14 C.F.R. §§ 121.305–121.321

§121.305. Flight and navigational equipment.

14 C.F.R. § 121.305

No person may operate an airplane unless it is equipped with the following flight and navigational instruments and equipment:

(a)

An airspeed indicating system with heated pitot tube or equivalent means for preventing malfunctioning due to icing.

(b)

A sensitive altimeter.

(c)

A sweep-second hand clock (or approved equivalent).

(d)

A free-air temperature indicator.

(e)

A gyroscopic bank and pitch indicator (artificial horizon).

(f)

A gyroscopic rate-of-turn indicator combined with an integral slip-skid indicator (turn-and-bank indicator) except that only a slip-skid indicator is required when a third attitude instrument system usable through flight attitudes of 360° of pitch and roll is installed in accordance with paragraph (k) of this section.

(g)

A gyroscopic direction indicator (directional gyro or equivalent).

(h)

A magnetic compass.

(i)

A vertical speed indicator (rate-of-climb indicator).

(j)

On the airplane described in this paragraph, in addition to two gyroscopic bank and pitch indicators (artificial horizons) for use at the pilot stations, a third such instrument is installed in accordance with paragraph (k) of this section:

(1)

On each turbojet powered airplane.

(2)

On each turbopropeller powered airplane having a passenger-seat configuration of more than 30 seats, excluding each crewmember seat, or a payload capacity of more than 7,500 pounds.

(3)

On each turbopropeller powered airplane having a passenger-seat configuration of 30 seats or fewer, excluding each crewmember seat, and a payload capacity of 7,500 pounds or less that is manufactured on or after March 20, 1997.

(4)

After December 20, 2010, on each turbopropeller powered airplane having a passenger seat configuration of 10-30 seats and a payload capacity of 7,500 pounds or less that was manufactured before March 20, 1997.

(k)

When required by paragraph (j) of this section, a third gyroscopic bank-and-pitch indicator (artificial horizon) that:

(1)

Is powered from a source independent of the electrical generating system;

(2)

Continues reliable operation for a minimum of 30 minutes after total failure of the electrical generating system;

(3)

Operates independently of any other attitude indicating system;

(4)

Is operative without selection after total failure of the electrical generating system;

(5)

Is located on the instrument panel in a position acceptable to the Administrator that will make it plainly visible to and usable by each pilot at his or her station; and

(6)

Is appropriately lighted during all phases of operation.

Notes, amendments, and revision history

Amendments

[Docket 6258, 29 FR 19205, Dec. 31, 1964, as amended by Amdt. 121-57, 35 FR 304, Jan. 8, 1970; Amdt. 121-60, 35 FR 7108, May 6, 1970; Amdt. 121-81, 36 FR 23050, Dec. 3, 1971; Amdt. 121-130, 41 FR 47229, Oct. 28, 1976; Amdt. 121-230, 58 FR 12158, Mar. 3, 1993; Amdt. 121-251, 60 FR 65929, Dec. 20, 1995; Amdt. 121-262, 62 FR 13256, Mar. 19, 1997]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket 6258, 29 FR 19205, Dec. 31, 1964, as amended by Amdt. 121-57, 35 FR 304, Jan. 8, 1970; Amdt. 121-60, 35 FR 7108, May 6, 1970; Amdt. 121-81, 36 FR 23050, Dec. 3, 1971; Amdt. 121-130, 41 FR 47229, Oct. 28, 1976; Amdt. 121-230, 58 FR 12158, Mar. 3, 1993; Amdt. 121-251, 60 FR 65929, Dec. 20, 1995; Amdt. 121-262, 62 FR 13256, Mar. 19, 1997]

§121.306. Portable electronic devices.

14 C.F.R. § 121.306

(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 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;

(5)

Portable oxygen concentrators that comply with the requirements in § 121.574; or

(6)

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)(6) of this section shall be made by that part 119 certificate holder operating the particular device to be used.

Notes, amendments, and revision history

Amendments

[Docket FAA-1998-4954, 64 FR 1080, Jan. 7, 1999, as amended by Docket FAA-2014-0554, Amdt. 121-374, 81 FR 33118, May 24, 2016]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket FAA-1998-4954, 64 FR 1080, Jan. 7, 1999, as amended by Docket FAA-2014-0554, Amdt. 121-374, 81 FR 33118, May 24, 2016]

§121.307. Engine instruments.

14 C.F.R. § 121.307

Unless the Administrator allows or requires different instrumentation for turbine engine powered airplanes to provide equivalent safety, no person may conduct any operation under this part without the following engine instruments:

(a)

A carburetor air temperature indicator for each engine.

(b)

A cylinder head temperature indicator for each air-cooled engine.

(c)

A fuel pressure indicator for each engine.

(d)

A fuel flowmeter or fuel mixture indicator for each engine not equipped with an automatic altitude mixture control.

(e)

A means for indicating fuel quantity in each fuel tank to be used.

(f)

A manifold pressure indicator for each engine.

(g)

An oil pressure indicator for each engine.

(h)

An oil quantity indicator for each oil tank when a transfer or separate oil reserve supply is used.

(i)

An oil-in temperature indicator for each engine.

(j)

A tachometer for each engine.

(k)

An independent fuel pressure warning device for each engine or a master warning device for all engines with a means for isolating the individual warning circuits from the master warning device.

(l)

A device for each reversible propeller, to indicate to the pilot when the propeller is in reverse pitch, that complies with the following:

(1)

The device may be actuated at any point in the reversing cycle between the normal low pitch stop position and full reverse pitch, but it may not give an indication at or above the normal low pitch stop position.

(2)

The source of indication must be actuated by the propeller blade angle or be directly responsive to it.

Notes, amendments, and revision history

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

§121.308. Lavatory fire protection.

14 C.F.R. § 121.308

(a)

Except as provided in paragraphs (c) and (d) of this section, no person may operate a passenger-carrying airplane unless each lavatory in the airplane is equipped with a smoke detector system or equivalent that provides a warning light in the cockpit or provides a warning light or audio warning in the passenger cabin which would be readily detected by a flight attendant, taking into consideration the positioning of flight attendants throughout the passenger compartment during various phases of flight.

