HELICOPTER, ATTACK, AH-64D LONGBOW APACHE. TECHNICAL MANUAL (2002)

TM 1-1520-251-10

Section VI. CARGO LOADING

6.8 CARGO LOADING

The survival equipment stowage bay, left flyaway kit bay

and right flyaway kit bay, may carry a survival equipment

kit and/or personal equipment. The flyaway equipment kit

CAUTION

and survival equipment kit are basic weight items and are

listed on Chart A (DD 365-1). Personal items or extra

To prevent damage to helicopter, all car-

equipment that has not been identified as basic weight

go must be securely tied down.

must be entered on Form F.

6.8.1 Extra Cargo. All extra cargo should be weighed

There are four stowage bays on the helicopter; left - aft

so that exact weight and moments are used for the weight

storage bay, survival equipment stowage bay, left flyaway

and balance computations. If weighing facilities are not

kit bay and right flyaway kit bay. The left aft storage bay

available, weight should be estimated in terms of probable

contains the flyaway equipment kit which consists of:

maximum weight to reduce the possibility of exceeding

• Tiedown and mooring kit

the aft CG limit. Tables 6-11 and 6-12 provide quick refer-

ence lists of accumulative weight and moment of extra

• Main rotor tiedown assembly

cargo in the stowage bays.

• Main rotor blade tiedown pole assembly

NOTE

• Safety pins and stowage pouch

All calculated moments must be divided by

• Protective covers kit

100 before being entered on Form F.

Table 6-11. Storage Bay and Survival Equipment Stowage Bay

Left Aft Equipment Storage Bay

Survival Equipment Stowage Bay

Accum. Wt.

Moment

Accum. Wt.

Moment

(lb)

(in.-lb/100)

(lb)

(in.-lb/100)

101

133

151

148

168

60*

177

218

268

302

318

100*

335

*Max. Load 60lb. @15 lb/ft²

*Max. Load 100lb. @15 lb/ft²

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

6-16

TM 1-1520-251-10

Section VII. ALLOWABLE LOADING

6.9 ALLOWABLE LOADING

2. Check CG limits using the chart (fig 6-3). If CG

limits are exceeded, then the loading must be

revised. Refer to paragraph 6.2.1, subpara-

This section contains information needed to determine

graph f (center of gravity management) for guid-

whether the helicopter loading (gross weight and moment

ance.

combination) will fall within the helicopter center of gravity

limits.

3. After the takeoff CG limits are satisfied, deter-

mine estimated landing weight and CG

6.9.1 Center of Gravity Parameters. The normal for-

(Form F).

ward CG limit is at fuselage station 201.0 inches to 23,000

pounds. The normal aft CG limit is at fuselage station

4. Check CG limits using the chart (fig 6-3). If CG

207.0 inches to 14,660 pounds and a straight taper from

limits are exceeded, then the loading must be

207.0 to 202.2 inches from 14,660 to 23,000 pounds.

revised. Refer to paragraph 6.2.1, subpara-

graph f (center of gravity management) for guid-

6.9.2 Center of Gravity Limits Chart. The normal cen-

ance.

ter of gravity limits chart is shown in Figure 6-3. All flight

CGs must remain within these limits. This chart is used in

5. When either takeoff or landing CG is close to the

conjunction with Chart F (DD 365 - 4) as follows:

CG limits, further analysis is required to deter-

mine if intermediate flight conditions will exceed

1. Load the helicopter to takeoff condition and de-

limits. Refer to paragraph 6.2.1, subparagraph f

termine takeoff CG (Form F).

(center of gravity management) for guidance.

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

6-18

TM 1-1520-251-10

CHAPTER 7

PERFORMANCE DATA FOR AH-64D HELICOPTERS

EQUIPPED WITH T700-GE-701 ENGINES

Section I. INTRODUCTION

NOTE

Performance data can be obtained by using the PER-

FORMANCE (PERF) page or the performance charts

contained in this chapter.

This chapter contains performance data for

helicopters equipped with T-700-GE-701

engines. Performance data for helicop-

ters equipped with T-700-GE-701C

en-

gines is contained in Chapter 7A.

WARNING

7.1 PERFORMANCE DATA

Do not rely on parameters displayed on

The purpose of this chapter is to provide the best avail-

the PERF page for flight critical perfor-

able performance data for the AH-64D helicopter

mance information until validated by

equipped with 701

engines. Regular use of this in-

hover power check.

formation will allow maximum safe use of the helicop-

ter. Although maximum performance is not always re-

quired, regular use of the information in this chapter is

recommended for the following reasons:

7.2 PERF PAGE

• Knowledge of performance margins will allow

better decisions when unexpected conditions

or alternate missions are encountered.

The aircraft PERF page (fig 7-1) displays both dynamic

and projected performance parameters and operating

• Situations requiring maximum performance will

limitations. Parameters include engine performance,

be readily recognized.

fuel consumption data, and weight and balance in-

formation. The PERF page displays all the controls and

• Familiarity with the data will allow performance

information required to operate the functions of the

to be computed easily and quickly.

performance system. The PERF page is accessed by

• Experience will be gained in accurately estimat-

selecting the PERF button depicted at the top of the

ing the effects of conditions for which data is not

ENG, FLT, FUEL, and UTIL pages or directly from the

presented.

MENU page. Buttons display the status of Pressure Al-

titude (PA), Free Air Temperature (FAT), and Gross

Weight (GWT). The page information will display data

NOTE

based on these conditions and the PERFORMANCE

The information is primarily intended for

(PERF) MODE selection. Selection of any other page

mission planning and is most useful when

will freeze the latest entries to the PERF page display.

planning operations in unfamiliar areas or

Uncompleted entries will be cleared (cancelled).

extreme conditions. The data may also be

Selection of the PERF label at any time during uncom-

used in flight, to establish unit or area

pleted entries will clear (cancel) any uncompleted en-

standing operating procedures, and to in-

tries and return the format to the MENU page. All data

form ground commanders of performan-

entries will be made through the keyboard inputs or

ce/risk trade-offs.

loaded from the DTU.

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

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the CUR perf mode reflect the anti - ice on or off condition

based on the current state of the anti - ice system. Buttons

that are not selectable in the CUR perf mode are:

• L1

PA button

• L2

FAT button

• L3

GWT button

b. MAX Button. The MAX perf mode selection dis-

plays projected performance indications in digital repre-

sentations according to the input of forecast data by the

aircrew through the DTU or Keyboard Unit (KU). Required

entries include: forecast PA, forecast FAT, and forecast

GWT.

c. PLAN Button. The PLAN perf mode selection

will provide the same information as MAX perf mode. The

PLAN information is loaded from either the DTU or the

KU. The DTU is loaded through the AMPS. If the system

for automatic input fails, manual input can be accom-

plished through the PLAN perf mode.

