Federal Aviation Administration, DOT § 25.1165 (b) Each intermediate position of the thrust regime for turbojet powered air- mixture controls that corresponds to a planes). normal operating setting must be iden- [Amdt. 25–11, 32 FR 6913, May 5, 1967] tifiable by feel and sight. (c) The mixture controls must be ac- § 25.1157 Carburetor air temperature cessible to both pilots. However, if controls. there is a separate flight engineer sta- There must be a separate carburetor tion with a control panel, the controls air temperature control for each en- need be accessible only to the flight en- gine. gineer. § 25.1159 Supercharger controls. § 25.1149 Propeller speed and pitch controls. Each supercharger control must be accessible to the pilots or, if there is a (a) There must be a separate pro- separate flight engineer station with a peller speed and pitch control for each control panel, to the flight engineer. propeller. (b) The controls must be grouped and § 25.1161 Fuel jettisoning system con- arranged to allow— trols. (1) Separate control of each pro- Each fuel jettisoning system control peller; and must have guards to prevent inad- (2) Simultaneous control of all pro- vertent operation. No control may be pellers. near any fire extinguisher control or (c) The controls must allow synchro- other control used to combat fire. nization of all propellers. (d) The propeller speed and pitch con- § 25.1163 Powerplant accessories. trols must be to the right of, and at (a) Each engine mounted accessory least one inch below, the pilot’s throt- must— tle controls. (1) Be approved for mounting on the engine involved; § 25.1153 Propeller feathering controls. (2) Use the provisions on the engine (a) There must be a separate pro- for mounting; and peller feathering control for each pro- (3) Be sealed to prevent contamina- peller. The control must have means to tion of the engine oil system and the prevent its inadvertent operation. accessory system. (b) If feathering is accomplished by (b) Electrical equipment subject to movement of the propeller pitch or arcing or sparking must be installed to speed control lever, there must be minimize the probability of contact means to prevent the inadvertent with any flammable fluids or vapors movement of this lever to the feath- that might be present in a free state. ering position during normal oper- (c) If continued rotation of an engine- ation. driven cabin supercharger or of any re- mote accessory driven by the engine is [Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as hazardous if malfunctioning occurs, amended by Amdt. 25–11, 32 FR 6913, May 5, 1967] there must be means to prevent rota- tion without interfering with the con- § 25.1155 Reverse thrust and propeller tinued operation of the engine. pitch settings below the flight re- [Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as gime. amended by Amdt. 25–57, 49 FR 6849, Feb. 23, Each control for reverse thrust and 1984] for propeller pitch settings below the flight regime must have means to pre- § 25.1165 Engine ignition systems. vent its inadvertent operation. The (a) Each battery ignition system means must have a positive lock or must be supplemented by a generator stop at the flight idle position and that is automatically available as an must require a separate and distinct alternate source of electrical energy to operation by the crew to displace the allow continued engine operation if control from the flight regime (forward any battery becomes depleted. 495 VerDate Mar<15>2010 11:30 Mar 22, 2012 Jkt 226044 PO 00000 Frm 00505 Fmt 8010 Sfmt 8010 Y:\SGML\226044.XXX 226044 pmangrum on DSK3VPTVN1PROD with CFR.