Federal Aviation Administration, DOT § 27.1457

§ 27.1413 Safety belts. its components must be shown by Each safety belt must be equipped flight tests of the rotorcraft or its com- with a metal to metal latching device. ponents in measured natural atmos- pheric and by one or (Secs. 313, 314, and 601 through 610 of the Fed- more of the following tests as found eral Aviation Act of 1958 (49 U.S.C. 1354, 1355, necessary to determine the adequacy of and 1421 through 1430) and sec. 6(c), Dept. of the : Transportation Act (49 U.S.C. 1655(c))) (1) Laboratory dry air or simulated [Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as icing tests, or a combination of both, of amended by Amdt. 27–15, 43 FR 46233, Oct. 5, the components or models of the com- 1978; Amdt. 27–21, 49 FR 44435, Nov. 6, 1984] ponents. § 27.1415 Ditching equipment. (2) Flight dry air tests of the ice pro- tection system as a whole, or its indi- (a) Emergency flotation and sig- vidual components. naling equipment required by any oper- (3) Flight tests of the rotorcraft or ating rule in this chapter must meet its components in measured simulated the requirements of this section. icing conditions. (b) Each raft and each life preserver (d) The ice protection provisions of must be approved and must be installed this section are considered to be appli- so that it is readily available to the cable primarily to the . Power- crew and passengers. The storage pro- plant installation requirements are visions for life preservers must accom- contained in Subpart E of this part. modate one life preserver for each oc- (e) A means must be indentified or cupant for which certification for provided for determining the formation ditching is requested. of ice on critical parts of the rotor- (c) Each raft released automatically craft. Unless otherwise restricted, the or by the pilot must be attached to the means must be available for nighttime rotorcraft by a line to keep it alongside as well as daytime operation. The the rotorcraft. This line must be weak rotorcraft flight manual must describe enough to break before submerging the the means of determining ice forma- empty raft to which it is attached. tion and must contain information nec- (d) Each signaling device must be essary for safe operation of the rotor- free from hazard in its operation and craft in icing conditions. must be installed in an accessible loca- tion. [Amdt. 27–19, 48 FR 4389, Jan. 31, 1983]

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as § 27.1435 Hydraulic systems. amended by Amdt. 27–11, 41 FR 55470, Dec. 20, 1976] (a) Design. Each hydraulic system and its elements must withstand, with- § 27.1419 Ice protection. out yielding, any structural loads ex- (a) To obtain certification for flight pected in addition to hydraulic loads. into icing conditions, compliance with (b) Tests. Each system must be sub- this section must be shown. stantiated by proof pressure tests. (b) It must be demonstrated that the When proof tested, no part of any sys- rotorcraft can be safely operated in the tem may fail, malfunction, or experi- continuous maximum and intermittent ence a permanent set. The proof load of maximum icing conditions determined each system must be at least 1.5 times under appendix C of Part 29 of this the maximum operating pressure of chapter within the rotorcraft altitude that system. envelope. An analysis must be per- (c) Accumulators. No hydraulic accu- formed to establish, on the basis of the mulator or pressurized reservoir may rotorcraft’s operational needs, the ade- be installed on the engine side of any quacy of the ice protection system for firewall unless it is an integral part of the various components of the rotor- an engine. craft. (c) In addition to the analysis and § 27.1457 Cockpit voice recorders. physical evaluation prescribed in para- (a) Each cockpit voice recorder re- graph (b) of this section, the effective- quired by the operating rules of this ness of the ice protection system and chapter must be approved, and must be

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