Federal Aviation Administration, DOT § 25.1419

(g) Life line stowage provisions. If cer- § 25.1419 Ice protection. tification for ditching under § 25.801 is If the applicant seeks certification requested, there must be provisions to for flight in , the air- store life lines. These provisions plane must be able to safely operate in must— the continuous maximum and inter- (1) Allow one life line to be attached mittent maximum icing conditions of to each side of the ; and appendix C. To establish this— (2) Be arranged to allow the life lines (a) An analysis must be performed to to be used to enable the occupants to establish that the ice protection for stay on the wing after ditching. the various components of the airplane is adequate, taking into account the [Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25–32, 37 FR 3972, Feb. 24, various airplane operational configura- 1972; Amdt. 25–46, 43 FR 50598, Oct. 30, 1978; tions; and Amdt. 25–53, 45 FR 41593, June 19, 1980; Amdt. (b) To verify the ice protection anal- 25–70, 54 FR 43925, Oct. 27, 1989; Amdt. 25–79, ysis, to check for icing anomalies, and 58 FR 45229, Aug. 26, 1993; Amdt. 25–116, 69 FR to demonstrate that the ice protection 62789, Oct. 27, 2004] system and its components are effec- tive, the airplane or its components § 25.1415 Ditching equipment. must be flight tested in the various (a) Ditching equipment used in air- operational configurations, in meas- planes to be certificated for ditching ured natural atmospheric icing condi- under § 25.801, and required by the oper- tions and, as found necessary, by one ating rules of this chapter, must meet or more of the following means: the requirements of this section. (1) Laboratory dry air or simulated icing tests, or a combination of both, of (b) Each liferaft and each life pre- the components or models of the com- server must be approved. In addition— ponents. (1) Unless excess rafts of enough ca- (2) Flight dry air tests of the ice pro- pacity are provided, the buoyancy and tection system as a whole, or of its in- seating capacity beyond the rated ca- dividual components. pacity of the rafts must accommodate (3) Flight tests of the airplane or its all occupants of the airplane in the components in measured simulated event of a loss of one raft of the largest icing conditions. rated capacity; and (c) Caution information, such as an (2) Each raft must have a trailing amber caution light or equivalent, line, and must have a static line de- must be provided to alert the signed to hold the raft near the air- flightcrew when the anti-ice or de-ice plane but to release it if the airplane system is not functioning normally. becomes totally submerged. (d) For turbine engine powered air- (c) Approved survival equipment planes, the ice protection provisions of must be attached to each liferaft. this section are considered to be appli- (d) There must be an approved sur- cable primarily to the . For vival type emergency locator trans- the powerplant installation, certain ad- mitter for use in one life raft. ditional provisions of subpart E of this (e) For airplanes not certificated for part may be found applicable. (e) One ditching under § 25.801 and not having of the following methods of icing detec- approved life preservers, there must be tion and activation of the airframe 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

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(3) Identification of conditions con- same source when all other power ducive to airframe icing as defined by sources are inoperative; and an appropriate static or total air tem- (2) An additional time duration in its perature and visible moisture for use standby state appropriate or required by the flightcrew to activate the air- for any other loads that are powered by frame ice protection system. the same source and that are essential (f) Unless the applicant shows that to safety of flight or required during the airframe ice protection system emergency conditions. need not be operated during specific (b) Be capable of operation within 3 phases of flight, the requirements of seconds from the time a microphone is paragraph (e) of this section are appli- removed from its stowage. cable to all phases of flight. (c) Be intelligible at all passenger (g) After the initial activation of the seats, lavatories, and flight attendant airframe ice protection system— seats and work stations. (1) The ice protection system must be (d) Be designed so that no unused, designed to operate continuously; unstowed microphone will render the (2) The airplane must be equipped system inoperative. with a system that automatically cy- (e) Be capable of functioning inde- cles the ice protection system; or pendently of any required crewmember interphone system. (3) An ice detection system must be (f) Be accessible for immediate use provided to alert the flightcrew each from each of two flight crewmember time the ice protection system must be stations in the pilot compartment. cycled. (g) For each required floor-level pas- (h) Procedures for operation of the senger emergency exit which has an ad- ice protection system, including acti- jacent flight attendant seat, have a vation and deactivation, must be estab- microphone which is readily accessible lished and documented in the Airplane to the seated flight attendant, except Flight Manual. that one microphone may serve more [Amdt. 25–72, 55 FR 29785, July 20, 1990, as than one exit, provided the proximity amended by Amdt. 25–121, 72 FR 44669, Aug. 8, of the exits allows unassisted verbal 2007; Amdt. 25–129, 74 FR 38339, Aug. 3, 2009] communication between seated flight attendants. § 25.1421 Megaphones. [Doc. No. 26003, 58 FR 45229, Aug. 26, 1993, as If a megaphone is installed, a re- amended by Amdt. 25–115, 69 FR 40527, July 2, straining means must be provided that 2004] is capable of restraining the mega- phone when it is subjected to the ulti- MISCELLANEOUS EQUIPMENT mate inertia forces specified in § 25.561(b)(3). § 25.1431 Electronic equipment. (a) In showing compliance with [Amdt. 25–41, 42 FR 36970, July 18, 1977] § 25.1309 (a) and (b) with respect to radio and electronic equipment and § 25.1423 Public address system. their installations, critical environ- A public address system required by mental conditions must be considered. this chapter must— (b) Radio and electronic equipment (a) Be powerable when the is must be supplied with power under the in flight or stopped on the ground, requirements of § 25.1355(c). after the shutdown or failure of all en- (c) Radio and electronic equipment, gines and auxiliary power units, or the controls, and wiring must be installed disconnection or failure of all power so that operation of any one unit or sources dependent on their continued system of units will not adversely af- operation, for— fect the simultaneous operation of any (1) A time duration of at least 10 min- other radio or electronic unit, or sys- utes, including an aggregate time dura- tem of units, required by this chapter. tion of at least 5 minutes of announce- (d) Electronic equipment must be de- ments made by flight and cabin crew- signed and installed such that it does members, considering all other loads not cause essential loads to become in- which may remain powered by the operative as a result of electrical

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