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3 pads or any other isolation means that is used must

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(3)Pads or any other isolation means that is used must be nonabsorbent ormust be treated to prevent absorption of flammable fluids; and(4)No air or vapor can be trapped in any part of the system, except thecoolant tank expansion space, during filling or during operation.(b)Coolant tank. The tank capacity must be at least one gallon, plus 10 percent ofthe cooling system capacity. In addition -(1)Each coolant tank must be able to withstand the vibration, inertia, and fluidloads to which it may be subjected in operation;(2)Each coolant tank must have an expansion space of at least 10 percent ofthe total cooling system capacity; and(3)It must be impossible to fill the expansion space inadvertently with theairplane in the normal ground attitude.(c)Filler connection. Each coolant tank filler connection must be marked asspecified in sec. 23.1557(c). In addition -(1)Spilled coolant must be prevented from entering the coolant tankcompartment or any part of the airplane other than the tank itself; and(2)Each recessed coolant filler connection must have a drain that dischargesclear of the entire airplane.(d)Lines and fittings. Each coolant system line and fitting must meet therequirements of sec. 23.993, except that the inside diameter of the enginecoolant inlet and outlet lines may not be less than the diameter of thecorresponding engine inlet and outlet connections.(e)Radiators. Each coolant radiator must be able to withstand any vibration, inertia,and coolant pressure load to which it may normally be subjected. In addition -
September 2014CASR Part 23 Amdt. 2SUBPART EPage E-27(1)Each radiator must be supported to allow expansion due to operatingtemperatures and prevent the transmittal of harmful vibration to theradiator; and(2)If flammable coolant is used, the air intake duct to the coolant radiatormust be located so that (in case of fire) flames from the nacelle cannotstrike the radiator.(f)Drains. There must be an accessible drain that -(1)Drains the entire cooling system (including the coolant tank, radiator, andthe engine) when the airplane is in the normal ground altitude;(2)Discharges clear of the entire airplane; and(3)Has means to positively lock it closed.23.1063Coolant tank tests.Each coolant tank must be tested under sec. 23.965, except that -(a)The test required by sec. 23.965(a) (1) must be replaced with a similar testusing the sum of the pressure developed during the maximum ultimateacceleration with a full tank or a pressure of 3.5 pounds per square inch,whichever is greater, plus the maximum working pressure of the system; and(b)For a tank with a nonmetallic liner the test fluid must be coolant rather than fuelas specified in sec. 23.965(d), and the slosh test on a specimen liner must beconducted with the coolant at operating temperature.

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Term
Fall
Professor
NoProfessor
Tags
Fuel tank, Longitudinal static stability, Fuel pump

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