(b)

Except as provided in paragraph (c) of this section, no person may operate a passenger-carrying airplane unless each lavatory in the airplane is equipped with a built-in fire extinguisher for each disposal receptacle for towels, paper, or waste located within the lavatory. The built-in fire extinguisher must be designed to discharge automatically into each disposal receptacle upon occurrence of a fire in the receptacle.

(c)

Until December 22, 1997, a certificate holder described in § 121.2(a) (1) or (2) may operate an airplane with a passenger seat configuration of 30 or fewer seats that does not comply with the smoke detector system requirements described in paragraph (a) of this section and the fire extinguisher requirements described in paragraph (b) of this section.

(d)

After December 22, 1997, no person may operate a nontransport category airplane type certificated after December 31, 1964, with a passenger seat configuration of 10-19 seats unless that airplane complies with the smoke detector system requirements described in paragraph (a) of this section, except that the smoke detector system or equivalent must provide a warning light in the cockpit or an audio warning that would be readily detected by the flightcrew.

Notes, amendments, and revision history

Amendments

[Docket 28154, 60 FR 65929, Dec. 20, 1995]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket 28154, 60 FR 65929, Dec. 20, 1995]

§121.309. Emergency equipment.

14 C.F.R. § 121.309

(a)

General— No person may operate an airplane unless it is equipped with the emergency equipment listed in this section and in § 121.310.

(b)

Each item of emergency and flotation equipment listed in this section and in §§ 121.310, 121.339, and 121.340—

(1)

Must be inspected regularly in accordance with inspection periods established in the operations specifications to ensure its condition for continued serviceability and immediate readiness to perform its intended emergency purposes;

(2)

Must be readily accessible to the crew and, with regard to equipment located in the passenger compartment, to passengers;

(3)

Must be clearly identified and clearly marked to indicate its method of operation; and

(4)

When carried in a compartment or container, must be carried in a compartment or container marked as to contents and the compartment or container, or the item itself, must be marked as to date of last inspection.

(c)

Hand fire extinguishers for crew, passenger, cargo, and galley compartments. Hand fire extinguishers of an approved type must be provided for use in crew, passenger, cargo, and galley compartments in accordance with the following:

(1)

The type and quantity of extinguishing agent must be suitable for the kinds of fires likely to occur in the compartment where the extinguisher is intended to be used and, for passenger compartments, must be designed to minimize the hazard of toxic gas concentrations.

(2)

Cargo compartments. At least one hand fire extinguisher must be conveniently located for use in each class E cargo compartment that is accessible to crewmembers during flight.

(3)

Galley compartments. At least one hand fire extinguisher must be conveniently located for use in each galley located in a compartment other than a passenger, cargo, or crew compartment.

(4)

Flightcrew compartment. At least one hand fire extinguisher must be conveniently located on the flight deck for use by the flightcrew.

(5)

Passenger compartments. Hand fire extinguishers for use in passenger compartments must be conveniently located and, when two or more are required, uniformly distributed throughout each compartment. Hand fire extinguishers shall be provided in passenger compartments as follows:

(i)

For airplanes having passenger seats accommodating more than 6 but fewer than 31 passengers, at least one.

(ii)

For airplanes having passenger seats accommodating more than 30 but fewer than 61 passengers, at least two.

(iii)

For airplanes having passenger seats accommodating more than 60 passengers, there must be at least the following number of hand fire extinguishers:

(6)

Notwithstanding the requirement for uniform distribution of hand fire extinguishers as prescribed in paragraph (c)(5) of this section, for those cases where a galley is located in a passenger compartment, at least one hand fire extinguisher must be conveniently located and easily accessible for use in the galley.

(7)

At least two of the required hand fire extinguisher installed in passenger-carrying airplanes must contain Halon 1211 (bromochlorofluoromethane) or equivalent as the extinguishing agent. At least one hand fire extinguisher in the passenger compartment must contain Halon 1211 or equivalent.

(d)

[Reserved]

(e)

Crash ax. Except for nontransport category airplanes type certificated after December 31, 1964, each airplane must be equipped with a crash ax.

(f)

Megaphones. Each passenger-carrying airplane must have a portable battery-powered megaphone or megaphones readily accessible to the crewmembers assigned to direct emergency evacuation, installed as follows:

(1)

One megaphone on each airplane with a seating capacity of more than 60 and less than 100 passengers, at the most rearward location in the passenger cabin where it would be readily accessible to a normal flight attendant seat. However, the Administrator may grant a deviation from the requirements of this subparagraph if he finds that a different location would be more useful for evacuation of persons during an emergency.

(2)

Two megaphones in the passenger cabin on each airplane with a seating capacity of more than 99 passengers, one installed at the forward end and the other at the most rearward location where it would be readily accessible to a normal flight attendant seat.

Notes, amendments, and revision history

Amendments

[Docket 6258, 29 FR 19205, Dec. 31, 1964]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket 6258, 29 FR 19205, Dec. 31, 1964]

§121.310. Additional emergency equipment.

14 C.F.R. § 121.310

(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, if the Administrator finds that the design of the exit makes compliance impractical, he may grant a deviation from the requirement of automatic deployment 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). This paragraph does not apply to the rear window emergency exit of DC-3 airplanes operated with less than 36 occupants, including crewmembers and less 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 location 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)

Except as provided in paragraph (b)(2)(iii) of this section, 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 a transport category 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.

(iii)

For a nontransport category turbopropellerpowered airplane type certificated after December 31, 1964, each passenger emergency exit marking and each locating sign must be manufactured to have white letters 1 inch high on a red background 2 inches high, be self-illuminated or independently, internally electrically illuminated, and have a minimum brightness of at least 160 microlamberts. The color may be reversed if the passenger compartment illumination is essentially the same. On these airplanes, no sign may continue to be used if its luminescence (brightness) decreases to below 100 microlamberts.

(c)

Lighting for interior emergency exit markings. Except for nontransport category airplanes type certificated after December 31, 1964, 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, after November 26, 1986, 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 comply with the following:

(1)

Each light must—

(i)

Be operable manually both from the flightcrew station and, for airplanes on which a flight attendant is required, from a point in the passenger compartment that is readily accessible to a normal flight attendant seat;

(ii)

Have a means to prevent inadvertent operation of the manual controls; and

(iii)

When armed or turned on at either station, remain lighted or become lighted upon interruption of the airplane's normal electric power.

