14 C.F.R. Subpart C—Aircraft and Equipment
Title 14 - Aeronautics and Space
This subpart prescribes aircraft and equipment requirements for operations under this part. The requirements of this subpart are in addition to the aircraft and equipment requirements of part 91 of this chapter. However, this part does not require the duplication of any equipment required by this chapter. (a) No person may operate an aircraft under this part unless that aircraft and its equipment meet the applicable regulations of this chapter. (b) Except as provided in §135.179, no person may operate an aircraft under this part unless the required instruments and equipment in it have been approved and are in an operable condition. (c) ATC transponder equipment installed within the time periods indicated below must meet the performance and environmental requirements of the following TSO's: (1) Through January 1, 1992: (i) Any class of TSO-C74b or any class of TSO-C74c as appropriate, provided that the equipment was manufactured before January 1, 1990; or (ii) The appropriate class of TSO-C112 (Mode S). (2) After January 1, 1992: The appropriate class of TSO-C112 (Mode S). For purposes of paragraph (c)(2) of this section, “installation” does not include— (i) Temporary installation of TSO-C74b or TSO-C74c substitute equipment, as appropriate, during maintenance of the permanent equipment; (ii) Reinstallation of equipment after temporary removal for maintenance; or (iii) For fleet operations, installation of equipment in a fleet aircraft after removal of the equipment for maintenance from another aircraft in the same operator's fleet. [Doc. No. 16097, 43 FR 46783, Oct. 10, 1978, as amended by Amdt. 135–22, 52 FR 3392, Feb. 3, 1987] (a) Except as provided in paragraph (b) of this section, no person may operate, nor may any operator or pilot in command of an aircraft allow the operation of, any portable electronic device on any of the following U.S.-registered civil aircraft operating under this part. (b) Paragraph (a) of this section does not apply to— (1) Portable voice recorders; (2) Hearing aids; (3) Heart pacemakers; (4) Electric shavers; or (5) Any other portable electronic device that the part 119 certificate holder has determined will not cause interference with the navigation or communication system of the aircraft on which it is to be used. (c). The determination required by paragraph (b)(5) of this section shall be made by that part 119 certificate holder operating the aircraft on which the particular device is to be used. [Doc. No. FAA–1998–4954, 64 FR 1080, Jan. 7, 1999] (a) No certificate holder may operate an aircraft, other than a turbojet aircraft, for which two pilots are required by this chapter for operations under VFR, if it has not previously proved such an aircraft in operations under this part in at least 25 hours of proving tests acceptable to the Administrator including— (1) Five hours of night time, if night flights are to be authorized; (2) Five instrument approach procedures under simulated or actual conditions, if IFR flights are to be authorized; and (3) Entry into a representative number of en route airports as determined by the Administrator. (b) No certificate holder may operate a turbojet airplane if it has not previously proved a turbojet airplane in operations under this part in at least 25 hours of proving tests acceptable to the Administrator including— (1) Five hours of night time, if night flights are to be authorized; (2) Five instrument approach procedures under simulated or actual conditions, if IFR flights are to be authorized; and (3) Entry into a representative number of en route airports as determined by the Administrator. (c) No certificate holder may carry passengers in an aircraft during proving tests, except those needed to make the tests and those designated by the Administrator to observe the tests. However, pilot flight training may be conducted during the proving tests. (d) Validation testing is required to determine that a certificate holder is capable of conducting operations safely and in compliance with applicable regulatory standards. Validation tests are required for the following authorizations: (1) The addition of an aircraft for which two pilots are required for operations under VFR or a turbojet airplane, if that aircraft or an aircraft of the same make or similar design has not been previously proved or validated in operations under this part. (2) Operations outside U.S. airspace. (3) Class II navigation authorizations. (4) Special performance or operational authorizations. (e) Validation tests must be accomplished by test methods acceptable to the Administrator. Actual flights may not be required when an applicant can demonstrate competence and compliance with appropriate regulations without conducting a flight. (f) Proving tests and validation tests may be conducted simultaneously when appropriate. (g) The Administrator may authorize deviations from this section if the Administrator finds that special circumstances make full compliance with this section unnecessary. [Doc. No. FAA–2001–10047, 68 FR 54586, Sept. 17, 2003] No person may operate an aircraft in operations requiring two pilots unless it is equipped with functioning dual controls. However, if the aircraft type certification operating limitations do not require two pilots, a throwover control wheel may be used in place of two control wheels. No person may operate an aircraft unless it is equipped with— (a) A sensitive altimeter that is adjustable for barometric pressure; (b) Heating or deicing equipment for each carburetor or, for a pressure carburetor, an alternate air source; (c) For turbojet airplanes, in addition to two gyroscopic bank-and-pitch indicators (artificial horizons) for use at the pilot stations, a third indicator that is installed in accordance with the instrument requirements prescribed in §121.305(j) of this chapter. (d) [Reserved] (e) For turbine powered aircraft, any other equipment as the Administrator may require. [Doc. No. 16097, 43 FR 46783, Oct. 10, 1978, as amended at Amdt. 135–1, 44 FR 26737, May 7, 1979; Amdt. 135–34, 54 FR 43926, Oct. 27, 1989; Amdt. 135–38, 55 FR 43310, Oct. 26, 1990] No person may operate an aircraft having a passenger seating configuration, excluding any pilot seat, of more than 19 unless it is equipped with— (a) A public address system which— (1) Is capable of operation independent of the crewmember interphone system required by paragraph (b) of this section, except for handsets, headsets, microphones, selector switches, and signaling devices; (2) Is approved in accordance with §21.305 of this chapter; (3) Is accessible for immediate use from each of two flight crewmember stations in the pilot compartment; (4) For each required floor-level passenger emergency exit which has an adjacent flight attendant seat, has a microphone which is readily accessible to the seated flight attendant, except that one microphone may serve more than one exit, provided the proximity of the exits allows unassisted verbal communication between seated flight attendants; (5) Is capable of operation within 10 seconds by a flight attendant at each of those stations in the passenger compartment from which its use is accessible; (6) Is audible at all passenger seats, lavatories, and flight attendant seats and work stations; and (7) For transport category airplanes manufactured on or after November 27, 1990, meets the requirements of §25.1423 of this chapter. (b) A crewmember interphone system which— (1) Is capable of operation independent of the public address system required by paragraph (a) of this section, except for handsets, headsets, microphones, selector switches, and signaling devices; (2) Is approved in accordance with §21.305 of this chapter; (3) Provides a means of two-way communication between the pilot compartment and— (i) Each passenger compartment; and (ii) Each galley located on other than the main passenger deck level; (4) Is accessible for immediate use from each of two flight crewmember stations in the pilot compartment; (5) Is accessible for use from at least one normal flight attendant station in each passenger compartment; (6) Is capable of operation within 10 seconds by a flight attendant at each of those stations in each passenger compartment from which its use is accessible; and (7) For large turbojet-powered airplanes— (i) Is accessible for use at enough flight attendant stations so that all floor-level emergency exits (or entryways to those exits in the case of exits located within galleys) in each passenger compartment are observable from one or more of those stations so equipped; (ii) Has an alerting system incorporating aural or visual signals for use by flight crewmembers to alert flight attendants and for use by flight attendants to alert flight crewmembers; (iii) For the alerting system required by paragraph (b)(7)(ii) of this section, has a means for the recipient of a call to determine whether it is a normal call or an emergency call; and (iv) When the airplane is on the ground, provides a means of two-way communication between ground personnel and either of at least two flight crewmembers in the pilot compartment. The interphone system station for use by ground personnel must be so located that personnel using the system may avoid visible detection from within the airplane. [Doc. No. 24995, 54 FR 43926, Oct. 27, 1989] (a) No person may operate a multiengine, turbine-powered airplane or rotorcraft having a passenger seating configuration of six or more and for which two pilots are required by certification or operating rules unless it is equipped with an approved cockpit voice recorder that: (1) Is installed in compliance with §23.1457(a) (1) and (2), (b), (c), (d), (e), (f), and (g); §25.1457(a) (1) and (2), (b), (c), (d), (e), (f), and (g); §27.1457(a) (1) and (2), (b), (c), (d), (e), (f), and (g); or §29.1457(a) (1) and (2), (b), (c), (d), (e), (f), and (g) of this chapter, as applicable; and (2) Is operated continuously from the use of the check list before the flight to completion of the final check list at the end of the flight. (b) No person may operate a multiengine, turbine-powered airplane or rotorcraft having a passenger seating configuration of 20 or more seats unless it is equipped with an approved cockpit voice recorder that— (1) Is installed in compliance with §23.1457, §25.1457, §27.1457 or §29.1457 of this chapter, as applicable; and (2) Is operated continuously from the use of the check list before the flight to completion of the final check list at the end of the flight. (c) In the event of an accident, or occurrence requiring immediate notification of the National Transportation Safety Board which results in termination of the flight, the certificate holder shall keep the recorded information for at least 60 days or, if requested by the Administrator or the Board, for a longer period. Information obtained from the record may be used to assist in determining the cause of accidents or occurrences in connection with investigations. The Administrator does not use the record in any civil penalty or certificate action. (d) For those aircraft equipped to record the uninterrupted audio signals received by a boom or a mask microphone the flight crewmembers are required to use the boom microphone below 18,000 feet mean sea level. No person may operate a large turbine engine powered airplane manufactured after October 11, 1991, or on which a cockpit voice recorder has been installed after October 11, 1991, unless it is equipped to record the uninterrupted audio signal received by a boom or mask microphone in accordance with §25.1457(c)(5) of this chapter. (e) In complying with this section, an approved cockpit voice recorder having an erasure feature may be used, so that during the operation of the recorder, information: (1) Recorded in accordance with paragraph (a) of this section and recorded more than 15 minutes earlier; or (2) Recorded in accordance with paragraph (b) of this section and recorded more than 30 minutes earlier; may be erased or otherwise obliterated. [Doc. No. 16097, 43 FR 46783, Oct. 10, 1978, as amended by Amdt. 135–23, 52 FR 9637, Mar. 25, 1987; Amdt. 135–26, 53 FR 26151, July 11, 1988; Amdt. 135–60, 61 FR 2616, Jan. 26, 1996] (a) Except as provided in paragraph (k) of this section, no person may operate under this part a multi-engine, turbine-engine powered airplane or rotorcraft having a passenger seating configuration, excluding any required crewmember seat, of 10 to 19 seats, that was either brought onto the U.S. register after, or was registered outside the United States and added to the operator's U.S. operations specifications after, October 11, 1991, unless it is equipped with one or more approved flight recorders that use a digital method of recording and storing data and a method of readily retrieving that data from the storage medium. The parameters specified in either Appendix B or C of this part, as applicable must be recorded within the range, accuracy, resolution, and recording intervals as specified. The recorder shall retain no less than 25 hours of aircraft operation. (b) After October 11, 1991, no person may operate a multiengine, turbine-powered airplane having a passenger seating configuration of 20 to 30 seats or a multiengine, turbine-powered rotorcraft having a passenger seating configuration of 20 or more seats unless it is equipped with one or more approved flight recorders that utilize a digital method of recording and storing data, and a method of readily retrieving that data from the storage medium. The parameters in appendix D or E of this part, as applicable, that are set forth below, must be recorded within the ranges, accuracies, resolutions, and sampling intervals as specified. (1) Except as provided in paragraph (b)(3) of this section for aircraft type certificated before October 1, 1969, the following parameters must be recorded: (i) Time; (ii) Altitude; (iii) Airspeed; (iv) Vertical acceleration; (v) Heading; (vi) Time of each radio transmission to or from air traffic control; (vii) Pitch attitude; (viii) Roll attitude; (ix) Longitudinal acceleration; (x) Control column or pitch control surface position; and (xi) Thrust of each engine. (2) Except as provided in paragraph (b)(3) of this section for aircraft type certificated after September 30, 1969, the following parameters must be recorded: (i) Time; (ii) Altitude; (iii) Airspeed; (iv) Vertical acceleration; (v) Heading; (vi) Time of each radio transmission either to or from air traffic control; (vii) Pitch attitude; (viii) Roll attitude; (ix) Longitudinal acceleration; (x) Pitch trim position; (xi) Control column or pitch control surface position; (xii) Control wheel or lateral control surface position; (xiii) Rudder pedal or yaw control surface position; (xiv) Thrust of each engine; (xv) Position of each thrust reverser; (xvi) Trailing edge flap or cockpit flap control position; and (xvii) Leading edge flap or cockpit flap control position. (3) For aircraft manufactured after October 11, 1991, all of the parameters listed in appendix D or E of this part, as applicable, must be recorded. (c) Whenever a flight recorder required by this section is installed, it must be operated continuously from the instant the airplane begins the takeoff roll or the rotorcraft begins the lift-off until the airplane has completed the landing roll or the rotorcraft has landed at its destination. (d) Except as provided in paragraph (c) of this section, and except for recorded data erased as authorized in this paragraph, each certificate holder shall keep the recorded data prescribed in paragraph (a) of this section until the aircraft has been operating for at least 25 hours of the operating time specified in paragraph (c) of this section. In addition, each certificate holder shall keep the recorded data prescribed in paragraph (b) of this section for an airplane until the airplane has been operating for at least 25 hours, and for a rotorcraft until the rotorcraft has been operating for at least 10 hours, of the operating time specified in paragraph (c) of this section. A total of 1 hour of recorded data may be erased for the purpose of testing the flight recorder or the flight recorder system. Any erasure made in accordance with this paragraph must be of the oldest recorded data accumulated at the time of testing. Except as provided in paragraph (c) of this section, no record need be kept more than 60 days. (e) In the event of an accident or occurrence that requires the immediate notification of the National Transportation Safety Board under 49 CFR part 830 of its regulations and that results in termination of the flight, the certificate holder shall remove the recording media from the aircraft and keep the recorded data required by paragraphs (a) and (b) of this section for at least 60 days or for a longer period upon request of the Board or the Administrator. (f)(1) For airplanes manufactured on or before August 18, 2000, and all other aircraft, each flight recorder required by this section must be installed in accordance with the requirements of §23.1459, 25.1459, 27.1459, or 29.1459, as appropriate, of this chapter. The correlation required by paragraph (c) of §23.1459, 25.1459, 27.1459, or 29.1459, as appropriate, of this chapter need be established only on one aircraft of a group of aircraft: (i) That are of the same type; (ii) On which the flight recorder models and their installations are the same; and (iii) On which there are no differences in the type designs with respect to the installation of the first pilot's instruments associated with the flight recorder. The most recent instrument calibration, including the recording medium from which this calibration is derived, and the recorder correlation must be retained by the certificate holder. (f)(2) For airplanes manufactured after August 18, 2000, each flight data recorder system required by this section must be installed in accordance with the requirements of §23.1459 (a), (b), (d) and (e) of this chapter, or §25.1459 (a), (b), (d), and (e) of this chapter. A correlation must be established between the values recorded by the flight data recorder and the corresponding values being measured. The correlation must contain a sufficient number of correlation points to accurately establish the conversion from the recorded values to engineering units or discrete state over the full operating range of the parameter. Except for airplanes having separate altitude and airspeed sensors that are an integral part of the flight data recorder system, a single correlation may be established for any group of airplanes— (i) That are of the same type; (ii) On which the flight recorder system and its installation are the same; and (iii) On which there is no difference in the type design with respect to the installation of those sensors associated with the flight data recorder system. Documentation sufficient to convert recorded data into the engineering units and discrete values specified in the applicable appendix must be maintained by the certificate holder. (g) Each flight recorder required by this section that records the data specified in paragraphs (a) and (b) of this section must have an approved device to assist in locating that recorder under water. (h) The operational parameters required to be recorded by digital flight data recorders required by paragraphs (i) and (j) of this section are as follows, the phrase “when an information source is installed” following a parameter indicates that recording of that parameter is not intended to require a change in installed equipment. (1) Time; (2) Pressure altitude; (3) Indicated airspeed; (4) Heading—primary flight