Figure 7-1. MPD PERF Page (MPD)

7.2.2 Hover Torque (HOVER Q) Status Window. The

current hover torque REQUIRED in percent per engine is

The following selections are available on the PERF page

indicated for both In Ground Effect (IGE) and Out of

depending upon PERF MODE selection:

Ground Effect (OGE) conditions based on the current

• T1

ENG button

conditions of PA, FAT, and GWT. The current indicated

engine torque is displayed in a status window below these

• T2

FLT button

digital readouts for real-time comparison. Indicated torque

• T3

FUEL button

will be the greater of the two engines. The indicated

• T6

UTIL button

torque is displayed in color according to operating ranges

as described for the ENG page. Go-No/Go torque is cal-

• L1

PA button

culated on the maximum allowable dual engine gross

• L2

FAT button

weight (para 7.2.4) and it is based on the 5 ft line.

• L3

GWT button

• B1

MENU button

7.2.3 CRUISE Status Window. The following items are

calculated based on the data of PA, FAT, and GWT.

• B2

PERF MODE CUR button

• B3

PERF MODE MAX button

a. Torque (Q) Status. The estimated torque is dis-

• B4

PERF MODE PLAN button

played as indicated percentage torque per engine for both

the maximum range (RNG) and maximum endurance

• B5

HIT button

(END) based on the current conditions of PA, FAT, and

7.2.1 PERF MODE. The PERF MODE controls the sys-

GWT. Range for torque estimate will be from 20 to 100%,

tem calculations being accomplished and consists of

in 1% increments.

three modes of operation, Current (CUR), Maximum

(MAX), and PLAN. Each mode has page buttons, data

b. Fuel Flow (FF) Status. The estimated fuel flow

fields, and control buttons, some of which are not dis-

will be displayed in total pounds per hour for both engines.

played under certain conditions.

It will be displayed for both maximum range (RNG) and

maximum endurance (END) based on the current condi-

a. CUR Button. The CUR perf mode selection dis-

tions of PA, FAT, and GWT. Range will be from 400 to

plays current conditions. Performance data displayed in

1,400 lb/hr in 10 lb increments.

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-2

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7.2.4 Maximum Gross Weight (MAX GWT) Status Win-

NOTE

dow. The maximum allowable gross weight for the condi-

Forward CG will not be displayed forward of

tions of PA, FAT, and torque available will be given in pounds.

201.0

The maximum gross weight readout is displayed in YELLOW

when exceeded by the current aircraft gross weight (GWT).

7.2.8 Center of Gravity (CG) Status. The forward and

Gross weight range will be 11,000 to 23,000 lbs in 10 lb incre-

aft CG limits are displayed along the horizontal bar in the

ments. Weights will be for Dual Engine (DE), Single Engine

CUR perf mode. The actual CG will be displayed under

(SE), for both IGE hover or OGE hover.

CG and a vertical bar will move between the limits in direct

proportion to the actual CG.

7.2.5 True Airspeed (TAS) Status Window. The current

TAS parameters and limitations will be indicated in knots

7.2.9 Weight (WT) Button. The WT button is used to

based on the current conditions of PA, FAT, and GWT. Pa-

call up the weight data entry buttons. This button is dis-

rameters will include TAS velocity not to exceed VNE, (dual

played only in the CUR mode (Figure 7-2).

or single engine), minimum TAS to maintain safe single en-

gine (VSSE) flight, TAS at which the aircraft should cruise in

order to attain maximum RNG, and TAS at which the aircraft

should cruise in order to attain the maximum fuel END or rate

of climb. TAS range is from 0 to 250 kts in 1 knot increments.

See Airspeed Limits (Chapter 5, Section V) for specific val-

ues.

7.2.6

Maximum Torque

(MAX Q) Status Win-

dow. The current engine MAX Q available (30 minute

limit) in percent per engine for DE and SE operation is in-

dicated based on the current conditions of PA, FAT, and

GWT. MAX Q available range is from 0 to 130% in 1% in-

crements. The current engine MAX Q available in percent

per engine for DE and SE operation is indicated based on

the current conditions of PA, FAT, and GWT. Digital read-

outs indicate the actual maximum torque available

derived from dual engine 30 minute limit and single engine

2.5 minute limit chart data. Readouts are displayed in col-

or according to dual and single engine torque limits:

0-100 GREEN

LBA3024

101 - 115 YELLOW

>115 RED

Figure

7-2. PERF Page with WT Selected

0-110 GREEN

• L1

AC BASIC WT/MOMENT button

111 - 125 YELLOW

>125 RED

• L2

LEFT AFT BAY button

MAX Q available range is from 0 to 130% in 1% incre-

• L3

SURVIVAL KIT button

ments.

•

PILOT button

7.2.7 WIND Status Window. The WIND condition will

• L5

CPG button

be displayed in the CUR perf mode to indicate direction

(heading in degrees) from which the wind is coming and

• R1

DUMMY MISSILES button

the speed in knots when wind speed is greater than 5

• R2

DUMMY ROCKETS button

knots, otherwise, the label “CALM” is displayed. When N_R

is less than 50% and wind speed is greater than 45 knots,

a. AC BASIC WT/MOMENT Button. The AC BA-

wind speed is displayed in YELLOW.

SIC WEIGHT data entry button is used for manual entry of

basic weight/moment when data from the DTC and/or de-

• Range for direction: 1 to 360° in 1° increments.

fault basic weight/moment is not accurate. This button is

• Range for wind speed: 0 to 99 knots

displayed only when the WT button is selected. The bot-

in 1 kt increments.

tom mode of this button indicates the aircraft basic weight

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

Change 3

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TM 1-1520-251-10

or moment currently being used by the system for perfor-

displayed only when the WT button is selected. The bot-

mance calculations. These values are stored in memory

tom mode of this button will indicate the CPG weight cur-

and will be updated only when weight data is uploaded

rently being used by the system for performance calcula-

from the DTC. A default value is only used during the first

tions. It is displayed in WHITE when it is the powerup

initialization of the SP or when the weight data in memory

default value (235 lbs).

is corrupted. The button is displayed in WHITE when the

f. DUMMY MISSILES Button. The DUMMY MIS-

default value is being used. The default value for aircraft

SILES button is used to manually enter the number of

with a - 701 engine without a FCR is 12,275 lbs; the de-

“dummy missiles” (M34) loaded on the wing store HF

fault value for aircraft with a - 701C engine with a FCR is

launchers. This button is displayed only when the WT but-

12,836 lbs. Upon completion of the basic weight entry, the

ton is selected. The range value entry is from 0 to 16 mis-

button will reconfigure to the MOMENT data entry. Once

siles. Dummy missiles are not detectable by the system

both the AC BASIC WEIGHT and MOMENT data entries

and, as such, are not accounted for in aircraft gross

are complete, the data will be sent to the SP and the but-

weight calculations. This data entry is used by the SP to

ton will reconfigure to the AC BASIC WEIGHT data entry.