(2)

Each light must 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.

(3)

Each light must provide the required level of illumination for at least 10 minutes at the critical ambient conditions after emergency landing.

(4)

Each light must 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 transport category airplane:

(1)

Each passage way 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)

For each Type I or Type II emergency exit equipped with an assist means, there must be enough space next to the 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. In addition, all airplanes manufactured on or after November 26, 2008 must comply with the provisions of §§ 25.813(b)(1), (b)(2), (b)(3) and (b)(4) in effect on November 26, 2004. However, a deviation from this requirement may be authorized for an airplane certificated under the provisions of part 4b of the Civil Air Regulations in effect before December 20, 1951, if the Administrator 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—

(i)

For an airplane for which the application for the type certificate was filed prior to May 1, 1972, the access must meet the requirements of § 25.813(c) of this chapter in effect on April 30, 1972; and

(ii)

For an airplane for which the application for the type certificate was filed on or after May 1, 1972, the access must meet the emergency exit access requirements under which the airplane was type certificated; except that,

(iii)

After December 3, 1992, the access for an airplane type certificated after January 1, 1958, must meet the requirements of § 25.813(c) of this chapter, effective June 3, 1992.

(iv)

Contrary provisions of this section notwithstanding, the Director of the division of the Aircraft Certification Service responsible for the airworthiness rules may authorize deviation from the requirements of paragraph (f)(3)(iii) of this section if it is determined that special circumstances make compliance impractical. Such special circumstances include, but are not limited to, the following conditions when they preclude achieving compliance with § 25.813(c)(1)(i) or (ii) without a reduction in the total number of passenger seats: emergency exits located in close proximity to each other; fixed installations such as lavatories, galleys, etc.; permanently mounted bulkheads; an insufficient number of rows ahead of or behind the exit to enable compliance without a reduction in the seat row pitch of more than one inch; or an insufficient number of such rows to enable compliance without a reduction in the seat row pitch to less than 30 inches. A request for such grant of deviation must include credible reasons as to why literal compliance with § 25.813(c)(1)(i) or (ii) is impractical and a description of the steps taken to achieve a level of safety as close to that intended by § 25.813(c)(1)(i) or (ii) as is practical.

(v)

The Director of the division of the Aircraft Certification Service responsible for the airworthiness rules may also authorize a compliance date later than December 3, 1992, if it is determined that special circumstances make compliance by that date impractical. A request for such grant of deviation must outline the airplanes for which compliance will be achieved by December 3, 1992, and include a proposed schedule for incremental compliance of the remaining airplanes in the operator's fleet. In addition, the request must include credible reasons why compliance cannot be achieved earlier.

(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. However, curtains may be used if they allow free entry through the passageway.

(5)

No door may be installed in any partition between passenger compartments.

(6)

No person may operate an airplane manufactured after November 27, 2006, that incorporates a door installed between any passenger seat occupiable for takeoff and landing and any passenger emergency exit, such that the door crosses any egress path (including aisles, crossaisles and passageways).

(7)

If it is necessary to pass through a doorway separating the passenger cabin from other areas to reach required emergency exit from any passenger seat, the door must have a means to latch it in 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)

Except for nontransport category airplanes certificated after December 31, 1964, 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 M-404 and CV-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)

Emergency exit features.

(1)

Each transport category airplane manufactured after November 26, 2007 must comply with the provisions of § 25.809(i) and

(2)

After November 26, 2007 each transport category airplane must comply with the provisions of § 25.813(b)(6)(ii) in effect on November 26, 2007.

(m)

Except for an airplane used in operations under this part on October 16, 1987, and having an emergency exit configuration installed and authorized for operation prior to October 16, 1987, for an airplane that is required to have more than one passenger emergency exit for each side of the fuselage, no passenger emergency exit shall be more than 60 feet from any adjacent passenger emergency exit on the same side of the same deck of the fuselage, as measured parallel to the airplane's longitudinal axis between the nearest exit edges.

(n)

Portable lights. No person may operate a passenger-carrying airplane unless it is equipped with flashlight stowage provisions accessible from each flight attendant seat.

Notes, amendments, and revision history

Amendments

[Docket 2033, 30 FR 3205, Mar. 9, 1965]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket 2033, 30 FR 3205, Mar. 9, 1965]

§121.311. Seats, safety belts, and shoulder harnesses.

14 C.F.R. § 121.311

(a)

No person may operate an airplane unless there are available during the takeoff, en route flight, and landing—

(1)

An approved seat or berth for each person on board the airplane who has reached his second birthday; and

(2)

An approved safety belt for separate use by each person on board the airplane who has reached his second birthday, except that two persons occupying a berth may share one approved safety belt and two persons occupying a multiple lounge or divan seat may share one approved safety belt during en route flight only.

(b)

Except as provided in this paragraph, each person on board an airplane operated under this part shall occupy an approved seat or berth with a separate safety belt properly secured about him or her during movement on the surface, takeoff, and landing. A safety belt provided for the occupant of a seat may not be used by more than one person who has reached his or her second birthday. Notwithstanding the preceding requirements, a child may:

(1)

Be held by an adult who is occupying an approved seat or berth, provided the child has not reached his or her second birthday and the child does not occupy or use any restraining device; or

(2)

Notwithstanding any other requirement of this chapter, occupy an approved child restraint system furnished by the certificate holder or one of the persons described in paragraph (b)(2)(i) of this section, provided:

(i)

The child is accompanied by a parent, guardian, or attendant designated by the child's parent or guardian to attend to the safety of the child during the flight;

(ii)

Except as provided in paragraph (b)(2)(ii)(D) of this section, the approved child restraint system bears one or more labels as follows:

(A)

Seats manufactured to U.S. standards between January 1, 1981, and February 25, 1985, must bear the label: “This child restraint system conforms to all applicable Federal motor vehicle safety standards.”

