MD Helicopters MD900 with PW206E, Руководство по эксплуатации самолета

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CSP–900RFM206E–1
ROTORCRAFT FLIGHT MANUAL
MD900 With PW 206E
Performance Data
FAA Approved
Original
5–2
5–3. DENSITY ALTITUDE CHART
Description: The chart allows a quick estimation of the density altitude when
pressure altitude and OAT are known. This chart can also be used to determine
true airspeed.
Use of Chart:
To determine density altitude, the pilot must know pressure altitude and outside
air temperature. Enter bottom of chart with known or estimated OAT, move
up to known pressure altitude line, move to left and note density altitude.
Pressure altitude is found by setting 29.92 (1013 mb) in Kolsman window
±
altimeter error.
To determine true airspeed convert indicated airspeed (IAS) to calibrated airspeed
(CAS) utilizing the Airspeed Calibration Curve (Ref. Figure 5−2). Read value
on right of chart opposite known density altitude. Multiply CAS by this value
to determine true airspeed.
Examples:
Find density altitude for 6000 H
P
at −15
°
C:
Follow −15
°
C line to 6,000 ft pressure altitude line; read density altitude (3800
ft).
Find density factor:
Read directly across from density altitude: (3800 ft). Note density factor of 1.058.
Find true airspeed:
130 KIAS = 127 KCAS (from Figure 5−2)
127 KCAS
1.058 = 134.4; round to 134 knots true airspeed.