crew reference (if selectable, record discrete, true or magnetic); (5) Normal acceleration (Vertical); (6) Pitch attitude; (7) Roll attitude; (8) Manual radio transmitter keying, or CVR/DFDR synchronization reference; (9) Thrust/power of each engine—primary flight crew reference; (10) Autopilot engagement status; (11) Longitudinal acceleration; (12) Pitch control input; (13) Lateral control input; (14) Rudder pedal input; (15) Primary pitch control surface position; (16) Primary lateral control surface position; (17) Primary yaw control surface position; (18) Lateral acceleration; (19) Pitch trim surface position or parameters of paragraph (h)(82) of this section if currently recorded; (20) Trailing edge flap or cockpit flap control selection (except when parameters of paragraph (h)(85) of this section apply); (21) Leading edge flap or cockpit flap control selection (except when parameters of paragraph (h)(86) of this section apply); (22) Each Thrust reverser position (or equivalent for propeller airplane); (23) Ground spoiler position or speed brake selection (except when parameters of paragraph (h)(87) of this section apply); (24) Outside or total air temperature; (25) Automatic Flight Control System (AFCS) modes and engagement status, including autothrottle; (26) Radio altitude (when an information source is installed); (27) Localizer deviation, MLS Azimuth; (28) Glideslope deviation, MLS Elevation; (29) Marker beacon passage; (30) Master warning; (31) Air/ground sensor (primary airplane system reference nose or main gear); (32) Angle of attack (when information source is installed); (33) Hydraulic pressure low (each system); (34) Ground speed (when an information source is installed); (35) Ground proximity warning system; (36) Landing gear position or landing gear cockpit control selection; (37) Drift angle (when an information source is installed); (38) Wind speed and direction (when an information source is installed); (39) Latitude and longitude (when an information source is installed); (40) Stick shaker/pusher (when an information source is installed); (41) Windshear (when an information source is installed); (42) Throttle/power lever position; (43) Additional engine parameters (as designated in appendix F of this part); (44) Traffic alert and collision avoidance system; (45) DME 1 and 2 distances; (46) Nav 1 and 2 selected frequency; (47) Selected barometric setting (when an information source is installed); (48) Selected altitude (when an information source is installed); (49) Selected speed (when an information source is installed); (50) Selected mach (when an information source is installed); (51) Selected vertical speed (when an information source is installed); (52) Selected heading (when an information source is installed); (53) Selected flight path (when an information source is installed); (54) Selected decision height (when an information source is installed); (55) EFIS display format; (56) Multi-function/engine/alerts display format; (57) Thrust command (when an information source is installed); (58) Thrust target (when an information source is installed); (59) Fuel quantity in CG trim tank (when an information source is installed); (60) Primary Navigation System Reference; (61) Icing (when an information source is installed); (62) Engine warning each engine vibration (when an information source is installed); (63) Engine warning each engine over temp. (when an information source is installed); (64) Engine warning each engine oil pressure low (when an information source is installed); (65) Engine warning each engine over speed (when an information source is installed; (66) Yaw trim surface position; (67) Roll trim surface position; (68) Brake pressure (selected system); (69) Brake pedal application (left and right); (70) Yaw or sideslip angle (when an information source is installed); (71) Engine bleed valve position (when an information source is installed); (72) De-icing or anti-icing system selection (when an information source is installed); (73) Computed center of gravity (when an information source is installed); (74) AC electrical bus status; (75) DC electrical bus status; (76) APU bleed valve position (when an information source is installed); (77) Hydraulic pressure (each system); (78) Loss of cabin pressure; (79) Computer failure; (80) Heads-up display (when an information source is installed); (81) Para-visual display (when an information source is installed); (82) Cockpit trim control input position—pitch; (83) Cockpit trim control input position—roll; (84) Cockpit trim control input position—yaw; (85) Trailing edge flap and cockpit flap control position; (86) Leading edge flap and cockpit flap control position; (87) Ground spoiler position and speed brake selection; and (88) All cockpit flight control input forces (control wheel, control column, rudder pedal). (i) For all turbine-engine powered airplanes with a seating configuration, excluding any required crewmember seat, of 10 to 30 passenger seats, manufactured after August 18, 2000— (1) The parameters listed in paragraphs (h)(1) through (h)(57) of this section must be recorded within the ranges, accuracies, resolutions, and recording intervals specified in Appendix F of this part. (2) Commensurate with the capacity of the recording system, all additional parameters for which information sources are installed and which are connected to the recording system must be recorded within the ranges, accuracies, resolutions, and sampling intervals specified in Appendix F of this part. (j) For all turbine-engine-powered airplanes with a seating configuration, excluding any required crewmember seat, of 10 to 30 passenger seats, that are manufactured after August 19, 2002 the parameters listed in paragraph (a)(1) through (a)(88) of this section must be recorded within the ranges, accuracies, resolutions, and recording intervals specified in Appendix F of this part. (k) For aircraft manufactured before August 18, 1997, the following aircraft types need not comply with this section: Bell 212, Bell 214ST, Bell 412, Bell 412SP, Boeing Chinook (BV–234), Boeing/Kawasaki Vertol 107 (BV/KV–107–II), deHavilland DHC–6, Eurocopter Puma 330J, Sikorsky 58, Sikorsky 61N, Sikorsky 76A. [Doc. No. 25530, 53 FR 26151, July 11, 1988, as amended by Amdt. 135–69, 62 FR 38396, July 17, 1997; 62 FR 48135, Sept. 12, 1997; Amdt. 135–89, 68 FR 42939, July 18, 2003] (a) No person may operate a turbine-powered airplane having a passenger seat configuration of 10 seats or more, excluding any pilot seat, unless it is equipped with an approved ground proximity warning system. (b) [Reserved] (c) For a system required by this section, the Airplane Flight Manual shall contain— (1) Appropriate procedures for— (i) The use of the equipment; (ii) Proper flight crew action with respect to the equipment; and (iii) Deactivation for planned abnormal and emergency conditions; and (2) An outline of all input sources that must be operating. (d) No person may deactivate a system required by this section except under procedures in the Airplane Flight Manual. (e) Whenever a system required by this section is deactivated, an entry shall be made in the airplane maintenance record that includes the date and time of deactivation. (f) This section expires on March 29, 2005. [Doc. No. 26202, 57 FR 9951, Mar. 20, 1992, as amended by Amdt. 135–60, 61 FR 2616, Jan. 26, 1996; Amdt. 135–66, 62 FR 13257, Mar. 19, 1997; Amdt. 135–75, 65 FR 16755, Mar. 29, 2000] (a) Airplanes manufactured after March 29, 2002: (1) No person may operate a turbine-powered airplane configured with 10 or more passenger seats, excluding any pilot seat, unless that airplane is equipped with an approved terrain awareness and warning system that meets the requirements for Class A equipment in Technical Standard Order (TSO)–C151. The airplane must also include an approved terrain situational awareness display. (2) No person may operate a turbine-powered airplane configured with 6 to 9 passenger seats, excluding any pilot seat, unless that airplane is equipped with an approved terrain awareness and warning system that meets as a minimum the requirements for Class B equipment in Technical Standard Order (TSO)–C151. (b) Airplanes manufactured on or before March 29, 2002: (1) No person may operate a turbine-powered airplane configured with 10 or more passenger seats, excluding any pilot seat, after March 29, 2005, unless that airplane is equipped with an approved terrain awareness and warning system that meets the requirements for Class A equipment in Technical Standard Order (TSO)–C151. The airplane must also include an approved terrain situational awareness display. (2) No person may operate a turbine-powered airplane configured with 6 to 9 passenger seats, excluding any pilot seat, after March 29, 2005, unless that airplane is equipped with an approved terrain awareness and warning system that meets as a minimum the requirements for Class B equipment in Technical Standard Order (TSO)–C151. (c) Airplane Flight Manual. The Airplane Flight Manual shall contain appropriate procedures for— (1) The use of the terrain awareness and warning system; and (2) Proper flight crew reaction in response to the terrain awareness and warning system audio and visual warnings. [Doc. No. 29312, 65 FR 16755, Mar. 29, 2000] No person may operate an aircraft carrying passengers unless it is equipped with hand fire extinguishers of an approved type for use in crew and passenger compartments as follows— (a) The type and quantity of extinguishing agent must be suitable for the kinds of fires likely to occur; (b) At least one hand fire extinguisher must be provided and conveniently located on the flight deck for use by the flight crew; and (c) At least one hand fire extinguisher must be conveniently located in the passenger compartment of each aircraft having a passenger