(B)

Seats manufactured to U.S. standards on or after February 26, 1985, must bear two labels:

(1) “This child restraint system conforms to all applicable Federal motor vehicle safety standards”; and

(2) “THIS RESTRAINT IS CERTIFIED FOR USE IN MOTOR VEHICLES AND AIRCRAFT” in red lettering;

(C)

Seats that do not qualify under paragraphs (b)(2)(ii)(A) and (b)(2)(ii)(B) of this section must bear a label or markings showing:

(1) That the seat was approved by a foreign government;

(2) That the seat was manufactured under the standards of the United Nations;

(3) That the seat or child restraint device furnished by the certificate holder was approved by the FAA through Type Certificate or Supplemental Type Certificate; or

(4) That the seat or child restraint device furnished by the certificate holder, or one of the persons described in paragraph (b)(2)(i) of this section, was approved by the FAA in accordance with § 21.8(d) of this chapter or Technical Standard Order C-100b, or a later version. The child restraint device manufactured by AmSafe, Inc. (CARES, Part No. 4082) and approved by the FAA in accordance with § 21.305(d) (2010 ed.) of this chapter may continue to bear a label or markings showing FAA approval in accordance with § 21.305(d) (2010 ed.) of this chapter.

(D)

Except as provided in § 121.311(b)(2)(ii)(C)(3) and § 121.311(b)(2)(ii)(C)(4), booster-type child restraint systems (as defined in Federal Motor Vehicle Safety Standard No. 213 (49 CFR 571.213)), vest- and harness-type child restraint systems, and lap held child restraints are not approved for use in aircraft; and

(iii)

The certificate holder complies with the following requirements—

(A)

The restraint system must be properly secured to an approved forward-facing seat or berth;

(B)

The child must be properly secured in the restraint system and must not exceed the specified weight limit for the restraint system; and

(C)

The restraint system must bear the appropriate label(s).

(c)

Except as provided in paragraph (c)(3) of this section, the following prohibitions apply to certificate holders:

(1)

Except as provided in § 121.311(b)(2)(ii)(C)(3) and § 121.311(b)(2)(ii)(C)(4), no certificate holder may permit a child, in an aircraft, to occupy a booster-type child restraint system, a vest-type child restraint system, a harness-type child restraint system, or a lap held child restraint system during take off, landing, and movement on the surface.

(2)

Except as required in paragraph (c)(1) of this section, no certificate holder may prohibit a child, if requested by the child's parent, guardian, or designated attendant, from occupying a child restraint system furnished by the child's parent, guardian, or designated attendant provided—

(i)

The child holds a ticket for an approved seat or berth or such seat or berth is otherwise made available by the certificate holder for the child's use;

(ii)

The requirements of paragraph (b)(2)(i) of this section are met;

(iii)

The requirements of paragraph (b)(2)(iii) of this section are met; and

(iv)

The child restraint system has one or more of the labels described in paragraphs (b)(2)(ii)(A) through (b)(2)(ii)(C) of this section.

(3)

This section does not prohibit the certificate holder from providing child restraint systems authorized by this section or, consistent with safe operating practices, determining the most appropriate passenger seat location for the child restraint system.

(d)

Each sideward facing seat must comply with the applicable requirements of § 25.785(c) of this chapter.

(e)

Except as provided in paragraphs (e)(1) through (e)(3) of this section, no certificate holder may take off or land an airplane unless each passenger seat back is in the upright position. Each passenger shall comply with instructions given by a crewmember in compliance with this paragraph.

(1)

This paragraph does not apply to seat backs placed in other than the upright position in compliance with § 121.310(f)(3).

(2)

This paragraph does not apply to seats on which cargo or persons who are unable to sit erect for a medical reason are carried in accordance with procedures in the certificate holder's manual if the seat back does not obstruct any passenger's access to the aisle or to any emergency exit.

(3)

On airplanes with no flight attendant, the certificate holder may take off or land as long as the flightcrew instructs each passenger to place his or her seat back in the upright position for takeoff and landing.

(f)

No person may operate a transport category airplane that was type certificated after January 1, 1958, or a nontransport category airplane manufactured after March 20, 1997, unless it is equipped at each flight deck station with a combined safety belt and shoulder harness that meets the applicable requirements specified in § 25.785 of this chapter, effective March 6, 1980, except that—

(1)

Shoulder harnesses and combined safety belt and shoulder harnesses that were approved and installed before March 6, 1980, may continue to be used; and

(2)

Safety belt and shoulder harness restraint systems may be designed to the inertia load factors established under the certification basis of the airplane.

(g)

Each flight attendant must have a seat for takeoff and landing in the passenger compartment that meets the requirements of § 25.785 of this chapter, effective March 6, 1980, except that—

(1)

Combined safety belt and shoulder harnesses that were approved and installed before March, 6, 1980, may continue to be used; and

(2)

Safety belt and shoulder harness restraint systems may be designed to the inertia load factors established under the certification basis of the airplane.

(3)

The requirements of § 25.785(h) do not apply to passenger seats occupied by flight attendants not required by § 121.391.

(h)

Each occupant of a seat equipped with a shoulder harness or with a combined safety belt and shoulder harness must have the shoulder harness or combined safety belt and shoulder harness properly secured about that occupant during takeoff and landing, except that a shoulder harness that is not combined with a safety belt may be unfastened if the occupant cannot perform the required duties with the shoulder harness fastened.

(i)

At each unoccupied seat, the safety belt and shoulder harness, if installed, must be secured so as not to interfere with crewmembers in the performance of their duties or with the rapid egress of occupants in an emergency.

(j)

After October 27, 2009, no person may operate a transport category airplane type certificated after January 1, 1958 and manufactured on or after October 27, 2009 in passenger-carrying operations under this part unless all passenger and flight attendant seats on the airplane meet the requirements of § 25.562 in effect on or after June 16, 1988.

(k)

Seat dimension disclosure.

(1)

Each air carrier that conducts operations under this part and that has a Web site must make available on its Web site the width of the narrowest and widest passenger seats in each class of service for each airplane make, model and series operated by that air carrier in passenger-carrying operations.

(2)

For purposes of paragraph (k)(1) of this section, the width of a passenger seat means the distance between the inside of the armrests for that seat.

Notes, amendments, and revision history

Amendments

[Docket 7522, 32 FR 13267, Sept. 20, 1967]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket 7522, 32 FR 13267, Sept. 20, 1967]

§121.312. Materials for compartment interiors.

