(6) Equipped with a restraint system consisting of a combined safety belt and shoulder harness unit with a single point release. There must be means to secure each restraint system when not in use to prevent interference with rapid egress in an emergency.
(i) Each safety belt must be equipped with a metal to metal latching device.
(j) If the seat backs do not provide a firm handhold, there must be a handgrip or rail along each aisle to enable persons to steady themselves while using the aisles in moderately rough air.
(k) Each projecting object that would injure persons seated or moving about the airplane in normal flight must be padded.
(l) Each forward observer's seat required by the operating rules must be shown to be suitable for use in conducting the necessary enroute inspection.
[Amdt. 25-15, 32 FR 13262, Sep. 20, 1967; Amdt. 25-20, 34 FR 5544, Apr. 23, 1969; Amdt. 25-32, May 1, 1974; Amdt. 25-51, 45 FR 7755, Mar. 6, 1980; Amdt.
25-64, 53 FR 17647, June 16, 1988; Amdt. 25-72, 55 FR 29780, July 20, 1990;
Amdt. 25-88, 61 FR 57956, Nov. 8, 1996] NOTE: Refer to Advisory Circular (AC) 25-17, or latest revision, Transport Airplane Cabin Interiors Crashworthiness Handbook, for guidance.
1051 - 1054. [RESERVED] 1055. SECTION 25.787 - STOWAGE COMPARTMENTS.
a. Rule Text.
(a) Each compartment for the stowage of cargo, baggage, carry-on articles, and equipment (such as life rafts), and any other stowage compartment must be designed for its placarded maximum weight of contents and for the critical load distribution at the appropriate maximum load factors corresponding to the specified flight and ground load conditions, and to the emergency landing conditions of § 25.561(b), except that the forces specified in the emergency landing conditions need not be applied to compartments located below, or forward, of all occupants in the airplane. If the airplane has a passenger seating configuration, excluding pilots seats, of 10 seats or more, each stowage compartment in the passenger cabin, except for underseat and overhead compartments for passenger convenience, must be completely enclosed.
(b) There must be a means to prevent the contents in the compartments from becoming a hazard by shifting, under the loads specified in paragraph (a) of this section. For stowage compartments in the passenger and crew cabin, if the 1154
means used is a latched door, the design must take into consideration the wear and deterioration expected in service.
1155
(c) If cargo compartment lamps are installed, each lamp must be installed so as to prevent contact between lamp bulb and cargo.
[Amdt. 25-32, 37 FR 3969, Feb. 24, 1972; Amdt. 25-38, 41 FR 55466, Dec. 20, 1976; Amdt. 25-51, 45 FR 7755, Feb. 4, 1980] NOTE: Refer to Advisory Circular (AC) 25-17, or latest revision, Transport Airplane Cabin Interiors Crashworthiness Handbook, for guidance.
1056 - 1059. [RESERVED] 1060. SECTION 25.789 - RETENTION OF ITEMS OF MASS IN PASSENGER AND CREW COMPARTMENTS AND GALLEYS.
a. Rule Text.
(a) Means must be provided to prevent each item of mass (that is part of the airplane type design) in a passenger or crew compartment or galley from becoming a hazard by shifting under the appropriate maximum load factors corresponding to the specified flight and ground load conditions, and to the emergency landing conditions of § 25.561(b).
(b) Each interphone restraint system must be designed so that when subjected to the load factors specified in § 25.561(b)(3), the interphone will remain in its stowed position.
[Amdt. 25-32, 37 FR 3969, Feb. 24, 1972; Amdt. 25-46, 43 FR 50596, Oct. 30, 1978]
b. Intent of Rule. The purpose of this rule is to protect passengers and crewmembers from loose objects that could become a safety hazard by shifting under flight, ground, and emergency landing loads.
c. Background. This rule was introduced by Amendment 25-32. The requirement to retain the interphone in its stowed position was introduced by Amendment 25-46.
d. Acceptable Compliance Methods. Retention of each of item of mass within the cabin can be shown by analysis for the flight and ground load factors.
e. References. Advisory Circular (AC) 25.562-1A, or latest revision, Dynamic Evaluation of Seat Restraint Systems & Occupant Protection on Transport Airplanes; and AC 25-17, or latest revision, Transport Airplane Cabin Interiors Crashworthiness Handbook.
