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비행장치를 항공기로 분류하게 되면 법적으로 갖추어야하는 필수장비가 만만치 않기 때문에 항공기로 분류되기를 망설이지는 않습니까? 불합리한 현행 항공법을 합리적으로 개정 한다면 초경량항공기(스포츠항공기)에는 무전기 한대만 달면 충분할 것입니다.
현재 250Kg로 신고하기 위해서 엔진을 달았다 떼었다 검사를 두번 받는데 드는 쓸데없는 비용이면 무전기 한대는 사고도 남을겁니다.
물론 여유가 되는 사람은 안전과 원할한 관제을 위해서 트랜스폰더까지 갖추면 금상첨화 이고요.
관련법규를 제대로만 고치면 비행장치가 아닌 항공기로 분류하여도 최소한 지금보다 손해날 일은 하나도 없다고 봅니다.
예전에는 무전기 2대, 비상위치무선표지설비(ELT), 트랜스폰더가 모든 항공기에 반드시 장착하여야 하는 필수장비는 아니던 것이 이제는 항공법 제40조가 개정되어 마치 필수장비처럼 되어 버렸습니다만 문제가 많은 규정으로,언제가 될지는 몰라도, 초경량을 항공기로 포함시키거나 스포츠항공기를 신설할 때에는 개정이 되어야 합니다.
1) 비상위치무선표지설비(ELT)
미국 항공법에서 ELT 규정을 보면 사업용이 아닌 소형자가용이나 스포츠항공기에는 적용이 되지 않는 것 같습니다.
2) 트랜스폰더
아래 글에서 소개한 우리날 AIP에서 공역 등급에 따른 의무무선 설비 규정에 의하면 E등급에서는 분명 트랜스폰더가 없어도 되도록 되어 있습니다.
항공기는 반드시 공항에 들어가야 한다는 법규정도 없는데 모든 항공기에 트랜스폰더는 왜 반드시 갖추어야 합니까?
초경량이나 스포츠항공기 같은 경우는 공항에 들어가지 않고도 E등급 공역만해도 얼마든지 다닙니다.
우리나라의 현행 AIP 규정 또는 미국이나 캐나다처럼, 트랜스폰더는 A, B, C, D 등급의 공역에서만 필수장비가 되도록 규정을 개정
3) 무전기 2대
마찬가지로 AIP에서 공역등급에 따른 의무무선설비로 모든 항공기에 무전기를 2대씩 요구하는 등급이나 규정이 없습니다.
미국 항공법에서도 운송사업용항공기에는 무전기를 2대 요구하지만 소형항공기에는 무전기를 2대씩이나 요구하지 않는 것 같습니다. VFR인 경우는 주간 야간 모두 무전기가 필수장비가 아니며, IFR 비행에도 무전기는 한대만 요구되는듯 합니다.
항공법
제40조 (의무무선설비) 항공기를 항공에 사용하고자 하는 자 또는 소유자등은 당해 항공기에 비상위치무선표지설비, 2차감시레이더용트랜스폰더 등 건설교통부령이 정하는 무선설비를 설치·운용하여야 한다.[전문개정 2005.11.8]
항공법시행규칙
제122조 (무선설비) ①법 제40조의 규정에 의하여 설치·운용하여야 하는 무선설비는 다음 각호와 같다. 다만, 항공운송사업에 사용되는 항공기외의 항공기가 계기비행방식외의 방식(이하 "시계비행방식"이라 한다)에 의한 비행을 하는 경우에는 제3호 내지 제7호의 무선설비를 설치·운용하지 아니할 수 있다. <개정 1994.11.30, 2001.9.24, 2004.7.3, 2005.3.11>
1. 비행중 항공교통관제기관과 교신할 수 있는 초단파(VHF) 또는 극초단파(UHF)무선 전화 송·수신기 각 2대. 이 경우 항공기의 운항승무원은 항공안전본부장이 정하여 고시하는 기압고도계의 수정을 위한 고도(이하 "전이고도"라 한다) 미만에서 교신을 하고자 할 경우에는 붐(Boom) 마이크로폰 또는 쓰롯(Throat) 마이크로폰을 사용하여야 한다.
2. 기압고도에 관한 정보를 제공하는 2차감시 항공교통관제 레이더용 트랜스폰다(Mode3/A 및 ModeC SSR transponder) 1대
3-7 생략
8. 다음 각목의 구분에 의한 비상위치지시용 무선표지설비(ELT)
가. 2대를 설치하여야 하는 경우 : 비상착륙에 적합한 육지로부터 순항속도로 120분 또는 740킬로미터(400해리)중 짧은거리 이상의 해상을 비행하는 항공기로서 다음의 1에 해당하는 항공기. 이 경우 비상위치지시용 무선표지 설비 2대중 1대는 자동으로 작동되는 구조이어야 한다.
(1) 2003년 1월 1일 이후 항공기 제작국가로부터 형식증명을 받는 항공기
(2) 2005년 1월 1일 이후의 모든 항공기
나. 1대 이상을 설치하여야 하는 경우 : 가목외의 항공기. 이 경우 2003년 1월 1일 이후 항공기 제작국가로부터 형식증명을 받는 항공기 및 2005년 1월 1일 이후의 모든 항공기에 장착되는 비상위치지시용 무선표지설비는 자동으로 작동되는 구조이어야 한다.