include the weight of dummy missiles in gross weight cal-

culations. The value is stored in memory and will be up-

b. LEFT AFT BAY Button. The LEFT AFT BAY

dated only when manually entered.

button is used for manual entry of weight in the left aft bay

g. DUMMY ROCKETS Button. The DUMMY

when data from the DTC and/or default left aft bay weight

ROCKETS button is used to manually enter the number of

is not accurate. This button is displayed only when the WT

“dummy rockets” loaded in the wing store rocket launch-

button is selected. The bottom mode of this button will in-

ers. This button is displayed only when the WT button is

dicate the left aft bay weight currently being used by the

selected. The range value entry is from 0 to 76 rockets.

system for performance calculations. It is displayed in

Dummy rockets are not detectable by the system and, as

WHITE when it is the powerup default value (0 lbs).

such, are not accounted for in aircraft gross weight cal-

culations. This data entry is used by the SP to include the

c. SURVIVAL KIT Button. The SURVIVAL KIT

weight of dummy rockets in gross weight calculations.

button is used for manual entry of weight in the survival kit

The value is stored in memory and will be updated only

bay when data from the DTC and/or default survival kit

when manually entered.

bay weight is not accurate. This button is displayed only

7.3 ETF PAGE

when the WT button is selected. The bottom mode of this

button will indicate the survival kit bay weight currently be-

The engine torque factor (ETF) page is used to perform

ing used by the system for performance calculations. It is

the maximum power check for the T701 engine. The pur-

displayed in WHITE when it is the powerup default value

pose of this check is to determine the ETF for each en-

(0 lbs).

gine. The torque factor method of performing the maxi-

mum power check provides an accurate indication of

d. PILOT Button. The PILOT button is used for

available power by incorporating ambient temperature ef-

manual entry of weight for the pilot when data from the

fects into the power available calculation. The intent of the

DTC and/or default pilot weight is not accurate. This but-

ETF is to provide the system a numerical health value

ton is displayed only when the WT button is selected. The

upon which performance computations can be derived us-

bottom mode of this button will indicate the pilot weight

ing performance algorithms and tables within the system

currently being used by the system for performance cal-

processors. This maintenance procedure is described in

culations. It is displayed in WHITE when it is the powerup

TM 55 - 2840 - 251 - 23.

default value (235 lbs).

Selecting ETF page button (B3) displays the ETF page

with button controls necessary to initiate power check and

e. CPG Button. The CPG button is used for manu-

the 701 TORQUE FACTOR status window which contains

al entry of weight for the CPG when data from the DTC

current ETF/ATF values: aircraft (ACFT), engine 1

and/or default pilot weight is not accurate. This button is

(ENG1), and engine 2 (ENG2) (fig 7-3 ).

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-4

Change 3

TM 1-1520-251-10

pressure altitude (PA) and free air temperature (FAT).

This selection also displays the LAST and TEST buttons

at the bottom of the format (fig 7-4).

LBA3025

Figure 7-3. ETF Page

LBA3026

The following selections are available on the ETF page:

• T2

FLT button

Figure 7-4. ENG1 Selected

• T3

FUEL button

7.3.2 LAST Topping Check Button. The LAST button

• T4

PERF button

(B4) is used to call up the last test results. Selecting the

• T6

UTIL button

LAST button displays the LAST TOPPING CHECK status

• L5

ENG1 button

window. This contains a list of engine and ambient condi-

tions of the last maximum power check performed on the

• L6

ETF1 button

selected engine (fig 7-5):

• R5

ENG2 button

• date (MM/DD/YY)

• R6

ETF2 button

• engine TORQUE

• B3

ETF button

• Target Torque Value (TTV)

7.3.1 Engine 1 and 2 Buttons. ENG1 and ENG2 but-

tons are used to select an engine for the maximum power

• indicated airspeed (IAS)

check. Selecting the ENG1 or ENG2 button sets the sys-

• engine TGT, NG, and NP

tem for a maximum power check and displays the TOP-

PING CHECK status window for the selected engine:

• PA and FAT

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-5

TM 1-1520-251-10

• Engine TORQUE, Target Torque Value (TTV),

indicated airspeed (IAS), engine TGT, N_G, and N_P,

PA and FAT

LBA5249

Figure 7-5. Last Selected

LBA5250

7.3.3 Engine TEST Button. The TEST button (B5) is

used to initiate a test once flight parameters are achieved.

Figure

7-6.

ENG1 Selected

Selecting the TEST button commands the SP to perform

power check calculations to derive the ETF for the se-

lected engine. Results of the test are displayed as either

the TOPPING CHECK ABORTED status window (fig 7-6)

or the TOPPING CHECK COMPLETE status window (fig

7-7).

a. Test Aborted Indication. An aborted test will

display the RESET button (B6) and the ENG1 or ENG2

TOPPING CHECK TEST ABORTED, DATA NOT VALID

status window which is displayed to provide an indication

that the engine test was aborted due to invalid data (fig

7-6).

b. Test Complete Indication. A completed test will

display the STORE and RESET buttons (B5, B6) and the

ENG1 or ENG2 TOPPING CHECK TEST COMPLETE

status window which contains current data for a valid test

performed on the selected engine (fig 7-7).

• ETF1 or ETF2 PASS/FAIL indication with ETF

value and difference value from last check

LBA3029

• ATF1 or ATF2 PASS/FAIL indication with ATF

value and difference value from last check

Figure

7-7.

Test Complete Indication

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-6

TM 1-1520-251-10

7.3.4 STORE Button. The power check STORE button

7.6.2 Reading the Charts. The primary use of each

(B5) is used to store the test values. Selecting the STORE

chart is given in the example and a guideline is provided to

button commands the SP to store test data for the se-

help you follow the route through the chart. The use of a

lected engine in non - volatile memory and in the mainte-

straight edge (ruler or page edge) and a hard fine-point

nance data recorder (MDR). In addition, this selection re-

pencil is recommended to avoid cumulative errors. The

turns the format to the top level ETF page.

majority of the charts provide a standard pattern for use as

follows: Enter first variable on top left scale, move right to

second variable, deflect down at right angles to third vari-

7.3.5 RESET Button. The power check RESET button

able, deflect left at right angles to fourth variable, and de-

(B6) is provided as an alternative to storing test data. Se-

flect down, etc., until final variable is read out at final

lecting the RESET button returns the format to the former

scale. In addition to the primary use, other uses of each

state (prior to performing the test).

chart are explained in the text accompanying each set of

performance charts. Correct operating limits can also be

7.4 PERFORMANCE DATA - GENERAL

found in Chapter 5. Abbreviations and symbols used in

the charts are listed in Appendix B.