14 C.F.R. § 121.312

(a)

All interior materials; transport category airplanes and nontransport category airplanes type certificated before January 1, 1965. Except for the materials covered by paragraph (b) of this section, all materials in each compartment of a transport category airplane, or a nontransport category airplane type certificated before January 1, 1965, used by the crewmembers and passengers, must meet the requirements of § 25.853 of this chapter in effect as follows, or later amendment thereto:

(1)

Airplane with passenger seating capacity of 20 or more—

(i)

Manufactured after August 19, 1988, but prior to August 20, 1990. Except as provided in paragraph (a)(3)(ii) 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) (see App. L of this part), except that the total heat release over the first 2 minutes of sample exposure must not exceed 100 kilowatt minutes per square meter and the peak heat release rate must not exceed 100 kilowatts per square meter.

(ii)

Manufactured after August 19, 1990. 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 § 25.853(a-1)(see app. L of this part) in effect on September 26, 1988).

(2)

Substantially complete replacement of the cabin interior on or after May 1, 1972—

(i)

Airplane for which the application for type certificate was filed prior to May 1, 1972. Except as provided in paragraph (a)(3)(i) or (a)(3)(ii) 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 passenger capacity, if there is a substantially complete replacement of the cabin interior after April 30, 1972.

(ii)

Airplane for which the application for type certificate was filed on or after May 1, 1972. Except as provided in paragraph (a)(3)(i) or (a)(3)(ii) of this section, each airplane for which the application for type certificate was filed on or after May 1, 1972, must comply with the material requirements under which the airplane was type certificated, regardless of passenger capacity, if there is a substantially complete replacement of the cabin interior on or after that date.

(3)

Airplane type certificated after January 1, 1958, with passenger capacity of 20 or more—

(i)

Substantially complete replacement of the cabin interior on or after March 6, 1995. Except as provided in paragraph (a)(3)(ii) of this section, each airplane that was type certificated after January 1, 1958, and has a passenger capacity of 20 or more, 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)(see app. L of this part), if there is a substantially complete replacement of the cabin interior components identified in § 25.853(d), 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 must not exceed 100 kilowatts per square meter.

(ii)

Substantially complete replacement of the cabin interior on or after August 20, 1990. Each airplane that was type certificated after January 1, 1958, and has a passenger capacity of 20 or more, 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 September 26, 1988)(see app. L of this part), if there is a substantially complete replacement of the cabin interior components identified in § 25.853(d), on or after August 20, 1990.

(4)

Contrary provisions of this section notwithstanding, the Director of the division of the Aircraft Certification Service responsible for the airworthiness rules may authorize deviation from the requirements of paragraph (a)(1)(i), (a)(1)(ii), (a)(3)(i), or (a)(3)(ii) 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(a-1), 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.

(5)

Contrary provisions of this section notwithstanding, galley carts and galley standard 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)) (see app. L of this part) may be used in airplanes that must meet the requirements of paragraphs (a)(1)(i), (a)(1)(ii), (a)(3)(i), or (a)(3)(ii) of this section, provided the galley carts or standard containers were manufactured prior to March 6, 1995.

(b)

Seat cushions. Seat cushions, except those on flight crewmember seats, in each compartment occupied by crew or passengers, must comply with the requirements pertaining to seat cushions in § 25.853(c) effective on November 26, 1984, on each airplane as follows:

(1)

Each transport category airplane type certificated after January 1, 1958; and

(2)

On or after December 20, 2010, each nontransport category airplane type certificated after December 31, 1964.

(c)

All interior materials; airplanes type certificated in accordance with SFAR No. 41 of 14 CFR part 21. No person may operate an airplane that conforms to an amended or supplemental type certificate issued in accordance with SFAR No. 41 of 14 CFR part 21 for a maximum certificated takeoff weight in excess of 12,500 pounds unless 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)(see app. L of this part).

(d)

All interior materials; other airplanes. For each material or seat cushion to which a requirement in paragraphs (a), (b), or (c) of this section does not apply, the material and seat cushion in each compartment used by the crewmembers and passengers must meet the applicable requirement under which the airplane was type certificated.

(e)

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.

(3)

For airplanes with a passenger capacity of 20 or greater, manufactured after September 2, 2009, thermal/acoustic insulation materials installed in the lower half of the fuselage must meet the flame penetration resistance requirements of § 25.856 of this chapter, effective September 2, 2003.

Notes, amendments, and revision history

Amendments

[Docket 28154, 60 FR 65930, Dec. 20, 1995, as amended by Amdt. 121-301, 68 FR 45083, July 31, 2003; Amdt. 121-320, 70 FR 77752, Dec. 30, 2005; Amdt. 121-330, 72 FR 1442, Jan. 12, 2007; Docket FAA-2018-0119, Amdt. 121-380, 83 FR 9173, Mar. 5, 2018]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket 28154, 60 FR 65930, Dec. 20, 1995, as amended by Amdt. 121-301, 68 FR 45083, July 31, 2003; Amdt. 121-320, 70 FR 77752, Dec. 30, 2005; Amdt. 121-330, 72 FR 1442, Jan. 12, 2007; Docket FAA-2018-0119, Amdt. 121-380, 83 FR 9173, Mar. 5, 2018]

§121.313. Miscellaneous equipment.

14 C.F.R. § 121.313

No person may conduct any operation unless the following equipment is installed in the airplane:

(a)

If protective fuses are installed on an airplane, the number of spare fuses approved for that airplane and appropriately described in the certificate holder's manual.

(b)

A windshield wiper or equivalent for each pilot station.

(c)

A power supply and distribution system that meets the requirements of §§ 25.1309, 25.1331, 25.1351(a) and (b)(1) through (4), 25.1353, 25.1355, and 25.1431(b) or that is able to produce and distribute the load for the required instruments and equipment, with use of an external power supply if any one power source or component of the power distribution system fails. The use of common elements in the system may be approved if the Administrator finds that they are designed to be reasonably protected against malfunctioning. Engine-driven sources of energy, when used, must be on separate engines.

(d)

A means for indicating the adequacy of the power being supplied to required flight instruments.

(e)

Two independent static pressure systems, vented to the outside atmospheric pressure so that they will be least affected by air flow variation or moisture or other foreign matter, and installed so as to be airtight except for the vent. When a means is provided for transferring an instrument from its primary operating system to an alternate system, the means must include a positive positioning control and must be marked to indicate clearly which system is being used.

