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

TM 1-1520-251-10

4.6.7 MANRNG Button. The MANRNG button sets the

active range source to a manually entered value or com-

mands the range source to an automatic mode via the KU.

With auto mode selected the last entered manual range

will remain displayed on the WPN page. This selection is

independent in each crewstation.

4.6.8 SIGHT Select Status Window. The SIGHT select

status window indicates the current state of the sight se-

lect function in that crew station: HMD, TADS (CPG only),

and FCR.

4.6.9 Acquisition (ACQ) Select Status Window. The

ACQ select status window indicates the current state of

the acquisition select function in that crew station; PHS,

GHS, SKR, RFI, FCR, FXD, TADS, TXX, and TRN.

4.6.10 LRFD Status Window. The LRFD status window

indicates the current state of the LRFD Code selection.

4.6.11 LST Status Window. The LST status window in-

dicates the current state of the LST Code selection.

4.7 WPN UTILITY (UTIL) PAGE

LBA0966

4.7.1

Pilot WPN UTIL Page. The WPN UTIL page

Figure 4-7. Pilot WPN UTIL Page

(figs 4-7 and 4-7A) in the pilot station is as depicted below.

LBA5408

Figure 4-7A.

[

Pilot WPN UTIL Page]

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

Change 4

4-5

TM 1-1520-251-10

The WPN UTIL page is unique to each crew station and

provides the Pilot the following selections:

• L1

IHADSS button

• L2

RFI Enable button

• L3

FCR button

• L4

PNVS button

• L5

[

EOCCM button]

• R1

CUEING button

• R3

FCR STOW button

• R6

MMA button

a. IHADSS Button. The IHADSS button enables

the IHADSS.

b. RFI Button

The RFI button enables the RFI.

LBA0968

If MMA NORM, the RFI is enabled automatically. If MMA

pinned, the RFI may be enabled manually.

Figure 4-8. CPG WPN UTIL Page

c. FCR Button

The FCR button enables the

FCR. If MMA NORM, this function is selectable.

The WPN UTIL page is unique to each crew station and

provides the CPG the following unique selections:

d. PNVS Button. The PNVS button enables the

PNVS. The PNVS is enabled automatically 1 minute fol-

• L4

TADS button

lowing aircraft power up. This button may be used to en-

• L5

FLIR button

able the PNVS should it become necessary to begin

• L6

LASER button

PNVS powerup sooner than 1 minute.

• R4

TADS STOW button

[

EOCCM Button. The EOCCM button se-

a. TADS Button. The TADS button enables the

lects the type of FLIR EOCCM filter in the pilot station:

TADS. The TADS and FLIR are enabled automatically upon

FILTER 1, CLEAR, or FILTER 2. The selected state is

aircraft power up. The TADS and FLIR are enabled automati-

reflected in the NVS selected status on the flight format on

cally 1 minute following aircraft power up. This button may be

the pilot’s HMD.]

used to enable the TADS should it become necessary to be-

gin TADS/FLIR powerup sooner than 1 minute.

e. CUEING Button. The CUEING button selects

b. FLIR Button. The FLIR button enables the TADS

sensor cueing in the pilot station.

FLIR.

f. FCR STOW Button

The FCR STOW button

c. LASER Button. The LASER button enables the

stows the FCR antenna.

TADS laser transceiver.

d. TADS STOW Button. The TADS STOW button

g. MMA Button

The MMA button selects the

stows the TADS turret.

state of the MMA: NORM or PINNED. For the FCR to be

turned on, MMA NORM must be selected. The default set-

4.8 BORESIGHT PAGE

ting is PINNED. Selecting the MMA button to NORM pow-

ers up the FCR and RFI.

The sight BORESIGHT page accesses IHADSS bore-

sight controls in both crew stations and TADS boresight

4.7.2 CPG WPN UTIL Page. The WPN UTIL page (fig

controls in the CPG station. The sight BORESIGHT page

4-8) in the CPG station is as depicted below.

is unique to each crew station.

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

4-6

Change 4

TM 1-1520-251-10

4.8.1

Pilot BORESIGHT Page. The BORESIGHT

• L4

IHADSS button

page (figs 4-9 and 4-9A) in the pilot station provides the

• L5

Sight BORESIGHT button

following selections:

a. IHADSS Button. The IHADSS button is used to

perform IHADSS boresight. Selecting the IHADSS boresight

button causes the IHADSS to enter the boresight mode, turn

on the light in the boresight reticle unit (BRU), and activate

the B/S HMD function on the collective flight control grip.

If the aircraft is equipped with MTADS - MPNVS provi-

sions, selecting the IHADSS boresight button causes the

IHADSS to enter the boresight mode, turn on the light in the

boresight reticle unit (BRU), and display the B/S NOW button

with the MPD cursor within the button selection area (for use

with the collective ENTER switch). The REMOVE MES-

SAGE button is also presented.

b. BORESIGHT Button. The BORESIGHT button

is used to access the BORESIGHT page controls.

c. B/S NOW Button. The B/S NOW button is used to

boresight the IHADSS. Selecting the B/S NOW button stores

IHADSS boresight data.

d. REMOVE MESSAGE Button. The REMOVE

MESSAGE button is used to remove the IHADSS B/S RE-

LBA0554

QUIRED HAD sight status message when the selected sight

is HMD.

Figure

4-9.

Pilot BORESIGHT Page

4.8.2

CPG BORESIGHT Page. The BORESIGHT

page (fig 4-10) in the CPG station provides identical selec-

tions as in the pilot station except for the following:

LBA5492

LBA1019

Figure 4-9A. Pilot BORESIGHT Page (Aircraft

Equipped with MTADS Provisions)

Figure 4-10. CPG BORESIGHT Page

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

Change 4

4-7

TM 1-1520-251-10

• L1

TADS OUTFRONT button

• L2

TADS INTERNAL button

• L3

TADS OFF button

• R1

LASER button

a. TADS OUTFRONT Button. The OUTFRONT

button is used to perform the outfront boresight proce-

dure. Selecting the TADS OUTFRONT button causes the

TADS to enter the outfront boresight mode. [

This

button is not displayed if the aircraft is equipped with

MTADS.]

b. TADS INTERNAL Button. The TADS INTER-

NAL button is used to perform the internal boresight pro-

cedure. Selecting the TADS INTERNAL button causes

the TADS to enter the internal boresight mode. [

This

selection initiates the automated internal boresight se-

LBA0962

quence (para 4.30).]

Figure 4-11. CODE Page

c. TADS OFF Button. The OFF button is used to

set the Outfront and Internal boresight modes to off. Se-

• T2

Code SET button

lecting the boresight OFF button causes the TADS to exit

• T4

Laser CODE button

the selected boresight mode.

• T5

Laser FREQ button

• L1 - L6

Code buttons

d. LASER Button. The LASER button is used to

• R1 - R6 Code buttons

ARM and SAFE the LRFD when performing an internal or

outfront boresight procedure. It is displayed in YELLOW

• B2 - B5

Code buttons

when in the ARM state. This button is presented only

4.9.1

SET Button. The laser code SET button sets

when the laser is enabled on the WPN UTIL page and the

which system is to be the recipient of a code selection. Se-

TADS OUTFRONT or TADS INTERNAL option is se-

lecting the SET button sets the state for code selection to

lected. The LASER button will default to the state of the

the LRFD or the LST. This selection is common to both

A/S button on the ARMAMENT panel. When the A/S but-

ton is in the ARM state, the LASER button will be dis-

crew stations.

played with a barrier in the ARM state. When the A/S but-

ton is in the SAFE state, the LASER button is selectable.

4.9.2 Laser Code Buttons.

16 buttons containing the

In the latter case, if the LASER button is in the ARM state

codes and frequencies currently set are used to select the

and a selection is made to leave the BORESIGHT page,

active laser code for the LRFD or LST as selected at the

the LASER button will be set to SAFE.

SET button. A laser code button will be displayed with a

barrier when that code is not available.

4.9 LASER CODE (CODE) PAGE

4.9.3 FREQ Button. The laser FREQ button accesses

stored laser code frequencies.

The laser CODE page (fig 4-11) is used to access 16

4.9.4 LRFD/LST Status Window. The LRFD/LST sta-

stored laser codes. This selection is common to both crew

tus window in the upper area of the laser CODE page indi-

stations. In addition, it is used to provide access to the la-

cates the current LRFD/LST code selections as set by the

ser FREQ page to set the laser frequency for each code.

SET button described above. PIM codes are not available

The CODE page contains the following selections and

for use by the LST. [

PIM codes are available for use

status windows:

by the LST.]

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

4-8

Change 4

TM 1-1520-251-10

4.9.5

CODE RANGE and KEYWORD STATUS Win-

[

LST/MSL ONLY Indicates that only the LST

dow. The CODE RANGE and STATUS window is lo-

and the Hellfire subsystem is capable of using this

cated in the center area of the laser CODE, FREQ and

code range.

CHAN pages.

“?“ Indicates that data for display of keyword data

is not valid.]

a. CODE RANGE. The CODE RANGE indicates

the laser code ranges which are supported by the laser

4.10 LASER FREQUENCY (FREQ) PAGE

keywords resident on the DTC. The helicopter is capable

of supporting the Tri - Service pulse repetition frequency

The laser FREQ page (fig 4-12) provides access to the la-

(PRF) laser codes and USAF, Hellfire and Copperhead

ser code frequency buttons to change the frequency of

pulse interval modulation (PIM) laser codes. In order for

available laser codes. Selecting the laser FREQ button

the LRFD, [

LST] and Hellfire subsystem to use a

calls up the laser code frequency data entry buttons which

PIM laser code the appropriate keyword, for the specific

appear with respect to the same 16 locations as the laser

code range, is required:

buttons described above.

1111 - 1788

Tri - Service .

PRF

2111 - 2888

USAF .

PIM

4111 - 4288

Hellfire - A .

PIM

4311 - 4488

Hellfire - B .

PIM

4511 - 4688

Hellfire - C .

PIM

4711 - 4888

Hellfire - D .

PIM

5111 - 5288

Copperhead - A .

PIM

5311 - 5488

Copperhead - B .

PIM

5511 - 5688

Copperhead - C .

PIM

5711 - 5888

Copperhead - D .

PIM

b. STATUS Area. The STATUS area indicates the

code range status for the LRFD, [

LST] and Hellfire

subsystems.

FAIL Indicates the DTC laser keyword for this

code range has a checksum error.

N/A Indicates that no equipment is capable of us-

ing this code range.

MSL ONLY Indicates that only the missile subsys-

tem is capable of using this code range.

LBA5244

LRFD ONLY Indicates that only the LRFD is capa-

ble of using this code range.

Figure

4-12.

FREQ Page

[

LST ONL Indicates that only the LST is ca-

pable of using this code range.]

[

LRFD/LST ONLY Indicates that only the

4.10.1

Laser Code Frequency Buttons.

The 16 laser

LRFD and LST is capable of using this code range.]

code frequency buttons are used in conjunction with the

[

LRFD/MSL ONLY Indicates that only the

KU to enter laser code frequencies for each of the avail-

LRFD and the Hellfire subsystem is capable of using

able laser codes. Each character of the four digit entry is

this code range.]

limited in range as listed in paragraph 4.9.5.a.

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

Change 4

4-8.1/(4-8.2 blank)

TM 1-1520-251-10

HDU shall be stored in the holster located on the right con-

sole. The DEU provides power and video signals to each

4.11 IHADSS DESCRIPTION

crewmember HDU through DAP located in each crew sta-

tion. The BRU in each crew station is used to boresight

the crewmember helmet. Adjustments on the HDU permit

WARNING

image rotation (leveling), collimation with the crewmem-

ber LOS (centering), and focusing. Both crewmembers

In the event of IHADSS failure with gun

can adjust symbol brightness, video brightness, and con-

selected and the HMD as the selected

trast. The CPG controls are on the ORT or TEDAC panel,

sight, the gun will remain at its last com-

while the pilot uses the VIDEO panel.

mand position. Gun firing is inhibited.

When the gun is de-actioned, it will re-

4.13 IHADSS SYMBOLOGY FORMATS

turn to the stowed position.