seating configuration, excluding any pilot seat, of at least 10 seats but less than 31 seats. (a) Unpressurized aircraft. No person may operate an unpressurized aircraft at altitudes prescribed in this section unless it is equipped with enough oxygen dispensers and oxygen to supply the pilots under §135.89(a) and to supply, when flying— (1) At altitudes above 10,000 feet through 15,000 feet MSL, oxygen to at least 10 percent of the occupants of the aircraft, other than the pilots, for that part of the flight at those altitudes that is of more than 30 minutes duration; and (2) Above 15,000 feet MSL, oxygen to each occupant of the aircraft other than the pilots. (b) Pressurized aircraft. No person may operate a pressurized aircraft— (1) At altitudes above 25,000 feet MSL, unless at least a 10-minute supply of supplemental oxygen is available for each occupant of the aircraft, other than the pilots, for use when a descent is necessary due to loss of cabin pressurization; and (2) Unless it is equipped with enough oxygen dispensers and oxygen to comply with paragraph (a) of this section whenever the cabin pressure altitude exceeds 10,000 feet MSL and, if the cabin pressurization fails, to comply with §135.89 (a) or to provide a 2-hour supply for each pilot, whichever is greater, and to supply when flying— (i) At altitudes above 10,000 feet through 15,000 feet MSL, oxygen to at least 10 percent of the occupants of the aircraft, other than the pilots, for that part of the flight at those altitudes that is of more than 30 minutes duration; and (ii) Above 15,000 feet MSL, oxygen to each occupant of the aircraft, other than the pilots, for one hour unless, at all times during flight above that altitude, the aircraft can safely descend to 15,000 feet MSL within four minutes, in which case only a 30-minute supply is required. (c) The equipment required by this section must have a means— (1) To enable the pilots to readily determine, in flight, the amount of oxygen available in each source of supply and whether the oxygen is being delivered to the dispensing units; or (2) In the case of individual dispensing units, to enable each user to make those determinations with respect to that person's oxygen supply and delivery; and (3) To allow the pilots to use undiluted oxygen at their discretion at altitudes above 25,000 feet MSL. (a) Except as provided in paragraph (b) of this section, after April 12, 1981, no person may operate a transport category airplane equipped with a flight instrument pitot heating system unless the airplane is also equipped with an operable pitot heat indication system that complies with §25.1326 of this chapter in effect on April 12, 1978. (b) A certificate holder may obtain an extension of the April 12, 1981, compliance date specified in paragraph (a) of this section, but not beyond April 12, 1983, from the Director, Flight Standards Service if the certificate holder— (1) Shows that due to circumstances beyond its control it cannot comply by the specified compliance date; and (2) Submits by the specified compliance date a schedule for compliance, acceptable to the Director, indicating that compliance will be achieved at the earliest practicable date. [Doc. No. 18094, Amdt. 135–17, 46 FR 48306, Aug. 31, 1981, as amended by Amdt. 135–33, 54 FR 39294, Sept. 25, 1989] No person may operate an aircraft carrying passengers under VFR at night or under VFR over-the-top, unless it is equipped with— (a) A gyroscopic rate-of-turn indicator except on the following aircraft: (1) 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 §121.305(j) of this chapter. (2) Helicopters 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 §29.1303(g) of this chapter. (3) Helicopters with a maximum certificated takeoff weight of 6,000 pounds or less. (b) A slip skid indicator. (c) A gyroscopic bank-and-pitch indicator. (d) A gyroscopic direction indicator. (e) A generator or generators able to supply all probable combinations of continuous in-flight electrical loads for required equipment and for recharging the battery. (f) For night flights— (1) An anticollision light system; (2) Instrument lights to make all instruments, switches, and gauges easily readable, the direct rays of which are shielded from the pilots' eyes; and (3) A flashlight having at least two size “D” cells or equivalent. (g) For the purpose of paragraph (e) of this section, a continuous in-flight electrical load includes one that draws current continuously during flight, such as radio equipment and electrically driven instruments and lights, but does not include occasional intermittent loads. (h) Notwithstanding provisions of paragraphs (b), (c), and (d), helicopters having a maximum certificated takeoff weight of 6,000 pounds or less may be operated until January 6, 1988, under visual flight rules at night without a slip skid indicator, a gyroscopic bank-and-pitch indicator, or a gyroscopic direction indicator. [Doc. No. 24550, 51 FR 40709, Nov. 7, 1986, as amended by Amdt. 135–38, 55 FR 43310, Oct. 26, 1990] (a) No person may operate an aircraft carrying passengers under VFR at night, or under VFR over-the-top, unless it has two-way radio communications equipment able, at least in flight, to transmit to, and receive from, ground facilities 25 miles away. (b) No person may operate an aircraft carrying passengers under VFR over-the-top unless it has radio navigational equipment able to receive radio signals from the ground facilities to be used. (c) No person may operate an airplane carrying passengers under VFR at night unless it has radio navigational equipment able to receive radio signals from the ground facilities to be used. No person may operate an aircraft under IFR, carrying passengers, unless it has— (a) A vertical speed indicator; (b) A free-air temperature indicator; (c) A heated pitot tube for each airspeed indicator; (d) A power failure warning device or vacuum indicator to show the power available for gyroscopic instruments from each power source; (e) An alternate source of static pressure for the altimeter and the airspeed and vertical speed indicators; (f) For a single-engine aircraft: (1) Two independent electrical power generating sources each of which is able to supply all probable combinations of continuous inflight electrical loads for required instruments and equipment; or (2) In addition to the primary electrical power generating source, a standby battery or an alternate source of electric power that is capable of supplying 150% of the electrical loads of all required instruments and equipment necessary for safe emergency operation of the aircraft for at least one hour; (g) For multi-engine aircraft, at least two generators or alternators each of which is on a separate engine, of which any combination of one-half of the total number are rated sufficiently to supply the electrical loads of all required instruments and equipment necessary for safe emergency operation of the aircraft except that for multi-engine helicopters, the two required generators may be mounted on the main rotor drive train; and (h) Two independent sources of energy (with means of selecting either) of which at least one is an engine-driven pump or generator, each of which is able to drive all required gyroscopic instruments powered by, or to be powered by, that particular source and installed so that failure of one instrument or source, does not interfere with the energy supply to the remaining instruments or the other energy source unless, for single-engine aircraft in all cargo operations only, the rate of turn indicator has a source of energy separate from the bank and pitch and direction indicators. For the purpose of this paragraph, for multi-engine aircraft, each engine-driven source of energy must be on a different engine. (i) For the purpose of paragraph (f) of this section, a continuous inflight electrical load includes one that draws current continuously during flight, such as radio equipment, electrically driven instruments, and lights, but does not include occasional intermittent loads. [Doc. No. 16097, 43 FR 46783, Oct. 10, 1978, as amended by Amdt. 135–70, 62 FR 42374, Aug. 6, 1997; Amdt. 135–72, 63 FR 25573, May 8, 1998] (a) No person may operate a turbojet airplane having a passenger seating configuration, excluding any pilot seat, of 10 seats or more, or a multiengine airplane in a commuter operation, as defined in part 119 of this chapter, under IFR or in extended overwater operations unless it has at least the following radio communication and navigational equipment appropriate to the facilities to be used which are capable of transmitting to, and receiving from, at any place on the route to be flown, at least one ground facility: (1) Two transmitters, (2) two microphones, (3) two headsets or one headset and one speaker, (4) a marker beacon receiver, (5) two independent receivers for navigation, and (6) two independent receivers for communications. (b) No person may operate an aircraft other than that specified in paragraph (a) of this section, under IFR or in extended overwater operations unless it has at least the following radio communication and navigational equipment appropriate to the facilities to be used and which are capable of transmitting to, and receiving from, at any place on the route, at least one ground facility: (1) A transmitter, (2) two microphones, (3) two headsets or one headset and one speaker, (4) a marker beacon receiver, (5) two independent receivers for navigation, (6) two independent receivers for communications, and (7) for extended overwater operations only, an additional transmitter. (c) For the purpose of paragraphs (a)(5), (a)(6), (b)(5), and (b)(6) of this section, a receiver is independent if the function of any part of it does not depend on the functioning of any part of another receiver. However, a receiver that can receive