(f)

A door between the passenger and pilot compartments (i.e., flightdeck door), with a locking means to prevent passengers from opening it without the pilot's permission, except that nontransport category airplanes certificated after December 31, 1964, are not required to comply with this paragraph. For airplanes equipped with a crew rest area having separate entries from the flightdeck and the passenger compartment, a door with such a locking means must be provided between the crew rest area and the passenger compartment.

(g)

A key for each door that separates a passenger compartment from another compartment that has emergency exit provisions. Except for flightdeck doors, a key must be readily available for each crewmember. Except as provided below, no person other than a person who is assigned to perform duty on the flightdeck may have a key to the flightdeck door. Before April 22, 2003, any crewmember may have a key to the flightdeck door but only if the flightdeck door has an internal flightdeck locking device installed, operative, and in use. Such “internal flightdeck locking device” has to be designed so that it can only be unlocked from inside the flightdeck.

(h)

A placard on each door that is the means of access to a required passenger emergency exit, to indicate that it must be open during takeoff and landing.

(i)

A means for the crew, in an emergency to unlock each door that leads to a compartment that is normally accessible to passengers and that can be locked by passengers.

(j)

After April 9, 2003, for airplanes required by paragraph (f) of this section to have a door between the passenger and pilot or crew rest compartments, and for transport category, all-cargo airplanes that have a door installed between the pilot compartment and any other occupied compartment on January 15, 2002;

(1)

After April 9, 2003, for airplanes required by paragraph (f) of this section to have a door between the passenger and pilot or crew rest compartments,

(i)

Each such door must meet the requirements of § 25.795(a)(1) and (2) in effect on January 15, 2002; and

(ii)

Each operator must establish methods to enable a flight attendant to enter the pilot compartment in the event that a flightcrew member becomes incapacitated. Any associated signal or confirmation system must be operable by each flightcrew member from that flightcrew member's duty station.

(2)

After October 1, 2003, for transport category, all-cargo airplanes that had a door installed between the pilot compartment and any other occupied compartment on or after January 15, 2002, each such door must meet the requirements of § 25.795(a)(1) and (2) in effect on January 15, 2002; or the operator must implement a security program approved by the Transportation Security Administration (TSA) for the operation of all airplanes in that operator's fleet.

(k)

Except for all-cargo operations as defined in § 110.2 of this chapter, for all passenger-carrying airplanes that require a lockable flightdeck door in accordance with paragraph (f) of this section, a means to monitor from the flightdeck side of the door the area outside the flightdeck door to identify persons requesting entry and to detect suspicious behavior and potential threats.

(l)

For airplanes required by paragraph (f) of this section to have a door between the passenger and pilot or crew rest compartments, and for passenger-carrying transport category airplanes that have a door installed between the pilot compartment and any other occupied compartment, that were manufactured after August 25, 2025, an installed physical secondary barrier (IPSB) that meets the requirements of § 25.795(a)(4) of this chapter in effect on August 25, 2023.

Notes, amendments, and revision history

Amendments

[Docket 6258, 29 FR 19205, Dec. 31, 1964, as amended by Amdt. 121-5, 30 FR 6113, Apr. 30, 1965; Amdt. 121-251, 60 FR 65931, Dec. 20, 1995; Amdt. 121-288, 67 FR 2127, Jan. 15, 2002; Amdt. 121-299, 68 FR 42881, July 18, 2003; Amdt. 121-334, 72 FR 45635, Aug. 15, 2007; Amdt. 121-353, 76 FR 7488, Feb. 10, 2011; Amdt. 121-389, 88 FR 41308, June 26, 2023]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket 6258, 29 FR 19205, Dec. 31, 1964, as amended by Amdt. 121-5, 30 FR 6113, Apr. 30, 1965; Amdt. 121-251, 60 FR 65931, Dec. 20, 1995; Amdt. 121-288, 67 FR 2127, Jan. 15, 2002; Amdt. 121-299, 68 FR 42881, July 18, 2003; Amdt. 121-334, 72 FR 45635, Aug. 15, 2007; Amdt. 121-353, 76 FR 7488, Feb. 10, 2011; Amdt. 121-389, 88 FR 41308, June 26, 2023]

§121.314. Cargo and baggage compartments.

14 C.F.R. § 121.314

For each transport category airplane type certificated after January 1, 1958:

(a)

Each Class C or Class D compartment, as defined in § 25.857 of this Chapter in effect on June 16, 1986 (see Appendix L to this part), that is greater than 200 cubic feet in volume must have ceiling and sidewall liner panels which are constructed of:

(1)

Glass fiber reinforced resin;

(2)

Materials which meet the test requirements of part 25, appendix F, part III of this chapter; or

(3)

In the case of liner installations approved prior to March 20, 1989, aluminum.

(b)

For compliance with paragraph (a) of this section, 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.

(c)

After March 19, 2001, each Class D compartment, regardless of volume, must meet the standards of §§ 25.857(c) and 25.858 of this Chapter for a Class C compartment unless the operation is an all-cargo operation in which case each Class D compartment may meet the standards in § 25.857(e) for a Class E compartment.

(d)

Reports of conversions and retrofits.

(1)

Until such time as all Class D compartments in aircraft operated under this part by the certificate have been converted or retrofitted with appropriate detection and suppression systems, each certificate holder must submit written progress reports to the FAA that contain the information specified below.

(i)

The serial number of each airplane listed in the operations specifications issued to the certificate holder for operation under this part in which all Class D compartments have been converted to Class C or Class E compartments;

(ii)

The serial number of each airplane listed in the operations specification issued to the certificate holder for operation under this part, in which all Class D compartments have been retrofitted to meet the fire detection and suppression requirements for Class C or the fire detection requirements for Class E; and

(iii)

The serial number of each airplane listed in the operations specifications issued to the certificate holder for operation under this part that has at least one Class D compartment that has not been converted or retrofitted.

(2)

The written report must be submitted to the responsible Flight Standards office by July 1, 1998, and at each three-month interval thereafter.

Notes, amendments, and revision history

Amendments

[Docket 28937, 63 FR 8049, Feb. 17, 1998, as amended by Docket FAA-2018-0119, Amdt. 121-380, 83 FR 9173, Mar. 5, 2018]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket 28937, 63 FR 8049, Feb. 17, 1998, as amended by Docket FAA-2018-0119, Amdt. 121-380, 83 FR 9173, Mar. 5, 2018]

§121.315. Cockpit check procedure.

