359 part 25—airworthiness stand- ards: transport category airplanes

258 Pages·2014·3.97 MB·English

Federal Aviation Administration, DOT Pt. 25
TABLEI.—HIRF ENVIRONMENTI (5) From 400 MHz to 8 gigahertz (GHz), use
radiated susceptibility tests at a minimum
Field strength of 150 V/m peak with pulse modulation of 4
Frequency (volts/meter) percent duty cycle with a 1 kHz pulse repeti-
Peak Average tion frequency. This signal must be switched
on and off at a rate of 1 Hz with a duty cycle
10 kHz–2 MHz................................... 50 50 of 50 percent.
2 MHz–30 MHz ................................. 100 100 (d) Equipment HIRF Test Level 2. Equipment
30 MHz–100 MHz ............................. 50 50 HIRF test level 2 is HIRF environment II in
100 MHz–400 MHz ........................... 100 100 table II of this appendix reduced by accept-
400 MHz–700 MHz ........................... 700 50 able aircraft transfer function and attenu-
700 MHz–1 GHz................................ 700 100 ation curves. Testing must cover the fre-
GHz–2 GHz....................................... 2,000 200
quency band of 10 kHz to 8 GHz.
2 GHz–6 GHz.................................... 3,000 200
6 GHz–8 GHz.................................... 1,000 200 (e) Equipment HIRF Test Level 3. (1) From 10
8 GHz–12 GHz.................................. 3,000 300 kHz to 400 MHz, use conducted susceptibility
12 GHz–18 GHz................................ 2,000 200 tests, starting at a minimum of 0.15 mA at 10
18 GHz–40 GHz................................ 600 200 kHz, increasing 20 dB per frequency decade
to a minimum of 7.5 mA at 500 kHz.
In this table, the higher field strength applies at the fre-
quency band edges. (2) From 500 kHz to 40 MHz, use conducted
susceptibility tests at a minimum of 7.5 mA.
(b) HIRF environment II is specified in the
(3) From 40 MHz to 400 MHz, use conducted
following table:
susceptibility tests, starting at a minimum
of 7.5 mA at 40 MHz, decreasing 20 dB per fre-
TABLEII.–HIRF ENVIRONMENTII quency decade to a minimum of 0.75 mA at
400 MHz.
Field strength
Frequency (volts/meter) su(s4c)e pFtriobmili t1y0 0t eMstHsz a tto a 8m GinHizm, uumse orfa 5d iVat/med.
Peak Average
[Doc. No. FAA–2006–23657, 72 FR 44025, Aug. 6,
10 kHz–500 kHz................................ 20 20 2007]
500 kHz–2 MHz................................. 30 30
2 MHz–30 MHz ................................. 100 100
PART 25—AIRWORTHINESS STAND-
30 MHz–100 MHz ............................. 10 10
100 MHz–200 MHz ........................... 30 10 ARDS: TRANSPORT CATEGORY
200 MHz–400 MHz ........................... 10 10 AIRPLANES
400 MHz–1 GHz................................ 700 40
1 GHz–2 GHz.................................... 1,300 160
2 GHz–4 GHz.................................... 3,000 120 SPECIAL FEDERAL AVIATION REGULATION NO.
4 GHz–6 GHz.................................... 3,000 160
13
6 GHz–8 GHz.................................... 400 170
8 GHz–12 GHz.................................. 1,230 230 SPECIAL FEDERAL AVIATION REGULATION NO.
12 GHz–18 GHz................................ 730 190 109
18 GHz–40 GHz................................ 600 150
Subpart A—General
In this table, the higher field strength applies at the fre-
quency band edges.
Sec.
(c) Equipment HIRF Test Level 1. (1) From 10 25.1 Applicability.
kilohertz (kHz) to 400 megahertz (MHz), use 25.2 Special retroactive requirements.
conducted susceptibility tests with contin- 25.3 Special provisions for ETOPS type de-
uous wave (CW) and 1 kHz square wave mod- sign approvals.
ulation with 90 percent depth or greater. The 25.5 Incorporations by reference.
conducted susceptibility current must start
at a minimum of 0.6 milliamperes (mA) at 10 Subpart B—Flight
kHz, increasing 20 decibels (dB) per fre-
quency decade to a minimum of 30 mA at 500 GENERAL
kHz. 25.21 Proof of compliance.
(2) From 500 kHz to 40 MHz, the conducted 25.23 Load distribution limits.
susceptibility current must be at least 30 25.25 Weight limits.
mA. 25.27 Center of gravity limits.
(3) From 40 MHz to 400 MHz, use conducted 25.29 Empty weight and corresponding cen-
susceptibility tests, starting at a minimum ter of gravity.
of 30 mA at 40 MHz, decreasing 20 dB per fre- 25.31 Removable ballast.
quency decade to a minimum of 3 mA at 400 25.33 Propeller speed and pitch limits.
MHz.
(4) From 100 MHz to 400 MHz, use radiated PERFORMANCE
R susceptibility tests at a minimum of 20 volts 25.101 General.
F
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OD depth or greater. 25.107 Takeoff speeds.
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Pt. 25 14 CFR Ch. I (1–1–11 Edition)
25.109 Accelerate-stop distance. 25.349 Rolling conditions.
25.111 Takeoff path. 25.351 Yaw maneuver conditions.
25.113 Takeoff distance and takeoff run.
25.115 Takeoff flight path. SUPPLEMENTARYCONDITIONS
25.117 Climb: general.
25.361 Engine torque.
25.119 Landing climb: All-engines-operating.
25.363 Side load on engine and auxiliary
25.121 Climb: One-engine-inoperative.
power unit mounts.
