14 CFR 23.963 - Fuel tanks: General.
(a) Each fuel tank must be able to withstand, without failure, the vibration, inertia, fluid, and structural loads that it may be subjected to in operation.
(b) Each flexible fuel tank liner must be shown to be suitable for the particular application.
(c) Each integral fuel tank must have adequate facilities for interior inspection and repair.
(d) The total usable capacity of the fuel tanks must be enough for at least one-half hour of operation at maximum continuous power.
(e) Each fuel quantity indicator must be adjusted, as specified in § 23.1337(b), to account for the unusable fuel supply determined under § 23.959(a).
Title 14 published on 03-May-2017 03:58
The following are ALL rules, proposed rules, and notices (chronologically) published in the Federal Register relating to 14 CFR Part 23 after this date.
GPO FDSys XML | Text type regulations.gov FR Doc. 2017-08234 RIN Docket No. FAA-2017-0381 Special Conditions No. 23-280-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; request for comments. The effective date of these special conditions is April 24, 2017. We must receive your comments by June 8, 2017. 14 CFR Part 23 These special conditions are issued for the Viking Air, Ltd., models DHC-6-100/-200/-300, Twin Otter, Turbopropeller airplanes. This airplane, as modified by Avmax Aviation Services, Inc., will have a novel or unusual design feature associated with the use of a replacement option of a lithium battery instead of nickel-cadmium and lead-acid rechargeable batteries. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2017-07382 RIN Docket No. FAA-2017-0290 Notice No. 23-17-01-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed special conditions. Send your comment on or before May 15, 2017. 14 CFR Part 23 This action proposes a special condition for the Pilatus Aircraft Limited PC-12, PC-12/45, and PC-12/47 airplanes. These airplanes, as modified by Innovative Solutions & Support, Inc., will have a novel or unusual design feature associated with the use of an autothrust system. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. This proposed special condition contains the additional safety standards the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
GPO FDSys XML | Text type regulations.gov FR Doc. 2017-02582 RIN 2120-AJ94 Docket No. FAA-2013-0485 Amdt. Nos. 1-70A, 23-63A, 25-144A, 27-48A, 29-56A, 61-139A, 91-345A, 121-376A, 125-66A, and 135-135A DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final rule; delay of effective date. The effective date of the rule amending 14 CFR parts 1, 23, 25, 27, 29, 61, 91, 121, 125, and 135 published at 81 FR 90126, December 13, 2016, is delayed until March 21, 2017, except for the amendments to §§ 61.66 (amendatory instruction no. 15), 91.175 (amendatory instruction no. 18), 91.1039 (amendatory instruction no. 23), 121.651 (amendatory instruction no. 27), 125.325 (amendatory instruction no. 33), 125.381 (amendatory instruction no. 35), and 135.225 (amendatory instruction no. 38), which are effective March 13, 2018. 14 CFR Parts 1, 23, 25, 27, 29, 61, 91, 121, 125, and 135 On December 13, 2016, the Federal Aviation Administration (FAA) published a final rule to permit operators to use an enhanced flight vision system in lieu of natural vision to continue descending from 100 feet above the touchdown zone elevation to the runway and to land on certain straight-in instrument approach procedures under instrument flight rules. The FAA is delaying the effective date of this final rule.
