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weight to reduce the possibility of exceeding the
aft cg limits.
Table 6-12. Storage Bay and Survival Kit Bay Equipment Weights and Moments
6-16 Change 2
TM 1-1520-238-10
Section VII. CENTER OF GRAVITY
6.20 CENTER OF GRAVITY.
This section contains information needed to determine
whether the helicopter loading (gross weight and moment
combination) will fall within the helicopter center
of gravity limits.
6.21 CENTER OF GRAVITY LIMITS CHART.
a. The normal forward cg limit is at fuselage station
201.0 inches to 19,400 pounds and a straight taper
from 201.0 to 202.2 inches from 19,400 to 21,000
pounds. The normal aft cg limit is at fuselage station
207.0 inches to 14,660 pounds and a straight taper from
207.0 to 203.3 inches from 14,660 to 21,000 pounds.
b. The normal center of gravity limits chart is
shown in figure 6-3. All flight cg must remain within
these limits. This chart is used in conjunction with
Chart F (DD 365F) as follows:
1.
2.
3.
4.
5.
Load the helicopter to takeoff condition and
determine takeoff cg (Form F, ref 12 and ref
13).
Check cg limits using the chart (fig 6-3). If cg
limits are exceeded, then the loading must be
revised. Refer to paragraph 6.10 for guidance.
After the takeoff cg limits are satisfied, determine
estimated landing weight
F, ref 15 and ref 16).
Check cg limits using the chart
and cg (Form
(fig 6-3). If cg
limits are exceeded, ‘the loading must be revised.
Refer to paragraph 6.10 for guidance.
When either takeoff or landing cg is close to
the cg limits, further analysis is required to
determine if intermediate flight conditions
will exceed limits. Refer to paragraph 6.10 for
guidance.
6-17
TM 1-1520-238-10
NORMAL LONGITUDINAL CENTER OF GRAVITY LIMITS
Figure 6-3. Center of Gravity Limits
6-18 Change 3
CAUTION
TM 1-1520-238-10
CHAPTER 7
PERFORMANCE DATA FOR AH-64A HELlCOPTERS EQUIPPED
WITH T-700-GE-701 ENGINES
Section I. INTRODUCTION
NOTE NOTE
This chapter contains performance data
for helicopters equipped with
T-700-GE-701 engines. Performance
data for helicopters equipped with
T-700-GE-701C ~ engines is contained
in Chapter 7A. Users are authorized to
remove the chapter that is not applicable
and are not required to carry both chapters
on the helicopter.
7.1 PERFORMANCE DATA.
The purpose of this chapter is to provide the best available
performance data for the AH-64A helicopter
equipped with -701 engines. Regular use of this information
will allow maximum safe use of the helicopter.
Although maximum performance is not always required,
regular use of the information in this chapter is
recommended for the following reasons:
a. Knowledge of performance margins will allow
better decisions when unexpected conditions or alternate
missions are encountered.
b. Situations requiring maximum performance will
be more readily recognized.
c. Familiarity with the data will allow performance
to be computed more easily and quickly.
d. Experience will be gained in accurately estimating
the effects of conditions for which data is not presented.
The information is primarily intended for
mission planning and is most useful when
planning operations in unfamiliar areas
or at extreme conditions. The data may
also be used in flight, to establish unit or
area standing operating procedures, and
to inform ground commanders of performance/
risk tradeoffs.
The data presented covers the maximum range of
conditions and performance that can reasonably be expected.
In each area of performance, the effects of altitude,
temperature, gross weight and other parameters
relating to that phase of flight are presented. In addition
to the presented data, judgment and experience
will be necessary to accurately determine performance
under a given set of circumstances. The conditions for
the data are listed under the title of each chart. The effects
of different conditions are discussed in the text accompanying
each phase of performance. Where practical,
data is presented at conservative conditions.
However, NO GENERAL CONSERVATISM HAS
BEEN APPLIED.
7.2 OPERATIONAL LIMITS.
Exceeding operational limits can
cause permanent damage to critical
components. Overlimit operation can
decrease performance, cause immediate
failure or failure on a subsequent
flight.
Applicable limits are shown on the charts as bold lines
with a description. Performance generally deteriorates
　
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