14 C.F.R. § 121.315

(a)

Each certificate holder shall provide an approved cockpit check procedure for each type of aircraft.

(b)

The approved procedures must include each item necessary for flight crewmembers to check for safety before starting engines, taking off, or landing, and in engine and systems emergencies. The procedures must be designed so that a flight crewmember will not need to rely upon his memory for items to be checked.

(c)

The approved procedures must be readily usable in the cockpit of each aircraft and the flight crew shall follow them when operating the aircraft.

Notes, amendments, and revision history

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

§121.316. Fuel tanks.

14 C.F.R. § 121.316

Each turbine powered transport category airplane operated after October 30, 1991, must meet the requirements of § 25.963(e) of this chapter in effect on October 30, 1989.

Notes, amendments, and revision history

Amendments

[Docket 25614, 54 FR 40354, Sept. 29, 1989]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket 25614, 54 FR 40354, Sept. 29, 1989]

§121.317. Passenger information requirements, smoking prohibitions, and additional seat belt requirements.

14 C.F.R. § 121.317

(a)

Except as provided in paragraph (l) of this section, no person may operate an airplane unless it is equipped with passenger information signs that meet the requirements of § 25.791 of this chapter.

(b)

Except as provided in paragraph (l) of this section, the “Fasten Seat Belt” sign shall be turned on during any movement on the surface, for each takeoff, for each landing, and at any other time considered necessary by the pilot in command.

(c)

No person may operate an airplane on a flight on which smoking is prohibited by part 252 of this title unless either the “No Smoking” passenger information signs are lighted during the entire flight, or one or more “No Smoking” placards meeting the requirements of § 25.1541 of this chapter are posted during the entire flight segment. If both the lighted signs and the placards are used, the signs must remain lighted during the entire flight segment.

(d)

No person may operate a passenger-carrying airplane under this part unless at least one legible sign or placard that reads “Fasten Seat Belt While Seated” is visible from each passenger seat. These signs or placards need not meet the requirements of paragraph (a) of this section.

(e)

No person may operate an airplane unless there is installed in each lavatory a sign or placard that reads: “Federal law provides for a penalty of up to $2,000 for tampering with the smoke detector installed in this lavatory.” These signs or placards need not meet the requirements of paragraph (a) of this section.

(f)

Each passenger required by § 121.311(b) to occupy a seat or berth shall fasten his or her safety belt about him or her and keep it fastened while the “Fasten Seat Belt” sign is lighted.

(g)

No person may smoke while a “No Smoking” sign is lighted or while “No Smoking” placards are posted, except as follows:

(1)

Supplemental operations. The pilot in command of an airplane engaged in a supplemental operation may authorize smoking on the flight deck (if it is physically separated from any passenger compartment), but not in any of the following situations:

(i)

During airplane movement on the surface or during takeoff or landing;

(ii)

During scheduled passenger-carrying public charter operations conducted under part 380 of this title; or

(iii)

During any operation where smoking is prohibited by part 252 of this title or by international agreement.

(2)

Certain intrastate domestic operations. Except during airplane movement on the surface or during takeoff or landing, a pilot in command of an airplane engaged in a domestic operation may authorize smoking on the flight deck (if it is physically separated from the passenger compartment) if—

(i)

Smoking on the flight deck is not otherwise prohibited by part 252 of this title;

(ii)

The flight is conducted entirely within the same State of the United States (a flight from one place in Hawaii to another place in Hawaii through the airspace over a place outside of Hawaii is not entirely within the same State); and

(iii)

The airplane is either not turbojet-powered or the airplane is not capable of carrying at least 30 passengers.

(h)

No person may smoke in any airplane lavatory.

(i)

No person may tamper with, disable, or destroy any smoke detector installed in any airplane lavatory.

(j)

On flight segments other than those described in paragraph (c) of this section, the “No Smoking” sign must be turned on during any movement on the surface, for each takeoff, for each landing, and at any other time considered necessary by the pilot in command.

(k)

Each passenger shall comply with instructions given him or her by a crewmember regarding compliance with paragraphs (f), (g), (h), and (l) of this section.

(l)

A certificate holder may operate a nontransport category airplane type certificated after December 31, 1964, that is manufactured before December 20, 1997, if it is equipped with at least one placard that is legible to each person seated in the cabin that states “Fasten Seat Belt,” and if, during any movement on the surface, for each takeoff, for each landing, and at any other time considered necessary by the pilot in command, a crewmember orally instructs the passengers to fasten their seat belts.

Notes, amendments, and revision history

Amendments

[Docket 25590, 53 FR 12361, Apr. 13, 1988, as amended by Amdt. 121-196, 53 FR 44182, Nov. 2, 1988; Amdt. 121-213, 55 FR 8367, Mar. 7, 1990; Amdt. 121-230, 57 FR 42673, Sept. 15, 1992; Amdt. 121-251, 60 FR 65931, Dec. 20, 1995; Amdt. 121-256, 61 FR 30434, June 14, 1996; Amdt. 121-277, 65 FR 36779, June 9, 2000; Docket FAA-2024-2052, Amdt. 121-393, 89 FR 68100, Aug. 23, 2024]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket 25590, 53 FR 12361, Apr. 13, 1988, as amended by Amdt. 121-196, 53 FR 44182, Nov. 2, 1988; Amdt. 121-213, 55 FR 8367, Mar. 7, 1990; Amdt. 121-230, 57 FR 42673, Sept. 15, 1992; Amdt. 121-251, 60 FR 65931, Dec. 20, 1995; Amdt. 121-256, 61 FR 30434, June 14, 1996; Amdt. 121-277, 65 FR 36779, June 9, 2000; Docket FAA-2024-2052, Amdt. 121-393, 89 FR 68100, Aug. 23, 2024]

§121.318. Public address system.

14 C.F.R. § 121.318

No person may operate an airplane with a seating capacity of more than 19 passengers unless it is equipped with a public address system which—

(a)

Is capable of operation independent of the crewmember interphone system required by § 121.319, except for handsets, headsets, microphones, selector switches, and signaling devices;

(b)

Is approved in accordance with § 21.305 of this chapter;

(c)

Is accessible for immediate use from each of two flight crewmember stations in the pilot compartment;

(d)

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;

(e)

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;

(f)

Is audible at all passenger seats, lavatories, and flight attendant seats and work stations; and

(g)

For transport category airplanes manufactured on or after November 27, 1990, meets the requirements of § 25.1423 of this chapter.