25.123 En route flight paths.
25.125 Landing. 25.365 Pressurized compartment loads.
25.367 Unsymmetrical loads due to engine
CONTROLLABILITYANDMANEUVERABILITY failure.
25.371 Gyroscopic loads.
25.143 General.
25.373 Speed control devices.
25.145 Longitudinal control.
25.147 Directional and lateral control. CONTROLSURFACEANDSYSTEMLOADS
25.149 Minimum control speed.
25.391 Control surface loads: General.
TRIM 25.393 Loads parallel to hinge line.
25.161 Trim. 25.395 Control system.
25.397 Control system loads.
STABILITY 25.399 Dual control system.
25.405 Secondary control system.
25.171 General.
25.173 Static longitudinal stability. 25.407 Trim tab effects.
25.175 Demonstration of static longitudinal 25.409 Tabs.
stability. 25.415 Ground gust conditions.
25.177 Static lateral-directional stability. 25.427 Unsymmetrical loads.
25.181 Dynamic stability. 25.445 Auxilliary aerodynamic surfaces.
25.457 Wing flaps.
STALLS 25.459 Special devices.
25.201 Stall demonstration.
GROUNDLOADS
25.203 Stall characteristics.
25.207 Stall warning. 25.471 General.
25.473 Landing load conditions and assump-
GROUNDANDWATERHANDLING tions.
CHARACTERISTICS 25.477 Landing gear arrangement.
25.231 Longitudinal stability and control. 25.479 Level landing conditions.
25.233 Directional stability and control. 25.481 Tail-down landing conditions.
25.235 Taxiing condition. 25.483 One-gear landing conditions.
25.237 Wind velocities. 25.485 Side load conditions.
25.239 Spray characteristics, control, and 25.487 Rebound landing condition.
stability on water. 25.489 Ground handling conditions.
25.491 Taxi, takeoff and landing roll.
MISCELLANEOUSFLIGHTREQUIREMENTS 25.493 Braked roll conditions.
25.251 Vibration and buffeting. 25.495 Turning.
25.253 High-speed characteristics. 25.497 Tail-wheel yawing.
25.255 Out-of-trim characteristics. 25.499 Nose-wheel yaw and steering.
25.503 Pivoting.
Subpart C—Structure 25.507 Reversed braking.
25.509 Towing loads.
GENERAL 25.511 Ground load: unsymmetrical loads on
25.301 Loads. multiple-wheel units.
25.303 Factor of safety. 25.519 Jacking and tie-down provisions.
25.305 Strength and deformation.
25.307 Proof of structure. WATERLOADS
25.521 General.
FLIGHTLOADS 25.523 Design weights and center of gravity
25.321 General. positions.
25.525 Application of loads.
FLIGHTMANEUVERANDGUSTCONDITIONS 25.527 Hull and main float load factors.
25.331 Symmetric maneuvering conditions. 25.529 Hull and main float landing condi-
25.333 Flight maneuvering envelope. tions.
25.335 Design airspeeds. 25.531 Hull and main float takeoff condi-
R 25.337 Limit maneuvering load factors. tion.
F
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OD 25.345 High lift devices. 25.537 Seawing loads.
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Federal Aviation Administration, DOT Pt. 25
EMERGENCYLANDINGCONDITIONS 25.753 Main float design.
25.755 Hulls.
25.561 General.
25.562 Emergency landing dynamic condi- PERSONNELANDCARGOACCOMMODATIONS
tions.
25.563 Structural ditching provisions. 25.771 Pilot compartment.
25.772 Pilot compartment doors.
FATIGUEEVALUATION 25.773 Pilot compartment view.
25.571 Damage—tolerance and fatigue eval- 25.775 Windshields and windows.
uation of structure. 25.777 Cockpit controls.
25.779 Motion and effect of cockpit controls.
LIGHTNINGPROTECTION 25.781 Cockpit control knob shape.
25.581 Lightning protection. 25.783 Fuselage doors.
25.785 Seats, berths, safety belts, and har-
Subpart D—Design and Construction nesses.
25.787 Stowage compartments.
GENERAL 25.789 Retention of items of mass in pas-
senger and crew compartments and gal-
25.601 General.
leys.
25.603 Materials.
25.605 Fabrication methods. 25.791 Passenger information signs and plac-
25.607 Fasteners. ards.
25.609 Protection of structure. 25.793 Floor surfaces.
25.611 Accessibility provisions. 25.795 Security considerations.
25.613 Material strength properties and ma-
terial design values. EMERGENCYPROVISIONS
25.619 Special factors. 25.801 Ditching.
25.621 Casting factors. 25.803 Emergency evacuation.
25.623 Bearing factors. 25.807 Emergency exits.
25.625 Fitting factors. 25.809 Emergency exit arrangement.
25.629 Aeroelastic stability requirements. 25.810 Emergency egress assist means and
25.631 Bird strike damage. escape routes.
25.811 Emergency exit marking.
CONTROLSURFACES
25.812 Emergency lighting.
25.651 Proof of strength. 25.813 Emergency exit access.
25.655 Installation. 25.815 Width of aisle.
25.657 Hinges. 25.817 Maximum number of seats abreast.
25.819 Lower deck service compartments
CONTROLSYSTEMS
(including galleys).
