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Federal Aviation Regulation Appendix B to Part 27 - Airworthiness Criteria for Helicopter Instrument Flight
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Appendix B to Part 27 — Airworthiness Criteria for Helicopter Instrument Flight
II. Definitions. (a) VYImeans instrument climb speed, utilized instead of VYfor compliance with the climb requirements for instrument flight.
(b) VNEImeans instrument flight never exceed speed, utilized instead of VNEfor compliance with maximum limit speed requirements for instrument flight.
(c) VMINImeans instrument flight minimum speed, utilized in complying with minimum limit speed requirements for instrument flight.
(i) The helicopter trimmed at VYI;
(iii) Power required for limit climb rate (at least 1,000 fpm) at VYIor maximum continuous power, whichever is less.
(2) Cruise. Stability must be shown throughout the speed range from 0.7 to 1.1 VHor VNEI, whichever is lower, not to exceed ±20 knots from trim with—
(i) The helicopter trimmed and power adjusted for level flight at 0.9 VHor 0.9 VNEI, whichever is lower; and
(3) Slow cruise. Stability must be shown throughout the speed range from 0.9 VMINIto 1.3 VMINIor 20 knots above trim speed, whichever is greater, with—
(i) The helicopter trimmed at 0.8 VHor 0.8 VNEI(or 0.8 VLEfor the landing gear extended case), whichever is lower;
(1) Any oscillation having a period of less than 5 seconds must damp to1/2amplitude in not more than one cycle.
(2) Any oscillation having a period of 5 seconds or more but less than 10 seconds must damp to1/2amplitude in not more than two cycles.
(1) Any oscillation having a period of less than 5 seconds must damp to1/2amplitude in not more than two cycles.
VIII. Equipment, systems, and installation. The basic equipment and installation must comply with §§29.1303, 29.1431, and 29.1433 through Amendment 29–14, with the following exceptions and additions:
(a) Flight and Navigation Instruments. (1) A magnetic gyro-stablized direction indicator instead of a gyroscopic direction indicator required by §29.1303(h); and
(2) A standby attitude indicator which meets the requirements of §§29.1303(g)(1) through (7) instead of a rate-of-turn indicator required by §29.1303(g). For two-pilot configurations, one pilot's primary indicator may be designated for this purpose. If standby batteries are provided, they may be charged from the aircraft electrical system if adequate isolation is incorporated.
(c) Performance. If VYIdiffers from VY, climb performance at VYIand with maximum continuous power throughout the ranges of weight, altitude, and temperature for which approval is requested.
[Amdt. 27–19, 48 FR 4389, Jan. 31, 1983, as amended by Amdt. No. 27–44, 73 FR 11000, Feb. 29, 2008]
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