The data presented covers the maximum range of condi-

NOTE

tions and performance that can reasonably be expected.

In each area of performance, the effects of altitude, tem-

An example of an auxiliary use of the per-

perature, gross weight, and other parameters relating to

formance charts follows: Although the hover

that phase of flight are presented. In addition to the pres-

chart is primarily arranged to find the torque

ented data, judgement and experience will be necessary

required to hover, maximum wheel height

to accurately determine performance under a given set of

for hover can also be found by entering

circumstances. The conditions for the data are listed un-

torque available as torque required. In gen-

der the title of each chart. The effects of different condi-

eral, any single variable can be found if all

tions are discussed in the text accompanying each phase

others are known. Also, the trade-offs be-

of performance. Where practical, data is presented at

tween two variables can be found. For ex-

conservative conditions. However, NO GENERAL CON-

ample, at a given density altitude and pres-

SERVATISM HAS BEEN APPLIED.

sure altitude, you can find the maximum

gross weight capability as free air tempera-

ture changes.

7.5 LIMITS

7.7 SPECIFIC CONDITIONS

CAUTION

The data presented is accurate only for specific conditions

listed under the title of each chart. Variables for which data

is not presented, but which may affect that phase of per-

Exceeding operating limits can cause

formance, are discussed in the text. Where data is avail-

permanent damage to critical compo-

able or reasonable estimates can be made, the amount

nents and can decrease performance,

that each variable affects performance is given.

cause immediate failure, or failure on a

subsequent flight.

7.8 GENERAL CONDITIONS

Applicable limits are shown on the charts as bold lines.

In addition to the specific conditions, the following general

Performance generally deteriorates rapidly beyond limits.

conditions are applicable to the performance data:

If limits are exceeded, minimize the amount and time. En-

7.8.1 Rigging. All airframe and engine controls are as-

ter the maximum value and time beyond limits on DA

sumed to be rigged within allowable tolerances.

Form 2408-13-1 so proper maintenance action can be

taken.

7.8.2

Pilot Technique. Normal pilot technique is as-

sumed. Control movements should be smooth and contin-

7.6 USE OF CHARTS

uous.

7.8.3 Aircraft Variation. Variations in performance be-

7.6.1 Chart Explanation. The first page of each sec-

tween individual helicopters are known to exist. The ma-

tion describes the chart or charts in that section, and ex-

jority of variation can be accounted for through the use of

plains how each chart is used.

Engine Torque Factors and Aircraft Torque Factors.

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-7

TM 1-1520-251-10

7.8.4

Instrument Variation. The data shown in the

by comparing actual performance with planned perform-

performance charts does not account for instrument inac-

ance. Knowledge will also be gained concerning the ef-

curacies or malfunctions.

fects of variables for which data is not provided, thereby

increasing the accuracy of performance predictions.

7.8.5

Configuration. Except as otherwise noted, all

7.10 TEMPERATURE CONVERSION

data is for the primary mission configuration consisting of

the basic helicopter configured with Aircraft Survival

A temperature conversion chart (fig 7-8) is included in the

Equipment (ASE) plus a pylon and a fully loaded hellfire

section for the purpose of converting Fahrenheit (F) tem-

missile launcher on each inboard stores station, and no

peratures to Celsius (C).

pylons or stores on outboard stations.

7.11 ABBREVIATIONS

Appendix B is a list of abbreviations and symbols used on

7.9 PERFORMANCE DISCREPANCIES

the charts in this chapter, as well as throughout the entire

operators manual. For units of measure, the same abbre-

Regular use of this chapter will also allow monitoring in-

viation applies to either the singular or plural form of the

struments and other helicopter systems for malfunction,

unit.

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-8

TM 1-1520-251-10

Section II. MAXIMUM TORQUE AVAILABLE

7.12 DESCRIPTION

of either the 30-minute or the 2.5-minute chart at the

known FAT and move right to the known pressure altitude,

The maximum torque available chart (fig 7-9) shows the

and then move down and read the maximum torque avail-

maximum torque available per engine for 30-minute op-

able. This is torque per engine. For dual-engine operation,

eration at various conditions of pressure altitude and Free

if the torque per engine exceeds the two-engine limit, the

Air Temperature (FAT). Both single and dual-engine oper-

maximum torque available must be reduced to the two-

ation limits are shown.

engine limit.

Figure 7-10 shows the maximum torque available for

2.5-minute operation when one engine is inoperative; only

single engine operation limits are shown.

7.14 CONDITIONS

The torque factor charts (figs 7-11 and 7-12) provide an

accurate indication of available power for the engines

installed in each individual aircraft.

These charts are based on 101% rotor RPM, zero air-

speed, JP-8 fuel, and ENG INLET ANTI-ICE system OFF.

7.13 USE OF CHARTS

With ENG INLET ANTI-ICE system ON, available torque

is reduced by as much as 16.8% for 30-minute operation

The primary use of the charts is illustrated by the example.

and 11.0% for 2.5-minute operation. For example, if the

To determine the maximum torque available, it is neces-

value from the 30-minute chart is 90%, with ANTI-ICE ON,

sary to know pressure altitude and FAT. Enter the left side

torque available would be 90 - 16.8 = 73.2%.

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-10

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TORQUE FACTOR

AH64D

T700GE701

T700-GE-701 ENGINE, 101% RPM

EXAMPLE

WANTED

TO CALCULATE MAXIMUM TORQUE AVAILABLE:

4. ENTER MAXIMUM TORQUE AVAILABLE CHART 30 MIN LIMIT

TORQUE RATIO AND MAXIMUM TORQUE AVAILABLE

(FIGURE 7−9 ) AT KNOWN FAT

30MIN LIMIT

5. MOVE RIGHT TO KNOWN PRESSURE ALTITUDE

KNOWN

6. MOVE DOWN, READ SPECIFICATION TORQUE = 97.5%

ATF = .95

PRESSURE ALTITUDE = 4000 FT

TO OBTAIN ACTUAL TORQUE VALUE AVAILABLE FROM THE

FAT = + 20 °C

TORQUE CONVERSION CHART (FIGURE 7−12):

METHOD

7. ENTER TORQUE CONVERSION CHART AT %

TO OBTAIN TORQUE RATIO

TORQUE OBTAINED FROM 30MIN LIMIT CHART

8. MOVE UP TO TORQUE RATIO OBTAINED FROM TORQUE

1. ENTER TORQUE FACTOR CHART AT KNOWN FAT

FACTOR CHART

2. MOVE RIGHT TO THE ATF VALUE

9. MOVE LEFT, READ MAXIMUM TORQUE AVAILABLE = 94.3%

3. MOVE DOWN, READ TORQUE RATIO = .967

TORQUE FACTOR ≈ ATF OR ETF

.85

.86

.87

.88

.89

.90

.91

.92

.93

.94

.95

.96

.97

.98

.99

1.0

FOR FAT’S

OF 35 °C AND

ABOVE:

TR = ATF

.85

.86

.87

.88

.89

.90

.91

.92

.93

.94

.95

.96

.97

.98

.99

1.0

TORQUE RATIO ~ TR

DATA BASE: CALCULATED

LBA2556A

Figure 7-11. Torque Factor Chart

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

Change 4

7-13

TM 1-1520-251-10

Section III. HOVER CEILING

7.15 DESCRIPTION

to the desired wheel height, and then move left and read

maximum gross weight.