25.671 General. 25.820 Lavatory doors.
25.672 Stability augmentation and auto-
matic and power-operated systems. VENTILATIONANDHEATING
25.675 Stops. 25.831 Ventilation.
25.677 Trim systems.
25.832 Cabin ozone concentration.
25.679 Control system gust locks.
25.833 Combustion heating systems.
25.681 Limit load static tests.
25.683 Operation tests. PRESSURIZATION
25.685 Control system details.
25.689 Cable systems. 25.841 Pressurized cabins.
25.693 Joints. 25.843 Tests for pressurized cabins.
25.697 Lift and drag devices, controls.
25.699 Lift and drag device indicator. FIREPROTECTION
25.701 Flap and slat interconnection. 25.851 Fire extinguishers.
25.703 Takeoff warning system. 25.853 Compartment interiors.
25.854 Lavatory fire protection.
LANDINGGEAR
25.855 Cargo or baggage compartments.
25.721 General. 25.856 Thermal/Acoustic insulation mate-
25.723 Shock absorption tests. rials.
25.725–25.727 [Reserved] 25.857 Cargo compartment classification.
25.729 Retracting mechanism. 25.858 Cargo or baggage compartment
25.731 Wheels. smoke or fire detection systems.
25.733 Tires. 25.859 Combustion heater fire protection.
25.735 Brakes and braking systems. 25.863 Flammable fluid fire protection.
R 25.737 Skis. 25.865 Fire protection of flight controls, en-
F
with C FLOATSANDHULLS 25.86g7ineF imreo uprnottse, catniodn o: tohtehre rf lciogmhtp osntreuncttsu. re.
OD 25.751 Main float buoyancy. 25.869 Fire protection: systems.
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Pt. 25 14 CFR Ch. I (1–1–11 Edition)
MISCELLANEOUS 25.1019 Oil strainer or filter.
25.1021 Oil system drains.
25.871 Leveling means.
25.1023 Oil radiators.
25.875 Reinforcement near propellers.
25.1025 Oil valves.
25.899 Electrical bonding and protection
against static electricity. 25.1027 Propeller feathering system.
Subpart E—Powerplant COOLING
25.1041 General.
GENERAL 25.1043 Cooling tests.
25.901 Installation. 25.1045 Cooling test procedures.
25.903 Engines.
25.904 Automatic takeoff thrust control sys- INDUCTIONSYSTEM
tem (ATTCS). 25.1091 Air induction.
25.905 Propellers. 25.1093 Induction system icing protection.
25.907 Propeller vibration and fatigue. 25.1101 Carburetor air preheater design.
25.925 Propeller clearance. 25.1103 Induction system ducts and air duct
25.929 Propeller deicing. systems.
25.933 Reversing systems. 25.1105 Induction system screens.
25.934 Turbojet engine thrust reverser sys- 25.1107 Inter-coolers and after-coolers.
tem tests.
25.937 Turbopropeller-drag limiting sys- EXHAUSTSYSTEM
tems.
25.1121 General.
25.939 Turbine engine operating characteris-
25.1123 Exhaust piping.
tics.
25.1125 Exhaust heat exchangers.
25.941 Inlet, engine, and exhaust compat-
25.1127 Exhaust driven turbo-superchargers.
ibility.
25.943 Negative acceleration.
POWERPLANTCONTROLSANDACCESSORIES
25.945 Thrust or power augmentation sys-
tem. 25.1141 Powerplant controls: general.
25.1142 Auxiliary power unit controls.
FUELSYSTEM 25.1143 Engine controls.
25.951 General. 25.1145 Ignition switches.
25.952 Fuel system analysis and test. 25.1147 Mixture controls.
25.953 Fuel system independence. 25.1149 Propeller speed and pitch controls.
25.954 Fuel system lightning protection. 25.1153 Propeller feathering controls.
25.955 Fuel flow. 25.1155 Reverse thrust and propeller pitch
25.957 Flow between interconnected tanks. settings below the flight regime.
25.959 Unusable fuel supply. 25.1157 Carburetor air temperature controls.
25.961 Fuel system hot weather operation. 25.1159 Supercharger controls.
25.963 Fuel tanks: general. 25.1161 Fuel jettisoning system controls.
25.965 Fuel tank tests. 25.1163 Powerplant accessories.
25.967 Fuel tank installations. 25.1165 Engine ignition systems.
25.969 Fuel tank expansion space. 25.1167 Accessory gearboxes.
25.971 Fuel tank sump.
25.973 Fuel tank filler connection. POWERPLANTFIREPROTECTION
25.975 Fuel tank vents and carburetor vapor 25.1181 Designated fire zones; regions in-
vents. cluded.
25.977 Fuel tank outlet. 25.1182 Nacelle areas behind firewalls, and
25.979 Pressure fueling system. engine pod attaching structures con-
25.981 Fuel tank ignition prevention. taining flammable fluid lines.
25.1183 Flammable fluid-carrying compo-
FUELSYSTEMCOMPONENTS
nents.
25.991 Fuel pumps. 25.1185 Flammable fluids.
25.993 Fuel system lines and fittings. 25.1187 Drainage and ventilation of fire
25.994 Fuel system components. zones.
25.995 Fuel valves. 25.1189 Shutoff means.
25.997 Fuel strainer or filter. 25.1191 Firewalls.
25.999 Fuel system drains. 25.1192 Engine accessory section diaphragm.
25.1001 Fuel jettisoning system. 25.1193 Cowling and nacelle skin.
25.1195 Fire extinguishing systems.
OILSYSTEM 25.1197 Fire extinguishing agents.
