6-9
3
4
I
2
I 2
3
VERTICAL SPEED
THOUSAND FT PER MIN
UP
DOWN
.5
.5
0
33
30
24
2I
I5
I2
6
3
2 MIN TURN
DC ELEC
L R
30.0
29.9
29.8
I00
FE ET
I
6 5 4
7
9
2
0
8
3
CALIBRATED
TO
20,000 FEET
ALT R
O
F20 20
I0 I0
I0 I0
20 20
TEST STBY PWR
IN Hg
ALg.
MANIFOLD
PRESS
25
5
15
30
20
10
35
A O
S
110
100
90
80
70
60
50
110
100
90
80
70
60
50
E R
%RPM
Figure 6-8. Flight instrum 6e-n7tb i Fnldigichatt iinosntsr uinm setnrat iinghdtic-aantido-nlesv inel s fltriagihgth wt-iathn dp-olewveerl fdliegchret awsiitnhg p. ower decreasing.
Figure 6-9. Flight instrument indications in straight-and-level flight at normal cruise speed.
6-10
Figure 6-10. Flight instrument indications in straight-and-level flight with airspeed decreasing.
Entry
To enter a constant airspeed climb from cruise airspeed when
the climb speed is lower than cruise speed, simultaneously
increase power to the climb power setting and adjust pitch
attitude to the approximate climb attitude. The increase in
power causes the helicopter to start climbing and only very
slight back cyclic pressure is needed to complete the change
from level to climb attitude. The attitude indicator should
be used to accomplish the pitch change. If the transition
from level flight to a climb is smooth, the VSI shows an
immediate upward trend and then stops at a rate appropriate
to the stabilized airspeed and attitude. Primary and supporting
instruments for climb entry are illustrated in Figure 6-11.
When the helicopter stabilizes at a constant airspeed and
attitude, the airspeed indicator becomes primary for pitch.
The manifold pressure continues to be primary for power and
should be monitored closely to determine if the proper climb
power setting is being maintained. Primary and supporting
instruments for a stabilized constant airspeed climb are shown
in Figure 6-12.
The technique and procedures for entering a constant rate
climb are very similar to those previously described for a
constant airspeed climb. For training purposes, a constant
To produce straight-and-level flight, the cross-check of the
pitch-and-bank instruments should be combined with the
power control instruments. With a constant power setting, a
normal cross-check should be satisfactory. When changing
power, the speed of the cross-check must be increased to
cover the pitch-and-bank instruments adequately. This is
necessary to counteract any deviations immediately.
Common Errors During Airspeed Changes
1. Improper use of power
2. Overcontrolling pitch attitude
3. Failure to maintain heading
4. Failure to maintain altitude
5. Improper pedal trim
Straight Climbs (Constant Airspeed and
Constant Rate)
For any power setting and load condition, there is only
one airspeed that gives the most efficient rate of climb.
To determine this, consult the climb data for the type of
helicopter being flown. The technique varies according to
the airspeed on entry and whether a constant airspeed or
constant rate climb is made.
6-11
Figure 6-11. Flight instrument indications during climb entry for a constant-airspeed climb.
A O M
3
4
I
0
2
I 2
3
VERTICAL SPEED
THOUSAND FT PER MIN
UP
DOWN
.5
.5
THO 33
30
24
2I
I5
I2
6
3
2 MIN TURN
DC ELEC
L R
30.0
29.9
29.8
I00
FEE T
I
6 5 4
7
9
2
0
8
3
CALIBRATED
TO
20,000 FEET
ALT RAT
20 20
I0 I0
I0 I0
20 20
TEST STBY PWR
IN Hg
ALg.
MANIFOLD
PRESS
25
5
15
30
20
10
35
A N
O
S
110
100
90
80
70
60
50
110
100
90
80
70
60
50
E R
%RPM
Supporting pitch and bank
Supporting bank Primary bank Supporting pitch
Remains constant
Primary power
Primary pitch
Figure 6-12. Flight instrFumigeunrte i n6d-9ic. a Ftiloignhst iinn sat rsutambeinlitz eindd cicoantsitoannst -inai ars spteaebdil iczleidm, bc.onstant-airspeed climb.
　
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