system, if such a system is installed. For certain airplanes, this proposed AD would require an additional one-time inspection to determine whether the outer cylinder has a certain other P/N. For those certain airplanes, this proposed AD would also require replacement of the outer cylinder with a reworked or new, improved part and related investigative/ corrective actions, if necessary. This proposed AD results from identification of an additional unsafe part. We are proposing this AD to prevent fracture of the outer cylinder of the wing landing gear, which could result in collapse of the wing landing gear.
Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F Airplanes
Document Number: E6-9718
Type: Proposed Rule
Date: 2006-06-21
Agency: Federal Aviation Administration, Department of Transportation
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.
Airworthiness Directives; 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)
Document Number: E6-9715
Type: Proposed Rule
Date: 2006-06-21
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model A300-600 series airplanes. The existing AD currently requires an inspection for evidence of chafing between the hydraulic flexible hose and the ram air turbine (RAT) hub, and related investigative and corrective actions if necessary. This proposed AD would extend the applicability to include all A300-600 series airplanes that are equipped with a certain RAT. This proposed AD results from reports of holes in the RAT hub cover. We are proposing this AD to prevent a hole in the RAT hub cover. A hole in the RAT hub cover could allow water to enter the RAT governing mechanism, freeze during flight, and jam the governing mechanism. In addition, the metal particles that result from chafing between the hydraulic flexible hose and the RAT could mix with the lubricant grease and degrade the governing mechanism. In an emergency, a jammed or degraded RAT could result in its failure to deploy, loss of hydraulic pressure or electrical power to the airplane, and consequent reduced controllability of the airplane.
Airworthiness Directives; Fokker Model F27 Mark 500 Airplanes
Document Number: E6-9714
Type: Proposed Rule
Date: 2006-06-21
Agency: Federal Aviation Administration, Department of Transportation
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.
Airworthiness Directives; Rolls-Royce Corporation (Formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) 250-B and 250-C Series Turboprop and Turboshaft Engines
Document Number: 06-5547
Type: Rule
Date: 2006-06-21
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation 250-B and 250-C series turboprop and turboshaft engines with certain part numbers (P/Ns) of gas producer rotor assembly tie bolts manufactured by EXTEX Ltd., Pacific Sky Supply Inc., Rolls- Royce Corporation (RRC), and Superior Air Parts Inc. This AD requires operators to remove from service affected gas producer rotor assembly tie bolts, and install serviceable tie bolts. This AD results from eleven reports of RRC tie bolt failure due to high cycle fatigue. We are issuing this AD to prevent tie bolt failure that could cause loss of engine power, resulting in a first stage turbine wheel overspeed and an uncontained engine failure.
Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 Airplanes
Document Number: 06-5532
Type: Rule
Date: 2006-06-21
Agency: Federal Aviation Administration, Department of Transportation
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.
Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
Document Number: 06-5530
Type: Rule
Date: 2006-06-21
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain Airbus airplanes as listed above. This AD requires repetitively inspecting for cracking in the web of nose rib 7 of the inner flap on the wings, and performing related investigative/corrective actions if necessary. This AD also requires eventual replacement of nose rib 7 with a new, improved rib, which would terminate the inspections. This AD results from reports of cracking in the web of nose rib 7 of the inner flap. We are issuing this AD to prevent cracking in the web of nose rib 7, which could result in rupture of the attachment fitting between the inner flap and flap track 2, and consequent reduced structural integrity of the flap.
Airworthiness Directives; Pacific Aerospace Corporation Ltd. 750XL Airplanes
Document Number: 06-5529
Type: Rule
Date: 2006-06-21
Agency: Federal Aviation Administration, Department of Transportation
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.
Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes
Document Number: E6-9639
Type: Proposed Rule
Date: 2006-06-20
Agency: Federal Aviation Administration, Department of Transportation
We propose to adopt a new airworthiness directive (AD) for certain Air Tractor, Inc. Models AT-802 and AT-802A airplanes. This proposed AD would require you to repetitively inspect the attach angles on the firewall mounted hopper rinse tank shelf for damage and/or cracks and replace damaged and/or cracked attach angles. Replacing the attach angles with steel attach angles would terminate the proposed repetitive inspection requirement. Reports of an uncommanded change in the engine power setting caused by separation of the hopper rinse tank shelf from the firewall prompted this proposed AD. We are proposing this AD to detect and correct damage and/or cracks in the attach angles on the firewall mounted hopper rinse tank shelf, which could result in failure of the attach angles. This failure could lead to shelf movement under maneuver load and shifting of the engine power cables, which could result in an uncommanded engine power setting change.
Airworthiness Directives; Airbus Model A310-300 Airplanes
Document Number: E6-9631
Type: Proposed Rule
Date: 2006-06-20
Agency: Federal Aviation Administration, Department of Transportation
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.
Petitions for Exemption; Summary of Petitions Received
Document Number: E6-9617
Type: Notice
Date: 2006-06-20
Agency: Federal Aviation Administration, Department of Transportation
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.
Petitions for Exemption; Summary of Petitions Received
Document Number: E6-9616
Type: Notice
Date: 2006-06-20
Agency: Federal Aviation Administration, Department of Transportation
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.
Airworthiness Directives; Boeing Model 757 Airplanes
Document Number: 06-5501
Type: Rule
Date: 2006-06-20
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757 airplanes. This AD requires, for certain airplanes, reworking the spar bonding path and reapplying sealant; and, for certain other airplanes, testing the electrical bond between the engine fuel feed hose and the wing front spar and, if applicable, reworking the spar bonding path and reapplying sealant. This AD also requires, for all airplanes, an inspection to ensure the electrical bonding jumper is installed between the engine fuel feed tube and the adjacent wing station. This AD also requires operators that may have installed an incorrect O-ring to install the correct part and do a re- test. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent arcing or sparking at the interface between the bulkhead fittings of the engine fuel feed tube and the front spar during a lightning strike, which could provide a possible ignition source for the fuel vapor inside the fuel tank and result in a fuel tank explosion.
Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes
Document Number: 06-5500
Type: Rule
Date: 2006-06-20
Agency: Federal Aviation Administration, Department of Transportation
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.
Airworthiness Directives; Boeing Model 727-200 Series Airplanes Equipped With a No. 3 Cargo Door
Document Number: 06-5498
Type: Rule
Date: 2006-06-20
Agency: Federal Aviation Administration, Department of Transportation
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 727-200 series airplanes. That AD currently requires initial and repetitive inspections for cracks in the forward frame of the No. 3 cargo door cutout; and corrective actions, if necessary. The existing AD also provides for an optional structural modification, which terminates the repetitive inspections. This new AD reduces the compliance time for the initial inspections and adds an optional method of inspection for both the initial and repetitive inspections. This AD also adds initial and repetitive inspections of an additional area, and repair if necessary. Additionally, this AD clarifies that the previously optional structural modification is now required by other rulemaking. This AD results from additional reports of cracking in the forward frame of the No. 3 cargo door cutout. We are issuing this AD to detect and correct cracking of the forward frame and fuselage skin of the No. 3 cargo door cutout, which could result in failure of the frame and skin, and consequent rapid decompression of the airplane.
Special Conditions; Sagem Avionics Inc.; Electronic Flight Instrument System (EFIS) Installation in Cessna C-180; Protection of Systems From High Intensity Radiated Fields (HIRF)
Document Number: E6-9590
Type: Rule
Date: 2006-06-19
Agency: Federal Aviation Administration, Department of Transportation
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.
Proposed Revision of Class E Airspace; Barter Island, AK
Document Number: E6-9589
Type: Proposed Rule
Date: 2006-06-19
Agency: Federal Aviation Administration, Department of Transportation
This action proposes to revise Class E airspace at Barter Island, AK. Two new Standard Instrument Approach Procedures (SIAPs) are being developed and one SIAP is being amended for the Barter Island Airport. Adoption of this proposal would result in amending Class E airspace upward from 700 feet (ft.) and 1,200 ft. above the surface at Barter Island, AK.
Airworthiness Directives; Gippsland Aeronautics Pty. Ltd. Model GA8 Airplanes
Document Number: E6-9560
Type: Proposed Rule
Date: 2006-06-19
Agency: Federal Aviation Administration, Department of Transportation
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.