both communications and navigational signals may be used in place of a separate communications receiver and a separate navigational signal receiver. (d) Notwithstanding the requirements of paragraphs (a) and (b) of this section, installation and use of a single long-range navigation system and a single long-range communication system, for extended overwater operations, may be authorized by the Administrator and approved in the certificate holder's operations specifications. The following are among the operational factors the Administrator may consider in granting an authorization: (1) The ability of the flightcrew to reliably fix the position of the airplane within the degree of accuracy required by ATC, (2) The length of the route being flown, and (3) The duration of the very high frequency communications gap. [Doc. No. 16097, 43 FR 46783, Oct. 10, 1978, as amended by Amdt. 135–58, 60 FR 65939, Dec. 20, 1995; Amdt. 135–61, 61 FR 7191, Feb. 26, 1996] (a) Except where the Administrator, by amending the operations specifications of the certificate holder, requires the carriage of all or any specific items of the equipment listed below for any overwater operation, or, upon application of the certificate holder, the Administrator allows deviation for a particular extended overwater operation, no person may operate an aircraft in extended overwater operations unless it carries, installed in conspicuously marked locations easily accessible to the occupants if a ditching occurs, the following equipment: (1) An approved life preserver equipped with an approved survivor locator light for each occupant of the aircraft. The life preserver must be easily accessible to each seated occupant. (2) Enough approved liferafts of a rated capacity and buoyancy to accommodate the occupants of the aircraft. (b) Each liferaft required by paragraph (a) of this section must be equipped with or contain at least the following: (1) One approved survivor locator light. (2) One approved pyrotechnic signaling device. (3) Either— (i) One survival kit, appropriately equipped for the route to be flown; or (ii) One canopy (for sail, sunshade, or rain catcher); (iii) One radar reflector; (iv) One liferaft repair kit; (v) One bailing bucket; (vi) One signaling mirror; (vii) One police whistle; (viii) One raft knife; (ix) One CO2 bottle for emergency inflation; (x) One inflation pump; (xi) Two oars; (xii) One 75-foot retaining line; (xiii) One magnetic compass; (xiv) One dye marker; (xv) One flashlight having at least two size “D” cells or equivalent; (xvi) A 2-day supply of emergency food rations supplying at least 1,000 calories per day for each person; (xvii) For each two persons the raft is rated to carry, two pints of water or one sea water desalting kit; (xviii) One fishing kit; and (xix) One book on survival appropriate for the area in which the aircraft is operated. (c) No person may operate an airplane in extended overwater operations unless there is attached to one of the life rafts required by paragraph (a) of this section, an approved survival type emergency locator transmitter. Batteries used in this transmitter must be replaced (or recharged, if the batteries are rechargeable) when the transmitter has been in use for more than 1 cumulative hour, or, 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. The battery useful life (or useful life of charge) requirements of this paragraph do not apply to batteries (such as water-activated batteries) that are essentially unaffected during probable storage intervals. [Doc. No. 16097, 43 FR 46783, Oct. 10, 1978, as amended by Amdt. 135–4, 45 FR 38348, June 30, 1980; Amdt. 135–20, 51 FR 40710, Nov. 7, 1986; Amdt. 135–49, 59 FR 32058, June 21, 1994; Amdt. 135–91, 68 FR 54586, Sept. 17, 2003]
Title 14: Aeronautics and Space
PART 135—OPERATING REQUIREMENTS: COMMUTER AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT
Subpart C—Aircraft and Equipment
§ 135.141 Applicability.
§ 135.143 General requirements.
§ 135.144 Portable electronic devices.
§ 135.145 Aircraft proving and validation tests.
§ 135.147 Dual controls required.
§ 135.149 Equipment requirements: General.
§ 135.150 Public address and crewmember interphone systems.
§ 135.151 Cockpit voice recorders.
§ 135.152 Flight recorders.
§ 135.153 Ground proximity warning system.
§ 135.154 Terrain awareness and warning system.
§ 135.155 Fire extinguishers: Passenger-carrying aircraft.
§ 135.157 Oxygen equipment requirements.
§ 135.158 Pitot heat indication systems.
§ 135.159 Equipment requirements: Carrying passengers under VFR at night or under VFR over-the-top conditions.
§ 135.161 Radio and navigational equipment: Carrying passengers under VFR at night or under VFR over-the-top.
§ 135.163 Equipment requirements: Aircraft carrying passengers under IFR.
§ 135.165 Radio and navigational equipment: Extended overwater or IFR operations.
§ 135.167 Emergency equipment: Extended overwater operations.
§ 135.168 [Reserved]
§ 135.169 Additional airworthiness requirements.
(a) Except for commuter category airplanes, no person may operate a large airplane unless it meets the additional airworthiness requirements of §§121.213 through 121.283 and 121.307 of this chapter.
(b) No person may operate a reciprocating-engine or turbopropeller-powered small airplane that has a passenger seating configuration, excluding pilot seats, of 10 seats or more unless it is type certificated—
(1) In the transport category;
(2) Before July 1, 1970, in the normal category and meets special conditions issued by the Administrator for airplanes intended for use in operations under this part;
(3) Before July 19, 1970, in the normal category and meets the additional airworthiness standards in Special Federal Aviation Regulation No. 23;
(4) In the normal category and meets the additional airworthiness standards in appendix A;
(5) In the normal category and complies with section 1.(a) of Special Federal Aviation Regulation No. 41;
(6) In the normal category and complies with section 1.(b) of Special Federal Aviation Regulation No. 41; or
(7) In the commuter category.
(c) No person may operate a small airplane with a passenger seating configuration, excluding any pilot seat, of 10 seats or more, with a seating configuration greater than the maximum seating configuration used in that type airplane in operations under this part before August 19, 1977. This paragraph does not apply to—
(1) An airplane that is type certificated in the transport category; or
(2) An airplane that complies with—
(i) Appendix A of this part provided that its passenger seating configuration, excluding pilot seats, does not exceed 19 seats; or
(ii) Special Federal Aviation Regulation No. 41.
(d) Cargo or baggage compartments:
(1) After March 20, 1991, each Class C or D compartment, as defined in §25.857 of part 25 of this chapter, greater than 200 cubic feet in volume in a transport category airplane type certificated after January 1, 1958, must have ceiling and sidewall panels which are constructed of:
(i) Glass fiber reinforced resin;
(ii) Materials which meet the test requirements of part 25, appendix F, part III of this chapter; or
(iii) In the case of liner installations approved prior to March 20, 1989, aluminum.
(2) For compliance with this paragraph, the term “liner” includes any design feature, such as a joint or fastener, which would affect the capability of the liner to safely contain a fire.
[Doc. No. 16097, 43 FR 46783, Oct. 10, 1978, as amended by Amdt. 135–2, 44 FR 53731, Sept. 17, 1979; Amdt. 135–21, 52 FR 1836, Jan. 15, 1987; 52 FR 34745, Sept. 14, 1987; Amdt. 135–31, 54 FR 7389, Feb. 17, 1989; Amdt. 135–55, 60 FR 6628, Feb. 2, 1995]
§ 135.170 Materials for compartment interiors.
(a) No person may operate an airplane that conforms to an amended or supplemental type certificate issued in accordance with SFAR No. 41 for a maximum certificated takeoff weight in excess of 12,500 pounds unless within one year after issuance of the initial airworthiness certificate under that SFAR, the airplane meets the compartment interior requirements set forth in §25.853(a) in effect March 6, 1995 (formerly §25.853 (a), (b), (b–1), (b–2), and (b–3) of this chapter in effect on September 26, 1978).
(b) Except for commuter category airplanes and airplanes certificated under Special Federal Aviation Regulation No. 41, no person may operate a large airplane unless it meets the following additional airworthiness requirements:
(1) Except for those materials covered by paragraph (b)(2) of this section, all materials in each compartment used by the crewmembers or passengers must meet the requirements of §25.853 of this chapter in effect as follows or later amendment thereto:
(i) Except as provided in paragraph (b)(1)(iv) of this section, each airplane with a passenger capacity of 20 or more and manufactured after August 19, 1988, but prior to August 20, 1990, must comply with the heat release rate testing provisions of §25.853(d) in effect March 6, 1995 (formerly §25.853(a–1) in effect on August 20, 1986), except that the total heat release over the first 2 minutes of sample exposure rate must not exceed 100 kilowatt minutes per square meter and the peak heat release rate must not exceed 100 kilowatts per square meter.
(ii) Each airplane with a passenger capacity of 20 or more and manufactured after August 19, 1990, must comply with the heat release rate and smoke testing provisions of §25.853(d) in effect March 6, 1995 (formerly §25.83(a–1) in effect on September 26, 1988).
(iii) Except as provided in paragraph (b)(1) (v) or (vi) of this section, each airplane for which the application for type certificate was filed prior to May 1, 1972, must comply with the provisions of §25.853 in effect on April 30, 1972, regardless of the passenger capacity, if there is a substantially complete replacement of the cabin interior after April 30, 1972.
