Federal Aviation Administration 2007 – Federal Register Recent Federal Regulation Documents

We are adopting a new airworthiness directive (AD) to supersede AD 98-19-15 R1 and AD 2000-03-17, which apply to M7 Aerospace LP SA226 and SA227 series airplanes equipped with certain pitch trim actuators. AD 98-19-15 R1 currently requires you to incorporate changes into the Limitations Section of the FAA-approved airplane flight manual (AFM) if certain part number (P/N) pitch trim actuators are installed. AD 2000-03-17 requires repetitive inspections and repetitive replacements of the pitch trim actuator. The repetitive inspection and repetitive replacement times vary depending on the combination of airplane model and pitch trim actuator P/N installed. Since we issued AD 98-19-15 R1 and AD 2000-03-17, we have determined that reliance on critical repetitive inspections on aging commuter-class airplanes carries an unnecessary safety risk when a design change exists that could eliminate or, in certain instances, reduce the number of those critical inspections. Consequently, this AD retains all of the actions of the previously referenced ADs, places life limits on certain P/N pitch trim actuators, and requires the replacement of certain P/N pitch trim actuators with one of an improved design. Once installed, the improved design pitch trim actuator will terminate the AFM limitations in this AD and reduce the repetitive inspection and repetitive replacement requirements. We are issuing this AD to detect excessive freeplay or rod slippage in the pitch trim actuator, which, if not detected and corrected, could result in pitch trim actuator failure. We are also issuing this AD to lessen the severity of pitch upset if a pitch trim actuator mechanical failure occurs. These conditions could lead to possible loss of control.

The FAA publishes a monthly notice, as appropriate, of PFC approvals and disapprovals under the provisions of the Aviation Safety and Capacity Expansion Act of 1990 (Title IX of the Omnibus Budget Reconciliation Act of 1990) (Pub. L. 101-508) and Part 158 of the Federal Aviation Regulations (14 CFR Part 158). This notice is published pursuant to paragraph d of Sec. 158.29.

The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 209, EUROCAE WG-49 Joint Plenary Session ATCRBS/Mode S Transponder MOPS Maintenance.

We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

These special conditions are issued for the Cirrus Design Corporation, Model SR22 airplane as modified by Centex Aerospace, Inc. This airplane as modified by Centex Aerospace, Inc. will have a novel or unusual design feature(s) associated with the installation of a full authority digital engine control (FADEC) engine. 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.

The FAA is revising an earlier proposed airworthiness directive (AD) for all Boeing Model 757 airplanes. The original NPRM would have required revising the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness by incorporating new limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. The original NPRM also would have required the initial inspection of certain repetitive inspections specified in the AWLs to phase-in those inspections, and repair if necessary. The original NPRM resulted from a design review of the fuel tank systems. This action revises the original NPRM by aligning the compliance time for revising the AWLs section with the compliance date of the special maintenance program requirements, updating the listing of applicable airplane maintenance manuals in Appendix 1, and clarifying certain actions. We are proposing this supplemental NPRM to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.

The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 707 airplanes and Model 720 and 720B series airplanes. This proposed AD would require accomplishing an airplane survey to define the configuration of certain system installations, and repair of any discrepancy found. This proposed AD would also require modifying the fuel system by installing lightning protection for the fuel quantity indication system (FQIS), ground fault relays for the fuel boost pumps, and additional power relays for the center tank fuel pumps and uncommanded on-indication lights at the flight engineer's panel. This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing this AD to prevent certain failures of the fuel pumps or FQIS, which could result in a potential ignition source inside the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.

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.

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 publishing notice of a proposed change of status of about 15 +/- acres of land on the Baton Rouge, Louisiana. The FAA invites public comment on the status change of this land under Title 49, United States Code Section 47153(c). The land status change will allow the primary airport access road known as Veteran's Boulevard to be extended from the end that is now found approximately the middle of the airport on to the northern boundary of the airport. No land barter is involved and it shall remain airport property on the Airport Layout Plan. This extension will allow development of the northwest portion of the airport for revenue producing activities. It will also provide public access to the terminal and aeronautical areas from the northern areas of the city of Baton Rouge and other suburban communities.

This amendment adopts a new airworthiness directive (AD) for Enstrom Helicopter Corporation (Enstrom) Model F-28, F-28A, F-28C, F- 28C-2, F-28C-2R, F-28F, F-28F-R, 280, 280C, 280F, 280FX, TH-28, 480, and 480B helicopters. This action requires a visual check to determine if a certain serial-numbered main rotor blade retention pin (retention pin) is installed, and removing and replacing any affected retention pin with an airworthy retention pin. This amendment is prompted by a report from the manufacturer that some retention pins were not manufactured in accordance with specifications cited on the engineering drawing. The actions specified in this AD are intended to prevent failure of a retention pin, separation of a main rotor blade from the helicopter, and subsequent loss of control of the helicopter.

The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 707 airplanes and Model 720 and 720B series airplanes. This proposed AD would require identifying the material used in the elevator hinge support fittings of the horizontal stabilizer trailing edge, doing repetitive detailed inspections for cracking of the fittings and corrective actions if necessary, and doing an eventual terminating action. This proposed AD results from a report that stress corrosion cracking of the elevator hinge support fittings has been discovered on several Model 707 airplanes. We are proposing this AD to prevent cracking of the elevator hinge support fittings, which could reduce the elevator support stiffness and lead to in-flight airframe vibration, consequent damage to the elevator and horizontal stabilizer, and reduced controllability of the airplane.

