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Ice Protection. Each Seated Occupant

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Ice Protection. Each Seated Occupant Federal Aviation Administration, DOT § 25.1419 (1) Be arranged so that the equip- § 25.1415 Ditching equipment. ment is directly accessible and its loca- (a) Ditching equipment used in air- tion is obvious; and planes to be certificated for ditching (2) Protect the safety equipment under § 25.801, and required by the oper- from inadvertent damage. ating rules of this chapter, must meet (c) Emergency exit descent device. The the requirements of this section. stowage provisions for the emergency (b) Each liferaft and each life pre- exit descent devices required by server must be approved. In addition— § 25.810(a) must be at each exit for (1) Unless excess rafts of enough ca- which they are intended. pacity are provided, the buoyancy and (d) Liferafts. (1) The stowage provi- seating capacity beyond the rated ca- sions for the liferafts described in pacity of the rafts must accommodate § 25.1415 must accommodate enough all occupants of the airplane in the rafts for the maximum number of occu- event of a loss of one raft of the largest pants for which certification for ditch- rated capacity; and ing is requested. (2) Each raft must have a trailing (2) Liferafts must be stowed near line, and must have a static line de- exits through which the rafts can be signed to hold the raft near the air- launched during an unplanned ditch- plane but to release it if the airplane ing. becomes totally submerged. (3) Rafts automatically or remotely (c) Approved survival equipment released outside the airplane must be must be attached to each liferaft. attached to the airplane by means of (d) There must be an approved sur- the static line prescribed in § 25.1415. vival type emergency locator trans- (4) The stowage provisions for each mitter for use in one life raft. portable liferaft must allow rapid de- (e) For airplanes not certificated for tachment and removal of the raft for ditching under § 25.801 and not having use at other than the intended exits. approved life preservers, there must be (e) Long-range signaling device. The an approved flotation means for each stowage provisions for the long-range occupant. This means must be within signaling device required by § 25.1415 easy reach of each seated occupant and must be near an exit available during must be readily removable from the an unplanned ditching. airplane. (f) Life preserver stowage provisions. [Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as The stowage provisions for life pre- amended by Amdt. 25–29, 36 FR 18722, Sept. servers described in § 25.1415 must ac- 21, 1971; Amdt. 25–50, 45 FR 38348, June 9, 1980; commodate one life preserver for each Amdt. 25–72, 55 FR 29785, July 20, 1990; Amdt. occupant for which certification for 25–82, 59 FR 32057, June 21, 1994] ditching is requested. Each life pre- server must be within easy reach of § 25.1419 Ice protection. each seated occupant. If the applicant seeks certification (g) Life line stowage provisions. If cer- for flight in icing conditions, the air- tification for ditching under § 25.801 is plane must be able to safely operate in requested, there must be provisions to the continuous maximum and inter- store life lines. These provisions mittent maximum icing conditions of must— appendix C. To establish this— (1) Allow one life line to be attached (a) An analysis must be performed to to each side of the fuselage; and establish that the ice protection for (2) Be arranged to allow the life lines the various components of the airplane to be used to enable the occupants to is adequate, taking into account the stay on the wing after ditching. various airplane operational configura- tions; and [Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as (b) To verify the ice protection anal- amended by Amdt. 25–32, 37 FR 3972, Feb. 24, ysis, to check for icing anomalies, and 1972; Amdt. 25–46, 43 FR 50598, Oct. 30, 1978; Amdt. 25–53, 45 FR 41593, June 19, 1980; Amdt. to demonstrate that the ice protection 25–70, 54 FR 43925, Oct. 27, 1989; Amdt. 25–79, system and its components are effec- 58 FR 45229, Aug. 26, 1993; Amdt. 25–116, 69 FR tive, the airplane or its components 62789, Oct. 27, 2004] must be flight tested in the various 511 VerDate Mar<15>2010 10:12 Mar 18, 2014 Jkt 232046 PO 00000 Frm 00521 Fmt 8010 Sfmt 8010 Y:\SGML\232046.XXX 232046 pmangrum on DSK3VPTVN1PROD with CFR § 25.1421 14 CFR Ch. I (1–1–14 Edition) operational configurations, in meas- (3) An ice detection system must be ured natural atmospheric icing condi- provided to alert the flightcrew each tions and, as found necessary, by one time the ice protection system must be or more of the following means: cycled. (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. § 25.1421 Megaphones. (c) Caution information, such as an If a megaphone is installed, a re- amber caution light or equivalent, straining means must be provided that must be provided to alert the is capable of restraining the mega- flightcrew when the anti-ice or de-ice phone when it is subjected to the ulti- system is not functioning normally. mate inertia forces specified in (d) For turbine engine powered air- § 25.561(b)(3). planes, the ice protection provisions of [Amdt. 25–41, 42 FR 36970, July 18, 1977] this section are considered to be appli- cable primarily to the airframe. For § 25.1423 Public address system. the powerplant installation, certain ad- A public address system required by ditional provisions of subpart E of this this chapter must— part may be found applicable. (e) One (a) Be powerable when the aircraft is of the following methods of icing detec- in flight or stopped on the ground, tion and activation of the airframe ice after the shutdown or failure of all en- protection system must be provided: gines and auxiliary power units, or the (1) A primary ice detection system disconnection or failure of all power that automatically activates or alerts sources dependent on their continued the flightcrew to activate the airframe operation, for— ice protection system; (1) A time duration of at least 10 min- (2) A definition of visual cues for rec- utes, including an aggregate time dura- ognition of the first sign of ice accre- tion of at least 5 minutes of announce- tion on a specified surface combined ments made by flight and cabin crew- with an advisory ice detection system members, considering all other loads that alerts the flightcrew to activate which may remain powered by the the airframe ice protection system; or same source when all other power (3) Identification of conditions con- sources are inoperative; and ducive to airframe icing as defined by (2) An additional time duration in its an appropriate static or total air tem- standby state appropriate or required perature and visible moisture for use for any other loads that are powered by by the flightcrew to activate the air- the same source and that are essential frame ice protection system. to safety of flight or required during (f) Unless the applicant shows that emergency conditions. the airframe ice protection system (b) Be capable of operation within 3 need not be operated during specific seconds from the time a microphone is phases of flight, the requirements of removed from its stowage. paragraph (e) of this section are appli- (c) Be intelligible at all passenger cable to all phases of flight. seats, lavatories, and flight attendant (g) After the initial activation of the seats and work stations. airframe ice protection system— (d) Be designed so that no unused, (1) The ice protection system must be unstowed microphone will render the designed to operate continuously; system inoperative. (2) The airplane must be equipped (e) Be capable of functioning inde- with a system that automatically cy- pendently of any required crewmember cles the ice protection system; or interphone system. 512 VerDate Mar<15>2010 10:12 Mar 18, 2014 Jkt 232046 PO 00000 Frm 00522 Fmt 8010 Sfmt 8010 Y:\SGML\232046.XXX 232046 pmangrum on DSK3VPTVN1PROD with CFR.
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