Notes, amendments, and revision history

Amendments

[Docket 24995, 54 FR 43926, Oct. 27, 1989]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket 24995, 54 FR 43926, Oct. 27, 1989]

§121.319. Crewmember interphone system.

14 C.F.R. § 121.319

(a)

No person may operate an airplane with a seating capacity of more than 19 passengers unless the airplane is equipped with a crewmember interphone system that:

(1)

[Reserved]

(2)

Is capable of operation independent of the public address system required by § 121.318(a) except for handsets, headsets, microphones, selector switches, and signaling devices; and

(3)

Meets the requirements of paragraph (b) of this section.

(b)

The crewmember interphone system required by paragraph (a) of this section must be approved in accordance with § 21.305 of this chapter and meet the following requirements:

(1)

It must provide 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.

(2)

It must be accessible for immediate use from each of two flight crewmember stations in the pilot compartment;

(3)

It must be accessible for use from at least one normal flight attendant station in each passenger compartment;

(4)

It must be capable of operation within 10 seconds by a flight attendant at those stations in each passenger compartment from which its use is accessible; and

(5)

For large turbojet-powered airplanes—

(i)

It must be 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)

It must have 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)

The alerting system required by paragraph (b)(5)(ii) of this section must have 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, it must provide 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.

Notes, amendments, and revision history

Amendments

[Docket 10865, 38 FR 21494, Aug. 9, 1973, as amended by Amdt. 121-121, 40 FR 42186, Sept. 11, 1975; Amdt. 121-149, 43 FR 50602, Oct. 30, 1978; Amdt. 121-178, 47 FR 13316, Mar. 29, 1982; Amdt. 121-253, 61 FR 2611, Jan. 26, 1996]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket 10865, 38 FR 21494, Aug. 9, 1973, as amended by Amdt. 121-121, 40 FR 42186, Sept. 11, 1975; Amdt. 121-149, 43 FR 50602, Oct. 30, 1978; Amdt. 121-178, 47 FR 13316, Mar. 29, 1982; Amdt. 121-253, 61 FR 2611, Jan. 26, 1996]

§121.321. Operations in icing.

14 C.F.R. § 121.321

After October 21, 2013, no person may operate an airplane with a certificated maximum takeoff weight less than 60,000 pounds in conditions conducive to airframe icing unless it complies with this section. As used in this section, the phrase “conditions conducive to airframe icing” means visible moisture at or below a static air temperature of 5 °C or a total air temperature of 10 °C, unless the approved Airplane Flight Manual provides another definition.

(a)

When operating in conditions conducive to airframe icing, compliance must be shown with paragraph (a)(1), or (2), or (3) of this section.

(1)

The airplane must be equipped with a certificated primary airframe ice detection system.

(i)

The airframe ice protection system must be activated automatically, or manually by the flightcrew, when the primary ice detection system indicates activation is necessary.

(ii)

When the airframe ice protection system is activated, any other procedures in the Airplane Flight Manual for operating in icing conditions must be initiated.

(2)

Visual cues of the first sign of ice formation anywhere on the airplane and a certificated advisory airframe ice detection system must be provided.

(i)

The airframe ice protection system must be activated when any of the visual cues are observed or when the advisory airframe ice detection system indicates activation is necessary, whichever occurs first.

(ii)

When the airframe ice protection system is activated, any other procedures in the Airplane Flight Manual for operating in icing conditions must be initiated.

(3)

If the airplane is not equipped to comply with the provisions of paragraph (a)(1) or (2) of this section, then the following apply:

(i)

When operating in conditions conducive to airframe icing, the airframe ice protection system must be activated prior to, and operated during, the following phases of flight:

(A)

Takeoff climb after second segment,

(B)

En route climb,

(C)

Go-around climb,

(D)

Holding,

(E)

Maneuvering for approach and landing, and

(F)

Any other operation at approach or holding airspeeds.

(ii)

During any other phase of flight, the airframe ice protection system must be activated and operated at the first sign of ice formation anywhere on the airplane, unless the Airplane Flight Manual specifies that the airframe ice protection system should not be used or provides other operational instructions.

(iii)

Any additional procedures for operation in conditions conducive to icing specified in the Airplane Flight Manual or in the manual required by § 121.133 must be initiated.

(b)

If the procedures specified in paragraph (a)(3)(i) of this section are specifically prohibited in the Airplane Flight Manual, compliance must be shown with the requirements of paragraph (a)(1) or (2) of this section.

(c)

Procedures necessary for safe operation of the airframe ice protection system must be established and documented in:

(1)

The Airplane Flight Manual for airplanes that comply with paragraph (a)(1) or (2) of this section, or

(2)

The Airplane Flight Manual or in the manual required by § 121.133 for airplanes that comply with paragraph (a)(3) of this section.

(d)

Procedures for operation of the airframe ice protection system must include initial activation, operation after initial activation, and deactivation. Procedures for operation after initial activation of the ice protection system must address—

(1)

Continuous operation,

(2)

Automatic cycling,

(3)

Manual cycling if the airplane is equipped with an ice detection system that alerts the flightcrew each time the ice protection system must be cycled, or

(4)

Manual cycling based on a time interval if the airplane type is not equipped with features necessary to implement (d)(1)-(3) of this section.

(e)

System installations used to comply with paragraph (a)(1) or (a)(2) of this section must be approved through an amended or supplemental type certificate in accordance with part 21 of this chapter.

Notes, amendments, and revision history

Amendments

[Docket FAA-2009-0675, 78 FR 15876, Mar. 13, 2013]

Source

Source: Docket 6258, 29 FR 19205, Dec. 31, 1964, unless otherwise noted.

Authority

Authority: 49 U.S.C. 106(f), 40103, 40113, 40119, 41706, 42301 preceding note added by Pub. L. 112-95, sec. 412, 126 Stat. 89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49 U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732 note); Pub. L. 115-254, 132 Stat. 3186 (49 U.S.C. 44701 note).

Amendments

[Docket FAA-2009-0675, 78 FR 15876, Mar. 13, 2013]