R 25.1011 General. 25.1199 Extinguishing agent containers.
F
with C 2255..11001135 OOiill ttaannkks t.e sts. 2255..11220013 FFiirree dexetteincgtouri sshyisntge msy.s tem materials.
OD 25.1017 Oil lines and fittings. 25.1207 Compliance.
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Federal Aviation Administration, DOT Pt. 25
Subpart F—Equipment 25.1419 Ice protection.
25.1421 Megaphones.
GENERAL 25.1423 Public address system.
25.1301 Function and installation. MISCELLANEOUSEQUIPMENT
25.1303 Flight and navigation instruments.
25.1305 Powerplant instruments. 25.1431 Electronic equipment.
25.1307 Miscellaneous equipment. 25.1433 Vacuum systems.
25.1309 Equipment, systems, and installa- 25.1435 Hydraulic systems.
tions. 25.1438 Pressurization and pneumatic sys-
25.1310 Power source capacity and distribu- tems.
tion. 25.1439 Protective breathing equipment.
25.1316 System lightning protection. 25.1441 Oxygen equipment and supply.
25.1317 High-intensity Radiated Fields 25.1443 Minimum mass flow of supplemental
(HIRF) Protection. oxygen.
25.1445 Equipment standards for the oxygen
INSTRUMENTS: INSTALLATION distributing system.
25.1447 Equipment standards for oxygen dis-
25.1321 Arrangement and visibility.
pensing units.
25.1322 Warning, caution, and advisory
25.1449 Means for determining use of oxy-
lights.
gen.
25.1323 Airspeed indicating system.
25.1450 Chemical oxygen generators.
25.1325 Static pressure systems.
25.1453 Protection of oxygen equipment
25.1326 Pitot heat indication systems.
from rupture.
25.1327 Magnetic direction indicator.
25.1455 Draining of fluids subject to freez-
25.1329 Flight guidance system.
ing.
25.1331 Instruments using a power supply.
25.1457 Cockpit voice recorders.
25.1333 Instrument systems.
25.1459 Flight data recorders.
25.1337 Powerplant instruments.
25.1461 Equipment containing high energy
ELECTRICALSYSTEMSANDEQUIPMENT rotors.
25.1351 General. Subpart G—Operating Limitations and
25.1353 Electrical equipment and installa- Information
tions.
25.1355 Distribution system. 25.1501 General.
25.1357 Circuit protective devices.
25.1360 Precautions against injury. OPERATINGLIMITATIONS
25.1362 Electrical supplies for emergency 25.1503 Airspeed limitations: general.
conditions. 25.1505 Maximum operating limit speed.
25.1363 Electrical system tests. 25.1507 Maneuvering speed.
25.1365 Electrical appliances, motors, and 25.1511 Flap extended speed.
transformers. 25.1513 Minimum control speed.
25.1515 Landing gear speeds.
LIGHTS 25.1516 Other speed limitations.
25.1381 Instrument lights. 25.1517 Rough air speed, V .
RA
25.1383 Landing lights. 25.1519 Weight, center of gravity, and
25.1385 Position light system installation. weight distribution.
25.1387 Position light system dihedral an- 25.1521 Powerplant limitations.
gles. 25.1522 Auxiliary power unit limitations.
25.1389 Position light distribution and in- 25.1523 Minimum flight crew.
tensities. 25.1525 Kinds of operation.
25.1391 Minimum intensities in the hori- 25.1527 Ambient air temperature and oper-
zontal plane of forward and rear position ating altitude.
lights. 25.1529 Instructions for Continued Air-
25.1393 Minimum intensities in any vertical worthiness.
plane of forward and rear position lights. 25.1531 Maneuvering flight load factors.
25.1395 Maximum intensities in overlapping 25.1533 Additional operating limitations.
beams of forward and rear position 25.1535 ETOPS approval.
lights.
25.1397 Color specifications. MARKINGSANDPLACARDS
25.1399 Riding light. 25.1541 General.
25.1401 Anticollision light system. 25.1543 Instrument markings: general.
25.1403 Wing icing detection lights. 25.1545 Airspeed limitation information.
R 25.1547 Magnetic direction indicator.
with CF 25.1411 GenerSaAlF. ETYEQUIPMENT 25.15i4n9strPuomweenrtpsl.a nt and auxiliary power unit
OD 25.1415 Ditching equipment. 25.1551 Oil quantity indication.
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Pt. 25, SFAR No. 13 14 CFR Ch. I (1–1–11 Edition)
25.1553 Fuel quantity indicator. SOURCE: Docket No. 5066, 29 FR 18291, Dec.
25.1555 Control markings. 24, 1964, unless otherwise noted.
25.1557 Miscellaneous markings and plac-
ards. SPECIALFEDERALAVIATIONREGULATION
25.1561 Safety equipment. NO. 13
25.1563 Airspeed placard.
1. Applicability. Contrary provisions of the
AIRPLANEFLIGHTMANUAL Civil Air Regulations regarding certification
25.1581 General. notwithstanding,1 this regulation shall pro-
25.1583 Operating limitations. vide the basis for approval by the Adminis-
25.1585 Operating procedures. trator of modifications of individual Douglas
25.1587 Performance information. DC–3 and Lockheed L–18 airplanes subse-
quent to the effective date of this regulation.