Modification of Class E Airspace; Mason City, IA
Document Number: 06-5516
Type: Rule
Date: 2006-06-19
Agency: Federal Aviation Administration, Department of Transportation
This document confirms the effective date of the direct final rule which revises Class E airspace at Mason City, IA.
Approval of Noise Compatibility Program for Scottsdale Airport, Scottsdale, AZ
Document Number: 06-5515
Type: Notice
Date: 2006-06-19
Agency: Federal Aviation Administration, Department of Transportation
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.
Revision of Class E Airspace; Huslia, AK
Document Number: 06-5514
Type: Rule
Date: 2006-06-19
Agency: Federal Aviation Administration, Department of Transportation
This action revises Class E airspace at Huslia, AK to provide adequate controlled airspace to contain aircraft executing one new and two amended Standard Instrument Approach Procedures (SIAPs). This rule results in revised Class E airspace revised upward from 700 feet (ft.) and 1,200 ft. above the surface at Huslia, AK.
Revision of Class E Airspace; Togiak Village, AK
Document Number: 06-5513
Type: Rule
Date: 2006-06-19
Agency: Federal Aviation Administration, Department of Transportation
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.
Modification of Legal Description of Class D and E Airspace; Fairbanks, Fort Wainwright Army Airfield, AK
Document Number: 06-5512
Type: Rule
Date: 2006-06-19
Agency: Federal Aviation Administration, Department of Transportation
The U.S. Army will soon be changing the name of Fort (Ft.) Wainwright Army Airfield (AAF) to Ladd AAF. This action amends the airport name accordingly for each of the Class D and Class E airspace descriptions in FAA Order 7400.9N.
Airworthiness Directives; Airbus Model A321 Airplanes
Document Number: 06-5502
Type: Proposed Rule
Date: 2006-06-19
Agency: Federal Aviation Administration, Department of Transportation
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.
Airworthiness Directives; CFM International CFM56-5 and -5B Series Turbofan Engines
Document Number: E6-9446
Type: Proposed Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to supersede an existing airworthiness directive (AD) for CFM International CFM56-5 and -5B series turbofan engines. That AD currently requires exhaust gas temperature (EGT) harness replacement or the establishment of an EGT baseline and trend monitoring. That AD also requires replacement, if necessary, of certain EGT harnesses and EGT couplings as soon as a slow and continuous EGT drift downward is noticed after the effective date of that AD. This proposed AD would require the same actions but for an increased population of affected EGT harnesses. This proposed AD results from CFM International adding subsequently certified engine models to the list of engines that could have affected harnesses installed. We are proposing this AD to prevent unexpected deterioration of critical rotating engine parts due to higher than desired engine operating EGTs.
Special Conditions: Aero Propulsion, Inc., Piper Model PA28-236; Installation of Societe de Motorisation Aeronautiques (SMA) Model SR305-230 Aircraft Diesel Engine (ADE) for Full Authority Digital Engine Control (FADEC) System and the Protection of the System From the Effects of High Intensity Radiated Fields (HIRF)
Document Number: E6-9410
Type: Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
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.
Special Conditions; Cessna Aircraft Company Model 510 Airplane; Full Authority Digital Engine Control (FADEC) System
Document Number: E6-9409
Type: Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
These special conditions are issued for the Cessna Aircraft Company, Model 510 airplane. This airplane will have a novel or unusual design feature(s) associated with the use of an electronic engine control system instead of a traditional 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.
Proposed Establishment, Modification and Revocation of VOR Federal Airways; East Central United States
Document Number: E6-9371
Type: Proposed Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
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).
Announcement of Policy for Landing Performance Assessments After Departure for All Turbojet Operators
Document Number: 06-5449
Type: Proposed Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
The Federal Aviation Administration is making minor changes to the Announcement of Policy for Landing Performance Assessments After Departure for All Turbojet Operators published in the Federal Register on June 7, 2006 (71 FR 32877).
