TITLE 14—CIVIL AVIATION

1 civil AIR REGULATIONS PART 4b-AIRPLANEAIRWORTHINESS TRANSPORTCATEGORIESAs amended to December 31, 1953 civil AERONAUTICS BOARDWASHINGTON, 14 civil AVIATIONC hapter 1 civil Aeronautics BoardSubpart A civil Air RegulationsPart 4b AIRPLANE AIRWORTHINESS;TRANSPORT CATEGORIESRECAPITULATION OF PARTB ecause of the number of outstandingamendments to Part 4b there follows a recapitulationof Part 4b incorporating all amendments up toDecember 31, A GeneralAPPLICABILITY AND of this for type of applicable of and , experimental, andproduction of materials, parts, processes,and in type B of of gravity limitations on of flap ; ; ; all engines of the landing distance; or float.

2 And lateral control speed, and directional , directional, and lateral for airplanes with four or longitudinal during during during during longitudinal directional and lateral directional and lateral ; symmetrical ; asymmetrical HANDLING stability and stability and cross HANDLING and stability on the FLIGHT and C and of of high lift flight flight SURFACE AND SYSTEM surface loads; flight control primary flight control gust control landing landing landing drift landing handling loads on dual-wheel weights and center of of and main float load and main float landing and main float take-off and main float bottom float LANDING ditching D Design and strength properties and , deformation, and of controls and flap flat system system system details; gear load factor AND main AND CARGO compartment; compartment.

3 And , berths, and safety and baggage , HEATING, AND cabins; and baggage compartment of fluid fire heater fire near E powerplant pitch and speed de-icing SYSTEM OPERATION AND system cross-feed flow of unusable fuel supplyand fuel system operation on low system hot weather between interconnected SYSTEM CONSTRUCTION AND tank tank tank expansion tank tank filler tank vents and carburetor tank fueling SYSTEM pump system lines and lines and fittings in designated system jettisoning tank tank tank lines and system feathering

4 Cooling test cooling test test procedure for flying cooling system AND EXHAUST system de-icing and air preheater system system air and system and CONTROLS AND controls; and system system air preheat Ignition FIRE fire and extinguisher detector and nacelle accessory section and ventilation of fire of other airplane componentsagainst F and installational basic and navigational , systems, and ; and visibility of and navigational SYSTEMS AND system equipment and system fire and system tests and light system light system dihedral light distribution and light color fire belt of safety and electronic equipment and systems; systems system fire G Operating Limitations and limitations.

5 Speed operating limit speed extended speed gear operating speed gear extended speed control speed weight, center of gravity andweight distribution flight of operating flight load factorsMARKINGS AND markings; direction instruments; quantity quantity markings; markings and FLIGHT IDENTIFICATION : to issued undersec. 205, 52 Stat. 984, as amended: 49 or apply secs. 601, 603, 52 Stat. 1007, asamended, 1009, as amended; 49 551, A GENERALAPPLICABILITY AND DEFINITIONS of this part. This partestablishes standards with which compliance shall bedemonstrated for the issuance of a type certificate fortransport category airplanes.

6 This part, untilsuperseded or rescinded, shall apply to all transportcategory airplanes for which applications for typecertification in the transport category are made afterthe effective date of this part (November 9, 1945). As used in this part termsare defined as follows:(a)Administration (1) Administrator. TheAdministrator is the Administrator of CivilAeronautics.(2)Applicant. An applicant is a person orpersons applying for approval of an airplane or anypart thereof(3)Approved. Approved, when used alone oras modifying terms such as means, devices,specifications, etc.

7 , shall mean approved by theAdministrator. (See )(b)General design (1) Standard standard atmosphere is an atmosphere defined asfollows:(i)The air is a dry, perfect gas,(ii)The temperature at sea level is 59 F.,(iii)The pressure at sea level is inches Hg,(iv)The temperature gradient from sea level tothe altitude at which the temperature equals -67 F. is and zero there above(v)The density 0 at sea level under the aboveconditions is pounds sec. (2)Maximum anticipated air temperature. Themaximum anticipated air temperature is a temperaturespecified for the purpose of compliance with thepowerplant cooling standard.

8 (See (b).)(3)Airplane configuration. Airplaneconfiguration is a term referring to the position of thevarious elements affecting the aerodynamicscharacteristics of the airplane ( , wing flaps,landing gear).(4)Aerodynamic coefficients. Aerodynamiccoefficients are nondimensional coefficients for forcesand moments. They correspond with those adoptedby the National Advisory Committee forAeronautics.(5)Critical engine(s). The critical engine isthat engine(s) the failure of which gives the mostadverse effect on the airplane flight characteristicsrelative to the case under consideration.

9 (6)Critical-engine-failure speed. The critical-engine-failure speed is the airplane speed used in thedetermination of the take-off at which the criticalengine is assumed to fail. (See ).(c)Weights (1) Maximum weight. Themaximum weight of the airplane is that maximum atwhich compliance with the requirements of this part isdemonstrated. (See (a).)(2)Minimum weight. The minimum weight ofthe airplane is that minimum at which compliance withthe requirements of this part is demonstrated. ( (c).)(3)Empty weight. The empty weight of theairplane is a readily reproducible weight which is usedin the determination of the operating weights.

10 (See )(4)Design maximum weight. The designmaximum weight is the maximum weight of the airplaneused in structural design for flight load conditions.(See )(5)Design minimum weight. The designminimum weight is the minimum weight of the airplaneat which compliance is shown with the structuralloading conditions. (See )(6)Design take-off weight. The design take-offweight is the maximum airplane weight used instructural design for taxying conditions, and forlanding conditions at a reduced velocity of descent.(See )(7)Design landing weight. The design landingweight is the maximum airplane weight used instructural design for landing conditions at themaximum velocity of descent.