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14 CFR Ch. I (1–1–12 Edition) § 23.1095

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14 CFR Ch. I (1–1–12 Edition) § 23.1095 § 23.1095 14 CFR Ch. I (1–1–12 Edition) and operating condition because of su- § 23.1101 Induction air preheater de- percharging. sign. Each exhaust-heated, induction air [Amdt. 23-7, 34 FR 13095, Aug. 13, 1969, as preheater must be designed and con- amended by Amdt. 23–15, 39 FR 35460, Oct. 1, structed to— 1974; Amdt. 23–17, 41 FR 55465, Dec. 20, 1976; (a) Ensure ventilation of the pre- Amdt. 23–18, 42 FR 15041, Mar. 17, 1977; Amdt. heater when the induction air pre- 23–29, 49 FR 6847, Feb. 23, 1984; Amdt. 23–43, 58 heater is not being used during engine FR 18973, Apr. 9, 1993; Amdt. 23–51, 61 FR 5137, operation; Feb. 9, 1996] (b) Allow inspection of the exhaust manifold parts that it surrounds; and § 23.1095 Carburetor deicing fluid flow (c) Allow inspection of critical parts rate. of the preheater itself. (a) If a carburetor deicing fluid sys- [Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as tem is used, it must be able to simulta- amended by Amdt. 23–43, 58 FR 18974, Apr. 9, neously supply each engine with a rate 1993] of fluid flow, expressed in pounds per hour, of not less than 2.5 times the § 23.1103 Induction system ducts. square root of the maximum contin- (a) Each induction system duct must uous power of the engine. have a drain to prevent the accumula- tion of fuel or moisture in the normal (b) The fluid must be introduced into ground and flight attitudes. No drain the air induction system— may discharge where it will cause a (1) Close to, and upstream of, the car- fire hazard. buretor; and (b) Each duct connected to compo- nents between which relative motion (2) So that it is equally distributed could exist must have means for flexi- over the entire cross section of the in- bility. duction system air passages. (c) Each flexible induction system duct must be capable of withstanding § 23.1097 Carburetor deicing fluid sys- the effects of temperature extremes, tem capacity. fuel, oil, water, and solvents to which (a) The capacity of each carburetor it is expected to be exposed in service deicing fluid system— and maintenance without hazardous deterioration or delamination. (1) May not be less than the greater (d) For reciprocating engine installa- of— tions, each induction system duct must (i) That required to provide fluid at be— the rate specified in § 23.1095 for a time (1) Strong enough to prevent induc- equal to three percent of the maximum tion system failures resulting from endurance of the airplane; or normal backfire conditions; and (2) Fire resistant in any compart- (ii) 20 minutes at that flow rate; and ment for which a fire extinguishing (2) Need not exceed that required for system is required. two hours of operation. (e) Each inlet system duct for an aux- iliary power unit must be— (b) If the available preheat exceeds 50 (1) Fireproof within the auxiliary ° ° F. but is less than 100 F., the capacity power unit compartment; of the system may be decreased in pro- (2) Fireproof for a sufficient distance portion to the heat rise available in ex- upstream of the auxiliary power unit cess of 50 °F. compartment to prevent hot gas re- verse flow from burning through the § 23.1099 Carburetor deicing fluid sys- duct and entering any other compart- tem detail design. ment of the airplane in which a hazard Each carburetor deicing fluid system would be created by the entry of the must meet the applicable requirements hot gases; for the design of a fuel system, except (3) Constructed of materials suitable as specified in §§ 23.1095 and 23.1097. to the environmental conditions ex- pected in service, except in those areas 290 VerDate Mar<15>2010 11:30 Mar 22, 2012 Jkt 226044 PO 00000 Frm 00300 Fmt 8010 Sfmt 8010 Y:\SGML\226044.XXX 226044 pmangrum on DSK3VPTVN1PROD with CFR Federal Aviation Administration, DOT § 23.1121 requiring fireproof or fire resistant ma- § 23.1109 Turbocharger bleed air sys- terials; and tem. (4) Constructed of materials that will The following applies to not absorb or trap hazardous quantities turbocharged bleed air systems used of flammable fluids that could be ig- for cabin pressurization: nited by a surge or reverse-flow condi- (a) The cabin air system may not be tion. subject to hazardous contamination (f) Induction system ducts that sup- following any probable failure of the ply air to a cabin pressurization sys- turbocharger or its lubrication system. tem must be suitably constructed of (b) The turbocharger supply air must material that will not produce haz- be taken from a source where it cannot ardous quantities of toxic gases or iso- be contaminated by harmful or haz- lated to prevent hazardous quantities ardous gases or vapors following any of toxic gases from entering the cabin probable failure or malfunction of the during a powerplant fire. engine exhaust, hydraulic, fuel, or oil [Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as system. amended by Amdt. 23–7, 34 FR 13095, Aug. 13, [Amdt. 23–42, 56 FR 354, Jan. 3, 1991] 1969; Amdt. 23–43, 58 FR 18974, Apr. 9, 1993] § 23.1105 Induction system screens. § 23.1111 Turbine engine bleed air sys- tem. If induction system screens are For turbine engine bleed air systems, used— the following apply: (a) Each screen must be upstream of (a) No hazard may result if duct rup- the carburetor or fuel injection system. ture or failure occurs anywhere be- (b) No screen may be in any part of tween the engine port and the airplane the induction system that is the only unit served by the bleed air. passage through which air can reach (b) The effect on airplane and engine the engine, unless— performance of using maximum bleed (1) The available preheat is at least air must be established. 100 °F.; and (c) Hazardous contamination of cabin (2) The screen can be deiced by heat- air systems may not result from fail- ed air; ures of the engine lubricating system. (c) No screen may be deiced by alco- hol alone; and [Amdt. 23–7, 34 FR 13095, Aug. 13, 1969, as (d) It must be impossible for fuel to amended by Amdt. 23–17, 41 FR 55465, Dec. 20, strike any screen. 1976] [Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30 EXHAUST SYSTEM FR 258, Jan. 9, 1996, as amended by Amdt. 23– 51, 61 FR 5137, Feb. 9, 1996] § 23.1121 General. For powerplant and auxiliary power § 23.1107 Induction system filters. unit installations, the following If an air filter is used to protect the apply— engine against foreign material par- (a) Each exhaust system must ensure ticles in the induction air supply— safe disposal of exhaust gases without (a) Each air filter must be capable of fire hazard or carbon monoxide con- withstanding the effects of tempera- tamination in any personnel compart- ture extremes, rain, fuel, oil, and sol- ment. vents to which it is expected to be ex- (b) Each exhaust system part with a posed in service and maintenance; and surface hot enough to ignite flammable (b) Each air filter shall have a design fluids or vapors must be located or feature to prevent material separated shielded so that leakage from any sys- from the filter media from interfering tem carrying flammable fluids or va- with proper fuel metering operation. pors will not result in a fire caused by [Doc. No. 26344, 58 FR 18974, Apr. 9, 1993, as impingement of the fluids or vapors on amended by Amdt. 23–51, 61 FR 5137, Feb. 9, any part of the exhaust system includ- 1996] ing shields for the exhaust system. 291 VerDate Mar<15>2010 11:30 Mar 22, 2012 Jkt 226044 PO 00000 Frm 00301 Fmt 8010 Sfmt 8010 Y:\SGML\226044.XXX 226044 pmangrum on DSK3VPTVN1PROD with CFR.
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