GPO FDSys XML | Text type regulations.gov FR Doc. C1-2016-28714 RIN 2120-AJ94 Docket No. FAA-2013-0485 Amdt. Nos. 1-70, 23-63, 25-144, 27-48, 29-56, 61-139, 91-345, 121-376, 125-66, and 135-135 DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration 14 CFR Parts 1, 23, 25, 27, 29, 61, 91, 121, 125, and 135
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-31819 RIN Docket No. FAA-2016-9409 Special Conditions No. 23-279-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions. These special conditions are effective January 5, 2017 and are applicable on December 23, 2016. 14 CFR Part 23 These special conditions are issued for the Cessna Aircraft Company model 525 airplane. This airplane as modified by Cranfield Aerospace Limited will have a novel or unusual design feature associated with the installation of a Tamarack Active Technology Load Alleviation System and Cranfield Winglets. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-30246 RIN 2120-AK65 Docket No. FAA-2015-1621 Amdt. Nos. 21-100, 23-64, 35-10, 43-49, 91-346, 121-378, and 135-136 DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final rule. Effective August 30, 2017. 14 CFR Parts 21, 23, 35, 43, 91, 121, and 135 The FAA amends its airworthiness standards for normal, utility, acrobatic, and commuter category airplanes by replacing current prescriptive design requirements with performance-based airworthiness standards. These standards also replace the current weight and propulsion divisions in small airplane regulations with performance- and risk-based divisions for airplanes with a maximum seating capacity of 19 passengers or less and a maximum takeoff weight of 19,000 pounds or less. These airworthiness standards are based on, and will maintain, the level of safety of the current small airplane regulations, except for areas addressing loss of control and icing, for which the safety level has been increased. The FAA adopts additional airworthiness standards to address certification for flight in icing conditions, enhanced stall characteristics, and minimum control speed to prevent departure from controlled flight for multiengine airplanes. This rulemaking is in response to the Congressional mandate set forth in the Small Airplane Revitalization Act of 2013.
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-29769 RIN Docket No. FAA-2016-9172 Special Conditions No. 23-276-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions. These special conditions are effective December 13, 2016 and are applicable on December 6, 2016. 14 CFR Part 23 These special conditions are issued for the installation of an inflatable four-point restraint safety belt with an integrated airbag device at the pilot and copilot seats on the DAHER-SOCATA, Model TBM 700 airplane. These airplanes, as modified by the installation of these inflatable safety belts, will have novel and unusual design features associated with the upper-torso restraint portions of the four-point safety belts, which contain 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-28714 RIN 2120-AJ94 Docket No. FAA-2013-0485 Amdt. Nos. 1-70, 23-63, 25-144, 27-48, 29-56, 61-139, 91-345, 121-376, 125-66, and 135-135 DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final rule. The final rule is effective March 13, 2017, except for the amendments to §§ 61.66 (amendatory instruction no. 15), 91.175 (amendatory instruction no. 18), 91.1039 (amendatory instruction no. 23), 121.651 (amendatory instruction no. 27), 125.325 (amendatory instruction no. 33), 125.381 (amendatory instruction no. 35), and 135.225 (amendatory instruction no. 38), which are effective March 13, 2018. 14 CFR Parts 1, 23, 25, 27, 29, 61, 91, 121, 125, and 135 Prior to this final rule, persons could only use an Enhanced Flight Vision System (EFVS) in lieu of natural vision to descend below the decision altitude, decision height, or minimum descent altitude (DA/DH or MDA) down to 100 feet above the touchdown zone elevation (TDZE) using certain straight-in landing instrument approach procedures (IAPs). This final rule permits operators to use an EFVS in lieu of natural vision to continue descending from 100 feet above the TDZE to the runway and to land on certain straight-in IAPs under instrument flight rules (IFR). This final rule also revises and relocates the regulations that permit operators to use an EFVS in lieu of natural vision to descend to 100 feet above the TDZE using certain straight-in IAPs. Additionally, this final rule addresses provisions that permit operators who conduct EFVS operations under parts 121, 125, or 135 to use EFVS-equipped aircraft to dispatch, release, or takeoff under IFR, and revises the regulations for those operators to initiate and continue an approach, when the destination airport weather is below authorized visibility minimums for the runway of intended landing. This final rule establishes pilot training and recent flight experience requirements for operators who use EFVS in lieu of natural vision to descend below the DA/DH or MDA. EFVS-equipped aircraft conducting operations to touchdown and rollout are required to meet additional airworthiness requirements. This final rule also revises pilot compartment view certification requirements for vision systems using a transparent display surface located in the pilot's outside field of view. The final rule takes advantage of advanced vision capabilities, thereby achieving the Next Generation Air Transportation System (NextGen) goals of increasing access, efficiency, and throughput at many airports when low visibility is the limiting factor. Additionally, it enables EFVS operations in reduced visibilities on a greater number of approach procedure types while maintaining an equivalent level of safety.