The hover ceiling chart (fig 7-13) presents the maximum

gross weight for hover at various conditions of pressure

7.17 CONDITIONS

altitude, Free Air Temperature (FAT), and wheel height,

using maximum torque available, 30-minute limit.

The hover ceiling chart is based on maximum torque

available 30-minute limit, ATF = 1.0, 101% rotor RPM, and

7.16 USE OF CHART

ENG INLET anti-ice system OFF. For ENG INLET ANTI-

ICE system ON, use dashed lines. Applicable configura-

The primary use of the chart is illustrated by the example.

tion is all external stores except auxiliary fuel tanks. For

To determine the maximum gross weight for hover, it is

the four auxiliary tank configuration, reduce the maximum

necessary to know the pressure altitude, FAT, and desired

gross weight for hover as calculated from the hover ceiling

wheel height. Enter the appropriate power available chart

chart by 10.8 lbs for each 1000 lbs of gross weight. See

at the pressure altitude, move right to the FAT, move down

example below:

HOVER CEILING

EXAMPLE

WANTED

METHOD

ENTER PRESSURE ALTITUDE SCALE AT 8,000 FT

MAXIMUM GROSS WEIGHT FOR HOVER AT 10-FOOT

MOVE RIGHT TO +10 °C FAT, SOLID LINE FOR

WHEEL HEIGHT, 30-MINUTE LIMIT TORQUE

ANTI-ICE OFF, DASHED LINE FOR ANTI-ICE ON

AVAILABLE, FOR ENGINE INLET ANTI-ICE OFF AND

MOVE DOWN TO 10 FEET WHEEL HEIGHT

MOVE LEFT TO READ GROSS WEIGHT FOR HOVER:

ANTI-ICE OFF, HOVER GW = 17,150 LB

KNOWN

ANTI-ICE ON, HOVER GW = 15,040 LB

WITH 4 EXT TANKS INSTALLED

PRESSURE ALTITUDE = 8,000 FEET

ANTI-ICE OFF

FAT = +10 °C

HOVER GW = 17,150 - 10.8 (17,150/1000)

WHEEL HEIGHT = 10 FEET

= 16,965 LB

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

Change 4

7-15

TM 1-1520-251-10

Section IV. HOVER

7.18 DESCRIPTION

necessary to know pressure altitude, FAT, gross weight,

and maximum torque available. Enter at the known pres-

The hover chart (fig 7-14) presents the torque required to

sure altitude, move right to the FAT, move down to the

hover at various conditions of pressure altitude, Free Air

gross weight, then move left to intersection with maximum

Temperature (FAT), gross weight, wheel height, and with

torque available and read wheel height. This wheel height

or without external tanks.

is the maximum hover height.

7.19 USE OF CHART

7.19.3 Maximum Gross Weight. The hover chart may

also be used to determine the maximum gross weight for

7.19.1

Chart Explanation. The primary use of the

hover at a given wheel height, pressure altitude, and FAT

chart is illustrated by the example. To determine the

condition. Enter at the known pressure altitude, move

torque required to hover, it is necessary to know the pres-

right to the FAT, then move down to the bottom of the low-

sure altitude, FAT, gross weight and desired wheel height.

er grid and read density altitude. Now enter upper left grid

Enter the upper right grid at the known pressure altitude,

at maximum torque available, move down to wheel height,

move right to the FAT, move down to the gross weight,

and then move right to density altitude and read gross

move left to the desired wheel height and then move up

weight. This is the maximum gross weight at which the he-

and read the torque required to hover.

licopter will hover.

7.19.2 Maximum Hover Height. In addition to its pri-

7.20 CONDITIONS

mary use, the hover chart may be used to predict the max-

imum hover height. This capability is needed for use of the

The hover chart is based on calm wind, level surface, and

takeoff chart. To determine maximum hover height, it is

101% rotor RPM.

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-17

TM 1-1520-251-10

Section V. CRUISE

7.21 DESCRIPTION

torque available, 30-minutes maximum torque available,

and maximum torque available single engine limit, when

The cruise charts (figs 7-15 thru 7-25) present the level

less than the two-engine transmission limit. These torque

flight torque required and total fuel flow at various condi-

lines are the minimum torque available at the engine tur-

tions of airspeed, pressure, pressure altitude, Free Air

bine gas temperature limits specified in Chapter 5. Higher

Temperature (FAT), and gross weight. Cruise charts are

torque than that represented by these lines may be used

provided for pressure altitudes from sea level to 16,000

if it is available without exceeding the limitations pres-

feet in 2000-foot increments. FAT range from -50° C to

ented in Chapter 5. The limit torque line shown on these

+60° C in 10° C increments. In addition to basic cruise in-

charts is for the dual engine transmission limit and is de-

formation, maximum endurance, and maximum rate of

fined as 100% torque. An increase or decrease in torque

climb. Change in torque with change in frontal area in-

required because of a drag area change is calculated by

formation is presented in the upper left corner of each

adding or subtracting the change in torque from the torque

chart.

change (∆Q) curve on the chart, and then reading the new

fuel flow total.

7.22 USE OF CHARTS

7.22.3 Fuel Flow. Fuel flow scales are provided oppo-

site the torque scales. On any chart, torque may be con-

The primary use of the charts are illustrated by the exam-

verted directly to fuel flow without regard to other chart in-

ples. To use the charts, it is usually necessary to know the

formation. Sea level ground fuel flow at flat pitch and

planned pressure altitude, estimated FAT, planned cruise

101% N_P is approximately 555 pounds per hour.

speed, TAS and gross weight. First select the proper chart

on the basis of pressure altitude and FAT. Enter the chart

7.22.4 Maximum Range. The maximum range lines in-

at the cruise airspeed IAS, move right and read TAS,

dicate the combinations of gross weight and airspeed that

move left to the gross weight, move down and read torque

will produce the greatest flight range per pound of fuel un-

required, and then move up and read associated fuel flow.

der zero wind conditions.

