Pt. 25 14 CFR Ch. I (1–1–13 Edition) TABLE I.—HIRF ENVIRONMENT I (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 2 GHz–6 GHz .................................... 3,000 200 quency band of 10 kHz to 8 GHz. 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 In this table, the higher field strength applies at the fre- to a minimum of 7.5 mA at 500 kHz. 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- TABLE II.–HIRF ENVIRONMENT II quency decade to a minimum of 0.75 mA at 400 MHz. Field strength (volts/meter) (4) From 100 MHz to 8 GHz, use radiated Frequency susceptibility tests at a minimum of 5 V/m. 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 30 MHz–100 MHz ............................. 10 10 PART 25—AIRWORTHINESS STAND- 100 MHz–200 MHz ........................... 30 10 ARDS: TRANSPORT CATEGORY 200 MHz–400 MHz ........................... 10 10 400 MHz–1 GHz ................................ 700 40 AIRPLANES 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 6 GHz–8 GHz .................................... 400 170 13 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 In this table, the higher field strength applies at the fre- Subpart A—General 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 susceptibility tests at a minimum of 20 volts 25.101 General. per meter (V/m) peak with CW and 1 kHz 25.103 Stall speed. square wave modulation with 90 percent 25.105 Takeoff. depth or greater. 25.107 Takeoff speeds. 356 VerDate Mar<15>2010 08:36 Apr 02, 2013 Jkt 229045 PO 00000 Frm 00366 Fmt 8010 Sfmt 8010 Y:\SGML\229045.XXX 229045 wreier-aviles on DSK5TPTVN1PROD with CFR Federal Aviation Administration, DOT Pt. 25 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. SUPPLEMENTARY CONDITIONS 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. 25.123 En route flight paths. power unit mounts. 25.125 Landing. 25.365 Pressurized compartment loads. 25.367 Unsymmetrical loads due to engine CONTROLLABILITY AND MANEUVERABILITY failure. 25.371 Gyroscopic loads. 25.143 General. 25.373 Speed control devices. 25.145 Longitudinal control. 25.147 Directional and lateral control. CONTROL SURFACE AND SYSTEM LOADS 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. 25.171 General. 25.405 Secondary control system. 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 Auxiliary aerodynamic surfaces. 25.457 Wing flaps. STALLS 25.459 Special devices. 25.201 Stall demonstration. GROUND LOADS 25.203 Stall characteristics. 25.207 Stall warning. 25.471 General. 25.473 Landing load conditions and assump- GROUND AND WATER HANDLING 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. MISCELLANEOUS FLIGHT REQUIREMENTS 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. WATER LOADS 25.521 General. FLIGHT LOADS 25.523 Design weights and center of gravity 25.321 General. positions. 25.525 Application of loads. FLIGHT MANEUVER AND GUST CONDITIONS 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- 25.337 Limit maneuvering load factors. tion. 25.341 Gust and turbulence loads. 25.533 Hull and main float bottom pressures. 25.343 Design fuel and oil loads. 25.535 Auxiliary float loads. 25.345 High lift devices. 25.537 Seawing loads. 357 VerDate Mar<15>2010 08:36 Apr 02, 2013 Jkt 229045 PO 00000 Frm 00367 Fmt 8010 Sfmt 8010 Y:\SGML\229045.XXX 229045 wreier-aviles on DSK5TPTVN1PROD with CFR Pt. 25 14 CFR Ch. I (1–1–13 Edition) EMERGENCY LANDING CONDITIONS 25.753 Main float design. 25.755 Hulls. 25.561 General. 25.562 Emergency landing dynamic condi- PERSONNEL AND CARGO ACCOMMODATIONS tions. 25.563 Structural ditching provisions. 25.771 Pilot compartment. 25.772 Pilot compartment doors. FATIGUE EVALUATION 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. LIGHTNING PROTECTION 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- 25.601 General. senger and crew compartments and gal- 25.603 Materials. leys. 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. EMERGENCY PROVISIONS 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. CONTROL SURFACES 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 CONTROL SYSTEMS (including galleys).