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[Compliance withSec.23.1041mustbe shownforthe climb(or,for multiengine air-planes with negative one-engine-inoperative rates of climb, the descent) stage of .ight. The airplane must be .own in the con.gurations, at the speeds and following the pro-cedures recommended in the Airplane Flight Manual, that correspond to the applicable performance requirements that are critical to cooling.] Amdt. 23-51, E.. 03/11/96
32.6 Liquid Cooling
FAR 23.1061 : Installation.
(a) General. Eachliquid-cooled engine must have anindependent cooling system(inclu-ding coolant tank) installed so that–
(1)
Each coolant tank is supported so that tank loads are distributed over a large part of the tank surface;

(2)
[There arepads or otherisolationmeansbetweenthetankandits supportsto prevent cha.ng;

(3)
Pads or any other isolation means that is used must be nonabsorbent or must betreatedtopreventabsorptionof .ammable .uids; and

(4)
No air or vapor can be trapped in any part of the system, except the coolant tank expansion space, during .lling or during operation.]

(b)
Coolant tank.Thetank capacity mustbe atleast onegallon,plus10percent of the cooling system capacity. In addition–

(1)
Each coolant tank must be able to withstand the vibration, inertia, and .uid loads to which it may be subjected in operation;

(2)
Each coolant tank must have an expansion space of at least 10 percent of the total cooling system capacity; and

(3)
Itmustbeimpossibleto .lltheexpansionspaceinadvertently withtheairplane in the normal ground attitude.

 

(c)
Filler connection. Each coolant tank .ller connection must be marked as speci.ed in Sec. 23.1557(c). In addition–

(1)
Spilled coolant mustbepreventedfrom enteringthe coolanttank compartment or anypart of the airplane otherthanthetankitself; and

(2)
Each recessed coolant .ller connection must have a drain that discharges clear of the entire airplane.

 

(d)
Lines and .ttings. Each coolant system line and .tting must meet the requirements ofSec.23.993, except that theinsidediameter of the engine coolantinlet and outlet lines maynotbeless than thediameter of the corresponding engineinlet 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–

(1)
Each radiator must be supported to allow expansion due to operating tem-peratures and prevent the transmittal of harmful vibration to the radiator; and

(2)
If .ammable coolant is used, the air intake duct to the coolant radiator must belocated sothat(incaseof .re) .amesfromthenacellecannotstrikethe radiator.

 

(f)
Drains. There must be an accessible drain that–

(1)
Drains the entire cooling system(including the coolant tank, radiator, and the engine) whenthe airplaneisinthe normalground attitude;

(2)
Discharges clear of the entire airplane; and

(3)
Has means to positively lock it closed.

 

Amdt. 23-43, E.. 05/10/93
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
FAR 23.1063 : Coolant tank tests.
Each coolant tank must be tested under Sec. 23.965, except that–
(a)
The test requiredbySec.23.965(a)(1) mustbe replaced with a similar test using the sum of thepressuredevelopedduring the maximum ultimate accelerationwith a full tank or a pressure of 3.5 pounds per square inch, whichever is greater, plus the maximum workingpressure ofthe system; and

(b)
Foratank with anonmetalliclinerthetest .uid mustbecoolant ratherthanfuel as speci.edinSec.23.965(d), andthe sloshtest on a specimenliner mustbe conducted with the coolant at operating temperature.
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 2(68)