IHADSS symbology is displayed in one of two formats: the

The IHADSS (fig 4-13) establishes the crewmember line

flight symbology format or the weapons symbology for-

of sight (LOS). The pilot/CPG LOS is provided to the

mat. The flight symbology format consists of those sym-

weapons processor for sensor pointing, symbol genera-

bols, scales, and digital readouts required for pilotage.

tion, ranging, and/or weapons aiming. It also provides the

The weapons symbology format consists of the symbolo-

display of TADS/PNVS video and symbology. The

gy required for employment of the sight and weapons sys-

IHADSS consists of the Integrated Helmet Unit (IHU), the

tems by the CPG. Weapons engagements can be con-

Helmet Display Unit (HDU), Sensor Survey Units (SSU),

ducted using either weapons or flight symbology. Unique

Sight Electronics Unit (SEU), Display Electronics Unit

weapon symbols are displayed in either format when the

(DEU), Display Adjustment panel (DAP), and a Boresight

respective weapon is selected in a crew station. Pilot sta-

Reticle unit (BRU). HMD symbology is generated and

tion HMD provides pilot flight symbology in all normal (2

then mixed with any sensor video underlay by the display

display processor) operating modes. CPG station HMD

processor.

provides CPG flight symbology when the CPG selected

sight is HMD or the CPG NVS MODE switch is set to the

4.12 HELMET DISPLAY UNIT (HDU)

NORM or FIXED position. CPG station HMD provides pi-

lot flight symbology when the ORT video select switch has

The HMD is provided on the HDU in each crew station.

been set to PNVS or the TEDAC PNV video select button

The HDU consists of a CRT with optical elements which

is selected. CPG station provides Weapons symbology

project the selected symbology and sensor imagery onto

whenever it has not been out - prioritized by Flight symbol-

a combining lens. The HDU is attached to the right side of

ogy: When the selected sight is TADS or FCR, the NVS

the helmet during normal use. The attached HDU is ro-

MODE switch is set to OFF; and the ORT video select

tated in front of the right eye for viewing of the display or

switch is set to TADS, FCR, or GS or the TEDAC TAD,

can be rotated vertically away from the eye when not in

FCR, or G/S video select button is selected. Single DP op-

immediate use. When not attached to the helmet, the

eration of the IHADSS is described in paragraph 4.50.3.

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

Change 3

4-9

TM 1-1520-251-10

4.14 FLIGHT SYMBOLOGY FORMAT

error greater than 0.3 meters per second exists. The vec-

tor will blank when inertial data is not valid.

Flight symbology provides either crewmember flight in-

2. Acceleration Cue . The Acceleration Cue pro-

formation for use as the primary flight display within the

vides magnitude and direction indication of the aircraft’s

crew station. These flight formats can be configured to ei-

acceleration.

ther Hover (H), Bob-up (B), Transition (T), and Cruise (C)

modes. The flight mode presented can be selected by the

(a) Hover and Bob-up Modes. The origin of the

crewmember using the Cyclic Symbology Select switch.

Acceleration Cue is the outer end of the Velocity Vector

When presented on the HMD, ORT or TEDAC Display

when the vector is at less than maximum scale. The origin

Unit (TDU), all flight symbology is green in color. When

of the Acceleration Cue is the center of the LOS Reticle

presented on the MPD (as can be done using the VIDEO

when the Velocity Vector is at or greater than maximum

Page, VSEL selected), and the MPD is operating in DAY

scale.

or NIGHT mode, the non - green colors noted in the follow-

ing paragraphs will be presented. Conditions under which

(b) Transition Mode. The acceleration cue is al-

flight symbols are presented are defined in paragraphs

ways referenced to the tip of the velocity vector. The sym-

4.13 and 4.50.3.

bol flashes when a greater than 0.3 meters per second er-

4.14.1 Hover Mode Symbology. The following sym-

ror in inertial data exists and blanks when inertial data is

bols are provided within the Hover Mode symbol set (fig

not valid.

4-14).

3. Cueing Dots. Cueing dots are displayed at the

NOTE

outer tips of the LOS Reticle, and indicate the quadrant

containing the selected acquisition source. A cueing dot

Items not described below function as de-

appears at the upper or lower tip of the reticle when a

scribed in Chapter 2, Section XIV.

change in elevation is required and, appears at the left or

right tip when a change in azimuth is required. They ap-

pear at all four tips of the LOS Reticle and flash when the

IHADSS B/S REQUIRED message is present within the

High Action Display’s Sight Status field. The cueing dots

do not appear when the acquisition source is within 4° of

the line of sight.

4. LOS Reticle . The LOS Reticle is a cross-hair lo-

cated in the center area of the flight format. It represents

the LOS of the crewmember’s selected sight and is used

as an aiming reticle. It is also used as a reference for bore-

sighting as well as for the Head Tracker, the Horizon Line,

the Velocity Vector, the Acceleration Cue, and the Hover

Position Box. The LOS Reticle flashes when the crew-

member’s LOS is invalid or his selected PNVS or TADS

sensor is at its limit. It also flashes when the gun is the se-

lected weapon and the gun system has failed and is not

following the crewmember’s head.

Figure 4-14. Flight Symbology - Hover Mode

5. Cued LOS Dot . The CUED LOS dot is a dynam-

ic dot symbol displayed within the sensor field of regard. It

1. Velocity Vector . The Velocity Vector symbol in-

represents the active acquisition LOS. It is edge limited to

dicates the magnitude and direction of the aircraft velocity

the current field of regard.

relative to the nose of the aircraft. It represents 6 kts

ground speed during hover and bob-up modes and 60 kts

6. FCR Last Centerline

The FCR last scan

ground speed in transition mode. The velocity vector is a

centerline is a dashed, vertical line displayed within the

solid line whose origin is the center of the LOS Reticle.

sensor field of regard. It is displayed to represent the FCR

The line orients in the direction of the helicopter move-

centerline of the most recent scan for which target in-

ment. It extends and withdraws (in length) from the origin

formation is currently being displayed. It is only visible

to indicate longitudinal and lateral velocities of ground

when the current centerline has been repositioned from

movement. The symbol flashes when an inertial velocity

the azimuth of the most recent scan, and the FCR is valid.

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

Change 4

4-11

TM 1-1520-251-10

7. Field of View Box . The field of view box is a

90°

0°

90°

+30°

small, dynamic box displayed within the field of regard. it

represents the relative position of the TADS/PNVS 30° X

0°

40° field of view within the field of regard. It is edge limited

to the currently displayed field of regard. The field of view

box is not presented if the field of regard is not presented.

The field of view box represents the pilots HMD on the pi-

60°

lot’s flight formats. It represents the CPG’s HMD when the

90°

0°

90°

120°

CPG’s selected sight is HMD. It represents the TADS

LBA2558

when the CPG’s selected sight is TADS or FCR

Figure 4-16. TADS Field Of Regard

8. FCR Current Centerline

The FCR current

10. Head Tracker . The Head Tracker indicates the

centerline is a solid, vertical line within the current sensor

pilot head position relative to the aircraft datum line. This

field of regard. This line represents the current centerline

is a virtual symbol whose range of display is 30° vertically

of the FCR.

and 40° horizontally about the nose of the helicopter.

9. Field of Regard. A box representing the selected

11. Cued LOS Reticle . The Cued LOS reticle is a

sensor’s field of regard (FOR) is displayed at the bottom

dashed crosshair symbol which represents the crewmem-

of the flight symbology format. The FOR box edges mark

bers selected acquisition source. In the pilots station the

the AZ limits for each sensor.

Cued LOS reticle is only presented when the CUEING

button is selected.

(a) PNVS FOR. The PNVS field of regard (fig

12.

[

Selected PNVS Sensor. The PNVS se-

4-15) represents the following: The top of the box marks

lected sensor data field presents the name of the selected

+20°, the horizontal tic marks indicate the 0° position, and

PNVS sensor: TV or FLIR. The selected EOCCM FLIR fil-

the bottom of the box marks - 45°. The left side of the box

ter is incorporated into this status: 1FLIR (filter 1). 2FLIR

marks - 90°, the center vertical tic marks indicate 0°, and

(filter 2), or FLIR (clear). TV status is a growth provision

the right side of the box marks +90°.

for an image intensification system.]

13.

[

Video Degraded/Frozen Status. The

0°

+20°

VIDEO DEGRADED or VIDEO FROZEN status is dis-

played when the respective condition is detected (para

0°

4.50.4A). This status is displayed as confirmation, when

experiencing either condition, that it has been detected by

the system.]

14. Rate of Climb . The rate of climb scale and indi-

45°

0°

cator triangle are located to the left and adjacent to the ra-

90°

dar altitude vertical scale. The scale is presented with a

LBA2557

filled triangle pointer indicating the current rate of climb.

Tic marks designate rates of climb or descent at 100 fpm

Figure 4-15. PNVS Field Of Regard

increments to +/ - 500 fpm, and a single tic mark desig-

nates the 1000 fpm location. When the triangle is in the

(b) TADS FOR. The TADS field of regard (fig

1000 fpm descent limit position, a WHITE data field indi-

4-16) represents the following: The top of the box marks

cating the current rate of descent is presented adjacent to

+30°, the horizontal tic marks indicate the 0° position, and

the triangle. The data field shall present the rate of de-

the bottom of the box marks - 60°. The left side of the box

scent to the nearest 100 fpm when the rate of descent ex-

marks - 120°, the left vertical tic marks indicate - 90°, the

ceeds 1000 fpm. The rate of climb limit data field is re-

center vertical tic marks indicate 0°, the right vertical tic

served for barometric altitude. Rates of climb/descent are

marks indicate +90°, and the right side of the box marks

not presented if the EGI is not providing valid vertical

+120°.

speed information.

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

4-12

Change 4

TM 1-1520-251-10

15. Additional Symbols. The following symbols are

Scale. It represent the heading of the helicopter upon the

defined in chapter 2 for the FLT Page:

initiation of the Bob-up Mode. It remains at that heading

until the Bob-up Mode is disengaged or heading becomes

• Airspeed

invalid. If heading was not valid upon bob-up initiation or

• Altitude Hold

the heading scale is not presented, this symbol is not dis-

• Attitude Hold

played.

• Engine Torque

• G Status

WARNING

• Heading Scale

• ADF Bearing

The Bob-up box may drift in a stationary

• Alternate Crew member Sensor Bearing

hover. Outside cockpit visual cues must

be the principle source of rotor clear-

• Command Heading

ance.

• FCR Centerline Bearing

• Lubber Line

2. Bob-up Box. The bob-up box is a dynamic box

displayed in the shape of an octagon. It initializes at the

• Radar Altitude

center of the LOS Reticle upon selection of the Bob-up

• Radar Altitude HI

Mode. The bob-up box moves about the format to indicate

• Radar Altitude LO

the relative position of the helicopter to the spot on the

• Radar Altitude Vertical Scale

earth where the box was initialized. If the bob-up box

moves to the maximum displacement on the format, it

• Rate of Climb

hangs at the edge and continues to move about the edge

• Skid/Slip Ball

of the format to indicate the relative direction to the initial-

• Turbine Gas Temperature (TGT)

ization point. The bob-up box shows an approximately 12

ft square area on the ground. Maximum displacement to

4.14.2 Bob-up Mode Symbology. The Bob-up Mode

the edge of the format represents approximately 40 ft lat-

symbols (fig 4-17) consist of the Hover Mode symbols,

erally or 40 ft longitudinally. The symbol is not presented

with the following additions:

when inertial data is not valid.

4.14.3 Transition Mode Symbology. The Transition

Mode symbols (fig 4-18) consist of the Hover Mode sym-

bols, with the following additions:

LBA2025A

Figure 4-17. Flight Symbology - Bob-up Mode

LBA0444B

1. Bob-up Heading. The bob-up heading chevron

is presented along the bottom of the magnetic Heading

Figure 4-18. Flight Symbology - Transition Mode

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

Change 4

4-13

TM 1-1520-251-10

NOTE

4.14.4 Cruise Mode Symbology. The Cruise Mode

The horizon line and attitude indicator hori-

symbols (fig 4-19) consist of the Transition Mode symbols,

zon bar will appear to jump when changing

with the following additions or changes:

between transition and cruise modes. This

1. Bank Angle. The bank angle presentation oper-

is due to the difference in display scaling/

ates as described in chapter 2 for the FLT page. However,

rate of movement between the horizon line

the bank angle triangle is presented without the

(2:1 movement) and the horizon bar (4:1

associated tic mark scale on the Cruise Mode flight for-

movement).

mat.