We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. This AD requires repetitive high frequency eddy current inspections for cracks of the fuselage skin at stringer 5 left and right between stations 340 and 350, and corrective actions if necessary. This AD results from reports of fatigue cracks in the fuselage skin near stringer 5 between stations 340 and 350. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin near stringer 5. Cracks in this area could join together and result in in-flight depressurization of the airplane.

These special conditions are issued for the Boeing Model 787-8 airplane. This airplane will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. These design features include electronic flight control systems and high bypass engines. These special conditions also pertain to the effects of such novel or unusual design features, such as effects on the structural performance of the airplane. Finally, these special conditions pertain to effects of certain conditions on these novel or unusual design features, such as the effects of high intensity radiated fields (HIRF). The applicable airworthiness regulations do not contain adequate or appropriate safety standards for these design features. 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 standards. Additional special conditions will be issued for other novel or unusual design features of the Boeing Model 787-8 airplanes.

This amendment establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and/or Weather Takeoff Minimums 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.

We propose to adopt a new airworthiness directive (AD) for certain Thrush Aircraft, Inc. (Thrush) Model S2R series airplanes. This proposed AD would require repetitive visual inspections of the vertical and horizontal stabilizer attach fitting, attach fitting bolts, and the vertical fin aft spar for cracks or corrosion and require immediate replacement of cracked or corroded parts and eventual replacement if no cracks or corrosion is found as terminating action for the repetitive inspections. This proposed AD results from reports of cracks in the empennage of Thrush S2R series airplanes. We are proposing this AD to detect and correct these cracks, which could cause the vertical stabilizer to lose structural integrity. This condition could lead to loss of control.

This action establishes a high altitude RNAV route in the Seattle, WA area to facilitate air traffic operations by providing a direct route to the Phoenix, AZ, area. The FAA is implementing this route to enhance safety and to provide a more efficient use of navigable airspace.

The FAA withdraws a notice of proposed rulemaking (NPRM) that proposed a new airworthiness directive (AD) for certain EMBRAER Model ERJ 170 airplanes. The proposed AD would have required installing updated software revisions and, as applicable, doing concurrent actions. Since the proposed AD was issued, we have received a report that all affected airplanes have already been modified as described in the proposed AD. Accordingly, the proposed AD is withdrawn.

The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 airplanes. This AD requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.

The FAA is adopting a new airworthiness directive (AD) for all Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires revising the Certification Maintenance Requirements and the Maintenance Review Board Report sections of the Canadair Regional Jet Maintenance Requirements Manual to include changes and additions to checks of the aileron power control units (PCUs) and a change to the interval of the backlash check of the aileron control system. This AD results from a report that data collected from in- service airplanes show that approximately 19 percent of aileron backlash checks conducted at 4,000-flight-hour intervals reveal that aileron backlash wear limits are being exceeded. We are issuing this AD to prevent exceeded backlashes in both aileron PCUs, which, if accompanied by the failure of the flutter damper, could result in aileron vibration/flutter and reduced controllability of the airplane.

The FAA is superseding an existing airworthiness directive (AD) that applies to certain Boeing Model 737-800 series airplanes. The existing AD currently requires inspecting flight spoilers to determine spoiler position after every landing and after any rejected takeoff maneuver. For airplanes on which any flight spoiler is found in the up position with the speedbrake handle in the down position, the existing AD requires replacing the flight spoiler actuator with a flight spoiler actuator having a certain part number. The existing AD also requires an operational test of the speedbrake control system after any maintenance actions that operate the spoiler system, and replacement of the flight spoiler actuator if necessary. The existing AD also provides for optional terminating action for those requirements. This new AD requires the previously optional terminating action. This AD results from a report of seven flight spoiler actuator jams on Model 737-800 airplanes equipped for short field performance (SFP). The cause of the failure has been identified as interference within the actuator main control valve. We are issuing this AD to prevent operation with defective flight spoiler actuators, which could result in a flight spoiler actuator hardover, and could cause the flight spoiler surface to jam in the fully extended position. Two or more hardover failures of the flight spoiler surfaces in the up direction on the same wing, if undetected prior to takeoff, can cause significant roll and consequent loss of control of the airplane.

The Federal Aviation Administration (FAA) announces its findings on the noise compatibility program submitted by the City of Flagstaff under the provisions of Title I of the Aviation Safety and Noise Abatement Act, as amended, (Pub. L. 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 April 7, 2005, the FAA determined that the noise exposure maps submitted by the City of Flagstaff under part 150 were in compliance with applicable requirements.

The Federal Aviation Administration (FAA) announces its determination that the noise exposure maps submitted by Clark County Department of Aviation, Las Vegas, Nevada for McCarran 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 is revising an earlier proposed airworthiness directive (AD) for certain McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes; Model DC-10-40 and DC-10-40F airplanes; and Model MD-11 and MD-11F airplanes. The original NPRM would have required, for certain airplanes, modifying the thrust reverser command wiring of the number 2 engine. For certain other airplanes, the original NPRM would have required modifying the thrust reverser system wiring from the flight compartment to engines 1, 2, and 3 thrust reversers. The original NPRM also would have required installing thrust reverser locking systems on certain airplanes. The original NPRM resulted from a determination that the thrust reverser systems on these McDonnell Douglas airplanes do not adequately preclude unwanted deployment of a thrust reverser. This action revises the original NPRM by revising, for certain airplanes, the requirements for the modification of the thrust reverser system wiring from the flight compartment to engines 1, 2, and 3 thrust reversers. We are proposing this supplemental NPRM to prevent an unwanted deployment of a thrust reverser during flight, which could result in reduced controllability of the airplane.