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-28016 RIN Docket No. FAA-2016-9409 Notice No. 23-16-03-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed special conditions. Send your comments on or before December 22, 2016. 14 CFR Part 23 This action proposes special conditions for the Cessna Aircraft Company model 525 airplane. This airplane as modified by Cranfield Aerospace Limited will have a novel or unusual design features associated with the installation of a Tamarack Active Technology Load Alleviation System and Cranfield Winglets. These design features will include winglets and an Active Technology Load Alleviation System. 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 the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-28013 RIN Docket No. FAA-2016-9001 Special Conditions No. 23-278-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions. These special conditions are effective November 21, 2016 and are applicable on November 10, 2016. 14 CFR Part 23 These special conditions are issued for the Pilatus Aircraft, Ltd., Model PC-12, PC-12/45, and PC-12/47 airplanes. This airplane as modified by Finnoff Aviation will have a novel or unusual design feature associated with the installation of a rechargeable lithium battery. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-24343 RIN Docket No. FAA-2016-9224 Special Conditions No. 23-277-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; request for comments. The effective date of these special conditions is October 7, 2016. We must receive your comments by November 21, 2016. 14 CFR Part 23 These special conditions are issued for the Beechcraft, Model A36, Bonanza airplane. This airplane, as modified by Avionics Design Services, Ltd., will have a novel or unusual design feature associated with the use of a replacement option of a lithium battery instead of nickel-cadmium and lead-acid rechargeable batteries. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-23564 RIN Docket No. FAA-2016-9172 Special Conditions No. 23-276-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; request for comments. The effective date of these special conditions is September 30, 2016. We must receive your comments by October 31, 2016. 14 CFR Part 23 These special conditions are issued for the installation of an inflatable four-point restraint safety belt with an integrated airbag device at the pilot and copilot seats on the DAHER-SOCATA, Model TBM 700 airplane. These airplanes, as modified by the installation of these inflatable safety belts, will have novel and unusual design features associated with the upper-torso restraint portions of the four-point safety belts, which contain 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-20273 RIN Docket No. FAA-2016-9001 Notice No. 23-16-02-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed special conditions. Send your comments on or before October 11, 2016. 14 CFR Part 23 This action proposes special conditions for the Pilatus Aircraft, Ltd., Model PC-12, PC-12/45, and PC-12/47 airplanes. This airplane as modified by Finnoff Aviation will have a novel or unusual design feature associated with the installation of a rechargeable lithium battery. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-16813 RIN Docket No. FAA-2016-3462 Notice No. 23-275-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions. These special conditions are effective August 15, 2016 and are applicable on July 6, 2016. 14 CFR Part 23 These special conditions are issued for the Cirrus Design Corporation (Cirrus), model SF50 airplane. This airplane will have a novel or unusual design feature(s) associated with a whole airplane parachute recovery 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-15765 RIN Docket No. FAA-2015-5034 Special Conditions No. 23-273-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions. These special conditions are effective July 5, 2016 and are applicable on June 23, 2016. 14 CFR Part 23 These special conditions are issued for the Kestrel Aircraft Company, Model K-350 Turboprop airplane. This airplane will have a novel or unusual design feature associated with the installation of a rechargeable lithium battery. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-11502 RIN Docket No. FAA-2016-6567 Special Conditions No. 23-274-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; request for comments. The effective date of these special conditions is May 16, 2016. We must receive your comments by June 15, 2016. 14 CFR Part 23 These special conditions are issued for the Cessna Aircraft Company, Models 208 and 208B Caravan airplanes. This airplane, as modified by Peregrine, will have a novel or unusual design feature associated with the use of a replacement option of a lithium battery instead of nickel-cadmium (Ni-Cd) and lead-acid rechargeable batteries. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-07943 RIN Docket No. FAA-2015-1621 DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of public meeting. The public meetings will be held on the following dates: (Note that the meetings may be adjourned early if the agenda is completed in less time than is scheduled for the meetings.) • May 3, 2016 from 8:00 a.m. until no later than 5:00 p.m. • May 4, 2016 from 8:00 a.m. until no later than 5:00 p.m. The NPRM written comment period will close on May 13, 2016. 14 CFR Part 23 The FAA announces public meeting on its proposal to revise Part 23 Airworthiness Standards for Normal, Utility, Acrobatic, and Commuter Category Airplanes. The purpose of the public meeting is for the FAA to explain and answer questions concerning the language related to its Notice of Proposed Rulemaking (NPRM) (81 FR 13452, March 14, 2016).