(iv) Except as provided in paragraph (b)(1) (v) or (vi) of this section, each airplane for which the application for type certificate was filed after May 1, 1972, must comply with the material requirements under which the airplane was type certificated regardless of the passenger capacity if there is a substantially complete replacement of the cabin interior after that date.
(v) Except as provided in paragraph (b)(1)(vi) of this section, each airplane that was type certificated after January 1, 1958, must comply with the heat release testing provisions of §25.853(d) in effect March 6, 1995 (formerly §25.853(a–1) in effect on August 20, 1986), if there is a substantially complete replacement of the cabin interior components identified in that paragraph on or after that date, except that the total heat release over the first 2 minutes of sample exposure shall not exceed 100 kilowatt-minutes per square meter and the peak heat release rate shall not exceed 100 kilowatts per square meter.
(vi) Each airplane that was type certificated after January 1, 1958, must comply with the heat release rate and smoke testing provisions of §25.853(d) in effect March 6, 1995 (formerly §25.853(a–1) in effect on August 20, 1986), if there is a substantially complete replacement of the cabin interior components identified in that paragraph after August 19, 1990.
(vii) Contrary provisions of this section notwithstanding, the Manager of the Transport Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, may authorize deviation from the requirements of paragraph (b)(1)(i), (b)(1)(ii), (b)(1)(v), or (b)(1)(vi) of this section for specific components of the cabin interior that do not meet applicable flammability and smoke emission requirements, if the determination is made that special circumstances exist that make compliance impractical. Such grants of deviation will be limited to those airplanes manufactured within 1 year after the applicable date specified in this section and those airplanes in which the interior is replaced within 1 year of that date. A request for such grant of deviation must include a thorough and accurate analysis of each component subject to §25.853(d) in effect March 6, 1995 (formerly §25.853(a–1) in effect on August 20, 1986), the steps being taken to achieve compliance, and, for the few components for which timely compliance will not be achieved, credible reasons for such noncompliance.
(viii) Contrary provisions of this section notwithstanding, galley carts and standard galley containers that do not meet the flammability and smoke emission requirements of §25.853(d) in effect March 6, 1995 (formerly §25.853(a–1) in effect on August 20, 1986), may be used in airplanes that must meet the requirements of paragraph (b)(1)(i), (b)(1)(ii), (b)(1)(iv) or (b)(1)(vi) of this section provided the galley carts or standard containers were manufactured prior to March 6, 1995.
(2) For airplanes type certificated after January 1, 1958, seat cushions, except those on flight crewmember seats, in any compartment occupied by crew or passengers must comply with the requirements pertaining to fire protection of seat cushions in §25.853(c) effective November 26, 1984.
(c) Thermal/acoustic insulation materials. For transport category airplanes type certificated after January 1, 1958:
(1) For airplanes manufactured before September 2, 2005, when thermal/acoustic insulation is installed in the fuselage as replacements after September 2, 2005, the insulation must meet the flame propagation requirements of §25.856 of this chapter, effective September 2, 2003, if it is:
(i) Of a blanket construction, or
(ii) Installed around air ducting.
(2) For airplanes manufactured after September 2, 2005, thermal/acoustic insulation materials installed in the fuselage must meet the flame propagation requirements of §25.856 of this chapter, effective September 2, 2003.
[Doc. No. 26192, 60 FR 6628, Feb. 2, 1995; Amdt. 135–55, 60 FR 11194, Mar. 1, 1995; Amdt. 135–56, 60 FR 13011, Mar. 9, 1995; Amdt. 135–90, 68 FR 45084, July 31, 2003; Amdt. 135–103, 70 FR 77752, Dec. 30, 2005]
§ 135.171 Shoulder harness installation at flight crewmember stations.
(a) No person may operate a turbojet aircraft or an aircraft having a passenger seating configuration, excluding any pilot seat, of 10 seats or more unless it is equipped with an approved shoulder harness installed for each flight crewmember station.
(b) Each flight crewmember occupying a station equipped with a shoulder harness must fasten the shoulder harness during takeoff and landing, except that the shoulder harness may be unfastened if the crewmember cannot perform the required duties with the shoulder harness fastened.
§ 135.173 Airborne thunderstorm detection equipment requirements.
(a) No person may operate an aircraft that has a passenger seating configuration, excluding any pilot seat, of 10 seats or more in passenger-carrying operations, except a helicopter operating under day VFR conditions, unless the aircraft is equipped with either approved thunderstorm detection equipment or approved airborne weather radar equipment.
(b) No person may operate a helicopter that has a passenger seating configuration, excluding any pilot seat, of 10 seats or more in passenger-carrying operations, under night VFR when current weather reports indicate that thunderstorms or other potentially hazardous weather conditions that can be detected with airborne thunderstorm detection equipment may reasonably be expected along the route to be flown, unless the helicopter is equipped with either approved thunderstorm detection equipment or approved airborne weather radar equipment.
(c) No person may begin a flight under IFR or night VFR conditions when current weather reports indicate that thunderstorms or other potentially hazardous weather conditions that can be detected with airborne thunderstorm detection equipment, required by paragraph (a) or (b) of this section, may reasonably be expected along the route to be flown, unless the airborne thunderstorm detection equipment is in satisfactory operating condition.
(d) If the airborne thunderstorm detection equipment becomes inoperative en route, the aircraft must be operated under the instructions and procedures specified for that event in the manual required by §135.21.
(e) This section does not apply to aircraft used solely within the State of Hawaii, within the State of Alaska, within that part of Canada west of longitude 130 degrees W, between latitude 70 degrees N, and latitude 53 degrees N, or during any training, test, or ferry flight.
(f) Without regard to any other provision of this part, an alternate electrical power supply is not required for airborne thunderstorm detection equipment.
[Doc. No. 16097, 43 FR 46783, Oct. 10, 1978, as amended by Amdt. 135–20, 51 FR 40710, Nov. 7, 1986; Amdt. 135–60, 61 FR 2616, Jan. 26, 1996]
§ 135.175 Airborne weather radar equipment requirements.
(a) No person may operate a large, transport category aircraft in passenger-carrying operations unless approved airborne weather radar equipment is installed in the aircraft.
(b) No person may begin a flight under IFR or night VFR conditions when current weather reports indicate that thunderstorms, or other potentially hazardous weather conditions that can be detected with airborne weather radar equipment, may reasonably be expected along the route to be flown, unless the airborne weather radar equipment required by paragraph (a) of this section is in satisfactory operating condition.
(c) If the airborne weather radar equipment becomes inoperative en route, the aircraft must be operated under the instructions and procedures specified for that event in the manual required by §135.21.
(d) This section does not apply to aircraft used solely within the State of Hawaii, within the State of Alaska, within that part of Canada west of longitude 130 degrees W, between latitude 70 degrees N, and latitude 53 degrees N, or during any training, test, or ferry flight.
(e) Without regard to any other provision of this part, an alternate electrical power supply is not required for airborne weather radar equipment.
§ 135.177 Emergency equipment requirements for aircraft having a passenger seating configuration of more than 19 passengers.
(a) No person may operate an aircraft having a passenger seating configuration, excluding any pilot seat, of more than 19 seats unless it is equipped with the following emergency equipment:
(1) At least one approved first-aid kit for treatment of injuries likely to occur in flight or in a minor accident that must:
(i) Be readily accessible to crewmembers.
(ii) Be stored securely and kept free from dust, moisture, and damaging temperatures.