Subpart H—Electrical Wiring 2. General modifications. Except as modified
Interconnection Systems (EWIS) in sections 3 and 4 of this regulation, an ap-
plicant for approval of modifications to a
25.1701 Definition. DC–3 or L–18 airplane which result in
25.1703 Function and installation: EWIS. changes in design or in changes to approved
25.1705 Systems and functions: EWIS. limitations shall show that the modifica-
25.1707 System separation: EWIS. tions were accomplished in accordance with
25.1709 System safety: EWIS. the rules of either Part 4a or Part 4b in ef-
25.1711 Component identification: EWIS. fect on September 1, 1953, which are applica-
25.1713 Fire protection: EWIS. ble to the modification being made: Provided,
25.1715 Electrical bonding and protection That an applicant may elect to accomplish a
against static electricity: EWIS. modification in accordance with the rules of
25.1717 Circuit protective devices: EWIS. Part 4b in effect on the date of application
25.1719 Accessibility provisions: EWIS. for the modification in lieu of Part 4a or
25.1721 Protection of EWIS. Part 4b as in effect on September 1, 1953: And
25.1723 Flammable fluid fire protection: provided further, That each specific modifica-
EWIS. tion must be accomplished in accordance
25.1725 Powerplants: EWIS. with all of the provisions contained in the
25.1727 Flammable fluid shutoff means: elected rules relating to the particular modi-
EWIS. fication.
25.1729 Instructions for Continued Air- 3. Specific conditions for approval. An appli-
worthiness: EWIS. cant for any approval of the following spe-
25.1731 Powerplant and APU fire detector cific changes shall comply with section 2 of
system: EWIS. this regulation as modified by the applicable
25.1733 Fire detector systems, general: provisions of this section.
EWIS. (a) Increase in take-off power limitation—
APPENDIXA TOPART25 1,200 to 1,350 horsepower. The engine take-off
APPENDIXB TOPART25 power limitation for the airplane may be in-
APPENDIXC TOPART25 creased to more than 1,200 horsepower but
APPENDIXD TOPART25 not to more than 1,350 horsepower per engine
APPENDIXE TOPART25 if the increase in power does not adversely
APPENDIXF TOPART25 affect the flight characteristics of the air-
APPENDIX G TO PART 25—CONTINUOUS GUST plane.
DESIGNCRITERIA (b) Increase in take-off power limitation to
APPENDIX H TO PART 25—INSTRUCTIONS FOR more than 1,350 horsepower. The engine take-
CONTINUEDAIRWORTHINESS off power limitation for the airplane may be
APPENDIX I TO PART 25—INSTALLATION OF AN increased to more than 1,350 horsepower per
AUTOMATIC TAKEOFF THRUST CONTROL engine if compliance is shown with the flight
SYSTEM(ATTCS) characteristics and ground handling require-
APPENDIX J TO PART 25—EMERGENCY EVACU- ments of Part 4b.
ATION (c) Installation of engines of not more than
APPENDIX K TO PART 25—EXTENDED OPER- 1,830 cubic inches displacement and not having
ATIONS(ETOPS) a certificated take-off rating of more than 1,350
APPENDIX L TO PART 25—HIRF ENVIRON- horsepower. Engines of not more than 1,830
MENTS AND EQUIPMENT HIRF TEST LEV- cubic inches displacement and not having a
ELS certificated take-off rating of more than
APPENDIXM TOPART25—FUELTANKSYSTEM 1,350 horsepower which necessitate a major
FLAMMABILITYREDUCTIONMEANS
APPENDIX N TO PART 25—FUEL TANK FLAM- 1It is not intended to waive compliance
R MABILITY EXPOSURE AND with such airworthiness requirements as are
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OD 44702 and 44704. ation.
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Federal Aviation Administration, DOT Pt. 25, SFAR No. 109
modification of redesign of the engine instal- section. The airplane flight manual shall
lation may be installed, if the engine fire contain the applicable performance informa-
prevention and fire protection are equivalent tion prescribed in that part of the regula-
to that on the prior engine installation. tions under which the new certificated
(d) Installation of engines of more than 1,830 weights were established and such additional
cubic inches displacement or having certificated information as may be necessary to enable
take-off rating of more than 1,350 horsepower. the application of the take-off, en route, and
Engines of more than 1,830 cubic inches dis- landing limitations prescribed for transport
placement or having certificated take-off category airplanes in the operating parts of
rating of more than 1,350 horsepower may be the Civil Air Regulations.
installed if compliance is shown with the en- (d) Performance operating limitations. Each
gine installation requirements of Part 4b: airplane for which new maximum certifi-
Provided, That where literal compliance with cated weights are established in accordance
the engine installation requirements of Part with paragraphs (a) or (b) of this section
4b is extremely difficult to accomplish and shall be considered a transport category air-
would not contribute materially to the ob- plane for the purpose of complying with the
jective sought, and the Administrator finds performance operating limitations applica-
that the experience with the DC–3 or L–18 ble to the operations in which it is utilized.
airplanes justifies it, he is authorized to ac- 5. Reference. Unless otherwise provided, all
cept such measures of compliance as he finds references in this regulation to Part 4a and
will effectively accomplish the basic objec- Part 4b are those parts of the Civil Air Regu-
tive. lations in effect on September 1, 1953.
4. Establishment of new maximum certificated This regulation supersedes Special Civil
weights. An applicant for approval of new Air Regulation SR–398 and shall remain ef-
maximum certificated weights shall apply fective until superseded or rescinded by the
for an amendment of the airworthiness cer- Board.
tificate of the airplane and shall show that
the weights sought have been established, [19 FR 5039, Aug. 11, 1954. Redesignated at 29
and the appropriate manual material ob- FR 19099, Dec. 30, 1964]
tained, as provided in this section.