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-06072 RIN Docket No. FAA-2016-3462 Notice No. 23-16-01-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed special conditions. Send your comments on or before May 2, 2016. 14 CFR Part 23 This action proposes special conditions for the Cirrus Design Corporation (Cirrus), model SF50 airplane. This airplane will have a novel or unusual design feature(s) associated with a whole airplane parachute recovery system. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2016-05493 RIN 2120-AK65 Docket No. FAA-2015-1621 Notice No. 16-01 DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed rulemaking (NPRM). Send comments on or before May 13, 2016. 14 CFR Parts 21, 23, 35, 43, 91, 121, and 135 The FAA proposes to amend its airworthiness standards for normal, utility, acrobatic, and commuter category airplanes by removing current prescriptive design requirements and replacing them with performance-based airworthiness standards. The proposed standards would also replace the current weight and propulsion divisions in small airplane regulations with performance- and risk-based divisions for airplanes with a maximum seating capacity of 19 passengers or less and a maximum takeoff weight of 19,000 pounds or less. The proposed airworthiness standards are based on, and would maintain, the level of safety of the current small airplane regulations. Finally, the FAA proposes to adopt additional airworthiness standards to address certification for flight in icing conditions, enhanced stall characteristics, and minimum control speed to prevent departure from controlled flight for multiengine airplanes. This notice of proposed rulemaking addresses the Congressional mandate set forth in the Small Airplane Revitalization Act of 2013.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-31058 RIN Docket No. FAA-2015-3464 Special Conditions No. 23-272-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions. The effective date of these special conditions is December 9, 2015 and are applicable on December 2, 2015. 14 CFR Part 23 These special conditions are issued for the Cirrus Aircraft Corporation Model SF50 airplane. This airplane will have a novel or unusual design feature(s) associated with installation of an Auto Throttle 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-28125 RIN Docket No. FAA-2015-5034 Notice No. 23-15-01-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed special conditions. Send your comments on or before December 21, 2015. 14 CFR Part 23 This action proposes special conditions for the Kestrel Aircraft Company, Model K-350 Turboprop airplane. This airplane will have a novel or unusual design feature associated with the installation of a rechargeable lithium battery. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-27700 RIN Docket No. FAA-2015-3880 Special Conditions No. 23-271-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions. These special conditions are effective October 30, 2015 and are applicable on October 26, 2015. 14 CFR Part 23 These special conditions are issued for the Honda Aircraft Company HA-420 airplane. This airplane will have a novel or unusual design feature(s) associated with the use of a cruise speed 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-24156 RIN Docket No. FAA-2015-3881 Special Conditions No. 23-267-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; request for comments. The effective date of these special conditions is September 23, 2015. We must receive your comments by October 23, 2015. 14 CFR Part 23 These special conditions are issued for the Cirrus Design Corporation SF50 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-24164 RIN Docket No. FAA-2015-0721 Notice No. 23-269-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions. These special conditions are effective September 23, 2015. 14 CFR Part 23 These special conditions are issued for the Honda Aircraft Company, Model HA-420 airplane. This airplane will have a novel or unusual design feature associated with the installation of lithium-ion (Li-ion) batteries. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-24161 RIN Docket No. FAA-2015-3880 Notice No. 23-15-05-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed special conditions. Send your comments on or before October 23, 2015. 14 CFR Part 23 This action proposes special conditions for the Honda Aircraft Company HA-420 airplane. This airplane will have a novel or unusual design feature(s) associated with the use of a cruise speed control system. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-22872 RIN Docket No. FAA-2015-3678 Special Conditions No. 23-268-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; request for comments. The effective date of these special conditions is September 11, 2015. We must receive your comments by October 26, 2015. 14 CFR Part 23 These special conditions are issued for the Korea Aerospace Industries, Ltd., Model K-100 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-20756 RIN Docket No. FAA-2015-3464 Notice No. 23-15-04-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed special conditions. Send your comments on or before October 5, 2015. 14 CFR Part 23 This action proposes special conditions for the Cirrus Aircraft Corporation Model SF50 airplane. This airplane will have a novel or unusual design feature(s) associated with installation of an Auto Throttle System. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-20555 RIN 2120-AJ94 Docket No. FAA-2013-0485 Notice No. 12-09B DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed rulemaking; reopening of comment period. The comment period for the NPRM published on June 11, 2013 (78 FR 34935) closed October 15, 2013, and is reopened until September 21, 2015. 14 CFR Part 1, 23, 25, 27, 29, 61, 91, 121, 125, 135 This action reopens the comment period for the regulatory evaluation associated with the FAA's June 11, 2013 Notice of Proposed Rulemaking (NPRM), Revisions to Operational Requirements for the Use of Enhanced Flight Vision Systems (EFVS) and to Pilot Compartment View Requirements for Vision Systems. The regulatory evaluation associated with the NPRM was not posted to the docket prior to the close of the comment period. Therefore, the FAA is reopening the comment period to allow the public the opportunity to adequately analyze the full regulatory evaluation for the NPRM. The FAA will accept comments on the regulatory evaluation only; and not on the regulatory changes proposed in the NPRM.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-19835 RIN Docket No. FAA-2015-2903 Special Conditions No. 23-270-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; request for comments. The effective date of these special conditions is August 12, 2015. We must receive your comments by September 11, 2015 14 CFR Part 23 These special conditions are issued for the Honda Aircraft Company, Model HA-420 airplane. This airplane will have a novel or unusual design feature associated with high altitude operations above 41,000 feet. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-14816 RIN Docket No. FAA-2015-0722 Special Conditions No. 23-265-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; request for comments. The effective date of these special conditions is June 16, 2015. We must receive your comments by July 16, 2015. 14 CFR Part 23 These special conditions are issued for the Honda Aircraft Company model HA-420 airplane. This airplane will have a novel or unusual design feature associated with mounting the engines on the wings in close proximity to the aft fuselage. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-12262 RIN Docket No. CE306 Special Conditions No. 23-246-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; withdrawal. Effective May 21, 2015, the special condition published on April 20, 2010 (75 FR 20518) is withdrawn. 14 CFR Part 23 The FAA is withdrawing a previously published document granting special conditions for the Cirrus Design Corporation model SF50 airplane. We are withdrawing Special Condition No. 23-246-SC through mutual agreement with Cirrus Design Corporation.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-09742 RIN Docket No. CE287 Special Conditions No. 23-227-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; withdrawal. This special condition published on September 23, 2008 (73 FR 54675) is withdrawn, effective April 27, 2015. 