Airworthiness Directives; Raytheon Aircraft Company Models C90A, B200, B200C, B300, and B300C Airplanes
We propose to supersede Airworthiness Directive (AD) 2006-23- 02 which applies to certain Raytheon Aircraft Company (RAC) (formerly Beech) Models C90A, B200, B200C, B300, and B300C airplanes. AD 2006-23- 02 currently requires you to inspect the flight controls for improper assembly or damage, and if any improperly assembled or damaged flight controls are found, take corrective action. Since we issued AD 2006-23- 02, we have determined the need to add airplane serial numbers that were not previously included in the applicability. Consequently, this proposed AD would retain the actions of AD 2006-23-02 and add airplane serial numbers to the applicability. We are proposing this AD to detect and correct improperly assembled or damaged flight controls, which could result in an unsafe condition by reducing capabilities of the flight controls and lead to loss of control of the airplane.
Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes
The FAA proposes to adopt a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This proposed AD would require a detailed inspection for wear of the attachment holes of the control levers of the braking system and applicable corrective actions. This proposed AD results from a report that, after landing, the flightcrew of a Model F.28 Mark 0100 airplane noted that an extreme difference in pedal angle was required to achieve equal braking action. We are proposing this AD to prevent failure of one or more brake control levers, which could result in uncommanded braking and loss of control of the airplane during takeoff, landing, or taxiing.
Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) ERJ 170 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 aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as an obstruction at the cargo compartment fire extinguisher system drier metering unit (DME) inlet, affecting the system effectiveness and, consequently, making the fire extinguishing capability at those compartments inadequate should a fire erupt. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.
Special Conditions: Boeing Model 787-8 Airplane; Interaction of Systems And Structures, Electronic Flight Control System-Control Surface Awareness, High Intensity Radiated Fields (HIRF) Protection, Limit Engine Torque Loads for Sudden Engine Stoppage, and Design Roll Maneuver Requirement
This notice proposes special conditions 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). Additional special conditions will be issued for other novel or unusual design features of the Boeing Model 787-8 airplanes.
Petitions for Exemption; Summary of Petitions Received
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; Microturbo Saphir 20 Models 095 Auxiliary Power Units (APU)
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:
Airworthiness Directives; Teledyne Continental Motors GTSIO-520 Series Reciprocating Engines
The FAA is superseding an existing airworthiness directive (AD) for Teledyne Continental Motors (TCM) GTSIO-520 series reciprocating engines. That AD currently requires initial and repetitive visual inspections of the starter adapter assembly and crankshaft gear and unscheduled visual inspections of the starter adapter assembly and crankshaft gear due to a rough-running engine. That AD also requires replacement of the starter adapter shaft gear needle bearing with a certain bushing and installation of a certain TCM service kit at the next engine overhaul, or at the next starter adapter replacement, whichever occurs first. This AD requires performing the inspection ordered in paragraph (h) of this AD every 100 hours time-in- service (TIS), or annually. This proposed AD results from an error discovered in AD 2005-20-04. We are issuing this AD to failure of the starter adapter assembly and or crankshaft gear, resulting in failure of the engine and possible forced landing.
Notice of Passenger Facility Charge (PFC) Approvals and Disapprovals
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 (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.
Danbury Municipal Airport, Danbury, CT; FAA Approval of Noise Compatibility Program
The Federal Aviation Administration (FAA) announces its findings on the noise compatibility program submitted by the City of Danbury, CT under the provisions of Title I of the Aviation Safety and Noise Abatement Act of 1979 (Pub. L. 96-193) and 14 CFR part 150. These findings are made in recognition of the description of federal and non- Federal responsibilities in Senate Report No. 96-52 (1980). On September 9, 2006, the FAA determined that the noise exposure maps submitted by the City of Danbury under part 150 were in compliance with applicable requirements. On February 15, 2007, the Airports Division Manager approved the Danbury Municipal Airport noise compatibility program. All 3 of the proposed program elements were approved.
Proposed Modification of Class E Airspace; St. Johns, AZ
This notice proposes to modify the Class E airspace area at St. Johns, AZ. The establishment of an Area Navigation (RNAV) Global Positioning System (GPS) Standard Instrument Approach Procedure (SIAP) to Runway 32 at St. Johns Industrial Air Park, St. Johns, AZ, has made this proposal necessary. Additional controlled airspace extending upward from 700 feet above the surface is needed to contain aircraft executing the RNAV (GPS) IAP to RWY 32 at St. Johns Industrial Air Park makes this proposal necessary. The intended effect of this proposal is to provide adequate controlled airspace for aircraft executing the RNAV (GPS) IAP to RWY 32 at St. Johns Industrial Air Park, St. Johns, AZ.
Airworthiness Directives; Raytheon Aircraft Company Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) Airplanes
We are adopting a new airworthiness directive (AD) that supersedes AD 62-24-01, which applies to all Raytheon Aircraft Company (RAC) Beech Models 45 (YT-34), A45 (T-34A, B45), and D45 (T-34B) airplanes. AD 62-24-01 currently requires you to repetitively inspect, using the dye penetrant method, the front and rear horizontal stabilizer spars for cracks and replace any cracked stabilizer. Since we issued AD 62-24-01, we determined that using the dye penetrant inspection method may not detect cracks before the crack grows to a critical length and causes failure of the horizontal stabilizer spars. Therefore, we are requiring the surface eddy current inspection method to detect cracks in the horizontal stabilizer spars. Consequently, this AD retains the actions required in AD 62-24-01 and changes the required inspection method from dye penetrant to surface eddy current. We are issuing this AD to prevent failure of the front and/or rear horizontal stabilizer spars caused by fatigue cracks. This failure could result in stabilizer separation and loss of control of the airplane.