1. Horizon Line. The horizon line is a brown dy-

namic split dashed line positioned horizontally in the cen-

NOTE

ter of the format about the center of the LOS reticle. It rep-

The horizon line and attitude indicator hori-

resents an artificial horizon relative to the LOS reticle. The

zon bar will appear to jump when changing

symbol moves within ±30° in pitch, and hangs at the end

between transition and cruise modes. This

positions of this range for pitch attitudes greater than

is due to the difference in display scaling/

±30°. The horizon line is not presented when inertial data

rate of movement between the horizon line

is not valid

(2:1 movement) and the horizon bar (4:1

2. Additional Symbols. The following symbols are

movement).

defined in chapter 2 for the FLT Page:

2. Attitude Indicator. The attitude indicator pre-

• Destination Point

sentation operates as described in chapter 2 for the FLT

• Distance to Go

page, however, to offer less obstruction of the real-world

• Time to Go

or imagery backg2round, 5° tic marks are not presented,

• Groundspeed

and the scaling has been changed.

• Flight Path

3. LOS Reticle. In Cruise Mode, the LOS reticle is a

• Nav Fly - To

bold cross-hair located in the center of the cruise mode

flight format. It represents the LOS of the pilots selected

sight and is used as an aiming reticle. It is also used as a

reference for boresighting and the pilot head tracker. The

reticle flashes when the pilots line of sight is invalid or the

selected sensor is at its limit. It also flashes when the gun

is selected and the gun system has failed.

LBA0445A

Figure 4-19. Flight Symbology - Cruise Mode

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

4-14

Change 4

TM 1-1520-251-10

4. Barometric or Inertial Altitude. The barometric

4.15.1 Weapon Symbology. When presented on the

or inertial altitude, is defined in chapter 2 for the FLT page.

HMD or ORT, all weapon symbology is green in color. When

presented on the MPD (as can be done using the VIDEO

4.15 WEAPON SYMBOLOGY FORMAT

Page, VSEL selected), and the MPD is operating in DAY or

The weapon symbology format (fig 4-20) is displayed in

NIGHT mode, the non-green colors noted in the following

the CPG station on the TDU, ORT HOD/HDD and HMD

paragraphs will be presented.

when FCR or TADS is the selected sight, and the HMD is

1. CPG LOS Bearing. The CPG LOS Bearing is a

not being used for NVS, as described in paragraphs 4.13

chevron displayed along the bottom of the magnetic head-

and 4.50.3.

ing scale (in place of the command heading). It represents

the LOS direction of the CPG HMD or TADS sensor in de-

grees of azimuth. If FCR is the CPG selected sight, it rep-

resents the LOS direction of the TADS sensor. If the head-

ing scale is not presented, this symbol is not displayed.

2. TADS LOS Reticle. The TADS LOS Reticle is a

crosshair symbol which represents the TADS line of sight.

It is internally generated by the TEU and is displayed as a

part of TADS imagery. The TADS LOS reticle will flash

when the gun is the selected weapon and the gun system

has failed. The TADS LOS reticle color corresponds to the

video color.

3. Image Auto Track Gates. The Image Auto Track

(IAT) gates are a set of four dynamic gate symbols dis-

played only when the IAT/OFS switch is activated. The

IAT gates originate at the TADS LOS reticle and move out

in the format to capture a selected object with FLIR or

DTV imagery. The IAT gates will attempt to capture an ob-

ject contrast according to the position of the IAT POLAR-

ITY switch. The IAT gates color corresponds to the video

color.

Figure 4-20. Weapons Symbology Format

[

Unique primary and secondary track symbols are dis-

played when activating the IAT/OFS switch. Objects are

The following symbols, defined in Chapter 2 for the FLT

tracked using edge tracking and inertial tracking (para

Page, are also presented in the Weapon format and in

4.26.2).]

Chapter 4 for the flight symbology format:

• Cued LOS reticle

4. Radar Altitude. The radar altitude presentation

operates as described in chapter 2 for the FLT page. It is

• Cueing dots

located to the right of the field of regard, above the high

• Cued LOS dot

action display.

5. Airspeed. The airspeed presentation operates as

• FCR current centerline

described in chapter 2 for the FLT page. Its location on the

• FCR last scan centerline

weapon format is to the left of the field of regard, above

• Field of view box

the high action display.

6. TADS FOV Brackets. The TADS FOV brackets

• TADS FOR box

are displayed in the center area of the format surrounding

• Heading scale

the LOS reticle. They appear as corner marks on the dis-

• FCR centerline bearing

play to indicate the amount of the currently displayed

imagery of TADS that will be displayed in the next narrow-

• Alternate sensor bearing

er field of view (FOV). They only appear when a next nar-

• LOS reticle

rower FOV is available, and TADS imagery is presented

• Lubber line

on the format.

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

Change 4

4-15

TM 1-1520-251-10

7. TADS Selected Sensor. The TADS selected sen-

when pylon articulation is in process. The cursor shall be

sor data field presents the name of the selected TADS sen-

dashed when a safety or performance inhibit (Table 4-5) is

sor: DVO (ORT only), DTV, or FLIR. [

The selected

in force, indicating crew action is required prior to firing

EOCCM FLIR filter is incorporated into this status: 1FLIR

rockets. A gap in the center vertical line indicates the py-

(filter 1). 2FLIR (filter 2), or FLIR (clear).] The TADS se-

lons are in ground stow position (Figure 4-21) shows the

lected sensor data field is not presented if there is no TADS

four possible appearances of the rocket steering cursor:

video shown.

8. LMC On Indicator. The LMC On (fig 4-20A) sym-

bol consists of four short end - cap lines displayed near the

end of the TADS LOS reiticle lines. If the aircraft is

equipped with MTADS - PNVS provisions, this indicator is

displayed when LMC is on.

9. Laser Firing Indicator. The Laser Firing indica-

(1)

(2)

(3)

(4)

LBA1999

tor (fig 4-20A) consists of a large “X” symbol displayed in

conjunction with the TADS LOS reticle. If the aircraft is

Figure 4-21. Rocket Steering Cursors

equipped with MTADS - PNVS provisions, this indicator is

(1) Articulating/inhibited rocket steering cursor.

displayed when the LRFD is lasing.

(2) Stowed/inhibited rocket steering cursor.

(3) Articulating rocket steering cursor.

(4) Stowed rocket steering cursor.

LMC On

Laser Firing Indicator

b. Fixed Gun Aiming Reticle. The fixed gun aiming

reticle (fig 4-22) is the same graphically as the cued LOS

Figure 4-20A. LMC On and Laser Firing Indicators

reticle. It represents a fixed impact point for a given range.

It is presented only when the crewmember actions the gun

4.15.2 Weapon Symbols. Unique weapons symbols are

in the fixed mode.

presented on the flight and weapon formats to indicate

weapon aiming and status information.

a. Rocket Steering Cursor. The rocket steering

cursor is a dynamic I-beam symbol which indicates the

delivery mode and how to point the aircraft for the rocket

LBA2000

delivery. If the CPG has actioned rockets, the rocket steer-

ing cursor is presented on both pilot and CPG formats. If

Figure 4-22. Fixed Gun Aiming Reticle

the pilot has actioned rockets, the pilots rocket steering

cursor is presented only on the pilot’s displays. The cursor

c. Gun DH Reticle. The Gun DH Reticle is the same

moves about in the format to indicate the azimuth and

graphically as the cued LOS reticle. The position of this

elevation position of the helicopter in relation to the se-

symbol is controlled by the MAN TRK thumb force control-

lected sight LOS to provide a steering cue to the crew-

ler to designate the impact point/area of the gun rounds

member. The cursor is displayed with a solid vertical line

following dynamic harmonization gun firing.

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

4-16

Change 4

TM 1-1520-251-10

d. Missile Constraints Box. The Hellfire missile

(1)

(2)

constraints box (fig 4-23) is used to indicate the delivery

mode and direction to orient the aircraft for the Hellfire

missile launch. A dashed line type indicates the missiles

are out of constraints. A solid line indicates the missiles

are in constraints. If a SAL missile is actioned but not

tracking, the constraints box size is set to LOAL (small

box). If the missile transitions into TRACK mode, the

constraints box will be set to LOBL (large box). RF missile

(3)

(4)

LBA2001

constraints box is based on target handover data, which

determines actual missile trajectory mode. If the missile

Figure 4-23. Missile Constraint Boxes

does not enter a LOBL RADAR mode, the constraints box

(1) LOAL out-of-constraints missile box.

is set to LOAL. The constraints box size does not directly

(2) LOAL in-constraints missile box.

correlate to an angle (such as seeker FOV). For SAL mis-

(3) LOBL out-of-constraints missile box.

siles, the allowable angle is larger for LOBL (20°) than for

(4) LOBL in-constraints missile box.

LOAL (7.5°). Alignment of the aircraft to the target LOS is

4.15.3 C-Scope Symbols

. FCR symbols are present-

not as critical so the LOBL constraints box is larger. For

ed in the C-Scope format on the flight and weapon symbolo-

RF missiles in either LOAL or LOBL trajectory mode, the

gy formats. Target symbols are displayed in GTM, RMAP, or

allowable angle is 20°. If the RF missile is tracking and the

ATM. Terrain profile lines and obstacle symbols are displayed

target range is w

1 km, the allowable angle is 20°. If the

in TPM.

RF missile is tracking and the target range is t

1 km, the

a. FCR Target Symbols. Target symbols (fig 4-24)

allowable angle is 5°.

are provided to indicate the azimuth and elevation loca-

tion of targets detected during last scan. Target symbol

color is IAW the FCR page presentation of targets de-

scribed in para 4.44.4

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

Change 4

4-16.1/(4-16.2 blank)

TM 1-1520-251-10

360

75%

FLIR

ÓÓ

Ó ÓÓ

ÓÓ

AAAAAAAAAAAA

AAAAA

AAAAAL AAAAA

AAAAAAAAAAAA

AAAA

AAAAAAAAAA

LBA2005A

LBA2002A

Figure 4-26. FCR Profile Lines and Obstacles in

Figure 4-24. FCR Target Symbols in C - Scope

C-Scope

(example TADS FLIR WFOV)

4.16 HIGH ACTION DISPLAY (HAD) FORMAT

WARNING

The HAD is located along the bottom of the weapons and

flight symbology formats (fig 4-27). It is subdivided into

The terrain profiling mode of the FCR

seven status message fields and provides information in-

shall not be relied upon for primary pilot-

dependently by crew station. The messages are typically

age information.

presented in priority order based on the selected sight

and/or weapon system. Messages on MPD will be in

b. Profile Line Symbols. Terrain profile lines (fig

green unless otherwise indicated in the following tables.

4-25) are provided to indicate the greatest elevation at up

to four ranges from the helicopter. The number of lines

OWNER CUE

displayed is selected on the FCR page, TPM Format. The

solid (nearest) line is shown WHITE in color.

RANGE AND

WEAPON

RANGE SOURCE

CONTROL

FURTHEST FROM HELICOPTER

ACQUISITION

SIGHT SELECT

SELECT STATUS

STATUS

NEAREST HELICOPTER

WEAPON

STATUS

LBA2003

SIGHT STATUS

WEAPON INHIBIT

LBA2006A

Figure 4-25. Terrain Profile Line Dash Patterns

Figure 4-27. Pilot and CPG HAD Format

c. Obstacle Symbol. Obstacle symbols are pro-

vided to indicate towers or other items with significant

4.16.1 Sight Status Field. The HAD sight status field

changes in vertical elevation plus radar cross section and

(Table 4-1) is located on the bottom left of the display field

minimum height detected by the FCR in Terrain Profiles

and occupies 12 character spaces. This field provides

mode (fig 4-26). The obstacles are YELLOW in color. Ob-

sight status messages in the priority order based on the

stacles are not presented if FCR data is not valid.

crew station and selected sight.

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

4-17

TM 1-1520-251-10

Table 4-1. HAD Sight Status Field Messages

Table 4 - 1. HAD Sight Status Field Messages (cont)

Message

Color

Description

BOT

(Beginning of Tape) The tape is

Message

Color

Description

at the beginning position.