14 CFR Part 23 The FAA is withdrawing a previously published notice granting special conditions for the Honda Aircraft Company model HA-420 jet airplane. We are withdrawing Special Condition No. 23-227-SC through mutual agreement with Honda Aircraft Company.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-09743 RIN Docket No. CE277 Special Conditions No. 23-217-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; withdrawal. This special condition published on December 10, 2007 (72 FR 69572) is withdrawn, effective April 27, 2015. 14 CFR Part 23 The FAA is withdrawing a previously published notice granting special conditions for the Honda Aircraft Company model HA-420 jet airplane. We are withdrawing Special Condition No. 23-217-SC through mutual agreement with Honda Aircraft Company.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-08586 RIN Docket No. FAA-2015-0721 Notice No. 23-15-03-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed special conditions. Send your comments on or before May 4, 2015. 14 CFR Part 23 This action proposes special conditions for the Honda Aircraft Company, Model HA-420 airplane. This airplane will have a novel or unusual design feature associated with the installation of lithium-ion (Li-ion) batteries. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-07503 RIN Docket No. FAA-2015-0720 Special Conditions No. 23-263-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; request for comments. The effective date of these special conditions is April 1, 2015, and is applicable on March 25, 2015. We must receive your comments by May 1, 2015. 14 CFR Part 23 These special conditions are issued for the Honda Aircraft Company HA-420 airplane. This airplane will have a novel or unusual design feature(s) associated with a side-facing passenger seat. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2015-07502 RIN Docket No. FAA-2015-0723 Special Conditions No. 23-264-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; request for comments. The effective date of these special conditions is April 1, 2015, and is applicable on March 25, 2015. We must receive your comments by May 1, 2015. 14 CFR Part 23 These special conditions are issued for the Honda Aircraft Company HA-420 airplane. This airplane will have a novel or unusual design feature 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2014-10392 RIN Docket No. FAA-2014-0155 Notice No. 23-262-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions. These special conditions are May 7, 2014, and are applicable beginning April 25, 2014. 14 CFR Part 23 These special conditions are issued for the Extra EA-300/LC airplane. This airplane will have a novel or unusual design feature(s) associated with static stability. This airplane can perform at the highest level of aerobatic competition. To be competitive, the aircraft was designed with positive and, at some points, neutral stability within its flight envelope. Its lateral and directional axes are also decoupled from each other providing more precise maneuvering. 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 airworthiness standards to EA-300/LC airplanes certified solely in the acrobatic category.
GPO FDSys XML | Text type regulations.gov FR Doc. 2014-05951 RIN Docket No. FAA-2014-0155 Notice No. 23-14-01-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed special conditions. Send your comments on or before April 17, 2014. 14 CFR Part 23 This action proposes special conditions for the Extra EA-300/LC airplane. This airplane will have a novel or unusual design feature(s) associated with static stability. This airplane can perform at the highest level of aerobatic competition. To be competitive, the aircraft was designed with positive and, at some points, neutral stability within its flight envelope. Its lateral and directional axes are also decoupled from each other providing more precise maneuvering. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for these design features. 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 to EA-300/LC airplanes certified solely in the acrobatic category.
