§ 23.1459 14 CFR Ch. I (1–1–12 Edition)

prevent each erasure feature from func- ability of inadvertent operation and ac- tioning, within 10 minutes after crash tuation of the device during crash im- impact; and pact. (3) There is an aural or visual means (g) Each recorder container must: for preflight checking of the recorder (1) Be either bright orange or bright for proper operation; yellow; (4) Any single electrical failure exter- (2) Have reflective tape affixed to its nal to the recorder does not disable external surface to facilitate its loca- both the voice recorder and the tion under water; and data recorder; (3) Have an underwater locating de- (5) It has an independent power vice, when required by the operating source— rules of this chapter, on or adjacent to (i) That provides 10 ± 1 minutes of the container which is secured in such electrical power to operate both the manner that they are not likely to be cockpit voice recorder and cockpit- separated during crash impact. mounted area microphone; [Amdt. 23–35, 53 FR 26142, July 11, 1988, as (ii) That is located as close as prac- amended by Amdt. 23–58, 73 FR 12562, Mar. 7, ticable to the cockpit voice recorder; 2008; 74 FR 32799, July 9, 2009] and (iii) To which the cockpit voice re- § 23.1459 Flight data recorders. corder and cockpit-mounted area (a) Each required by microphone are switched automati- the operating rules of this chapter cally in the event that all other power must be installed so that: to the cockpit voice recorder is inter- (1) It is supplied with airspeed, alti- rupted either by normal shutdown or tude, and directional data obtained by any other loss of power to the elec- from sources that meet the accuracy trical power bus; and requirements of §§ 23.1323, 23.1325, and (6) It is in a separate container from 23.1327, as appropriate; the flight data recorder when both are (2) The vertical sensor is required. If used to comply with only rigidly attached, and located longitu- the cockpit voice recorder require- dinally either within the approved cen- ments, a combination unit may be in- ter of gravity limits of the airplane, or stalled. at a distance forward or aft of these (e) The recorder container must be limits that does not exceed 25 percent located and mounted to minimize the of the airplane’s mean aerodynamic probability of rupture of the container chord; as a result of crash impact and con- (3)(i) It receives its electrical power sequent heat damage to the recorder from the bus that provides the max- from . imum reliability for operation of the (1) Except as provided in paragraph flight data recorder without jeopard- (e)(2) of this section, the recorder con- izing service to essential or emergency tainer must be located as far aft as loads. practicable, but need not be outside of (ii) It remains powered for as long as the pressurized compartment, and may possible without jeopardizing emer- not be located where aft-mounted en- gency operation of the airplane. gines may crush the container during (4) There is an aural or visual means impact. for preflight checking of the recorder (2) If two separate combination dig- for proper recording of data in the stor- ital flight data recorder and cockpit age medium; voice recorder units are installed in- (5) Except for recorders powered sole- stead of one cockpit voice recorder and ly by the engine-driven electrical gen- one digital flight data recorder, the erator system, there is an automatic combination unit that is installed to means to simultaneously stop a re- comply with the cockpit voice recorder corder that has a data erasure feature requirements may be located near the and prevent each erasure feature from cockpit. functioning, within 10 minutes after (f) If the cockpit voice recorder has a crash impact; bulk erasure device, the installation (6) Any single electrical failure exter- must be designed to minimize the prob- nal to the recorder does not disable

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both the cockpit 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 fire. In meeting this re- sonably ensure that no operating limi- tations affecting the integrity of high quirement the record container must energy rotors will be exceeded in serv- be located as far aft as practicable, but ice. need not be aft of the pressurized com- (c) It must be shown by test that partment, and may not be where aft- equipment containing high energy ro- mounted engines may crush the con- tors can contain any failure of a high tainer upon impact. energy rotor that occurs at the highest (c) A correlation must be established speed obtainable with the normal speed between the flight recorder readings of control devices inoperative. airspeed, altitude, and heading and the (d) Equipment containing high en- corresponding readings (taking into ac- ergy rotors must be located where count correction factors) of the first pi- rotor failure will neither endanger the lot’s instruments. The correlation occupants nor adversely affect contin- must cover the airspeed range over ued safe flight. which the airplane is to be operated, [Amdt. 23–20, 42 FR 36969, July 18, 1977, as the range of altitude to which the air- amended by Amdt. 23–49, 61 FR 5170, Feb. 9, plane is limited, and 360 degrees of 1996] heading. Correlation may be estab- lished on the ground as appropriate. Subpart G—Operating Limitations (d) Each recorder container must: and Information (1) Be either bright orange or bright yellow; § 23.1501 General. (2) Have reflective tape affixed to its (a) Each operating limitation speci- external surface to facilitate its loca- fied in §§ 23.1505 through 23.1527 and tion under water; and other limitations and information nec- (3) Have an underwater locating de- essary for safe operation must be es- vice, when required by the operating tablished. rules of this chapter, on or adjacent to (b) The operating limitations and the container which is secured in such other information necessary for safe a manner that they are not likely to be operation must be made available to separated during crash impact. the crewmembers as prescribed in (e) Any novel or unique design or §§ 23.1541 through 23.1589. operational characteristics of the air- [Amdt. 23–21, 43 FR 2319, Jan. 16, 1978] craft shall be evaluated to determine if any dedicated parameters must be re- § 23.1505 Airspeed limitations. corded on flight recorders in addition (a) The never-exceed speed VNE must to or in place of existing requirements. be established so that it is— [Amdt. 23–35, 53 FR 26143, July 11, 1988, as (1) Not less than 0.9 times the min- amended by Amdt. 23–58, 73 FR 12562, Mar. 7, imum value of VD allowed under 2008; 74 FR 32800, July 9, 2009] § 23.335; and

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