1156
1061 - 1068. [RESERVED] 1069. SECTION 25.791 - PASSENGER INFORMATION SIGNS AND PLACARDS.
a. Rule Text.
(a) If smoking is to be prohibited, there must be at least one placard so stating that is legible to each person seated in the cabin. If smoking is to be allowed, and if the crew compartment is separated from the passenger compartment, there must be at least one sign notifying when smoking is prohibited. Signs which notify when smoking is prohibited must be operable by a member of the flightcrew and, when illuminated, must be legible under all probable conditions of cabin illumination to each person seated in the cabin.
(b) Signs that notify when seat belts should be fastened and that are installed to comply with the operating rules of this chapter must be operable by a member of the flightcrew and, when illuminated, must be legible under all probable conditions of cabin illumination to each person seated in the cabin.
(c) A placard must be located on or adjacent to the door of each receptacle used for the disposal of flammable waste materials to indicate that use of the receptacle for disposal of cigarettes, etc., is prohibited,
(d) Lavatories must have “No Smoking” or “No Smoking in Lavatory” placards conspicuously located on or adjacent to each side of the entry door.
(e) Symbols that clearly express the intent of the sign or placard may be used in lieu of letters.
[Amdt. 25-72, 55 FR 29780, Jul. 20, 1990] NOTE: Refer to Advisory Circular (AC) 25-17, or latest revision Transport Airplane Cabin Interiors Crashworthiness Handbook, for guidance.
1070 - 1072. [RESERVED] 1157
1073. SECTION 25.793 - FLOOR SURFACES.
a. Rule Text.
The floor surface of all areas which are likely to become wet in service must have slip resistant properties.
[Amdt. 25-51, 45 FR 7755, Feb. 4, 1980] NOTE: Refer to Advisory Circular (AC) 25-17, or latest revision, Transport Airplane Cabin Interiors Crashworthiness Handbook, for guidance.
1074 - 1075. [RESERVED] 1158
Section 7. EMERGENCY PROVISIONS 1076. SECTION 25.801 - DITCHING.
a. Rule Text.
(a) If certification with ditching provisions is requested, the airplane must meet the requirements of this section and §§ 25.807(e), 25.1411, and 25.1415(a).
(b) Each practicable design measure, compatible with the general characteristics of the airplane, must be taken to minimize the probability that in an emergency landing on water, the behavior of the airplane would cause immediate injury to the occupants or would make it impossible for them to escape.
(c) The probable behavior of the airplane in a water landing must be investigated by model tests or by comparison with airplanes of similar configuration for which the ditching characteristics are known. Scoops, flaps, projections, and any other factor likely to affect the hydrodynamic characteristics of the airplane, must be considered.
(d) It must be shown that, under reasonably probable water conditions, the flotation time and trim of the airplane will allow the occupants to leave the airplane and enter the life-rafts required by § 25.1415. If compliance with this provision is shown by buoyancy and trim computations, appropriate allowances must be made for probable structural damage and leakage. If the airplane has fuel tanks (with fuel jettisoning provisions) that can reasonably be expected to withstand a ditching without leakage, the jettisonable volume of fuel may be considered as buoyancy volume.
(e) Unless the effects of the collapse of external doors and windows are accounted for in the investigation of the probable behavior of the airplane in a water landing (as prescribed in paragraphs (c) and (d) of this section), the external doors and windows must be designed to withstand the probable maximum local pressures.
[Amdt. 25-72, 55 FR 29781, Jul. 20,1990]
b. Intent of Rule. The purpose of this rule is to require protection of the occupants in the event of an emergency landing on water.
c. Background. This rule was carried forward from § 4b.361 of the Civil Air Regulations (CAR).
Editorial changes were introduced by Amendment 25-72.
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d. Acceptable Compliance Methods. Compliance with this requirement may be shown by test(s) and/or analysis.
e. References. Refer to Advisory Circular (AC) 25-17, or latest revision, Transport Airplane Cabin Interiors Crashworthiness Handbook, for guidance on emergency evacuation following ditching.
1077 - 1085. [RESERVED] 1258
Section 8. FIRE PROTECTION 1086. SECTION 25.865 - FIRE PROTECTION OF FLIGHT CONTROLS, ENGINE MOUNTS, AND OTHER FLIGHT STRUCTURE.
a. Rule Text.