Maximum performance conditions are determined by en-

tering the chart where the maximum range line or the

7.22.5 Maximum Endurance and Rate of Climb. The

maximum rate-of-climb intersect the gross weight line;

maximum endurance and rate of climb lines indicate the

then read airspeed, fuel flow, and torque required. Nor-

combinations of gross weight and airspeed that will pro-

mally sufficient accuracy can be obtained by selecting the

duce the maximum endurance and the maximum rate of

chart nearest the planned cruise attitude and FAT or, more

climb. The torque required for level flight at this condition

conservatively, by selecting the chart with the next higher

is a minimum, providing a minimum fuel flow (maximum

altitude and FAT. If greater accuracy is required, interpola-

endurance) and a maximum torque change available for

tion between altitudes and/or temperatures is permissible.

climb (maximum rate of climb).

To be conservative, use the gross weight chart at the be-

ginning of the cruise flight. For greater accuracy on long

7.22.6 Change in Frontal Area. Since the cruise in-

flights, however, it is preferable to determine cruise in-

formation is given for the primary mission configuration,

formation for several flight segments to allow for the de-

adjustments to torque should be made when operating

creasing gross weight.

with alternative wing-stores configurations. To determine

the change in torque, first obtain the appropriate multiply-

7.22.1

Airspeed. True and indicated airspeeds are

ing factor from the drag chart (figure 7-26), then enter the

presented at the opposite sides of each chart. On any

cruise chart at the planned cruise speed TAS, move right

chart, obtain indicated airspeed (or vice versa) by reading

to the broken nQ line, and move up and read nQ. Multiply

directly across the chart without regard for the other chart

nQ by the multiplying factor to obtain change in torque,

information.

then add or subtract change in torque from torque re-

quired for the primary mission configuration. Enter the

7.22.2 Torque. Since pressure altitude and FAT are

cruise chart at resulting torque required, move up, and

fixed for each chart, torque required varies according to

read fuel flow. If the resulting torque required exceeds the

gross weight and airspeed. The torque required and the

governing torque limit, the torque required must be re-

torque limits shown on these charts are for dual-engine

duced to the limit. The resulting reduction in airspeed may

operation. The torque available shown on these charts

be found by subtracting the change in torque from the limit

are maximum continuous torque available, maximum

torque; then enter the cruise chart at the reduced torque,

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-19

TM 1-1520-251-10

and move up to the gross weight. Move left or right to read

7.23 CONDITIONS

TAS or IAS. To determine the airspeed for maximum

The cruise charts are based on 101% rotor RPM, ENG IN-

range for alternative wing stores configuration, reduce the

LET ANTI-ICE switch OFF, JP-8 fuel, and dual engine op-

value from the cruise chart by 2 knots for each 5 square

eration. Engine inlet anti-ice effects are as follows:

feet increase in drag area, nF, or increase maximum

range airspeed 2 knots for each 5 square feet reduction in

7.23.1 ENG INLET ANTI-ICE ON. With ENG INLET

drag area. For example, for 16 Hellfire configuration nF =

ANTI-ICE ON, fuel flow will increase between approxi-

7.6 square feet, from (figure 7-26). Therefore, maximum

mately 45 pounds per hour at 30% torque and 60 pounds

range airspeed would be reduced by 2/5 x 7.6 =3.04

per hour at 100% torque. Maximum torque available

knots, or approximately 3 knots.

30-minute limit could be reduced by as much as 16.8%,

and maximum torque available 2.5-minute limit could be

reduced by as much as 11.0%.

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-20

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE SEA LEVEL

T700GE701C

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +10°C

INDICATED

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

700

900

1100

1300

170

∆Q %

∆ F = 10.0 SQ FT

170

160

150

EXAMPLE

140

WANTED

140

TORQUE REQUIRED AND FUEL FLOW

FOR 76 ROCKET CONFIGURATION

130

KNOWN

130

PRESSURE ALTITUDE=S.L., FAT = +10 °C.

120

GW = 14,000 LB. 4 LOADED ROCKET

MAX

RANGE

120

LAUNCHERS (76 ROCKETS), IAS = 140 KT

METHOD

110

FROM DRAG CHART (FIG 7−26) OBTAIN

110

MULTIPLYING FACTOR = 0.27

100

ENTER CRUISE CHART AT IAS = 140 Kt

MOVE RIGHT TO BROKEN D Q LINE

100

MOVE UP TO READ D Q = 11.5%

MULTIPLY D Q BY MULTIPLYING FACTOR

TO GET CHANGE IN TORQUE = 3.1

REENTER CRUISE CHART AT IAS = 140 Kt

MOVE RIGHT TO GW = 14,000 LB

MOVE DOWN AND READ INDICATED

TORQUE PER ENGINE=94.0%

MAX R/C

TORQUE REQUIRED = 94.0 3.1 = 90.9%

REENTER CRUISE CHART AT 91%

MAX END

MOVE UP AND READ FUEL FLOW = 1335 LB/HR.

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC No. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA0195

Figure 7-15. Cruise Chart, Example

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-21

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE SEA LEVEL

T700GE701C

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT=+10°C

INDICATED

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

700

900

1100

1300

EXAMPLE I

170

∆Q %

WANTED

∆ F = 10.0 SQ FT

170

TORQUE REQUIRED, AIRSPEED, AND FUEL FLOW

160

FOR MAXIMUM RANGE.

KNOWN

160

PRESSURE ALTITUDE = SL, FAT=+10 °C, AND

150

GROSS WEIGHT = 14,000 POUNDS.

150

METHOD

AT THE INTERSECTION OF THE MAXIMUM RANGE

140

LINE AND THE 14,000 POUND LINE

140

MOVE LEFT, READ IAS = 114 KT.

MOVE RIGHT, READ TAS = 120 KT.

130

MOVE UP, READ TOTAL FUEL FLOW = 1000 LB/HR.

130

MOVE DOWN, READ INDICATED TORQUE/ENGINE = 61%.

120

MAX

EXAMPLE II

RANGE

WANTED

120

TORQUE REQUIRED, AIRSPEED, AND FUEL FLOW

110

FOR MAXIMUM ENDURANCE.

110

KNOWN

PRESSURE ALTITUDE = SL, FAT = +10 °C, AND

100

GROSS WEIGHT = 14,000 POUNDS.

100

METHOD

AT THE INTERSECTION OF THE MAXIMUM RANGE

LINE AND THE 14,000 POUND LINE

MOVE LEFT, READ IAS = 58 KT.

MOVE RIGHT, READ TAS = 64 KT.

MOVE UP, READ TOTAL FUEL FLOW = 740 LB/HR.

MOVE DOWN, READ INDICATED TORQUE/ENGINE = 35%.

MAX R/C

EXAMPLE III

MAX END

(INTERPOLATION NOT ILLUSTRATED)

WANTED

TORQUE REQUIRED, AIRSPEED, AND FUEL FLOW,

AND TORQUE.

KNOWN

PRESSURE ALTITUDE = 1000 FEET FAT = +15 °C,

AND GROSS WEIGHT = 14000 POUNDS.

