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pounds.
Center of gravity limits for the helicopter to which this
manual applies and instructions for computation of the
5.15 TURBULENCE.
center of gravity are contained in Chapter 6. Intentional flight in extreme turbulence is prohibited.
5-10
TM 1-1520-238-10
Section V. AIRSPEED LIMITS MAXIMUM AND MINIMUM
5.16 AIRSPEED OPERATING LIMITS.
See figure 5-2 to determine the never exceed velocity
(VNE) as a function of weight, altitude, and temperature.
Additional airspeed limits are:
a. Maximum airspeed during autorotation is 145
KTAS.
b. Maximum airspeed with one engine inoperative
shall not exceed the greater of
(1) 67% of VNE determined from figure 5-2 sheet
1 using the GROSS WEIGHT line.
(2) The speed for minimum power determined
from the cruise charts in Chapter 7 or Chapter 7A
using the MAX END/MAX R/C lines.
c. The NOM SPD values depicted on the stabilator
position (STAB POS) indicator placard (fig 5-1) shall
be observed as maximum indicated airspeeds during
manual stabilator operations.
d. Maximum rearward/sideward flight speed is 45
KTAS for all gross weights.
e. Maximum airspeed for searchlight extension is
90 KIAS.
f. Maximum airspeed with symetrically loaded external
fuel tanks (2 or 4) installed is 130 KLAS.
g. Jettison of external armament stores is not authorized
except for emergency conditions, and then
only from unaccelerated flight during:
(1) Maximum airspeed for stores jettison is 120
KIAS, or
(2) Level flight - Hover to 40 KIAS (minimize
side slip), or
or
(3) Level flight - 40 to 120 KIAS (ball centered),
(4) Descents (0 fpm to full autorotation) 80 to
100 KIAS (ball centered).
h. Jettison of external fuel tanks is not authorized
except for emergency conditions, and then only from
airspeeds less than 100 KIAS. Jettison from level flight
if possible, and if not, jettison at an airspeed which
minimizes the rate of descent at the time of jettison.
5.16.1 Airspeed Operating Limits Chart. Referring
to figure 5-2 sheet 1, note that free air temperature
lines and pressure altitude scale are provided in the upper
grid, and gross weight lines and true airspeed scale
on the lower grid. Using the observed free air temperature
and altitude obtained from the aircraft instruments
and the calculated aircraft weight, enter the
chart as directed in the chart example. Determine maximum
true airspeed at the left side of the lower grid. To
determine the maximum indicated airspeed (pilots
gauge), refer to figure 5-2 sheet 2 and enter as directed
in the chart example with the true airspeed and density
altitude determined from figure 5-2 sheet 1.
Change 4 5-11
TM 1-1520-238-10
EXAMPLE
WANTED
MAXIMUM TRUE AND INDICATED AlRSPEED
AND DENSITY ALTITUDE
KNOWN
PRESSURE ALTITUDE = 6000 FEET
FAT = -30 °C
GROSS WEIGHT = 18,000 POUNDS
METHOD
ENTER AT 6000 FEET
PRESSURE ALTITUDE
MOVE RIGHT TO FAT = -30°C
MOVE DOWN TO 18.000 POUND
GROSS WEIGHT OR MACH LIMIT
FAT, WHICHEVER IS ENCOUNTERED
FIRST. IN THIS CASE. THE
MACH LIMIT IS ENCOUNTERED
FIRST. MOVE LEFT AT -30 °C
LINE AND READ TRUE
AIRSPEED = 166 KNOTS
MOVE DOWN, READ DENSITY
ALTITUDE = 1500 FEET
ON SHEET 2 ENTER AT
164 KNOTS TRUE AIRSPEED
AND MOVE TO RIGHT TO 1500
FEET DENSITY ALTITUDE.
MOVE DOWN, READ INDICATED
AIRSPEED = 156 KNOTS.
DATA BASIS: DERIVED FROM FLIGHT TEST
AIRSPEED OPERATING LIMITS
100% ROTOR RPM
LEVEL FLIGHT
Figure 5-2. Airspeed Operating Limits Chart (Sheet 1 of 2)
5-12
TM 1-1520-238-10
AIRSPEED CONVERSION
AIRSPEED
CONVERSION
AH-64A
DATA BASIS: DERIVED FROM FLIGHT TEST
Figure 5-2. Airspeed Operating Limits Chart (Sheet 2 of 2)
M01-231-2
5-13
TM 1-1520-238-10
Section VI. MANEUVERING LIMITS
5.17 MANEUVERING LIMITS.
The AH-64A helicopter is subject to the maneuvering
restrictions shown in figure 5-3.
a. Avoid large, abrupt pedal inputs in arresting
right hovering/low speed yawing turns greater than
60°/sec. This is to avoid excessive tail rotor drive systern
loads. Avoid rapid, abrupt pedal inputs when any
installed fuel tank(s) contain fuel. This is to avoid excessive
torquing of pylon structure.
b. Intentional maneuvers beyond attitudes of ± 30°
in pitch or ± 60° in roll are prohibited.
c. Flight, hovering flight, and ground taxiing with
the canopy enclosure open is prohibited, except for
smoke/fume elimination.
　
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