NOTE: Transport category performance re- SPECIALFEDERALAVIATIONREGULATION
quirements result in the establishment of NO. 109
maximum certificated weights for various
altitudes. 1. Applicability. Contrary provisions of 14
(a) Weights–25,200 to 26,900 for the DC–3 and CFR parts 21, 25, and 119 of this chapter not-
18,500 to 19,500 for the L–18. New maximum withstanding, an applicant is entitled to an
certificated weights of more than 25,200 but amended type certificate or supplemental
not more than 26,900 pounds for DC–3 and type certificate in the transport category, if
more than 18,500 but not more than 19,500 the applicant complies with all applicable
pounds for L–18 airplanes may be established provisions of this SFAR.
in accordance with the transport category
Operations
performance requirements of either Part 4a
or Part 4b, if the airplane at the new max- 2. General.
imum weights can meet the structural re- (a) The passenger capacity may not exceed
quirements of the elected part. 60. If more than 60 passenger seats are in-
(b) Weights of more than 26,900 for the DC–3 stalled, then:
and 19,500 for the L–18. New maximum certifi- (1) If the extra seats are not suitable for
cated weights of more than 26,900 pounds for occupancy during taxi, takeoff and landing,
DC–3 and 19,500 pounds for L–18 airplanes each extra seat must be clearly marked (e.g.,
shall be established in accordance with the a placard on the top of an armrest, or a
structural performance, flight characteris- placard sewn into the top of the back cush-
tics, and ground handling requirements of ion) that the seat is not to be occupied dur-
Part 4b: Provided, That where literal compli- ing taxi, takeoff and landing.
ance with the structural requirements of (2) If the extra seats are suitable for occu-
Part 4b is extremely difficult to accomplish pancy during taxi, takeoff and landing (i.e.,
and would not contribute materially to the meet all the strength and passenger injury
objective sought, and the Administrator criteria in part 25), then a note must be in-
finds that the experience with the DC–3 or L– cluded in the Limitations Section of the Air-
18 airplanes justifies it, he is authorized to plane Flight Manual that there are extra
accept such measures of compliance as he seats installed but that the number of pas-
finds will effectively accomplish the basic sengers on the airplane must not exceed 60.
objective. Additionally, there must be a placard in-
(c) Airplane flight manual-performance oper- stalled adjacent to each door that can be
R ating information. An approved airplane flight used as a passenger boarding door that states
F
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OD certificated weights established under this sengers entering the airplane.
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Pt. 25, SFAR No. 109 14 CFR Ch. I (1–1–11 Edition)
(b) For airplanes outfitted with interior (b) Injury criteria for multiple occupancy
doors under paragraph 10 of this SFAR, the side-facing seats. The following require-
airplane flight manual (AFM) must include ments are only applicable to airplanes that
an appropriate limitation that the airplane are subject to §25.562.
must be staffed with at least the following (1) Existing Criteria. All injury protection
number of flight attendants who meet the re- criteria of §25.562(c)(1) through (c)(6) apply to
quirements of 14 CFR 91.533(b): the occupants of side-facing seating. The
(1) The number of flight attendants re- Head Injury Criterion (HIC) assessments are
quired by §91.533(a)(1) and (2) of this chapter, only required for head contact with the seat
and and/or adjacent structures.
(2) At least one flight attendant if the air- (2) Body-to-Body Contact. Contact between
plane model was originally certified for 75 the head, pelvis, torso or shoulder area of
passengers or more. one Anthropomorphic Test Dummy (ATD)
(c) The AFM must include appropriate lim- with the head, pelvis, torso or shoulder area
itation(s) to require a preflight passenger of the ATD in the adjacent seat is not al-
briefing describing the appropriate functions lowed during the tests conducted in accord-
to be performed by the passengers and the ance with §25.562(b)(1) and (b)(2). Contact
relevant features of the airplane to ensure
during rebound is allowed.
the safety of the passengers and crew.
(3) Thoracic Trauma. If the torso of an ATD
(d) The airplane may not be offered for
at the forward-most seat place impacts the
common carriage or operated for hire. The
seat and/or adjacent structure during test-
operating limitations section of the AFM
ing, compliance with the Thoracic Trauma
must be revised to prohibit any operations
Index (TTI) injury criterion must be substan-
involving the carriage of persons or property
tiated by dynamic test or by rational anal-
for compensation or hire. The operators may
ysis based on previous test(s) of a similar
receive remuneration to the extent con-
seat installation. TTI data must be acquired
sistent with parts 125 and 91, subpart F, of
with a Side Impact Dummy (SID), as defined
this chapter.
by 49 CFR part 572, subpart F, or an equiva-
(e) A placard stating that ‘‘Operations in-
lent ATD or a more appropriate ATD and
volving the carriage of persons or property
for compensation or hire are prohibited,’’ must be processed as defined in Federal
must be located in the area of the Airworthi- Motor Vehicle Safety Standards (FMVSS)
ness Certificate holder at the entrance to the part 571.214, section S6.13.5 (49 CFR 571.214).
flightdeck. The TTI must be less than 85, as defined in
(f) For passenger capacities of 45 to 60 pas- 49 CFR part 572, subpart F. Torso contact
sengers, analysis must be submitted that during rebound is acceptable and need not be
demonstrates that the airplane can be evacu- measured.
ated in less than 90 seconds under the condi- (4) Pelvis. If the pelvis of an ATD at any
tions specified in §25.803 and appendix J to seat place impacts seat and/or adjacent
part 25. structure during testing, pelvic lateral accel-
(g) In order for any airplane certified under eration injury criteria must be substantiated
this SFAR to be placed in part 135 or part 121 by dynamic test or by rational analysis
operations, the airplane must be brought based on previous test(s) of a similar seat in-
back into full compliance with the applica- stallation. Pelvic lateral acceleration may
ble operational part. not exceed 130g. Pelvic acceleration data
must be processed as defined in FMVSS part
Equipment and Design 571.214, section S6.13.5 (49 CFR 571.214).