METHOD

READ AIRSPEED, TORQUE, AND FUEL FLOW FOR EACH

ADJACENT ALTITUDE AND FAT, THEN INTERPOLATE

BETWEEN FAT AND ALTITUDE AS FOLLOWS:

SOLUTION:

ALTITUDE

SEA LEVEL

2000 FEET

1000 FEET

FAT

TORQUE

FUEL FLOW

740

720

715

730

IAS

58.5

TAS

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC No. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA0196

Figure 7-16. Cruise Chart, Sea Level, +10°C Example

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-22

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE SEA LEVEL

T700GE701C

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 50°C

FAT = 40°C

TOTAL FUEL FLOW LB/HOUR

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

KNOTS

700

900

1100

1300

700

900

1100

1300

170

∆Q %

∆ F = 10.0 SQ FT

150

160

150

140

150

140

130

140

130

120

130

120

MAX

RANGE

120

110

RANGE

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA5251

Figure 7-17. Cruise Chart, Sea Level, - 50°C and - 40°C (sheet 1 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-23

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE SEA LEVEL

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 30°C

FAT = 20°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

700

900

1100

1300

700

900

1100

1300

170

160

∆Q %

∆ F = 10.0 SQ FT

160

150

140

130

120

MAX

120

RANGE

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2459

Figure 7-17. Cruise Chart, Sea Level, - 30°C and - 20°C (sheet 2 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-24

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE SEA LEVEL

T700GE701

101% NR RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 10° C

FAT = 0° C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

700

900

1100

1300

700

900

1100

1300

170

∆Q %

170

∆ F = 10.0 SQ FT

160

150

140

130

MAX

120

MAX

RANGE

120

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA5252

Figure 7-17. Cruise Chart, Sea Level, - 10°C and 0°C (sheet 3 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-25

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE SEA LEVEL

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +10°C

FAT = +20°C

INDICATED

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

700

900

1100

1300

700

900

1100

1300

170

∆Q %

170

∆ F = 10.0 SQ FT

170

160

150

140

130

120

MAX

RANGE

MAX

120

RANGE

120

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA5253

Figure 7-17. Cruise Chart, Sea Level, +10°C and +20°C (sheet 4 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-26

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE SEA LEVEL

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +30°C

FAT = +40°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

700

900

1100

1300

KNOTS

700

900

1100

1300

180

170

∆Q %

180

∆ F = 10.0 SQ FT

170

160

170

160

150

160

150

140

150

140

130

140

130

120

130

MAX

120

110

RANGE

120

110

100

110

100

MAX

R/C

MAX

R/C

MAX

END

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2462

Figure 7-17. Cruise Chart, Sea Level, +30°C and +40°C (sheet 5 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-27

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE SEA LEVEL

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +50°C

FAT = +60°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

700

900

1100

1300

KNOTS

700

900

1100

1300

170

∆Q %

∆ F = 10.0 SQ FT

180

160

170

150

160

140

150

130

140

120

130

MAX

110

RANGE

120

100

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

LBA2463

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

Figure 7-17. Cruise Chart, Sea Level, +50°C and +60°C (sheet 6 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-28

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 2000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 50°C

FAT = 40°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

700

900

1100

1300

700

900

1100

1300

170

160

∆Q %

∆ F = 10.0 SQ FT

160

150

140

130

120

MAX

120

MAX

RANGE

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2464

Figure 7-18. Cruise Chart, 2,000 Feet, - 50°C and - 40°C (sheet 1 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-29

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 2000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 30°C

FAT = 20°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

700

900

1100

1300

700

900

1100

1300

170

∆Q %

170

∆ F = 10.0 SQ FT

160

150

140

130

120

MAX

120

MAX

RANGE

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2465

Figure 7-18. Cruise Chart, 2,000 Feet, - 30°C and - 20°C (sheet 2 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-30

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 2000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 10°C

INDICATED

FAT = 0°C

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

TOTAL FUEL FLOW LB/HOUR

700

900

1100

1300

700

900

1100

1300

170

∆Q %

170

∆ F = 10.0 SQ FT

170

160

150

140

130

120

MAX

RANGE

120

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2466

Figure 7-18. Cruise Chart, 2,000 Feet, - 10°C and 0°C (sheet 3 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-31

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 2000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +10°C

INDICATED

FAT = +20°C

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

TOTAL FUEL FLOW LB/HOUR

700

900

1100

1300

700

900

1100

1300

180

∆Q %

170

∆Q %

∆ F = 10.0 SQ FT

180

170

160

170

160

150

160

150

140

150

140

130

140

130

120

130

MAX

RANGE

MAX

120

110

RANGE

120

110

100

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2467

Figure 7-18. Cruise Chart, 2,000 Feet, +10°C and +20°C (sheet 4 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-32

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 2000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +30°C

FAT = +40°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

700

900

1100

1300

700

900

1100

1300

170

DQ %

D F = 10.0 SQ FT

180

160

180

170

150

160

140

150

130

140

120

130

MAX

RANGE

130

110

120

100

110

100

MAX

100

R/C

MAX

R/C

MAX

END

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2468

Figure 7-18. Cruise Chart, 2,000 Feet, +30°C and +40°C (sheet 5 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-33

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 2000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +50°C

FAT = +60°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

KNOTS

700

900

1100

1300

700

900

1100

1300

170

∆Q %

∆ F = 10.0 SQ FT

160

180

150

170

160

140

160

150

130

150

140

120

140

MAX

130

RANGE

110

130

120

100

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2469

Figure 7-18. Cruise Chart, 2,000 Feet, +50°C and +60°C (sheet 6 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-34

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 4000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 50°C

FAT = 40°C

INDICATED

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

TOTAL FUEL FLOW LB/HOUR

600

800

1000

1200

600

800

1000

1200

170

∆Q %

∆ F = 10.0 SQ FT

160

150

140

130

120

MAX

RANGE

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2470

Figure 7-19. Cruise Chart, 4,000 Feet, - 50°C and - 40°C (sheet 1 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-35

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 4000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 30°C

FAT = 20°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

KNOTS

600

800

1000

1200

600

800

1000

1200

170

∆Q %

170

∆ F = 10.0 SQ FT

170

160

150

140

130

120

MAX

120

RANGE

110

RANGE

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2471

Figure 7-19. Cruise Chart, 4,000 Feet, - 30°C and - 20°C (sheet 2 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-36

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 4000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 10°C

FAT = 0°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

600

800

1000

1200

600

800

1000

1200

180

∆Q %

170

∆Q %

∆ F = 10.0 SQ FT

180

170

160

170

160

150

160

150

140

150

140

130

140

130

120

130

MAX

120

MAX

110

RANGE

120

RANGE

110

100

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2472

Figure 7-19. Cruise Chart, 4,000 Feet, - 10°C and 0°C (sheet 3 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-37