(iii) Contain at least the following appropriately maintained contents in the specified quantities:
------------------------------------------------------------------------ Contents Quantity------------------------------------------------------------------------Adhesive bandage compresses, 1-inch............ 16Antiseptic swabs............................... 20Ammonia inhalants.............................. 10Bandage compresses, 4-inch..................... 8Triangular bandage compresses, 40-inch......... 5Arm splint, noninflatable...................... 1Leg splint, noninflatable...................... 1Roller bandage, 4-inch......................... 4Adhesive tape, 1-inch standard roll............ 2Bandage scissors............................... 1Protective nonpermeable gloves or equivalent... 1 pair------------------------------------------------------------------------
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(2) A crash axe carried so as to be accessible to the crew but inaccessible to passengers during normal operations. (3) Signs that are visible to all occupants to notify them when smoking is prohibited and when safety belts must be fastened. The signs must be constructed so that they can be turned on during any movement of the aircraft on the surface, for each takeoff or landing, and at other times considered necessary by the pilot in command. “No smoking” signs shall be turned on when required by §135.127. (4) [Reserved] (b) Each item of equipment must be inspected regularly under inspection periods established in the operations specifications to ensure its condition for continued serviceability and immediate readiness to perform its intended emergency purposes. [Doc. No. 16097, 43 FR 46783, Oct. 10, 1978, as amended by Amdt. 135–25, 53 FR 12362, Apr. 13, 1988; Amdt. 135–43, 57 FR 19245, May 4, 1992; Amdt. 135–44, 57 FR 42676, Sept. 15, 1992; Amdt. 135–47, 59 FR 1781, Jan. 12, 1994; Amdt. 135–53, 59 FR 52643, Oct. 18, 1994; 59 FR 55208, Nov. 4, 1994; Amdt. 121–281, 66 FR 19045, Apr. 12, 2001] § 135.178 Additional emergency equipment.No person may operate an airplane having a passenger seating configuration of more than 19 seats, unless it has the additional emergency equipment specified in paragraphs (a) through (l) of this section. (a) Means for emergency evacuation. Each passenger-carrying landplane emergency exit (other than over-the-wing) that is more than 6 feet from the ground, with the airplane on the ground and the landing gear extended, must have an approved means to assist the occupants in descending to the ground. The assisting means for a floor-level emergency exit must meet the requirements of §25.809(f)(1) of this chapter in effect on April 30, 1972, except that, for any airplane for which the application for the type certificate was filed after that date, it must meet the requirements under which the airplane was type certificated. An assisting means that deploys automatically must be armed during taxiing, takeoffs, and landings; however, the Administrator may grant a deviation from the requirement of automatic deployment if he finds that the design of the exit makes compliance impractical, if the assisting means automatically erects upon deployment and, with respect to required emergency exits, if an emergency evacuation demonstration is conducted in accordance with §121.291(a) of this chapter. This paragraph does not apply to the rear window emergency exit of Douglas DC–3 airplanes operated with fewer than 36 occupants, including crewmembers, and fewer than five exits authorized for passenger use. (b) Interior emergency exit marking. The following must be complied with for each passenger-carrying airplane: (1) Each passenger emergency exit, its means of access, and its means of opening must be conspicuously marked. The identity and locating of each passenger emergency exit must be recognizable from a distance equal to the width of the cabin. The location of each passenger emergency exit must be indicated by a sign visible to occupants approaching along the main passenger aisle. There must be a locating sign— (i) Above the aisle near each over-the-wing passenger emergency exit, or at another ceiling location if it is more practical because of low headroom; (ii) Next to each floor level passenger emergency exit, except that one sign may serve two such exits if they both can be seen readily from that sign; and (iii) On each bulkhead or divider that prevents fore and aft vision along the passenger cabin, to indicate emergency exits beyond and obscured by it, except that if this is not possible, the sign may be placed at another appropriate location. (2) Each passenger emergency exit marking and each locating sign must meet the following: (i) For an airplane for which the application for the type certificate was filed prior to May 1, 1972, each passenger emergency exit marking and each locating sign must be manufactured to meet the requirements of §25.812(b) of this chapter in effect on April 30, 1972. On these airplanes, no sign may continue to be used if its luminescence (brightness) decreases to below 100 microlamberts. The colors may be reversed if it increases the emergency illumination of the passenger compartment. However, the Administrator may authorize deviation from the 2-inch background requirements if he finds that special circumstances exist that make compliance impractical and that the proposed deviation provides an equivalent level of safety. (ii) For an airplane for which the application for the type certificate was filed on or after May 1, 1972, each passenger emergency exit marking and each locating sign must be manufactured to meet the interior emergency exit marking requirements under which the airplane was type certificated. On these airplanes, no sign may continue to be used if its luminescence (brightness) decreases to below 250 microlamberts. (c) Lighting for interior emergency exit markings. Each passenger-carrying airplane must have an emergency lighting system, independent of the main lighting system; however, sources of general cabin illumination may be common to both the emergency and the main lighting systems if the power supply to the emergency lighting system is independent of the power supply to the main lighting system. The emergency lighting system must— (1) Illuminate each passenger exit marking and locating sign; (2) Provide enough general lighting in the passenger cabin so that the average illumination when measured at 40-inch intervals at seat armrest height, on the centerline of the main passenger aisle, is at least 0.05 foot-candles; and (3) For airplanes type certificated after January 1, 1958, include floor proximity emergency escape path marking which meets the requirements of §25.812(e) of this chapter in effect on November 26, 1984. (d) Emergency light operation. Except for lights forming part of emergency lighting subsystems provided in compliance with §25.812(h) of this chapter (as prescribed in paragraph (h) of this section) that serve no more than one assist means, are independent of the airplane's main emergency lighting systems, and are automatically activated when the assist means is deployed, each light required by paragraphs (c) and (h) of this section must: (1) Be operable manually both from the flightcrew station and from a point in the passenger compartment that is readily accessible to a normal flight attendant seat; (2) Have a means to prevent inadvertent operation of the manual controls; (3) When armed or turned on at either station, remain lighted or become lighted upon interruption of the airplane's normal electric power; (4) Be armed or turned on during taxiing, takeoff, and landing. In showing compliance with this paragraph, a transverse vertical separation of the fuselage need not be considered; (5) Provide the required level of illumination for at least 10 minutes at the critical ambient conditions after emergency landing; and (6) Have a cockpit control device that has an “on,” “off,” and “armed” position. (e) Emergency exit operating handles. (1) For a passenger-carrying airplane for which the application for the type certificate was filed prior to May 1, 1972, the location of each passenger emergency exit operating handle, and instructions for opening the exit, must be shown by a marking on or near the exit that is readable from a distance of 30 inches. In addition, for each Type I and Type II emergency exit with a locking mechanism released by rotary motion of the handle, the instructions for opening must be shown by— (i) A red arrow with a shaft at least three-fourths inch wide and a head twice the width of the shaft, extending along at least 70° of arc at a radius approximately equal to three-fourths of the handle length; and (ii) The word “open” in red letters 1 inch high placed horizontally near the head of the arrow. (2) For a passenger-carrying airplane for which the application for the type certificate was filed on or after May 1, 1972, the location of each passenger emergency exit operating handle and instructions for opening the exit must be shown in accordance with the requirements under which the airplane was type certificated. On these airplanes, no operating handle or operating handle cover may continue to be used if its luminescence (brightness) decreases to below 100 microlamberts. (f) Emergency exit access. Access to emergency exits must be provided as follows for each passenger-carrying airplane: (1) Each passageway between individual passenger areas, or leading to a Type I or Type II emergency exit, must be unobstructed and at least 20 inches wide. (2) There must be enough space next to each Type I or Type II emergency exit to allow a crewmember to assist in the evacuation of passengers without reducing the unobstructed width of the passageway below that required in paragraph (f)(1) of this section; however, the Administrator may authorize deviation from this requirement for an airplane certificated under the provisions of part 4b of the Civil Air Regulations in effect before December 20, 1951, if he finds that special circumstances exist that provide an equivalent level of safety. (3) There must be access from the main aisle to each Type III and Type IV exit. The access from the aisle to these exits must not be obstructed by seats, berths, or other protrusions in a manner that would reduce the effectiveness of the exit. In addition, for a transport category airplane type certificated after January 1, 1958, there must be placards installed in accordance with §25.813(c)(3) of this chapter for each Type III exit after December 3, 1992. (4) If it is necessary to pass through a passageway between passenger compartments to reach any required emergency exit from any seat in the passenger cabin, the passageway must not be obstructed. Curtains may, however, be used if they allow free entry