FIXED

The selected sight (FCR/TADS)

CHK

White

The VCR door is not latched or

is in the fixed position.

the tape presence is not de-

FLIR

The TADS FLIR has not cooled

tected. The crewmember should

check the tape or tape door.

NOT

down sufficiently for optimum

COOL

performance; cool down should

CUE

The TADS cue update boresight

not exceed 15 minutes. The

UPDT

has been selected by placing

message alternates (FLIR, then

the IAT in MANUAL and the

NOT COOL) at the alternating

SLAVE switch OFF when

text rate. Applies only to CPG.

BORESITE has been selected

FLIR OFF

The FLIR has been turned OFF,

via the MPD. Applies only to

the TADS is still powered. Ap-

CPG

plies only to CPG.

ENERGY

Laser energy has been detected

LOW

as low. Presented only when la-

HF TOF-

Indicates time (in seconds) until

ser is firing. Applies only to

missile impact for a remote

CPG.

launch. If more than one missile

is in flight, the display will show

EOT

(End of Tape) The VCR tape is

TOF for the missile first

at the end; no tape remains.

launched, then the subsequently

FCR FAIL

White

The FCR has been detected as

launched missiles.

NO - GO, and the FCR antenna

IHADSS

IHADSS boresight required. This

defaults to fixed forward, if pos-

B/S RE-

message alternates (IHADSS

sible.

QUIRED

B/S, then REQUIRED) at the al-

FCR HOT

Yellow

An impending overtemperature

ternating text rate.

condition exists (80 - 90% of

IHADSS

White

The IHADSS has been detected

overheat threshold) within the

FAIL

as NO - GO for that crewstation

FCR components. The FCR will

by the DMS. The IHADSS LOS

automatically shut down when

defaults to fixed forward for the

the temperature limit is exceed-

affected crewstation.

ed unless the FCR TEMP

ORIDE button is selected.

IHADSS

White

This condition is caused by any

LOS

one of the following conditions:

FCR

White

The FCR is not available be-

INVALID

IHADSS failure, IHADSS power

NOT

cause of BIT or Power-Up. The

being off, blockage of the line-of-

READY

message alternates (FCR, then

sight between the SSU and hel-

NOT READY) at the alternating

met, or the head of the crew-

text rate.

member being outside the head-

FCR

The FCR is transmitting.

motion box. The IHADSS LOS is

XMIT

frozen at the last valid computa-

tion until the LOS is computed

FIRE

The minimum interval between

as valid. The message alter-

MSLS

launches has elapsed in a rapid

nates (IHADSS LOS, then IN-

fire Hellfire missile engagement,

VALID) at the alternating text

and more than one missile is

rate.

present in the priority channel

after launch of a missile. This

INTER-

The TADS internal boresight has

message is displayed for 2 se-

NAL B/S

been selected via the MPD. Ap-

conds.

plies only to CPG.

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

4-18

Change 3

TM 1-1520-251-10

Table 4 - 1. HAD Sight Status Field Messages (cont)

Message

Color

Description

Message

Color

Description

NVS B/S

White

The weapon processor has de-

ERR

tected an alteration of internal

INTER-

White

The system has determined a

values affecting the PNVS align-

NAL B/

TADS internal boresight is nec-

ment. The PNVS will function

S.. RE-

essary. The boresight will be re-

normally but without alignment

QUIRED

quired at system power - up and

correction.

once every 50 minutes thereaf-

ter

NVS

White

The TADS Electronics Unit has

DIRECT

been detected as NO - GO. The

LASE NN

The laser designator must be

PNVS turret is being directed by

TRGT

lasing the target for missile ter-

the weapons processor and its

minal guidance. The message is

azimuth is limited to 75° left and

displayed for 4 seconds starting

right.

at TOF=12 calculated missile

time of flight during LOAL

NVS FAIL

White

DMS has determined the PNVS

launches.

turret or electronics or the TADS

(if it is the NVS) as NO - GO.

LASER

White

Indicates LRF/D Failure.

FAIL

Applies only to CPG.

NVS

The operator has selected the

FIXED

NVS fixed mode.

LIMITS

The selected sight, TADS, FCR,

or PNVS (in NVS mode) is at a

NVS NOT

White

The PNVS FLIR or TADS FLIR

limit. Also applies to TADS or

COOL

has not cooled down for opti-

FCR when linked

mum performance.

LRFD

White

The selected LRFD laser code is

OUT-

The TADS outfront boresight

CODE ?

not usable. Applies only to CPG.

FRONT

has been selected via the MPD.

B/S

Applies only to CPG.

LST

White

The selected LST laser code is

CODE ?

not usable. Applies only to CPG.

PNVS

White

At power - up, the PNVS is per-

ARTY

Indicates time (in seconds) until

SBIT..IN

forming a 30 second functional

TOF = NN

artillery rounds impact for a call

PROG-

test of electronic equipment

for fire mission. Time of flight

RESS

countdown will begin when the

RECORD

White

The video tape recorder is com-

message is opened and is

FAIL

manded to record video, but it is

based on estimated TOF deter-

not recording.

mined by the sender. If more

RE-

The video tape recorder is re-

than one “shot” time is issued,

time of flight is based upon the

CORD-

cording video.

ING

most recently opened message.

REMOTE

The Hellfire missile system is set

MMA

The operator has indicated to

up for remote missile launch,

PINNED

the system that the MMA is

i.e., the priority missile channel

pinned in a fixed forward posi-

does not match the LRFD code.

tion.

Applies only to CPG.

MSL

Indicates tactical missile launch

RFI

White

The FCR has been commanded

LAUNCH

for a remote designator. This

DATA?

to perform a cued search and no

message is displayed for 2 se-

threat data is available.

conds.

RFI FAIL

White

The RFI has been detected as

NAV

White

The FCR has been selected as

NO - GO.

DATA

the active sight and the RF

INVALID

handover data recently received

RFI NOT

White

The RFI is not available be-

has been detected as outside

READY

cause of BIT or Power-up. The

the optimum navigational pa-

message alternates (RFI, then

rameters for weapons engage-

NOT READY) at the alternating

ment. Safety inhibit.

text rate.

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

Change 4

4-19

TM 1-1520-251-10

Table 4 - 1. HAD Sight Status Field Messages (cont)

Table 4-2.

HAD Range and Range Source Status

Field Messages

Message

Color

Description

SA-

White

Indicates TADS or PNVS is per-

Message

Color

Description

NUC..IN

forming SANUC during ground

PROG-

initialization

*XXXX

Indicates range source is laser.

RESS

Range is displayed in meters,

maximum value is 9999. The as-

SA-

White

During TADS or PNVS initializa-

NUC..RE-

tion, the system has determined

terisk is present when the laser

QUIRED

that a SANUC should be per-

is firing and the Weapons Pro-

formed and the crew is in control

cessor is receiving valid range

data from the laser rangefinder/

of a sensor other than FLIR

designator. The asterisk flashes

SIM

Indicates training missile launch

when a multi-target condition is

LAUNCH

for a remote designator. This

detected in the range data.

message is displayed for 2 se-

conds.

1.5

The weapon processor is using

the default range in the pilot sta-

TADS B/S

White

The weapon processor has de-

tion because the selected range

tected an alteration of internal

source is not valid.

values affecting TADS align-

ment. The TADS will function

3.0

The weapon processor is using

normally without alignment

the default range in the CPG

correction. Applies only to CPG.

station because the selected

range source is not valid.

TADS

White

The TADS has been detected as

FAIL

NO - GO. Applies only to CPG.

AXX.X

The weapon processor is using

TADS

White

At power - up, the TADS is per-

an autorange solution . It is

SBIT..IN

forming a 30 second functional

based on selected sight LOS

PROG-

test of electronic equipment

and radar altitude. Range dis-

RESS

played is in km, maximum value

is 50 km.

TARGET

White

Indicates no target data is avail-

DATA?

able.

MXX.X

The weapon processor is using

WET

White

The VCR has detected moisture

a manual range entered at the

KU in the pilot station. Range

on the tape. The VCR can con-

displayed is in km (entered in

tinue to play or record, but to do

meters at the KU). The maxi-

so may damage the VCR and/or

mum value is 50 km.

tape. Recommend turning VCR

off to unthread the tape.

NXX.X

The weapon processor is using

White

An error has occurred. An illogi-

a valid navigational range value

cal and invalid condition has

to the target, waypoint/hazard,

been identified.

or control point in the acquisition

source option. The range value

4.16.2 Range and Range Source Status Field. The

will increase or decrease based

HAD range and range source field (table 4-2) is located on

on helicopter movement or posi-

the top left of the display field and occupies five character

tion changes. Range displayed

spaces. This field provides range and range source mes-

is in km, maximum value is 32

sages based on the crew station.

km.

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

4-20

Change 4

TM 1-1520-251-10

Table 4-2. HAD Range and Range Source Status

Table

4-4. Weapon Status Field Messages

Field Messages (cont)

Message

Color

Description

Message

Color

Description

2 CHAN

Indicates priority and alternate

TRACK

channels are tracking.

RX.X

The weapon processor is using

radar range as a result of em-

ALT

Indicates alternate channel is

ploying the FCR in the pilot sta-

CHAN

tracking.

tion. Range is displayed in km,

TRK

maximum value is 9.9 km.

ALT

White

Indicates selected code for alter-

White

?An error has occurred. An illog-

CODE ?

nate channel is unusable. This is

ical and invalid condition has

due to the lack of PIM Code/

been identified.

Keyword correlation or the SAL

SEL is AUTO, the selected code

4.16.3 Weapon Control Status Field. The HAD weap-

is PIM and no SAL 2 missiles

on control status field (table 4-3) is located on the top right

are available but SAL 1 missiles

of the display field and occupies 5 character spaces. This

are available. Only displayed in

field provides the status of the selected weapon in the op-

ripple mode.

posite crew station.

DIR MAN

HF Missile trajectory is set to

DIR and missile MODE is set to

Table 4-3. Weapon Control Status Field Messages

MAN.

DIR

HF Missile trajectory is set to

Message

Color

Description

NORM

DIR and missile MODE is set to

NORM.

CGUN

CPG has actioned GUN system.

DIR RIPL

HF Missile trajectory is set to

CMSL

CPG has actioned Missile sys-

DIR and missile MODE is set to

tem.

RIPL.

COOP

Both PILOT and CPG have ac-

FIRE

The minimum interval between

tioned the Rocket system.

MSLS

launches has elapsed in a rapid

CRKT

CPG has actioned Rocket sys-

fire HF missile engagement, and

tem.

more than one missile is present

PGUN

PILOT has actioned Gun sys-

in priority channel after launch of

tem.

a missile.

PMSL

PILOT has actioned Missile sys-

GUN B/S

White

The gun has not been bore-

tem.

sighted or failed the boresight

verification. The gun will function

PRKT

PILOT has actioned Rocket sys-

normally but without boresight

tem.

corrections.

White

An error has occurred. An illogi-

GUN

White

The gun system has been ac-

cal and invalid condition has

FAIL

tioned but has been detected as

been identified.

NO - GO. Recycle the GUN Sys-

4.16.4 Weapon Status Field. The HAD weapon status

tem- ON/OFF power button. If

field (table 4-4) is located on the bottom right of the display

the fault message clears, contin-

ue operation.

field and occupies 12 character spaces. This field pro-

vides weapon status messages based on the selected

GUN JAM

White

The gun has been detected as

weapon system.

jammed.

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

Change 4

4-21

TM 1-1520-251-10

Table 4 - 4. Weapon Status Field Messages (cont)

Message

Color

Description

Message

Color

Description

HANG-

Yellow

The fire signal was sent but um-

LOBL

Missile TRAJ is set to LOBL and

FIRE

bilical separation did not occur.

NORM

missile MODE is set to NORM.

This message is displayed for 6

LOBL

Missile trajectory is set to LOBL

seconds, during which time all

RIPL

and missile MODE is set to

HF missiles on that side of the

RIPL.

helicopter become “not avail-

able” and are inhibited from fir-

MISFIRE

Yellow

Indicates a HF misfire has oc-

ing.

curred. The fire signal was sent

but umbilical separation did not

Indicates time (in seconds) until

occur at the predicted time. This

TOF=NN

missile impact. If more than one

message is displayed for 2 se-

missile is in flight, the display will

conds.

show TOF for the missile first

launched, then the subsequently

MSL

Indicates launch commanded in

launched missiles.