Sec. 91.207
Emergency locator transmitters.
(a) Except as provided in paragraphs (e) and (f) of this section, no person may operate a U.S.-registered civil airplane unless--
(1) There is attached to the airplane an approved automatic type emergency locator transmitter that is in operable condition for the following operations, except that after June 21, 1995, an emergency locator transmitter that meets the requirements of TSO-C91 may not be used for new installations:
(i) Those operations governed by the supplemental air carrier and commercial operator rules of parts 121 and 125;
(ii) Charter flights governed by the domestic and flag air carrier rules of part 121 of this chapter; and
(iii) Operations governed by part 135 of this chapter; or
(2) For operations other than those specified in paragraph (a)(1) of this section, there must be attached to the airplane an approved personal type or an approved automatic type emergency locator transmitter that is in operable condition, except that after June 21, 1995, an emergency locator transmitter that meets the requirements of TSO-C91 may not be used for new installations.
(b) Each emergency locator transmitter required by paragraph (a) of this section must be attached to the airplane in such a manner that the probability of damage to the transmitter in the event of crash impact is minimized. Fixed and deployable automatic type transmitters must be attached to the airplane as far aft as practicable.
(c) Batteries used in the emergency locator transmitters required by paragraphs (a) and (b) of this section must be replaced (or recharged, if the batteries are rechargeable)--
(1) When the transmitter has been in use for more than 1 cumulative hour; or
(2) When 50 percent of their useful life (or, for rechargeable batteries, 50 percent of their useful life of charge) has expired, as established by the transmitter manufacturer under its approval.
The new expiration date for replacing (or recharging) the battery must be legibly marked on the outside of the transmitter and entered in the aircraft maintenance record. Paragraph (c)(2) of this section does not apply to batteries (such as water-activated batteries) that are essentially unaffected during probable storage intervals.
(d) Each emergency locator transmitter required by paragraph (a) of this section must be inspected within 12 calendar months after the last inspection for--
(1) Proper installation;
(2) Battery corrosion;
(3) Operation of the controls and crash sensor; and
(4) The presence of a sufficient signal radiated from its antenna.
(e) Notwithstanding paragraph (a) of this section, a person may--
(1) Ferry a newly acquired airplane from the place where possession of it was taken to a place where the emergency locator transmitter is to be installed; and
(2) Ferry an airplane with an inoperative emergency locator transmitter from a place where repairs or replacements cannot be made to a place where they can be made.
No person other than required crewmembers may be carried aboard an airplane being ferried under paragraph (e) of this section.
(f) Paragraph (a) of this section does not apply to--
[ (1) Before January 1, 2004, turbojet-powered aircraft; ]
(2) Aircraft while engaged in scheduled flights by scheduled air carriers;
(3) Aircraft while engaged in training operations conducted entirely within a 50-nautical mile radius of the airport from which such local flight operations began;
(4) Aircraft while engaged in flight operations incident to design and testing;
(5) New aircraft while engaged in flight operations incident to their manufacture, preparation, and delivery;
(6) Aircraft while engaged in flight operations incident to the aerial application of chemicals and other substances for agricultural purposes;
(7) Aircraft certificated by the Administrator for research and development purposes;
(8) Aircraft while used for showing compliance with regulations, crew training, exhibition, air racing, or market surveys;
(9) Aircraft equipped to carry not more than one person; and
(10) An aircraft during any period for which the transmitter has been temporarily removed for inspection, repair, modification, or replacement, subject to the following:
(i) No person may operate the aircraft unless the aircraft records contain an entry which includes the date of initial removal, the make, model, serial number, and reason for removing the transmitter, and a placard located in view of the pilot to show "ELT not installed."
(ii) No person may operate the aircraft more than 90 days after the ELT is initially removed from the aircraft; and
[(11) On and after January 1, 2004, aircraft with a maximum payload capacity of more than 18,000 pounds when used in air transportation.]
Sec. 91.205
Powered civil aircraft with standard category U.S. airworthiness certificates: Instrument and equipment requirements.
(a) General. Except as provided in paragraphs (c)(3) and (e) of this section, no person may operate a powered civil aircraft with a standard category U.S. airworthiness certificate in any operation described in paragraphs (b) through (f) of this section unless that aircraft contains the
instruments and equipment specified in those paragraphs (or FAA-approved equivalents) for that type of operation, and those instruments and items of equipment are in operable condition.
(b) Visual-flight rules (day). For VFR flight during the day, the following instruments and equipment are required:
(1) Airspeed indicator.
(2) Altimeter.
(3) Magnetic direction indicator.
(4) Tachometer for each engine.
(5) Oil pressure gauge for each engine using pressure system.
(6) Temperature gauge for each liquid-cooled engine.
(7) Oil temperature gauge for each air-cooled engine.
(8) Manifold pressure gauge for each altitude engine.
(9) Fuel gauge indicating the quantity of fuel in each tank.