through the passageway. (5) No door may be installed in any partition between passenger compartments. (6) If it is necessary to pass through a doorway separating the passenger cabin from other areas to reach a required emergency exit from any passenger seat, the door must have a means to latch it in the open position, and the door must be latched open during each takeoff and landing. The latching means must be able to withstand the loads imposed upon it when the door is subjected to the ultimate inertia forces, relative to the surrounding structure, listed in §25.561(b) of this chapter. (g) Exterior exit markings. Each passenger emergency exit and the means of opening that exit from the outside must be marked on the outside of the airplane. There must be a 2-inch colored band outlining each passenger emergency exit on the side of the fuselage. Each outside marking, including the band, must be readily distinguishable from the surrounding fuselage area by contrast in color. The markings must comply with the following: (1) If the reflectance of the darker color is 15 percent or less, the reflectance of the lighter color must be at least 45 percent. (2) If the reflectance of the darker color is greater than 15 percent, at least a 30 percent difference between its reflectance and the reflectance of the lighter color must be provided. (3) Exits that are not in the side of the fuselage must have the external means of opening and applicable instructions marked conspicuously in red or, if red is inconspicuous against the background color, in bright chrome yellow and, when the opening means for such an exit is located on only one side of the fuselage, a conspicuous marking to that effect must be provided on the other side. “Reflectance” is the ratio of the luminous flux reflected by a body to the luminous flux it receives. (h) Exterior emergency lighting and escape route. (1) Each passenger-carrying airplane must be equipped with exterior lighting that meets the following requirements: (i) For an airplane for which the application for the type certificate was filed prior to May 1, 1972, the requirements of §25.812 (f) and (g) of this chapter in effect on April 30, 1972. (ii) For an airplane for which the application for the type certificate was filed on or after May 1, 1972, the exterior emergency lighting requirements under which the airplane was type certificated. (2) Each passenger-carrying airplane must be equipped with a slip-resistant escape route that meets the following requirements: (i) For an airplane for which the application for the type certificate was filed prior to May 1, 1972, the requirements of §25.803(e) of this chapter in effect on April 30, 1972. (ii) For an airplane for which the application for the type certificate was filed on or after May 1, 1972, the slip-resistant escape route requirements under which the airplane was type certificated. (i) Floor level exits. Each floor level door or exit in the side of the fuselage (other than those leading into a cargo or baggage compartment that is not accessible from the passenger cabin) that is 44 or more inches high and 20 or more inches wide, but not wider than 46 inches, each passenger ventral exit (except the ventral exits on Martin 404 and Convair 240 airplanes), and each tail cone exit, must meet the requirements of this section for floor level emergency exits. However, the Administrator may grant a deviation from this paragraph if he finds that circumstances make full compliance impractical and that an acceptable level of safety has been achieved. (j) Additional emergency exits. Approved emergency exits in the passenger compartments that are in excess of the minimum number of required emergency exits must meet all of the applicable provisions of this section, except paragraphs (f) (1), (2), and (3) of this section, and must be readily accessible. (k) On each large passenger-carrying turbojet-powered airplane, each ventral exit and tailcone exit must be— (1) Designed and constructed so that it cannot be opened during flight; and (2) Marked with a placard readable from a distance of 30 inches and installed at a conspicuous location near the means of opening the exit, stating that the exit has been designed and constructed so that it cannot be opened during flight. (l) Portable lights. No person may operate a passenger-carrying airplane unless it is equipped with flashlight stowage provisions accessible from each flight attendant seat. [Doc. No. 26530, 57 FR 19245, May 4, 1992; 57 FR 29120, June 30, 1992, as amended at 57 FR 34682, Aug. 6, 1992] § 135.179 Inoperable instruments and equipment.(a) No person may take off an aircraft with inoperable instruments or equipment installed unless the following conditions are met: (1) An approved Minimum Equipment List exists for that aircraft. (2) The certificate-holding district office has issued the certificate holder operations specifications authorizing operations in accordance with an approved Minimum Equipment List. The flight crew shall have direct access at all times prior to flight to all of the information contained in the approved Minimum Equipment List through printed or other means approved by the Administrator in the certificate holders operations specifications. An approved Minimum Equipment List, as authorized by the operations specifications, constitutes an approved change to the type design without requiring recertification. (3) The approved Minimum Equipment List must: (i) Be prepared in accordance with the limitations specified in paragraph (b) of this section. (ii) Provide for the operation of the aircraft with certain instruments and equipment in an inoperable condition. (4) Records identifying the inoperable instruments and equipment and the information required by (a)(3)(ii) of this section must be available to the pilot. (5) The aircraft is operated under all applicable conditions and limitations contained in the Minimum Equipment List and the operations specifications authorizing use of the Minimum Equipment List. (b) The following instruments and equipment may not be included in the Minimum Equipment List: (1) Instruments and equipment that are either specifically or otherwise required by the airworthiness requirements under which the airplane is type certificated and which are essential for safe operations under all operating conditions. (2) Instruments and equipment required by an airworthiness directive to be in operable condition unless the airworthiness directive provides otherwise. (3) Instruments and equipment required for specific operations by this part. (c) Notwithstanding paragraphs (b)(1) and (b)(3) of this section, an aircraft with inoperable instruments or equipment may be operated under a special flight permit under §§21.197 and 21.199 of this chapter. [Doc. No. 25780, 56 FR 12311, Mar. 22, 1991; 56 FR 14920, Apr. 8, 1991, as amended by Amdt. 135–60, 61 FR 2616, Jan. 26, 1996; Amdt. 135–91, 68 FR 54586, Sept. 17, 2003] § 135.180 Traffic Alert and Collision Avoidance System.(a) Unless otherwise authorized by the Administrator, after December 31, 1995, no person may operate a turbine powered airplane that has a passenger seat configuration, excluding any pilot seat, of 10 to 30 seats unless it is equipped with an approved traffic alert and collision avoidance system. If a TCAS II system is installed, it must be capable of coordinating with TCAS units that meet TSO C–119. (b) The airplane flight manual required by §135.21 of this part shall contain the following information on the TCAS I system required by this section: (1) Appropriate procedures for— (i) The use of the equipment; and (ii) Proper flightcrew action with respect to the equipment operation. (2) An outline of all input sources that must be operating for the TCAS to function properly. [Doc. No. 25355, 54 FR 951, Jan. 10, 1989, as amended by Amdt. 135–54, 59 FR 67587, Dec. 29, 1994] § 135.181 Performance requirements: Aircraft operated over-the-top or in IFR conditions.(a) Except as provided in paragraphs (b) and (c) of this section, no person may— (1) Operate a single-engine aircraft carrying passengers over-the-top; or (2) Operate a multiengine aircraft carrying passengers over-the-top or in IFR conditions at a weight that will not allow it to climb, with the critical engine inoperative, at least 50 feet a minute when operating at the MEAs of the route to be flown or 5,000 feet MSL, whichever is higher. (b) Notwithstanding the restrictions in paragraph (a)(2) of this section, multiengine helicopters carrying passengers offshore may conduct such operations in over-the-top or in IFR conditions at a weight that will allow the helicopter to climb at least 50 feet per minute with the critical engine inoperative when operating at the MEA of the route to be flown or 1,500 feet MSL, whichever is higher. (c) Without regard to paragraph (a) of this section, if the latest weather reports or forecasts, or any combination of them, indicate that the weather along the planned route (including takeoff and landing) allows flight under VFR under the ceiling (if a ceiling exists) and that the weather is forecast to remain so until at least 1 hour after the estimated time of arrival at the destination, a person may operate an aircraft over-the-top. (d) Without regard to paragraph (a) of this section, a person may operate an aircraft over-the-top under conditions allowing— (1) For multiengine aircraft, descent or continuance of the flight under VFR if its critical engine fails; or (2) For single-engine aircraft, descent under VFR if its engine fails. [Doc. No. 16097, 43 FR 46783, Oct. 10, 1978, as amended by Amdt. 135–20, 51 FR 40710, Nov. 7, 1986; Amdt. 135–70, 62 FR 42374, Aug. 6, 1997] § 135.183 Performance requirements: Land aircraft operated over water.No person may operate a land aircraft carrying passengers over water unless— (a) It is operated at an altitude that allows it to reach land in the case of engine failure; (b) It is necessary for takeoff or landing; (c) It is a multiengine aircraft operated at a weight that will allow it to climb, with the critical engine inoperative, at least 50 feet a minute, at an altitude of 1,000 feet above the surface; or (d) It is a helicopter equipped with helicopter flotation devices. § 135.185 Empty weight and center of gravity: Currency requirement.(a) No person may operate a multiengine aircraft unless the current empty weight and center of gravity are calculated from values established by actual weighing of the aircraft within the preceding 36 calendar months. (b) Paragraph (a) of this section does not apply to— (1) Aircraft issued an original airworthiness certificate within the preceding 36 calendar months; and (2) Aircraft operated under a weight and balance system approved in the operations specifications of the certificate holder. Browse Previous | Browse Next |