LAUNCH

the tactical mode. This message

is displayed for 2 seconds.

HI MAN

Missile trajectory is set to HI and

missile MODE is set to MAN.

MSL SE-

Missiles have been actioned, but

LECT

no primary channel has been

HI NORM

Missile trajectory is set to HI and

selected.

missile MODE is set to NORM.

HI RIPL

Missile trajectory is set to HI and

MSL

White

Indicates no missiles of the se-

missile MODE is set to RIPL.

TYPE?

lected type (RF or SAL) are

available.

LASE NN

The message is displayed for 4

TRGT

seconds starting at TOF =12

NO AC-

White

Indicates the RF missile has

calculated missile time of flight

QUIRE

completed its attempts to ac-

during LOAL launches.

quire the target and has re-

turned to ready mode.

LIMITS

White

Indicates pylons commanded to

elevation limit.

NO MIS-

White

Indicates no missiles (RF or

SILES

SAL) are available.

LO MAN

Missile trajectory is set to LO

and missile MODE is set to

White

Indicates available rocket quan-

MAN.

ROCK-

tity is 0.

ETS

Missile trajectory is set to LO

NORM

and missile MODE is set to

PRI

Indicates priority channel is

NORM.

CHAN

tracking.

TRK

LO RIPL

Missile trajectory is set to LO

and missile MODE is set to

PRI

White

Indicates selected code for the

RIPL.

CODE ?

priority channel is unusable.

This is due to lack of PIM Code/

LOAL

RF missile trajectory is defaulted

Keyword correlation or the SAL

MAN

to LOAL and missile MODE is

SEL is AUTO, the selected code

set to MAN.

is PIM and no SAL 2 missiles

are available but SAL 1 missiles

LOAL

RF missile trajectory is defaulted

are available.

NORM

to LOAL and missile MODE is

set to NORM.

DEF

Indicates the selected lethal

SCHEME

ranges in use is the default data

LOBL

Indicates LOBL INHIBIT mode is

(within FCR) and the selected

INHIBIT

selected.

priority scheme (A - G) for the

LOBL

Missile trajectory is set to LOBL

FCR. This message is only giv-

MAN

and missile MODE is set to

en when no weapon is actioned

MAN.

and FCR is the selected sight.

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

4-22

Change 4

TM 1-1520-251-10

Table 4 - 4. Weapon Status Field Messages (cont)

Table 4-5. HAD Weapon Inhibit Status Field

Messages

Message

Color

Description

MOD

Indicates selected lethal ranges

Generic Inhibits

SCHEME

in use is the modified data (from

the DTC) and the selected prior-

ALL

White

Displayed for 4 seconds to indi-

ity scheme (A - G) for the FCR.

TRKS

cate all TADS target tracks have

This message is only given

DEL

been deleted by the CPG

when no weapon is actioned

LIVE

Yellow

Indicates live ammunition has

and FCR is the selected sight.

AMMO

been detected (or gun round en-

PYLON

White

Weapon has not been bore-

tered in rounds counter) when

B/S

sighted or failed the boresight

powering up a TESS missile.

verification. Subsystems will

Safety inhibit.

function normally but without py-

TRK X

White

Displayed for 4 seconds to indi-

lon CBHK corrections.

DEL

cate TADS target track number

RF MSL

Indicates an RF missile is track-

X has been deleted by the CPG

TRACK

ing.

RKT

Indicates time (in seconds) until

TRK X

White

Displayed for 4 seconds to indi-

TOF=NN

rocket impact. If more than one

DROP

cate TADS target track number

volley is in flight, the display will

X has been dropped by the

show TOF for the last volley

tracker

launched.

White

An error has occurred. An illogi-

ROUNDS

The gun system has been ac-

cal and invalid condition has

NNNN

tioned and the NNNN indicates

been identified.

the number of rounds remaining

and will count down one unit for

Message

Color

Description

each firing PULSE.

HELLFIRE Inhibits

SAL

White

Indicates the selected SAL mis-

ACCEL

White

Indicates the vertical accelera-

SEL?

sile type is unavailable. Only dis-

LIMIT

tion is less than or equal to .5

played in SAL1 or SAL2 SAL

Gs and may cause the main ro-

SELECT modes.

tor blades to obstruct the trajec-

SIM

Indicates launch commanded in

tory of the weapon. Safety inhib-

LAUNCH

the training mode. This mes-

it.

sage is displayed for 2 seconds.

ALT

White

Indicates an alternate launch is

TYPE?

White

Indicates no rocket type se-

LAUNCH

in progress. Safety inhibit.

lected.

BACK-

White

Indicates, based on Missile

WEAP-

White

The weapons trigger has been

SCAT-

Seeker vs TADS LOS, the seek-

ON?

pulled without a weapon being

TER

er is not tracking the TADS La-

actioned.

ser designation. Safety inhibit.

White

An error has occurred. An illogi-

BAL LIM-

White

Indicates range or other en-

cal and invalid condition has

gagement parameters exceed

been identified.

the ballistics processing capabil-

ity of the system.

4.16.5 Weapon Inhibit Status Field. The HAD weap-

on inhibit field (table 4-5) is located in the center area of

the display field just above the Sensor FOR box and occu-

pies 12 character spaces. This field provides an indication

of safety or performance inhibit messages based on the

selected weapon system.

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

Change 4

4-23

TM 1-1520-251-10

Table 4-5. HAD Weapon Inhibit Status Field

Messages (cont)

HELLFIRE Inhibits (cont)

Message

Color

Description

Message

Color

Description

HELLFIRE Inhibits (cont)

PYLON

White

Indicates that the commanded

DATA IN-

White

This weapon has been actioned,

LIMIT

pylon position exceed the pylon

VALID

the FCR has been selected as

articulation limits (+4° to - 5° on

the active sight and the RF

ground) (+4° to - 15° in air). Per-

handover data recently received

formance or safety inhibit de-

has been detected as outside

pendent on air/ground status.

the navigational performance

parameters for weapons en-

RATE

White

Indicates the aircraft pitch, roll or

gagement. Safety inhibit.

LIMIT

yaw rate or acceleration is ex-

cessive. Performance inhibit.

GUN

White

Indicates the missiles resident

ROLL

White

Indicates the aircraft roll position

OB-

on inboard launchers are inhib-

LIMIT

is excessive. Performance inhib-

STRUCT

ited from launch because the

it.

gun is out of coincidence and

may obstruct the trajectory of

SKR LIM-

White

Indicates the missile seeker azi-

the missile. Safety inhibit.

muth or elevation gimbal limit

has been reached. Performance

LASER

White

The ST/UPDT switch on the

inhibit.

RANGE?

LHG has been selected to the

UPDT position and the current

TRAIN-

White

Indicates the weapon training

range source is other than laser.

ING

mode is active, or the TESS is

enabled, and the armament con-

LOS

White

Indicates the selected LOS is ei-

trol is in the ARM state and a

INVALID

ther failed or invalid. Selection of

weapon is actioned in either

HMD as the sight when HMD

crew station.

symbology belongs to the alter-

nate crewmember will also gen-

TXX

White

Displayed for 4 seconds to indi-

erate this inhibit. This condition

cate file address in which the

can occur either when the CPG

coordinate data has been stored

selects presentation of the pilot

(TADS/FCR target store switch

information using the ORT VID

on LHG).

SEL select or TEDAC PNV

YAW

White

Indicates yaw position of the air-

switch, and can also occur dur-

LIMIT

craft with respect to the target is

ing single display processor op-

excessive. Applies to LOAL

erations. Safety inhibit.

mode only. Performance inhibit.

MSL NOT

White

No HF missiles are ready for

GUN Inhibits

RDY

launch: no SAL missile priority

channel selected or RF missile

ALT

White

Indicates a Rocket or Hellfire

transfer alignment not complete.

LAUNCH

launch is in progress. Safety in-

hibit.

PYLON

White

Indicates the pylon position is u

White

Indicates the gun is positioned

ANGLE

10 ° from the optimum launch

LIMIT

at an azimuth limit. Safety inhib-

position or that pylon position is

it.

unknown. Performance inhibit.

BAL

White

Indicates range or other en-

PYLON

White

Indicates the aircraft is on the

LIMIT

gagement parameters exceed

ERROR

ground and the pylons position

the ballistics processing capabil-

is unknown or that the pylons

ity of the system.

are positioned such that the mis-

sile may strike the ground near

COINCI-

White

Indicates the gun is currently out

the aircraft. Safety inhibit.

DENCE

of coincidence. Safety inhibit.

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

4-24

Change 4

TM 1-1520-251-10

Table

4-5. HAD Weapon Inhibit Status Field

Table 4-5. HAD Weapon Inhibit Status Field

Messages (cont)

ROCKET Inhibits (cont)

Message

Color

Description

PYLON

White

Indicates that the commanded

LIMIT

pylon position exceed the pylon

GUN Inhibits (cont)

articulation limits (+4° to - 5° on

ground) (+4° to - 15° in air). Per-

White

Indicates the gun is positioned

formance or safety inhibit de-

LIMIT

at an elevation limit. Safety in-

pendent on air/ground status.

hibit.

SAFE

White

Indicates the weapon system

LOS

White

Indicates the selected LOS is ei-

has not been ARMed through

INVALID

ther failed or invalid. Safety in-

the ARMAMENT control panel.

hibit.

TRAIN-

White

Indicates the weapon training

SAFE

White

Indicates the weapon system

ING

mode is active, or the TESS is

has not been ARMed through

enabled, and the armament con-

the ARMAMENT control panel.

trol is in the ARM state and a

weapon is actioned in either

TRAIN-

White

Indicates the weapon training

crew station.

ING

mode is active, or the TESS is

TXX

White

Displayed for 4 seconds to indi-

enabled, and the armament con-

cate the file address in which the

trol is in the ARM state and a

coordinate data has been

weapon is actioned in either

stored.

crew station.

TYPE

White

Indicates that no rocket type is

TXX

White

Displayed for 4 seconds to indi-

SELECT

selected. Safety inhibit.

cate the file address in which the

coordinate data has been

4.16.6 Sight Select Status Field. The HAD sight se-

stored.

lect status field (table 4-6) is located on the top left of the

display field and occupies 5 character spaces. This field

ROCKET Inhibits

provides status of the state of the selected sight in that

station. The LINK status

displays when the FCR and

ACCEL

White

Indicates that the vertical accel-

TADS are operating in a linked mode.

LIMIT

eration is less than .5 G’s and

may cause the main rotor

Table 4-6. HAD Sight Select Status Field Messages

blades to obstruct the trajectory

of the rockets. Safety inhibit.

Message

Color

Description

ALT

White

Indicates that a Hellfire launch is

P-FCR/

White

The PLT or CPG has selected

LAUNCH

in progress. Safety inhibit.

C-FCR

FCR as the active LOS.

GUN

White

Indicates the rockets resident on

P-FCRL/

White

FCR is the selected sight and

OB-

inboard launchers are inhibited

C-FCRL

TADS is linked to the FCR NTS.

STRUCT

from launch because the gun is

If a missile is tracking, TADS is

out of coincidence and may ob-

linked to the missile LOS.

struct the trajectory of the rock-

P-HMD/

White

The PLT or CPG has selected

ets. Safety inhibit.

C-HMD

HMD as the active LOS.

LOS

White

Indicates that the selected LOS

TADS

White

The CPG has selected TADS as

INVALID

is either failed or invalid. Safety

the active LOS.

inhibit.

TADSL

White

TADS is the selected sight and

FCR is linked to the TADS.

PYLON

White

Indicates that the pylon eleva-

ERROR

tion position is not equal to the

White

An error has occurred. An illogi-

commanded pylon position.

cal and invalid condition has

Safety inhibit.

been identified.