Essential flight controls, engine mounts, and other flight structures located in designated fire zones or in adjacent areas which would be subjected to the effects of fire in the fire zone must be constructed of fireproof material or shielded so that they are capable of withstanding the effects of fire.
[Amdt. 25-23, 35 FR 5676, Apr. 8, 1970]
b. Intent of Rule. The purpose of this rule is to protect the flight controls and other primary structures form the effects of fires in fire zones.
c. Background. This regulation was created by Amendment 25-23.
d. Acceptable Compliance Methods. Compliance with this requirement may be shown by test(s) and/or analysis.
e. References. Advisory Circular (AC) 25-XX, Transport Airplane Propulsion, Engine, and Auxiliary Power Unit (APU) Certification Handbook.
1087 - 1095. [RESERVED] 1096. SECTION 25.867 - FIRE PROTECTION: OTHER COMPONENTS.
a. Rule Text.
(a) Surfaces to the rear of the nacelles, within one nacelle diameter of the nacelle centerline, must be at least fire-resistant.
(b) Paragraph (a) of this section does not apply to tail surfaces to the rear of the nacelle that could not be readily affected by heat, flames, or sparks coming from a designated fire zone or engine compartment of any nacelle.
[Amdt. 25-23, 35 FR 5676, Apr. 8, 1970] 1279
b. Intent of Rule. The purpose of this rule is to ensure that structure located aft of any likely fire is at least fire resistant.
c. Background. This rule was created by Amendment 25-23.
d. Acceptable Compliance Methods. Compliance with this requirement may be shown by test(s) and/or analysis.
e. References. Advisory Circular (AC) 25-XX, Transport Airplane Propulsion, Engine, and APU Certification Handbook.
1097 - 1105. [RESERVED] 1280
Section 9. MISCELLANEOUS 1106. SECTION 25.871 - LEVELING MEANS.
a. Rule Text.
There must be means for determining when the airplane is in a level position on the ground.
[Amdt. 25-23, 35 FR 5676, Apr. 8, 1970]
b. Intent of Rule. The purpose of this rule is to ensure there will be a means for determining when the airplane is level.
c. Background. This rule was created by Amendment 25-23.
d. Acceptable Compliance Methods. Compliance with this requirement may be shown by drawing review.
e. References. None.
1107 - 1112. [RESERVED] 1355
Section 10. FUEL SYSTEM 1113. SECTION 25.963 - FUEL TANKS: GENERAL.
a. Rule Text.
a. Each fuel tank must be able to withstand, without failure, the vibration, inertia, fluid, and structural loads that it may be subjected to in operation.
b. Flexible fuel tank liners must be approved or must be shown to be suitable for the particular application.
c. Integral fuel tanks must have facilities for interior inspection and repair.
d. Fuel tanks within the fuselage contour must be able to resist rupture and to retain fuel, under the inertia forces prescribed for the emergency landing conditions in § 25.561. In addition, these tanks must be in a protected position so that exposure of the tanks to scraping action with the ground is unlikely.
e. Fuel tank access covers must comply with the following criteria in order to avoid loss of hazardous quantities of fuel:
(1) All covers located in an area where experience or analysis indicates a strike is likely must be shown by analysis or tests to minimize penetration and deformation by tire fragments, low energy engine debris, or other likely debris.
(2) All covers must be fire resistant as defined in part 1 of this chapter.
(f) For pressurized fuel tanks, a means with fail-safe features must be provided to prevent the buildup of an excessive pressure difference between the inside and the outside of the tank.
[Amdt. 25-40, 42 FR 15043, Mar. 17, 1977; Amdt. 25-69, 54 FR 40354, Sep. 29, 1989]
b. Intent of Rule. The purpose of this rule is to ensure structural integrity of the fuel tanks under all likely operating conditions, including emergency landing conditions.
c. Background. This rule was carried forward from § 4b.420 of the Civil Air Regulations (CAR).
Amendment 25-40 removed the requirements pertaining to the augmentation liquid tank capacity.
Amendment 25-69 added the requirements pertaining to fuel tank access covers.
d. Acceptable Compliance Methods. Advisory Circular (AC) 25-963-1, or latest revision, provides guidance information for showing compliance with the impact and fire resistance requirements of 25.963(e). Fuel tank access covers must be fire resistant and meet the impact criteria specified in 1375
Advisory Circular 25.963-1, or latest revision. Compliance with this requirement may be shown by test(s) and/or analysis.
1376