(10) Landing gear position indicator, if the aircraft has a retractable landing gear.
(11) For small civil airplanes certificated after March 11, 1996, in accordance with part 23 of this chapter, an approved aviation red or aviation white anticollision light system. In the event of failure of any light of the anticollision light system, operation of the aircraft may continue to a
location where repairs or replacement can be made.
[ (12) If the aircraft is operated for hire over water and beyond power-off gliding distance from shore, approved flotation gear readily available to each occupant and, unless the aircraft is operating under part 121 of this subchapter, at least one pyrotechnic signaling device. As used in this section, "shore" means that area of the land adjacent to the water which is above the high water mark and excludes land areas which are intermittently under water.]
(13) An approved safety belt with an approved metal-to-metal latching device for each occupant 2 years of age or older.
(14) For small civil airplanes manufactured after July 18, 1978, an approved shoulder harness for each front seat. The shoulder harness must be designed to protect the occupant from serious head injury when the occupant experiences the ultimate inertia forces specified in Sec. 23.561(b)(2) of this chapter. Each shoulder harness installed at a flight crewmember station
must permit the crewmember, when seated and with the safety belt and shoulder harness fastened, to perform all functions necessary for flight operations. For purposes of this paragraph--
(i) The date of manufacture of an airplane is the date the inspection acceptance records reflect that the airplane is complete and meets the FAA-approved type design data; and
(ii) A front seat is a seat located at a flight crewmember station or any seat located alongside such a seat.
(15) An emergency locator transmitter, if required by Sec. 91.207.
(16) For normal, utility, and acrobatic category airplanes with a seating configuration, excluding pilot seats, of 9 or less, manufactured after December 12, 1986, a shoulder harness for--
(i) Each front seat that meets the requirements of Sec. 23.785 (g) and (h) of this chapter in effect on December 12, 1985;
(ii) Each additional seat that meets the requirements of Sec. 23.785(g) of this chapter in effect on December 12, 1985.
(17) For rotorcraft manufactured after September 16, 1992, a shoulder harness for each seat that meets the requirements of Sec. 27.2 or Sec. 29.2 of this chapter in effect on September 16, 1991.
(c) Visual flight rules (night). For VFR flight at night, the following instruments and equipment are required:
(1) Instruments and equipment specified in paragraph (b) of this section.
(2) Approved position lights.
(3) An approved aviation red or aviation white anticollision light system on all U.S.-registered civil aircraft. Anticollision light systems initially installed after August 11, 1971, on aircraft for which a type certificate was issued or applied for before August 11, 1971, must at least meet the
anticollision light standards of part 23, 25, 27, or 29 of this chapter, as applicable, that were in effect on August 10, 1971, except that the color may be either aviation red or aviation white. In the event of failure of any light of the anticollision light system, operations with the aircraft may be
continued to a stop where repairs or replacement can be made.
(4) If the aircraft is operated for hire, one electric landing light.
(5) An adequate source of electrical energy for all installed electrical and radio equipment.
(6) One spare set of fuses, or three spare fuses of each kind required, that are accessible to the pilot in flight.
(d) Instrument flight rules. For IFR flight, the following instruments and equipment are required:
(1) Instruments and equipment specified in paragraph (b) of this section, and, for night flight, instruments and equipment specified in paragraph (c) of this section.
(2) Two-way radio communications system and navigational equipment appropriate to the ground facilities to be used.
(3) Gyroscopic rate-of-turn indicator, except on the following aircraft:
(i) Airplanes with a third attitude instrument system usable through flight attitudes of 360 degrees of pitch and roll and installed in accordance with the instrument requirements prescribed in Sec. 121.305(j) of this chapter; and
(ii) Rotorcraft with a third attitude instrument system usable through flight attitudes of ±80 degrees of pitch and ±120 degrees of roll and installed in accordance with Sec. 29.1303(g) of this chapter.
(4) Slip-skid indicator.
(5) Sensitive altimeter adjustable for barometric pressure.
(6) A clock displaying hours, minutes, and seconds with a sweep-second pointer or digital presentation.
(7) Generator or alternator of adequate capacity.
(8) Gyroscopic pitch and bank indicator (artificial horizon).
(9) Gyroscopic direction indicator (directional gyro or equivalent).
(e) Flight at and above 24,000 ft. MSL (FL 240). If VOR navigational equipment is required under paragraph (d)(2) of this section, no person may operate a U.S.-registered civil aircraft within the 50 states and the District of Columbia at or above FL 240 unless that aircraft is equipped with approved distance measuring equipment (DME). When DME required by this paragraph fails at and above FL 240, the pilot in command of the aircraft shall notify ATC immediately, and then may continue operations at and above FL 240 to the next airport of intended landing at which repairs or replacement of the equipment can be made.
(f) Category II operations. The requirements for Category II operations are the instruments and equipment specified in--
(1) Paragraph (d) of this section; and
(2) Appendix A to this part.
(g) Category III operations. The instruments and equipment required for Category III operations are specified in paragraph (d) of this section.
(h) Exclusions. Paragraphs (f) and (g) of this section do not apply to operations conducted by a holder of a certificate issued under part 121 or part 135 of this chapter.
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