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

Change 3

4-25

TM 1-1520-251-10

4.16.7 HMD FORMAT OWNER CUE. During single DP

EOCCM filters and growth provisions for an image intensi-

operations, the HMD FORMAT OWNER CUE will read

fication system to compliment the FLIR. This system per-

PLT FORMAT or CPG FORMAT. This will flash for 3 sec-

mits the pilot to fly nap-of-the-earth (NOE), and enhances

onds whenever the ownership changes, and upon entry/

navigation at night or in limited adverse weather. The

exit into single DP operations. Refer to paragraph 4.50.3.

PNVS provides the pilot or CPG with a high resolution

FLIR video.

4.16.8 Acquisition Select Status Field. The HAD ac-

4.18 PNVS OPERATION

quisition select status field (table 4-7) is located on the top

right of the display field and occupies 4 character spaces.

When NVS NORM is selected, the turret is slaved to the

This field provides status of the selected acquisition

helmet LOS. During normal operations, the pilot has con-

source in that crew station.

trol of the PNVS turret. However, if the pilot becomes inca-

pacitated, the CPG may take control of the PNVS.

4.18A [

FLIR SCENE ASSISTED

Table 4-7.

HAD Acquisition Status Field Messages

NON - UNIFORMITY CORRECTION (SANUC)

Message

Color

Description

The SANUC process is performed in order to assure full

convergence of the NUC coefficients to fully optimize

FCR

The operator has selected FCR

FLIR image quality for PNVS and TADS.

as the acquisition source.

FXD

The operator has selected FXD

Standard Process Initialization

as the acquisition source.

• The standard SANUC process will be automatical-

GHS

The operator has selected GHS

ly performed following FLIR cool - down. No imag-

as the acquisition source.

ery will be displayed during cool - down and

PHS

The operator has selected PHS

SANUC. Once the SANUC is completed (approxi-

as the acquisition source.

mately 14 seconds). FLIR imagery will be dis-

RFI

The operator has selected RFI

played and the sensor will become available for

as the acquisition source.

use.

SKR

The operator has selected SKR

• During SANUC, the optics are defocused to

as the acquisition source.

remove high frequency scene content and SA-

TADS

The operator has selected TADS

NUC thresholds are opened up to allow rapid

as the acquisition source.

update of both gain and level coefficients.

For PNVS, this operation requires the gimbal to

TXX, or

The operator has selected TXX,

move to fixed forward and dither in elevation for

CXX, or

CXX, WXX, or HXX as the ac-

several seconds so that the FLIR sensor sees a

WXX, or

quisition source.

variety of temperatures in the scene.

HXX

For TADS, the turret will move to fixed forward and

TRN

The operator has selected Ter-

dither in elevation for several seconds.

rain Point as the acquisition.

• If the turret is in use with a TV sensor when FLIR

White

An error has occurred. An illogi-

cool - down is complete, SANUC will not be

cal and invalid condition has

performed until FLIR is selected as the sensor.

been identified.

One - Touch Process Initialization

4.17 PNVS DESCRIPTION

•

The one- touch SANUC process will be performed

for FLIR power - up in the air. It will take approxi-

NOTE

mately one second to perform a single point

correction at the scene temperature when FLIR

If using EXT PWR TADS/PNVS will not pow-

cool - down is complete. No imagery will be dis-

er up automatically.

played during cool - down, however, imagery will

be available during the one - touch and the opaque

The PNVS consists of a FLIR sensor contained in a stabi-

filter will be visible. The opaque filter is used as the

lized rotating turret mounted above the TADS. The aircraft

single reference for the one - touch, which corrects

may be equipped with legacy PNVS or Modernized PNVS

for offset errors, but not gain or quadratic coeffi-

(MPNVS) which includes an improved FLIR sensor with

cient errors.

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

4-26

Change 4

TM 1-1520-251-10

The SANUC process is performed under the following cir-

4.20 TADS DESCRIPTION

cumstances:

NOTE

• For normal ground initialization, the standard

If using EXT PWR TADS/PNVS will not pow-

SANUC initialization process that involves gimbal

er up automatically.

slewing remains for normal TADS FLIR power - up

on the ground.

The TADS assembly is an Electro-Optical system that

uses direct view optics (DVO)(ORT only), a day television

• For rapid/emergency departure/power interrup-

(DTV) sensor, a laser spot tracker (LST), a laser range-

tions/in - flight initialization, a quick one - touch

finder/ designator (LRF/D), and a forward looking infrared

procedure is implemented for use while the aircraft

(FLIR) sensor for day, night, and limited adverse weather

is in the air. The weight - on - wheels signal being

operations. The aircraft may be equipped with legacy

sent form the aircraft to the M - TEU or M - PEU is

TADS or Modernized TADS (MTADS) which includes an

used to determine which procedure will be per-

improved FLIR sensor and, in addition to the components

formed.

listed above, automated internal boresight, EOCCM fil-

The SANUC coefficients change during operation

ters, a multi - target tracker and growth provisions for an

to remove residual fixed pattern noise and are able

extended range (XR) zoom FOV.

to pull the image in over the next few minutes.

During the remainder of the flight, additional

4.20A TADS ELECTRONIC DISPLAY AND CONTROL

one - touch updates are performed.

(TEDAC) CONTROLS

• For IBIT, a commanded SANUC update is inte-

The TEDAC bezel panel (fig 4-27A) provides access to

grated into the IBIT process (for ground testing).

the controls necessary to adjust video on the TEDAC Dis-

Also, a commanded one - touch update is inte-

play Unit (TDU) and the CPG HMD.

grated into the IBIT process (for flight testing).

• For TADS internal boresight, in the case of the

TADS FLIR, a one - touch is used to perform a

1a.

1b.

1c.

1d.

near - term SANUC coefficient update for bore-

sighting.

Typical in - flight boresight is performed twice per

flight. Integrating an additional one - touch update

into the beginning of the internal boresight process

provides the best - compensated image prior to

delivering weapons. This is an automatic step in

the boresight process and is performed during the

gimbal slew time.

• For standby (turret in stow), one touch update is

performed upon exit. This is a quick, easy method

to recalibrate the image.

4.19

PNVS ANTI-ICE

LBA5501

When the pilot or CPG selects anti-ice using the aircraft

UTIL page ANTI-ICE SENSOR button and the helicopter

Figure 4-27A. TEDAC Controls

is off the ground, 115 Vac is applied to the PNVS shroud

window and a shroud frame heater. When the anti-ice is

turned on (automatically or manually) and the aircraft is in

1. Video Select Buttons. These bezel pushbuttons

the air, power is applied to the PNVS window and shroud

select the video source to be displayed to the CPG on the

frame heaters. PNVS anti-ice can be selected when the

TDU. The default video upon initialization is based on the

aircraft is on the ground by using the GND button.

default sight selection of HMD (flight format, no video).

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

Change 4

4-26.1

TM 1-1520-251-10

Subsequently selecting one of these pushbuttons will pro-

NOTE

vide the selected video.

Symbol Brightness (SYM), Display Bright-

ness (BRT) and Display Contrast (CON)

a. TAD. The TAD pushbutton selects TADS as the

rocker switches operate in three different

video source.

modes:

Step Input - Momentarily pressing and re-

leasing the switch will cause a single step

b. FCR. The FCR pushbutton selects the FCR tar-

change.

geting format to be displayed.

Slow Rate Input - Pressing and holding the

switch for 1/2 second will cause change

c. PNV. The PNV pushbutton selects PNVS as the

continually at the slow rate.

video source.

Fast Rate Input - Pressing and holding the

switch for more than one second will cause

d. G/S. The G/S pushbutton activates the grayscale for

change continually at a fast rate.

the video display. The G/S format will completely fill the dis-

play area and the bottom bezel button labels will be removed.

7. Symbol Brightness. The SYM switch adjusts

the intensity of the TADS LOS reticle, IAT gates and FCR

2. Day/Night/Off Mode. The DAY/NT/OFF control

targeting format symbology brightness. The adjustment

knob selects the TEDAC day, night and off modes of op-

varies form black to white.

eration.

8. Display Brightness. The display BRT switch ad-

justs the grayscale and/or image brightness intensity.

a. DAY. The day mode provides a brighter day

mode luminance with a white backlight color. Video ap-

9. Display Contrast. The CON switch adjusts the

pears as shades of gray.

grayscale and/or image contrast intensity.

10. Asterisk (*) Button. The (*) pushbutton adjusts the

b. NT. The night mode extinguishes the backlight

brightness and contrast to nominal settings to rapidly regain

brightness and provides a lower night mode luminance

visibility of the selected video. The settings are unique to the

with a green NVG compatible backlight. Video appears as

day or night selection of the DAY/NT/OFF control.

shades of green.

11. Azimuth Adjust. The AZ adjust switch is used

c. OFF. The off position extinguishes all iluminating

for various boresight adjustments. It is active only when

backlight even though the video is routed to the TDU.

the AZ/EL boresight enable pushbutton is selected.

12. AZ/EL Boresight Enable. The AZ/EL boresight

enable button is used to enable boresight controls. Select-

3. FLIR Level. The FLIR LEV control adjusts FLIR

ing the pushbutton will cause the AZ/EL label to become

level for the TADS or PNVS FLIR imagery as selected at

boxed and enable the EL and AZ bezel switches for vari-

the NVS select switch.

ous boresight adjustments.

13. Automatic Contrast Mode (ACM). The ACM

4. FLIR Gain. The FLIR GAIN control adjusts FLIR

button is used to activate the ACM. Selecting the ACM

gain for the TADS or PNVS FLIR imagery as selected at

pushbutton will cause the ACM label to become boxed

the NVS select switch.

and activate the ACM. In this mode, FLIR LEV and GAIN

controls are disabled and FLIR gain and level are auto-

matically adjusted to compensate for scene thermal con-

5. Range Focus. The R/F switch adjusts video fo-

tent changes and switching polarities.

cus in DTV or FLIR video. The minimum distance that may

NOTE

be focused is 500m for FLIR NFOV or MFOV; 1500m for

DTV NFOV.

All other switches/pushbuttons on the TE-

DAC bezel remain active when the display is

in a FREEZE state. Any inputs/adjustments

6. Elevation Adjust. The EL adjust switch is used

made when the display is in this state will

for various boresight adjustments. It is active only when

become visible when the FREEZE button is

the AZ/EL boresight enable button is selected.

deselected.

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

4-26.2

Change 4

TM 1-1520-251-10

14. Display Freeze. The FREEZE button is used to

protection. Selecting the FILTER pushbutton will cause the

freeze the video imaging on the TDU. Selecting the

FILTER label to become boxed when Filter 1 or 2 is selected.

FREEZE button will cause the FREEZE label to become

Selections are set sequentially to Filter 1, Clear, Filter 2,

boxed and freeze the currently selected video. The video

Clear, Filter 1, etc. The selected state is reflected in the se-

image may be returned to normal by deselecting the

lected sensor status on the weapon format on the TDU/

FREEZE button or by selecting another video source.

HMD The filter should be inserted when a circular type

pattern containing saturated pixels and encompassing

15. Sensor Filter. The FILTER button is used to select

approximately 1/5 the FOV is observed. A reduced size in

between the two spectral filters in the TADS FLIR sensor. The

the circular type pattern will result.]

FLIR filters are used as countermeasures protection. Select-

ing the FILTER pushbutton will cause the FILTER label to be-

16. TEDAC Display Unit (TDU). The TDU is used

come boxed and set the FLIR filter to maximum. The filter

for viewing images generated by the TADS DTV or FLIR,

may be returned to clear by deselecting the FILTER button.

FCR

or VCR. It is an active matrix liquid crystal display

The TADS FLIR filter is functional only on aircraft equipped

(AMLCD) with a viewable area 5 inches square. Video im-

with the Optically Improved (OI) TADS.

agery is presented in a 4x3 aspect display area in the up-

[

The FILTER button is used to select between the

per portion of the viewable area. Control labels for the AZ/

three spectral filters in the TADS FLIR sensor: Clear, Filter 1,

EL, ACM, FREEZE, and FILTER buttons are displayed in

and Filter 2. The FLIR filters are used as countermeasures

the lower portion of the viewable area.

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

Change 4

4-26.3/(4-26.4 blank)

TM 1-1520-251-10

4.21 OPTICAL RELAY TUBE (ORT) CONTROLS

5. Grayscale. The GS switch activates the grays-

cale for the ORT HOD or HDD video displays. The grays-

The ORT control panel (fig 4-28) provides access to the

cale is displayed on these displays based on the selection

controls necessary to adjust video on the HOD/HDD and

of the HDD switch located on the ORT RHG.

the CPG HMD. The adjustable faceplate includes an opti-

cal eyepiece with adjustable focus.