GPO FDSys XML | Text type regulations.gov FR Doc. 2013-22848 RIN Docket No. FAA-2013-0650 Notice No. 23-13-01-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions. The effective date of these special conditions is September 11, 2013. 14 CFR Part 23 These special conditions are issued for the Eclipse EA500 airplane. This airplane as modified by Innovative Solutions and Support (IS&S) will have a novel or unusual design feature(s) associated with the autothrottle system (ATS). 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2013-22101 RIN Docket No. FAA-2013-0781 Special Conditions No. 23-261-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; request for comments. The effective date of these special conditions is September 11, 2013. We must receive comments by October 11, 2013. 14 CFR Part 23 These special conditions are issued for the Cirrus Design Corporation (Cirrus), model SF50. This airplane will have novel and unusual design features associated with installation of an inflatable three-point restraint safety belt with an integrated airbag device at the pilot and co-pilot seats to include optional installations at other passenger seat locations. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2013-21698 RIN 2120-AJ94 Docket No. FAA-2013-0485 Notice No. 1209 DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed rulemaking (NPRM); extension of comment period. The comment period for the NPRM published on June 11, 2013, was scheduled to close on September 9, 2013, and is extended until October 15, 2013. 14 CFR Part 1, 23, 25, 27, 29, 61, 91, 121, 125, and 135 This action extends the comment period for an NPRM that was published on June 11, 2013. In that document, the FAA proposed to permit operators to use an EFVS in lieu of natural vision to continue descending from 100 feet height above runway touchdown zone elevation and land on certain straight-in instrument approach procedures under instrument flight rules. This rule would also permit certain operators using EFVS-equipped aircraft to dispatch, release, or takeoff under instrument flight rules (IFR), and to initiate and continue an approach, when the destination airport weather is below authorized visibility minimums for the runway of intended landing. Pilot training, recent flight experience, and proficiency would be required for operators who use EFVS in lieu of natural vision to descend below decision altitude, decision height, or minimum descent altitude. EFVS-equipped aircraft conducting operations to touchdown and rollout would be required to meet additional airworthiness requirements. This rule would also revise pilot compartment view certification requirements for all vision systems. Given the technical complexity of the NPRM, Dassault-Aviation has requested that the FAA extend the comment period to October 15, 2013 to allow time to adequately analyze the NPRM and provide meaningful comments.
GPO FDSys XML | Text type regulations.gov FR Doc. 2013-20152 RIN Docket No. FAA-2013-0413 Special Conditions No. 23-259-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions. Effective Date: August 19, 2013. 14 CFR Part 23 These special conditions are issued for the Cessna Aircraft Company (Cessna) Model J182T airplane. This airplane will have a novel or unusual design feature(s) associated with the installation of an aircraft diesel engine (ADE). 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2013-18399 RIN Docket No. FAA-2013-0650 Notice No. 23-13-01-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed special conditions. We must receive your comments by August 30, 2013. 14 CFR Part 23 This action proposes special conditions for the Eclipse EA500 airplane. This airplane as modified by Innovative Solutions and Support (IS&S) will have a novel or unusual design feature(s) associated with the autothrottle system (ATS). 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2013-13841 RIN Docket No. FAA-2013-0493 Special Conditions No. 23-260-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; request for comments. The effective date of these special conditions is June 25, 2013. We must receive your comments by July 25, 2013. 14 CFR Part 23 These special conditions are issued for the Cessna Aircraft Company (Cessna) Model J182T airplane. This airplane will have a novel or unusual design feature(s) associated with the installation of an electronic engine control. 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2013-14327 RIN Docket No. CE308 Special Conditions No. 23-248-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; withdrawal. This special condition published on August 18, 2010 at 75 FR 50853 is withdrawn, effective June 17, 2013. 14 CFR Part 23 The FAA is withdrawing a previously published notice granting special conditions for the Cirrus Design Corporation model SF50 airplane. We are withdrawing Special Condition No. 23-248-SC through mutual agreement with Cirrus Design Corporation.
GPO FDSys XML | Text type regulations.gov FR Doc. 2013-14151 RIN Docket No. CE305 Special Conditions No. 23-245-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; withdrawal. This special condition published on April 20, 2010 at 75 FR 20518 is withdrawn, effective June 14, 2013. 14 CFR Part 23 The FAA is withdrawing a previously published notice granting special conditions for the Cirrus Design Corporation model SF50 airplane. We are withdrawing Special Condition No. 23-245-SC through mutual agreement with Cirrus Design Corporation.