3. General. Unless otherwise noted, compli- (5) Body-to-Wall/Furnishing Contact. If the
ance is required with the applicable certifi- seat is installed aft of a structure—such as
cation basis for the airplane. Some provi- an interior wall or furnishing that may con-
sions of this SFAR impose alternative re- tact the pelvis, upper arm, chest, or head of
quirements to certain airworthiness stand- an occupant seated next to the structure—
ards that do not apply to airplanes certifi- the structure or a conservative representa-
cated to earlier standards. Those airplanes tion of the structure and its stiffness must
with an earlier certification basis are not re- be included in the tests. It is recommended,
quired to comply with those alternative re- but not required, that the contact surface of
quirements. the actual structure be covered with at least
4. Occupant Protection. two inches of energy absorbing protective
(a) Firm Handhold. In lieu of the require- padding (foam or equivalent) such as
ments of §25.785(j), there must be means pro- Ensolite.
vided to enable persons to steady themselves (6) Shoulder Strap Loads. Where upper torso
in moderately rough air while occupying straps (shoulder straps) are used for sofa oc-
aisles that are along the cabin sidewall, or cupants, the tension loads in individual
R where practicable, bordered by seats (seat straps may not exceed 1,750 pounds. If dual
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Federal Aviation Administration, DOT Pt. 25, SFAR No. 109
(7) Occupant Retention. All side-facing seats side of the fuselage, no passenger emergency
require end closures or other means to pre- exit may be more than 60 feet from any adja-
vent the ATD’s pelvis from translating be- cent passenger emergency exit on the same
yond the end of the seat at any time during side of the same deck of the fuselage, as
testing. measured parallel to the airplane’s longitu-
(8) Test Parameters. dinal axis between the nearest exit edges,
(i) All seat positions need to be occupied by unless the following conditions are met:
ATDs for the longitudinal tests. (a) Each passenger seat must be located
(ii) A minimum of one longitudinal test, within 30 feet from the nearest exit on each
conducted in accordance with the conditions side of the fuselage, as measured parallel to
specified in §25.562(b)(2), is required to assess the airplane’s longitudinal axis, between the
the injury criteria as follows. Note that if a nearest exit edge and the front of the seat
seat is installed aft of structure (such as an bottom cushion.
interior wall or furnishing) that does not (b) The number of passenger seats located
have a homogeneous surface, an additional between two adjacent pairs of emergency
test or tests may be required to demonstrate exits (commonly referred to as a passenger
that the injury criteria are met for the area zone) or between a pair of exits and a bulk-
which an occupant could contact. For exam- head or a compartment door (commonly re-
ple, different yaw angles could result in dif- ferred to as a ‘‘dead-end zone’’), may not ex-
ferent injury considerations and may require ceed the following:
separate tests to evaluate. (1) For zones between two pairs of exits, 50
(A) For configurations without structure percent of the combined rated capacity of
(such as a wall or bulkhead) installed di- the two pairs of emergency exits.
rectly forward of the forward seat place, Hy- (2) For zones between one pair of exits and
brid II ATDs or equivalent must be in all a bulkhead, 40 percent of the rated capacity
seat places. of the pair of emergency exits.
(B) For configurations with structure (such (c) The total number of passenger seats in
as a wall or bulkhead) installed directly for- the airplane may not exceed 33 percent of the
ward of the forward seat place, a side impact maximum seating capacity for the airplane
dummy or equivalent ATD or more appro- model using the exit ratings listed in
priate ATD must be in the forward seat place §25.807(g) for the original certified exits or
and a Hybrid II ATD or equivalent must be the maximum allowable after modification
in all other seat places. when exits are deactivated, whichever is less.
(C) The test may be conducted with or (d) A distance of more than 60 feet between
without deformed floor. adjacent passenger emergency exits on the
(D) The test must be conducted with either same side of the same deck of the fuselage,
no yaw or 10 degrees yaw for evaluating oc- as measured parallel to the airplane’s longi-
cupant injury. Deviating from the no yaw tudinal axis between the nearest exit edges,
condition may not result in the critical area is allowed only once on each side of the fuse-
of contact not being evaluated. The upper lage.
torso restraint straps, where installed, must 8. Emergency Exit Signs. In lieu of the re-
remain on the occupant’s shoulder during quirements of §25.811(d)(1) and (2) a single
the impact condition of §25.562(b)(2). sign at each exit may be installed provided:
(c) For the vertical test, conducted in ac- (a) The sign can be read from the aisle
cordance with the conditions specified in while directly facing the exit, and
§25.562(b)(1), Hybrid II ATDs or equivalent (b) The sign can be read from the aisle ad-
must be used in all seat positions. jacent to the passenger seat that is farthest
5. Direct View. In lieu of the requirements from the exit and that does not have an in-
of §25.785(h)(2), to the extent practical with- tervening bulkhead/divider or exit.
out compromising proximity to a required 9. Emergency Lighting.