6. Visor Retract. Inactive.

1. FLIR Level. The FLIR LVL control is used to ad-

7. Night Mode. The NT switch activates the night

just FLIR level for the TADS or PNVS FLIR imagery as se-

filter. Momentarily pressing the NT pushbutton switch

lected at the NVS select switch.

toggles the red night filter for the HDD.

2. FLIR Gain. The FLIR GAIN control adjusts FLIR

gain for the TADS or PNVS FLIR imagery as selected at

8. Automatic Contrast Mode (ACM). The ACM

the NVS select switch.

control provides automatic FLIR gain and level control.

The ACM position disables the FLIR gain and level con-

trols and automatically adjusts FLIR gain and level control

3. Range Focus. The RNG FOC switch adjusts vid-

to compensate for scene thermal content changes and

eo focus in DTV or FLIR video. The minimum distance

switching polarities. The down position (no label) disables

that may be focused is 500m for FLIR NFOV or MFOV;

ACM and enables the FLIR GAIN and FLIR LVL knobs.

1500m for DTV NFOV.

4. Video Select. The VID SEL switch selects the

9. Symbol Brightness. The SYM BRT control ad-

video source to be displayed to the CPG on the ORT

justs the intensity of the ORT format, TADS LOS reticle,

HOD/HDD. Placing the switch to one of three positions will

and IAT gate symbology brightness. The adjustment va-

select the video source: TADS, FCR

, or PNVS.

ries from black to white.

LVL

ACM

GAIN

SYM

BRT

TADS

RNG

CLEAR

BRT

PNVS

FOC

GLARE

DSPL

VID

FLTR

SEL

CONT

FLTR SEL SWITCH FOR

V/RET

AND

OPTICALLY IMPROVED TADS

BRT

LBA1021

Figure 4-28. ORT Control Panel

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

4-27

TM 1-1520-251-10

10. Display Brightness. The display BRT control

The status fields (sections) displayed in the AND are:

adjusts the grayscale and/or image brightness intensity.

a. Sight Status Field.

11. Filter Select. The FLTR SEL switch located on

the right side of the ORT control panel selects a filter for

b. Weapon Status Field.

the DVO. Placing the switch to one of two positions will se-

lect the DVO filter: CLEAR, HAZE GLARE, GLARE, or

HAZE. In the Optically Improved (OI) TADS, filter selec-

c. Tracker Status Field.

tion can also be made when sensor select is FLIR. The

FLIR filters are used as countermeasures protection.

d. LRFD and LST Code Status Field.

There are two selections: CLEAR and MAX.

e. Enhancement Display Status Field.

[

The FLTR SEL switch located on the right side of

the ORT control panel selects between the three spectral

f. Missile Inventory and Status Field.

filters in the TADS FLIR sensor: Clear, Filter 1, and Filter 2.

The FLIR filters are used as countermeasures protection.

The selected state is reflected in the selected sensor sta-

4.22.1

AND Messages. Messages will be centered

tus on the weapon format on the ORT/HMD.]

within the appropriate status field.

12. Display Contrast. The DSPL CONT control ad-

4.22.2 AND Sight Status Field. The AND sight status

justs the grayscale and/or image contrast intensity.

field is located on the top left of the display adjacent to the

left missile status and inventory field and occupies 8 char-

13. Alphanumeric Display (AND) Brightness. The

acter spaces. Messages and their definitions are con-

AND BRT control adjusts the brightness intensity of the

tained in table 4-8.

AND.

14. Head Out Display (HOD). The HOD is used for

Table 4-8. Sight Status Field Messages

viewing images generated by the DTV, TADS FLIR,

PNVS, FCR

, and VCR.

MESSAGE

DEFINITION

15. Head Down Display (HDD). The HDD is viewed

CSCOPE

C-scope has been turned ON.

through the faceplate eyepiece. It is used for direct view-

FLIRFAIL

FLIR has been detected as NO - GO.

ing of real world images through the DVO as well as view-

Night side capabilities are lost includ-

ing of images generated by the DTV, TADS FLIR, PNVS,

ing use of the TADS for NVS pilotage.

FCR

, and VCR. It is also used to view the AND status

CPG must use DVO or DTV.

messages.

IMPEND

The laser is approaching conditions

LASER

which will prohibit it from firing. The

4.22 ORT ALPHANUMERIC DISPLAY (AND)

INHIBIT

message alternates (IMPEND, then

LASER, then INHIBIT).

The alphanumeric display (AND) is located below the

LASER

The laser has been inhibited from fir-

head down display in the ORT. It consists of a light emit-

INHIBIT

ing. The message alternates (LASER,

ting diode array of 24 character spaces long and 4 spaces

then INHIBIT).

high (fig 4-29). The AND provides information to the CPG

LRFD

TADS LRF/D power is ON and the

for use in the operation of sight and weapons systems.

COOLANT

transceiver coolant level detected as

low. The message alternates (LRFD,

then COOLANT).

LSTCODE?

The selected LST laser code is not us-

able.

PLT TADS

The pilot controls the TADS as the

LBA2560

NVS sensor through LINK.

RFDCODE?

The selected LRFD laser code is not

Figure 4-29. Alphanumeric Display

usable.

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

4-28

Change 4

TM 1-1520-251-10

Table 4-8. Sight Status Field Messages (cont)

Table 4-9. Weapon Status Field Messages

(WAS =MSL) (cont)

MESSAGE

DEFINITION

DIR RIPL

Missile trajectory is direct; missile

TADSFAIL

TADS has been detected as NO - GO

mode is ripple.

and the TADS LOS defaults to fixed

FIRE

Minimum time between launch has

forward.

MISSILES

elapsed in rapid fire Hellfire missile

engagement, and one or more mis-

TADS NOT

TADS is selected and turret internal

siles are present in the PRI channel

READY

temperature has not reached operat-

after launch of a missile. The mes-

ing temperature. The message alter-

sage alternates (FIRE, then MIS-

nates (TADS NOT, then READY).

SILES).

TADSTEMP

TADS is selected and the turret inter-

HANGFIRE

Fire signal sent but umbilical separa-

nal temperature is detected as over-

heating.

tion did not occur at predicted time.

Message is displayed for 6 seconds,

TGT LOS

The LOS to the selected TXX acquisi-

during which time all missiles on that

INVALID

tion source is invalid. The message

side of the aircraft become “not avail-

alternates (TGT LOS, then INVALID).

able” and are inhibited from firing.

TV FAIL

TADS has been detected as NO - GO.

Replaces “MSL LNCH/TOF = NN”.

CPG must use DVO or FLIR.

HFTOF=NN

Indicates time (in seconds) until mis-

sile impact. If more than one missile

is in flight, displays TOF for first mis-

4.22.3 AND Weapon Status Field. The AND weapon

sile launched, then subsequent mis-

status field is located between the sight status field and

siles.

the right missile status and inventory field and occupies

HI NORM

Missile trajectory is high; missile

eight character spaces. Messages and their definitions

mode is normal.

are contained in tables 4-9 through 4-11.

HI RIPL

Missile trajectory is high; missile

mode is ripple.

HI MAN

Missile trajectory is high; missile

mode is manual.

Table 4-9.

Weapon Status Field Messages

LASE NN

Cue to lase target for terminal missile

(WAS = MSL)

TARGET

guidance. Displayed for 4 seconds

starting at TOF=12. Calculated TOF

in place of “TOF = NN” message is

MESSAGE

DEFINITION

displayed if actual trajectory is not

ALT CHAN

Alternate missile channel tracking.

LOBL. The message alternates

TRACK

The message alternates (ALT

(LASE NN, then TARGET).

CHAN, then TRACK).

LOAL MAN

Missile launch mode is LOAL; missile

mode is manual.

ALTCODE?

Indicates selected code for the alter-

nate channel is unusable. This is due

LOALNORM

Missile launch mode is LOAL; missile

to the lack of PIM Code/Keyword cor-

mode is normal.

relation or the SAL SEL is AUTO, the

LOBL INH

The LOBL inhibit mode is selected

selected code is PIM and no SAL 2

(RF missile launch).

missiles are available but SAL 1 mis-

siles are. Only displayed in ripple

LOBL MAN

Missile launch mode is LOBL; missile

mode.

mode is manual.

DIR MAN

Missile trajectory is direct; missile

LOBLNORM

Missile launch mode is LOBL; missile

mode is manual.

mode is normal.

DIR NORM

Missile trajectory is direct; missile

LOBLRIPL

Missile launch mode is LOBL; missile

mode is normal.

mode is ripple.

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

4-29

TM 1-1520-251-10

Table 4-9. Weapon Status Field Messages

(WAS =MSL) (cont)

SAL SEL?

Indicates the selected SAL missile

LO MAN

Missile trajectory is low; missile mode

type is unavailable. Only displayed in

is manual.

SAL1 or SAL2 SAL SELECT modes.

LO NORM

Missile trajectory is low; missile mode

SIGHT?

Sight selected for HF missile launch

is normal.

is not valid or has failed.

LO RIPL

Missile trajectory is low; missile mode

SIM LNCH

Missile launch commanded in train-

is ripple.

ing mode. Message is displayed for 2

seconds.

MISFIRE

Indicates a HF misfire has occurred.

The HF launch sequence was initi-

TGTDATA?

No target data available for RF mis-

ated and aborted prior to missile

sile launch.

launch. This message is displayed

2CHAN...

Priority and alternate missile chan-

for 2 seconds.

TRACK

nels tracking. The message alter-

MSL LNCH

Missile launch commanded in tactical

nates (2CHAN, then TRACK).

mode. Message is displayed for 2 se-

conds.

Table 4-10.

Weapon Status Field Messages

MSL SEL

No priority channel selected.

(WAS=RKT)

MSLTYPE?

Indicates no missiles of the selected

MESSAGE

DEFINITION

type (RF or SAL) are available.

LIMITS

The wing pylons have articulated to

NO...

The RF missile has completed at-

the elevation limit.

ACQUIRE

tempts to acquire the target and has

returned to the standby mode. The

NO RKTS

The rocket quantity available is 0.

message shall alternate (NO, then

PYLON B/S

The pylons have not been bore-

ACQUIRE).

sighted or have failed the boresight

NO MSLS

Indicates missiles have been ac-

verification. Subsystems will function

tioned, but no RF missiles available.

normally but without pylon boresight

corrections.

PRI CHAN..

Priority missile channel tracking. The

TRACK

message alternates (PRI CHAN,

RKT BIT...

The rocket system components are

then TRACK).

INPROG

undergoing a power - on BIT. The

message alternates (RKT BIT, then

PRICODE?

Indicates selected code for the pri-

INPROG).

mary channels is unusable. This is

due to lack of PIM Code/Keyword

RKT G - S

The wing pylons are commanded to

correlation or the SAL SEL is AUTO,

ground stow.

the selected code is PIM and no SAL

RKT NORM

The rocket system is operating in the

2 missiles are available but SAL 1

normal articulation mode.

missiles are.

RTOF=NN

Indicates time (in seconds) until rock-

PYLN B/S

Pylons have not been boresighted, or

et impact. If more than one volley is

have failed boresight verification.

in flight, the display will show TOF for

Subsystems will function normally but

the volley last launched.

without pylon boresight corrections.

SIGHT?

The sight selected for rocket launch

RF MSL...

RF missile channel tracking. The

is not valid or it has failed.

TRACK

message alternates (RF MSL, then

TRACK).

TYPE?

No rocket warhead type is selected.

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

4-30

TM 1-1520-251-10

Table 4-11.

Weapon Status Field Messages

Table 4-12. AND Tracker Status Field (cont)

(WAS=GUN)

IAT BREAK-

The image auto tracker has broken

MESSAGE

DEFINITION

LOCK

track.

GUN B/S

The gun has not been boresighted or

IAT OFFSET

IAT offset tracking is engaged.

has failed the boresight verification.

IAT TRACK

IAT tracking is engaged and tracking.

The gun will function normally but

without pylon boresight corrections.

IAT B/W

IAT polarity is black on white.