Second Meeting, Special Committee 208, Aeronautical Mobile Satellite Services
Document Number: 06-5448
Type: Notice
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 208, Aeronautical Mobile Satellite Services.
Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
Document Number: 06-5430
Type: Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
The FAA is superseding an existing airworthiness directive (AD) that applies to certain Boeing Model 737-100, -200, -200C, -300, - 400, and -500 series airplanes. The existing AD currently requires initial and repetitive inspections of the elevator tab assembly to find any damage or discrepancy; and corrective actions if necessary. This new AD adds certain new inspections and removes certain existing inspections. This AD results from additional reports of airframe vibrations of the elevator tab during flight on airplanes inspected per the existing AD; subsequently, considerable damage was done to the elevator tab, elevator, and horizontal stabilizer. In several incidents, a portion of the elevator tab separated from the airplane. We are issuing this AD to prevent excessive in-flight vibrations of the elevator tab, which could lead to loss of the elevator tab and consequent loss of controllability of the airplane.
Airworthiness Directives; General Machine-Diecron, Inc. Actuator Nut Assembly for the Right Main Landing Gear Installed on Certain Raytheon Aircraft Company (Formerly Beech) Airplanes
Document Number: 06-5429
Type: Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
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.
Airworthiness Directives; Boeing Model 777-200, -300, and -300ER Series Airplanes
Document Number: 06-5428
Type: Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200, -300, and -300ER series airplanes. This AD requires a one-time inspection of the first bonding jumper aft of the bulkhead fitting to detect damage or failure and to determine the mechanical integrity of its electrical bonding path, and repair if necessary; measuring the bonding resistance between the fitting for the fuel feed tube and the front spar in the left and right main fuel tanks, and repairing the bonding if necessary; and applying additional sealant to completely cover the bulkhead fittings inside the fuel tanks. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent arcing or sparking during a lightning strike at the interface between the bulkhead fittings of the engine fuel feed tube and the front spar inside the fuel tank. This arcing or sparking could provide a potential ignition source inside the fuel tank, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
Airworthiness Directives; Engine Components Incorporated (ECi) Reciprocating Engine Connecting Rods; Correction
Document Number: 06-5427
Type: Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
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.
Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines
Document Number: 06-5426
Type: Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF6-45/-50 series turbofan engines. That AD currently requires an initial and repetitive on-wing visual inspection of the side links of the five-link forward mount assembly for cracks, and replacement of the side links and pylon attachment bolts and inspection of the fail-safe bolt and platform lug if the side links are cracked. That AD also requires a shop-level refurbishment of the side links as a terminating action to the on-wing inspection program. This ad requires inspecting and refurbishing the side link at every exposure of the side link. This AD also requires the same actions on certain part number side links installed on CF6-80A turbofan engines. This AD results from a report of a cracked side link. We are issuing this AD to prevent failure of the side links and possible engine separation from the airplane.
Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes
Document Number: 06-5425
Type: Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
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.
Airworthiness Directives; Airbus Model A319, A320, and A321 Airplanes
Document Number: 06-5424
Type: Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 airplanes. This AD requires a detailed inspection for cracks and marks on the carbon blades of the ram air turbine (RAT), and replacement of the RAT with a new or serviceable RAT if necessary. This AD results from a report of three chord-wise cracks on the aft side of one carbon blade of a certain RAT. We are issuing this AD to detect and correct cracks and/or marks on the RAT carbon blades, which could result in reduced structural integrity of the carbon blade, and consequent loss of the RAT as a source of hydraulic and electrical power in an emergency.
Airworthiness Directives; Raytheon Model HS.125 Series 700A and 700B Airplanes; Model BAe.125 Series 800A (Including Variants C-29A and U-125), 800B, 1000A, and 1000B Airplanes; and Hawker 800 (Including Variant U-125A), 800XP, and 1000 Airplanes
Document Number: 06-5327
Type: Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
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.