floor level emergency exit, the majority of (a) Exit Signs. In lieu of the requirements of
installed flight attendant seats must be lo- §25.812(b)(1), for airplanes that have a pas-
cated to face the cabin area for which the senger seating configuration, excluding pilot
flight attendant is responsible. seats, of 19 seats or less, the emergency exit
6. Passenger Information Signs. Compliance signs required by §25.811(d)(1), (2), and (3)
with §25.791 is required except that for must have red letters at least 1-inch high on
§25.791(a), when smoking is to be prohibited, a white background at least 2 inches high.
notification to the passengers may be pro- These signs may be internally electrically il-
vided by a single placard so stating, to be luminated, or self illuminated by other than
conspicuously located inside the passenger electrical means, with an initial brightness
compartment, easily visible to all persons of at least 160 microlamberts. The color may
entering the cabin in the immediate vicinity be reversed in the case of a sign that is self-
of each passenger entry door. illuminated by other than electrical means.
R 7. Distance Between Exits. For an airplane (b) Floor Proximity Escape Path Marking. In
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Pt. 25, SFAR No. 109 14 CFR Ch. I (1–1–11 Edition)
exiting the compartment, the following are ally, instructions must be provided at each
applicable: passenger seat for restoring the aisle width
(1) After a passenger leaves any passenger required by §25.815. Procedures must be es-
seat in the compartment, he/she must be tablished and documented in the AFM to en-
able to exit the compartment to the main sure that the required aisle widths are pro-
cabin aisle using only markings and visual vided during taxi, takeoff, and landing.
features not more that 4 feet above the cabin 12. Materials for Compartment Interiors.
floor, and Compliance is required with the applicable
(2) Proceed to the exits using the marking provisions of §25.853, except that compliance
system necessary to accomplish the actions with appendix F, parts IV and V, to part 25,
in §25.812(e)(1) and (e)(2). need not be demonstrated if it can be shown
(c) Transverse Separation of the Fuselage. In by test or a combination of test and analysis
the event of a transverse separation of the that the maximum time for evacuation of all
fuselage, compliance must be shown with occupants does not exceed 45 seconds under
§25.812(l) except as follows: the conditions specified in appendix J to part
(1) For each airplane type originally type 25.
certificated with a maximum passenger seat- 13. Fire Detection. For airplanes with a type
ing capacity of 9 or less, not more than 50 certificated passenger capacity of 20 or more,
percent of all electrically illuminated emer- there must be means that meet the require-
gency lights required by §25.812 may be ren- ments of §25.858(a) through (d) to signal the
dered inoperative in addition to the lights flightcrew in the event of a fire in any iso-
that are directly damaged by the separation. lated room not occupiable for taxi, takeoff
(2) For each airplane type originally type and landing, which can be closed off from the
certificated with a maximum passenger seat- rest of the cabin by a door. The indication
ing capacity of 10 to 19, not more than 33 per- must identify the compartment where the
cent of all electrically illuminated emer- fire is located. This does not apply to lava-
gency lights required by §25.812 may be ren- tories, which continue to be governed by
dered inoperative in addition to the lights §25.854.
that are directly damaged by the separation. 14. Cooktops. Each cooktop must be de-
10. Interior doors. In lieu of the require- signed and installed to minimize any poten-
ments of §25.813(e), interior doors may be in- tial threat to the airplane, passengers, and
stalled between passenger seats and exits, crew. Compliance with this requirement
provided the following requirements are met. must be found in accordance with the fol-
(a) Each door between any passenger seat, lowing criteria:
occupiable for taxi, takeoff, and landing, and (a) Means, such as conspicuous burner-on
any emergency exit must have a means to indicators, physical barriers, or handholds,
signal to the flightcrew, at the flightdeck, must be installed to minimize the potential
that the door is in the open position for taxi, for inadvertent personnel contact with hot
takeoff and landing. surfaces of both the cooktop and cookware.
(b) Appropriate procedures/limitations Conditions of turbulence must be considered.
must be established to ensure that any such (b) Sufficient design means must be in-
door is in the open configuration for takeoff cluded to restrain cookware while in place
and landing. on the cooktop, as well as representative
(c) Each door between any passenger seat contents, e.g., soup, sauces, etc., from the ef-
and any exit must have dual means to retain fects of flight loads and turbulence. Re-
it in the open position, each of which is capa- straints must be provided to preclude haz-
ble of reacting the inertia loads specified in ardous movement of cookware and contents.
§25.561. These restraints must accommodate any
(d) Doors installed across a longitudinal cookware that is identified for use with the
aisle must translate laterally to open and cooktop. Restraints must be designed to be
close, e.g., pocket doors. easily utilized and effective in service. The
(e) Each door between any passenger seat cookware restraint system should also be de-
and any exit must be frangible in either di- signed so that it will not be easily disabled,
rection. thus rendering it unusable. Placarding must
(f) Each door between any passenger seat be installed which prohibits the use of
and any exit must be operable from either cookware that cannot be accommodated by
side, and if a locking mechanism is installed, the restraint system.
it must be capable of being unlocked from ei- (c) Placarding must be installed which pro-
ther side without the use of special tools. hibits the use of cooktops (i.e., power on any
11. Width of Aisle. Compliance is required burner) during taxi, takeoff, and landing.
with §25.815, except that aisle width may be (d) Means must be provided to address the
reduced to 0 inches between passenger seats possibility of a fire occurring on or in the
during in-flight operations only, provided immediate vicinity of the cooktop. Two ac-
R that the applicant demonstrates that all ceptable means of complying with this re-
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