Federal Administration, DOT § 23.1501

(5) Except for recorders powered sole- (e) Any novel or unique design or ly by the engine-driven electrical gen- operational characteristics of the air- erator system, there is an automatic craft shall be evaluated to determine if means to simultaneously stop a re- any dedicated parameters must be re- corder that has a data erasure feature corded on recorders in addition and prevent each erasure feature from to or in place of existing requirements. functioning, within 10 minutes after [Amdt. 23–35, 53 FR 26143, July 11, 1988, as crash impact; amended by Amdt. 23–58, 73 FR 12562, Mar. 7, (6) Any single electrical failure exter- 2008; 74 FR 32800, July 9, 2009] nal to the recorder does not disable both the voice recorder and the § 23.1461 Equipment containing high flight data recorder; and energy rotors. (7) It is in a separate container from (a) Equipment, such as Auxiliary the cockpit voice recorder when both Power Units (APU) and constant speed are required. If used to comply with drive units, containing high energy ro- only the flight data recorder require- tors must meet paragraphs (b), (c), or ments, a combination unit may be in- (d) of this section. stalled. If a combination unit is in- (b) High energy rotors contained in stalled as a cockpit voice recorder to equipment must be able to withstand comply with § 23.1457(e)(2), a combina- damage caused by malfunctions, vibra- tion unit must be used to comply with tion, abnormal speeds, and abnormal this flight data recorder requirement. temperatures. In addition— (b) Each nonejectable record con- (1) Auxiliary rotor cases must be able tainer must be located and mounted so to contain damage caused by the fail- as to minimize the probability of con- ure of high energy rotor blades; and tainer rupture resulting from crash im- (2) Equipment control devices, sys- pact and subsequent damage to the tems, and instrumentation must rea- record from . In meeting this re- sonably ensure that no operating limi- quirement the record container must tations affecting the integrity of high be located as far aft as practicable, but energy rotors will be exceeded in serv- need not be aft of the pressurized com- ice. partment, and may not be where aft- (c) It must be shown by test that mounted engines may crush the con- equipment containing high energy ro- tainer upon impact. tors can contain any failure of a high (c) A correlation must be established energy rotor that occurs at the highest between the readings of speed obtainable with the normal speed airspeed, altitude, and heading and the control devices inoperative. corresponding readings (taking into ac- (d) Equipment containing high en- count correction factors) of the first pi- ergy rotors must be located where lot’s instruments. The correlation rotor failure will neither endanger the must cover the airspeed range over occupants nor adversely affect contin- which the airplane is to be operated, ued safe flight. the range of altitude to which the air- [Amdt. 23–20, 42 FR 36969, July 18, 1977, as plane is limited, and 360 degrees of amended by Amdt. 23–49, 61 FR 5170, Feb. 9, heading. Correlation may be estab- 1996] lished on the ground as appropriate. (d) Each recorder container must: Subpart G—Operating Limitations (1) Be either bright orange or bright and Information yellow; (2) Have reflective tape affixed to its § 23.1501 General. external surface to facilitate its loca- (a) Each operating limitation speci- tion under water; and fied in §§ 23.1505 through 23.1527 and (3) Have an underwater locating de- other limitations and information nec- vice, when required by the operating essary for safe operation must be es- rules of this chapter, on or adjacent to tablished. the container which is secured in such (b) The operating limitations and a manner that they are not likely to be other information necessary for safe separated during crash impact. operation must be made available to

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