GPO FDSys XML | Text type regulations.gov FR Doc. 2013-13454 RIN 2120-AJ94 Docket No. FAA-2013-0485 Notice No. 1209 DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Notice of proposed rulemaking (NPRM). Send comments on or before September 9, 2013. 14 CFR Parts 1, 23, 25, 27, 29, 61, 91, 121, 125, and 135 The FAA is proposing to permit operators to use an Enhanced Flight Vision System (EFVS) in lieu of natural vision to continue descending from 100 feet above the touchdown zone elevation to the runway and land on certain straight-in instrument approach procedures under instrument flight rules (IFR). This proposal would also permit certain operators using EFVS-equipped aircraft to dispatch, release, or takeoff under IFR, and to initiate and continue an approach, when the destination airport weather is below authorized visibility minimums for the runway of intended landing. Under this proposal, pilot training, recent flight experience, and proficiency would be required for operators who use EFVS in lieu of natural vision to descend below decision altitude, decision height, or minimum descent altitude. EFVS-equipped aircraft conducting operations to touchdown and rollout would be required to meet additional airworthiness requirements. This proposal would also revise pilot compartment view certification requirements for vision systems using a transparent display surface located in the pilot's outside view. The proposal would take advantage of advanced vision capabilities thereby achieving the NextGen goals of increasing access, efficiency, and throughput at many airports when low visibility is the limiting factor. Additionally, it would enable EFVS operations in reduced visibilities on a greater number of approach procedure types while maintaining an equivalent level of safety.
GPO FDSys XML | Text type regulations.gov FR Doc. 2013-11731 RIN Docket No. FAA-2013-0413 Special Conditions No. 23-259-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions; request for comments. The effective date of these special conditions is May 8, 2013. We must receive your comments by June 17, 2013. 14 CFR Part 23 These special conditions are issued for the Cessna Aircraft Company (Cessna) Model J182T airplane. This airplane will have a novel or unusual design feature(s) associated with the installation of an aircraft diesel engine (ADE). 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.
GPO FDSys XML | Text type regulations.gov FR Doc. 2013-03296 RIN Docket No. FAA-2012-0485 Special Conditions No. 23-258A-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Amended final special conditions; request for comments. This final rule is effective February 13, 2013, and is applicable beginning February 6, 2013. Comments must be received by March 15, 2013. 14 CFR Part 23 This action amends special conditions No. 23-258-SC, issued on July 13, 2012, for the Tamarack Aerospace Group's modification to the Cirrus Model SR22 airplane. This amendment clarifies the intent of two requirements: The requirement for reporting of load alleviation system failures (see paragraph (c) under Loads, Probability of Failure of Load Alleviation System) and the requirement for consideration of limit loads with an unannunciated load alleviation system failure (see paragraph (b) under Factor of Safety, Load Alleviation Systems). This airplane as modified by Tamarack will have a novel or unusual design feature(s) associated with Tamarack Aerospace Group's modification. The design change will install winglets and an Active Technology Load Alleviation System (ATLAS). The addition of the ATLAS mitigates the negative effects of the winglets by effectively aerodynamically turning off the winglet under limit gust and maneuver loads. This is accomplished by measuring the aircraft loading and moving a small aileron-like device called a Tamarack Active Control Surface (TACS). The TACS movement reduces lift at the tip of the wing, resulting in the wing center of pressure moving inboard, thus reducing bending stresses along the wing span. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These final 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. Additionally, this amendment corrects the issue date of special condition No. 23-258-SC to July 13, 2012.
GPO FDSys XML | Text type regulations.gov FR Doc. 2012-17864 RIN Docket No. FAA-2012-0485 Special Conditions No. 23-258-SC DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration Final special conditions. Effective Date: July 13, 2013. 14 CFR Part 23 These special conditions are issued for the Tamarack Aerospace Group's modification to the Cirrus SR22 airplane. This airplane as modified by Tamarack will have a novel or unusual design feature(s) associated with Tamarack Aerospace Group's modification. The design change will install winglets and an Active Technology Load Alleviation system (ATLAS). The addition of the ATLAS mitigates the negative effects of the winglets by effectively aerodynamically turning off the winglet under limit gust and maneuver loads. This is accomplished by measuring the aircraft loading and moving a small aileron-like device called a Tamarack Active Control Surface (TACS). The TACS movement reduces lift at the tip of the wing, resulting in the wing center of pressure moving inboard, thus reducing bending stresses along the wing span. 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.