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
Document Number: 06-5326
Type: Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) airplanes. That AD currently requires revising the airplane flight manual (AFM) to provide the flightcrew with revised procedures for checking the flap system. The existing AD also requires revising the maintenance program to provide procedures for checking the flap system, and performing follow-on actions, if necessary. This new AD requires installing new flap actuators, a new or retrofitted air data computer, a new skew detection system, and new airspeed limitation placards; and revising the AFM to include revised maximum allowable speeds for flight with the flaps extended, and a new skew detection system/crosswind-related limitation for take-off flap selection. This AD results from a number of cases of flap system failure that resulted in a twisted outboard flap panel. We are issuing this AD to prevent an unannunciated failure of the flap system, which could result in a flap asymmetry and consequent reduced controllability of the airplane.
Airworthiness Directives; Short Brothers Model SD3 Airplanes
Document Number: 06-5288
Type: Rule
Date: 2006-06-16
Agency: Federal Aviation Administration, Department of Transportation
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.
Airworthiness Directives; 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)
Document Number: E6-9342
Type: Proposed Rule
Date: 2006-06-15
Agency: Federal Aviation Administration, Department of Transportation
The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model A300-600 series airplanes. The existing AD currently requires repetitive eddy current inspections to detect cracks of the outer skin of the fuselage at certain frames, and repair or reinforcement of the structure at the frames, if necessary. The existing AD also requires eventual reinforcement of the structure at certain frames, which, when accomplished, terminates the repetitive inspections. This proposed AD would add, for airplanes that were previously reinforced but not repaired in accordance with the existing AD, a one-time inspection for cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, and repair if necessary. This proposed AD results from a report that the previously required actions were not sufficient to correct cracking before the structural reinforcement was installed. We are proposing this AD to prevent such fatigue cracking, which could result in reduced structural integrity, and consequent rapid decompression of the airplane.
Special Conditions: Societe de Motorisation Aeronautiques (SMA) Engines, Cessna Models 182Q and 182R: Installation of Model SR305-230 Aircraft Diesel Engine for Full Authority Digital Engine Control (FADEC) System and the Protection of the System From the Effects of High Intensity Radiated Fields (HIRF)
Document Number: E6-9241
Type: Rule
Date: 2006-06-15
Agency: Federal Aviation Administration, Department of Transportation
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.
Special Conditions: Thielert Aircraft Engines GmbH, Piper PA 28-161 Cadet, Warrior II and Warrior III Series Airplanes; Diesel Cycle Engine Using Turbine (Jet) Fuel
Document Number: E6-9242
Type: Proposed Rule
Date: 2006-06-14
Agency: Federal Aviation Administration, Department of Transportation
This notice proposes special conditions for the Piper PA 28- 161 Cadet, Warrior II and Warrior III series airplanes. These airplanes, as modified by Thielert Aircraft Engines GmbH, will have a novel or unusual design feature(s) associated with the installation of a diesel cycle engine utilizing turbine (jet) fuel. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for installation of this new technology engine. 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.
Special Conditions: Thielert Aircraft Engines; Piper PA 28-161 Cadet, Warrior II and Warrior III Series Airplanes; Installation of Thielert TAE-125-01 Aircraft Diesel Engine for Full Authority Digital Engine Control (FADEC) System and the Protection of the System From the Effects of High Intensity Radiated Fields (HIRF)
Document Number: E6-9228
Type: Rule
Date: 2006-06-14
Agency: Federal Aviation Administration, Department of Transportation
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.
Special Conditions: Aero Propulsion, Inc., Piper Model PA28-236; Diesel Cycle Engine Using Turbine (Jet) Fuel
Document Number: E6-9227
Type: Proposed Rule
Date: 2006-06-14
Agency: Federal Aviation Administration, Department of Transportation
This notice proposes special conditions for the Piper Model PA28-236 airplanes with a Societe de Motorisation Aeronautiques (SMA) Model SR305-230 Aircraft Diesel Engine (ADE). This airplane will have a novel or unusual design feature(s) associated with the installation of a diesel cycle engine utilizing turbine (jet) fuel. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for installation of this new technology engine. 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.
Special Conditions: AmSafe, Inc.; Approved Model List; Installation of AmSafe Inflatable Restraints in Normal and Utility Category Non-23.562 Certified Airplanes
Document Number: E6-9226
Type: Rule
Date: 2006-06-14
Agency: Federal Aviation Administration, Department of Transportation
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.