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Federal Aviation Administration, DOT § 25.1420

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Federal Aviation Administration, DOT § 25.1420 Federal Aviation Administration, DOT § 25.1420 (d) There must be an approved sur- the powerplant installation, certain ad- vival type emergency locator trans- ditional provisions of subpart E of this mitter for use in one life raft. part may be found applicable. (e) One (e) For airplanes not certificated for of the following methods of icing detec- ditching under § 25.801 and not having tion and activation of the airframe ice approved life preservers, there must be protection system must be provided: an approved flotation means for each (1) A primary ice detection system occupant. This means must be within that automatically activates or alerts easy reach of each seated occupant and the flightcrew to activate the airframe must be readily removable from the ice protection system; airplane. (2) A definition of visual cues for rec- [Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as ognition of the first sign of ice accre- amended by Amdt. 25–29, 36 FR 18722, Sept. tion on a specified surface combined 21, 1971; Amdt. 25–50, 45 FR 38348, June 9, 1980; with an advisory ice detection system Amdt. 25–72, 55 FR 29785, July 20, 1990; Amdt. that alerts the flightcrew to activate 25–82, 59 FR 32057, June 21, 1994] the airframe ice protection system; or (3) Identification of conditions con- § 25.1419 Ice protection. ducive to airframe icing as defined by If the applicant seeks certification an appropriate static or total air tem- for flight in icing conditions, the air- perature and visible moisture for use plane must be able to safely operate in by the flightcrew to activate the air- the continuous maximum and inter- frame ice protection system. mittent maximum icing conditions of (f) Unless the applicant shows that appendix C. To establish this— the airframe ice protection system (a) An analysis must be performed to need not be operated during specific establish that the ice protection for phases of flight, the requirements of the various components of the airplane paragraph (e) of this section are appli- is adequate, taking into account the cable to all phases of flight. various airplane operational configura- (g) After the initial activation of the tions; and airframe ice protection system— (b) To verify the ice protection anal- (1) The ice protection system must be ysis, to check for icing anomalies, and designed to operate continuously; to demonstrate that the ice protection (2) The airplane must be equipped system and its components are effec- with a system that automatically cy- tive, the airplane or its components cles the ice protection system; or must be flight tested in the various (3) An ice detection system must be operational configurations, in meas- provided to alert the flightcrew each ured natural atmospheric icing condi- time the ice protection system must be tions and, as found necessary, by one cycled. or more of the following means: (1) Laboratory dry air or simulated (h) Procedures for operation of the icing tests, or a combination of both, of ice protection system, including acti- the components or models of the com- vation and deactivation, must be estab- ponents. lished and documented in the Airplane (2) Flight dry air tests of the ice pro- Flight Manual. tection system as a whole, or of its in- [Amdt. 25–72, 55 FR 29785, July 20, 1990, as dividual components. amended by Amdt. 25–121, 72 FR 44669, Aug. 8, (3) Flight tests of the airplane or its 2007; Amdt. 25–129, 74 FR 38339, Aug. 3, 2009] components in measured simulated icing conditions. § 25.1420 Supercooled large drop icing (c) Caution information, such as an conditions. amber caution light or equivalent, (a) If certification for flight in icing must be provided to alert the conditions is sought, in addition to the flightcrew when the anti-ice or de-ice requirements of § 25.1419, an airplane system is not functioning normally. with a maximum takeoff weight less (d) For turbine engine powered air- than 60,000 pounds or with reversible planes, the ice protection provisions of flight controls must be capable of oper- this section are considered to be appli- ating in accordance with paragraphs cable primarily to the airframe. For (a)(1), (2), or (3), of this section. 525 VerDate Sep<11>2014 09:15 Mar 11, 2016 Jkt 238046 PO 00000 Frm 00535 Fmt 8010 Sfmt 8010 Y:\SGML\238046.XXX 238046 jstallworth on DSK7TPTVN1PROD with CFR.
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