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 4000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +10°C

FAT = +20°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

700

900

1100

1300

700

900

1100

1300

170

∆Q %

∆ F = 10.0 SQ FT

180

160

180

170

150

170

160

140

150

130

140

120

130

110

MAX

120

RANGE

120

100

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2473

Figure 7-19. Cruise Chart, 4,000 Feet, +10°C and +20°C (sheet 4 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-38

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 4000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +30°C

FAT = +40°C

TOTAL FUEL FLOW LB/HOUR

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

700

900

1100

1300

KNOTS

700

900

1100

1300

170

∆Q %

∆ F = 10.0 SQ FT

160

180

150

170

140

160

150

130

150

140

120

140

130

110

130

MAX

RANGE

120

100

120

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2474

Figure 7-19. Cruise Chart, 4,000 Feet, +30°C and +40°C (sheet 5 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-39

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 4000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +50°C

FAT = +60°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

700

900

1100

1300

KNOTS

700

900

1100

1300

170

∆Q %

∆ F = 10.0 SQ FT

160

180

150

180

170

140

160

130

150

120

140

110

130

MAX

130

RANGE

100

120

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2475

Figure 7-19. Cruise Chart, 4,000 Feet, +50°C and +60°C (sheet 6 of 6)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-40

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 6000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 50°C

FAT = 40°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

600

800

1000

1200

KNOTS

600

800

1000

1200

170

∆Q %

170

∆ F = 10.0 SQ FT

170

160

150

140

130

120

MAX

120

MAX

RANGE

110

RANGE

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2476

Figure 7-20. Cruise Chart, 6,000 Feet, - 50°C and - 40°C (sheet 1 of 5)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-41

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 6000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 30°C

FAT = 20°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

600

800

1000

1200

600

800

1000

1200

180

170

∆Q %

∆ F = 10.0 SQ FT

180

170

160

170

160

150

160

150

140

150

140

130

140

130

120

130

120

MAX

110

MAX

RANGE

120

RANGE

110

100

110

100

MAX

R/C

MAX

R/C

MAX

END

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2477

Figure 7-20. Cruise Chart, 6,000 Feet, - 30°C and - 20°C (sheet 2 of 5)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-42

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 6000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 10°C

FAT = 0°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

600

800

1000

1200

KNOTS

600

800

1000

1200

170

∆Q %

∆ F = 10.0 SQ FT

180

160

180

170

150

170

160

140

150

130

140

120

130

MAX

110

RANGE

120

100

110

100

MAX

R/C

MAX

R/C

END

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2478

Figure 7-20. Cruise Chart, 6,000 Feet, - 10°C and 0°C (sheet 3 of 5)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-43

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 6000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +10°C

FAT = +20°C

TOTAL FUEL FLOW LB/HOUR

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

KNOTS

600

800

1000

1200

600

800

1000

1200

170

∆Q %

∆ F = 10.0 SQ FT

160

180

150

170

140

160

150

130

150

140

120

140

130

110

130

MAX

RANGE

120

RANGE

100

120

110

100

MAX

R/C

MAX

R/C

END

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2479

Figure 7-20. Cruise Chart, 6,000 Feet, +10°C and +20°C (sheet 4 of 5)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-44

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 6000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +30°C

FAT = +40°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

600

800

1000

1200

600

800

1000

1200

170

∆Q %

∆ F = 10.0 SQ FT

160

180

150

180

170

140

170

160

130

150

120

140

110

130

MAX

130

RANGE

100

120

110

100

MAX

R/C

MAX

END

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2480

Figure 7-20. Cruise Chart, 6,000 Feet, +30°C and +40°C (sheet 5 of 5)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-45

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 8000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 50°C

FAT = 40°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

KNOTS

600

800

1000

1200

600

800

1000

1200

180

170

∆Q %

180

∆ F = 10.0 SQ FT

170

160

170

160

150

160

150

140

150

140

130

140

130

120

130

MAX

120

110

MAX

RANGE

120

RANGE

110

100

110

100

MAX

R/C

MAX

R/C

MAX

END

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2481

Figure 7-21. Cruise Chart, 8,000 Feet, - 50°C and - 40°C (sheet 1 of 5)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-46

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 8000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 30°C

FAT = 20°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

600

800

1000

1200

KNOTS

600

800

1000

1200

170

∆Q %

∆ F = 10.0 SQ FT

180

160

180

170

150

170

160

140

160

150

130

140

120

130

MAX

110

MAX

120

RANGE

120

100

110

100

MAX

R/C

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2482

Figure 7-21. Cruise Chart, 8,000 Feet, - 30°C and - 20°C (sheet 2 of 5)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-47

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 8000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = 10°C

FAT = 0°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

600

800

1000

1200

600

800

1000

1200

170

∆Q %

∆ F = 10.0 SQ FT

160

180

150

170

140

160

130

150

140

120

140

MAX

RANGE

130

110

130

120

100

120

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA5256

Figure 7-21. Cruise Chart, 8,000 Feet, - 10°C and 0°C (sheet 3 of 5)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-48

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 8000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +10°C

FAT = +20°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

TOTAL FUEL FLOW LB/HOUR

KNOTS

600

800

1000

1200

600

800

1000

1200

170

∆Q %

∆ F = 10.0 SQ FT

160

180

150

180

170

140

170

160

130

160

150

120

140

110

130

MAX

130

RANGE

MAX

100

RANGE

120

110

100

MAX

R/C

MAX

END

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2484

Figure 7-21. Cruise Chart, 8,000 Feet, +10°C and +20°C (sheet 4 of 5)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-49

TM 1-1520-251-10

CRUISE

AH64D

PRESSURE ALTITUDE 8000 FEET

T700GE701

101% N_R RPM, 8 HELLFIRE CONFIGURATION, JP8 FUEL

FAT = +30°C

FAT = +40°C

INDICATED

TOTAL FUEL FLOW LB/HOUR

AIRSPEED

KNOTS

600

800

1000

1200

600

800

1000

1200

170

∆Q %

∆ F = 10.0 SQ FT

160

150

180

140

170

130

160

150

120

150

140

110

140

130

MAX

130

RANGE

100

MAX

RANGE

120

110

100

MAX

R/C

MAX

END

100

INDICATED TORQUE PER ENGINE %

DATA BASIS: DERIVED FROM FLIGHT TEST AND ENGINE MODEL SPEC NO. DARCOMCP22202701A, DATED 15 JANUARY 1987

LBA2485

Figure 7-21. Cruise Chart, 8,000 Feet, +30°C and +40°C (sheet 5 of 5)

Use or disclosure of this information is subject to the restriction(s) on the title page of this document.

7-50

HELICOPTER, ATTACK, AH-64D LONGBOW APACHE. TECHNICAL MANUAL (2002) - page 13