GUN FAIL

The gun has been detected as failed.

IAT W/B

IAT polarity is white on black.

Recycle the GUN system - ON/OFF

IAT AUTO

IAT is in the automatic mode

POWER button. If the fault message

clears, continue operation.

4.22.5 AND LRFD and LST Code Status Field. The

GUN JAM

The gun has been detected as

AND LRFD and LST code status field is located directly

jammed.

below the tracker status field and occupies 16 character

spaces. Messages and their definitions are contained in

RDSNNNN

The gun system is operating in the

selected mode. The NNNN indicates

table 4-13.

the number of rounds remaining and

will count down in real time as the

Table 4-13. AND LRFD and LST Status Field

gun is fired.

SIGHT?

The sight selected for gun firing is not

MESSAGE

DEFINITION

valid or it has failed.

LRFD FIRST

The LRFD has been activated and

WEAPON?

The weapons trigger has been

the LRFD button is set to FIRST.

pressed with no weapon system ac-

LRFD LAST

The LRFD has been activated and

tioned.

the LRFD button is set to LAST.

CODELST=A

LRFD is not operational but the LST

4.22.4 AND Tracker Status Field. The AND tracker

is operational and the selected code

status field is located directly below the sight and weapon

is A.

status fields and occupies 16 character spaces. Mes-

CODELST=

LST is not operational but the LRFD

sages and their definitions are contained in table 4-12.

LRFD=G

is operational and the selected code

is G.

CODELST=A

Both systems are operational and the

Table 4-12. AND Tracker Status Field

LRFD=G

code selected from the CODE Page

is displayed for each.

MESSAGE

DEFINITION

4.22.6 AND Enhancement Display Status Field. The

PNVS STOW

The PNVS is stowed.

AND Enhancement Display status field is located directly

TADS STOW

The TADS is either stowed or in an

below the LRFD and LST code status field and occupies

internal boresight mode.

16 character spaces. Messages and their definitions are

TADS FIXED

The TADS is in the fixed forward

contained in table 4-14.

position.

LST FAIL

The LST has been detected as failed.

Table 4-14. AND Enhancement Display Status Field

LST TRACK

The LST is tracking remotely desig-

nated laser energy.

MESSAGE

DEFINITION

LST SEARCH

The LST is scanning under manual

FIXED

Rockets OR Gun Actioned, Rocket

control.

IMPACT RTCL

launchers stowed/Gun in fixed mode.

LST AUTO

The LST is scanning in the automatic

PRI=?ALT=?

No missiles ready.

search pattern.

PRI=AALT=B

The priority channel code is A with

IAT FAIL

The image auto tracker has broken

missile(s) ready; alternate channel

track.

missiles are ready.

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

4-31

TM 1-1520-251-10

Table 4-14. AND Enhancement Display Status Field

Table 4-17. AND Missile Inventory and Status Field

(cont)

(MISSILE FAULT CONDITION)

MESSAGE

DEFINITION

Missile Unlatched on the launcher.

PRI=BALT=?

The priority channel code is B with

Missile has failed.

missile(s) ready; alternate channel

missiles are not ready.

Missile launch has aborted/misfired.

AH - 64D

Displayed when no other message is

APACHE

displayed.

Missile has hangfired.

Missile launch station has failed.

4.22.7 AND Missile Inventory and Status Field. The

AND Missile Inventory and Status fields are located on

both ends of the AND and each field occupies 16 charac-

Missile not available.

ter spaces, 4 spaces wide and 4 spaces high. Each side is

divided vertically in half to provide space for the status of

Missile detected in over-temperature

missiles of 2 launchers on each wing. Each launcher is

status.

subdivided into 8 spaces, 2 vertical spaces for each mis-

Table 4-18. AND Missile Inventory and Status Field

sile status message. Messages and their definitions are

(MISSILE STATUS)

contained in tables 4-15 through 4-18.

MESSAGE

DEFINITION

F F

Missile launcher failed.

Table 4-15. AND Missile Inventory and Status Field

A A

I I

(MISSILE TYPE)

L L

S S

Missile launcher ARM/SAFE is in the

A A

SAFE position.

MESSAGE

DEFINITION

F F

Laser missile.

E E

A THROUGH

Code of missile in place of L.

4.23 ORT BOTTOM CONTROLS

The ORT bottom controls (fig 4-30) consists of those con-

RF Missile.

trols necessary to perform certain TADS boresight adjust-

T (STEADY)

Missile seeker in a track state.

ments.

Table 4-16. AND Missile Inventory and Status Field

(MISSILE STATUS)

MESSAGE

DEFINITION

Missile selected.

R (STEADY)

Missile ready.

Priority missile for LOAL engage-

(FLASHING)

ment.

LBA0441

Priority missile for LOBL engage-

(FLASHING)

ment.

Figure 4-30. ORT Bottom

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

4-32

TM 1-1520-251-10

4.23.1 BORESIGHT ENABLE (1). The BORESIGHT

TADS FOV SWITCH

TADS SENSOR

IAT/

SELECT SWITCH

ENABLE switch enables sensor boresighting functions.

OFFSET

SWITCH

Placing the switch to the UP position enables the azimuth

and elevation knobs for various boresight adjustments.

Placing the switch to the CENTER position disables the

azimuth knob, elevation knob, and DVO boresight switch.

Placing the switch to the DOWN position enables the DVO

STORE/

boresight adjust switch.

UPDATE

SWITCH

FCR

4.23.2 DVO Boresight Adjust (2). The DVO BRSIT

SCAN

FCR MODE

switch is used for boresight adjustment to the DVO cross-

SWITCH

hairs. Placing the switch to the UP position causes the

CUED

DVO crosshairs to rotate clockwise. Placing the switch to

the DOWN position causes the DVO crosshairs to rotate

SWITCH

counterclockwise in a helical motion.

LINEAR

MOTION

4.23.3 Azimuth Adjust (3). The azimuth adjust knob is

COMPENSATION

a knurl potentiometer knob used for various boresight ad-

SWITCH

justments.

LBA1038

Figure 4-31. LHG

4.23.4 Elevation Adjust (4). The elevation adjust knob

is a knurl potentiometer knob used for various boresight

4.24.1 Image Auto Track/Offset. The IAT/OFS switch

adjustments.

engages or disengages the image autotracker and offset

tracking.

4.24 LEFT HANDGRIP (LHG)

[

The IAT/OFS switch is used to control the multi - tar-

get tracker (MTT). The IAT position engages the tracker to

The LHG (fig 4-31) in the CPG station provides access to

establish a primary target track. Pressing and holding the

the various sight subsystem control functions.

switch in the IAT position for longer than 0.6 seconds will

initiate manual sizing control of the tracking gates. This

position is also used to adjust an aim point within the pri-

mary tracking gates. The OFS position returns the TADS

LOS to the primary track when offset tracking. This posi-

tion also deletes target tracks when the LOS is on a prima-

ry or secondary track (see 4.26.2).]

4.24.2 TADS Field of View (FOV) Select. The TADS

FOV select switch selects a field of view for the selected

sensor. Placing the switch momentarily to the desired

position will select the respective TADS FOV: Wide (W),

Medium (M), Narrow (N) , or Zoom (Z). The fields of view

available are dependent on the sensor selected.

4.24.3 TADS Sensor Select. The TADS sensor select

switch selects the desired TADS sensor for sighting or ac-

quisition of targets. Placing the switch to the desired posi-

tion will select the respective TADS sensor: FLIR, TV, or

DVO(ORT only).

4.24.4 Store/Update. The STORE/UPDT performs the

update or store function of waypoint/targeting.

4.24.5 FCR Scan

Functions as described on the

collective mission grip (para 4.5.6).

4.24.6 Cued Search

Functions as described on the

collective mission grip (para 4.5.7).

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

Change 4

4-33

TM 1-1520-251-10

4.24.7

Linear Motion Compensation. The LMC

4.25.6 Sight Slave. The sight SLAVE switch is used to

switch is used to aid in tracking. It compensates for heli-

slave the selected sight and/or provide cueing to the se-

copter movement as well as target movement.

lected acquisition LOS. The SLAVE state remains ON un-

til the SLAVE switch is toggled OFF or an acquisition

4.24.8 FCR Mode

Functions as described on the

selection is made.

collective mission grip (para 4.5.3 ).

4.25.7 Display Zoom

The display ZOOM switch is

4.25 RIGHT HANDGRIP (RHG)

used to view FCR targeting information at approximately a

6:1 zoom display. Pressing the pushbutton causes the se-

The RHG (fig 4-32) in the CPG station provides access to

lected FCR targeting format to be displayed in a zoom for-

the various sight subsystem control functions.

mat centered about the designated next-to-shoot (NTS)

target symbol. Pressing the ZOOM switch again will return

the display to the normal targeting format.

FCR SCAN SIZE SWITCH

LASER TRACKER

CSCOPE

MODE SWITCH

4.25.8 LRFD Trigger. The LRFD trigger is used to ob-

tain laser range and/or to designate a target for laser-

SIGHT

guided munitions. Pressing the trigger to the first detent

SELECT

FLIR

activates the laser transmitter to transmit a series of laser

SWITCH

POLARITY

ranging pulses. Pressing the trigger to the second detent

SWITCH

activates the laser transmitter for ranging and target de-

IAT

SIGHT

signation.

POLARITY

SLAVE

SWITCH

4.25.9 [

Spare Switch. The Spare Switch is used

DISPLAY

ZOOM

to select sequentially through multiple target tracks.

SIGHT

SWITCH

Pressing forward moves the TADS LOS to the next secon-

MANUAL

TRACKER

dary track in sequence and promotes it to primary. Press-

URFD

TRIGGER

ing aft moves the TADS LOS to the previous secondary

track in sequence and promotes it to primary (see

HDD SWITCH

SPARE

4.26.2).]

[MTADS] TRACK PRO−

MOTE

4.25.10 Head Down Display Select. The HDD select

switch is used to select the HDD display for viewing.

LBA1037A

Pressing the HDD pushbutton alternately selects between

the HDD and HOD.

Figure 4-32. RHG

4.25.11

Sensor Manual Tracker. The MAN TRK

thumb force controller is used to control the TADS turret or

FCR

antenna (centerline) to move during manual track-

4.25.1 Sight Select. Functions as described on the col-

ing.

lective mission grip (para 4.5.5).

4.25.12 IAT Polarity. The IAT polarity switch is used to

4.25.2 Laser Tracker Mode. The LT mode switch is

select the FLIR/DTV contrast polarity for the image auto

used to select the mode of the laser spot tracker. Placing

tracker. Placing the switch momentarily to the desired

the switch to the desired position selects the respective

position selects the respective tracker polarity: White (W),

mode: Automatic (A), Off (O), or Manual (M).

Auto (A), or Black (B).

4.25.3 FCR Scan Size

Functions as described on

4.26 TADS TARGET TRACKING

the collective mission grip (para 4.5.4).

Target track mode or cued (predetermined) turret position

commands are generated manually through CPG use of

4.25.4 C - SCOPE

The C - SCOPE switch is used to

the RHG MAN TRK control or electronically by the WP

activate the C - scope display of FCR target information on

and the TEU. Maximum TADS turret gimbal movement is

flight and weapons symbology formats.

+120° and -180° in azimuth, +30° and -60° in elevation.

4.25.5 FLIR Polarity. The FLIR PLRT switch is used to

Target track mode is selected with LHG and RHG

change FLIR polarity.

switches.

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

4-34

Change 4

TM 1-1520-251-10

4.26.1 Manual Track. Manual tracking is selected by

DTV and FLIR while tracking the target, however, the tar-

pressing the RHG SLAVE switch. To track the target in

get will still be tracked in the original sensor. If the sensor

manual, the CPG operates the RHG MAN TRK control in

is changed while tracking the target, symbology will offset

the direction needed to keep the TADS pointed at the tar-

due to internal paralax correction. The digital image track-

get. If the aircraft or target is moving, the use of LMC will

er functions based on the edge of the target. It also incor-

greatly reduce CPG workload.

porates an inertial track filter which uses previous track in-

formation to determine predicted target locations.

NOTE (ORT)

A primary target track is selected by setting the LHG IAT/

If IAT is selected while DVO is the selected

OFS switch to IAT. The primary autotrack function sur-

sensor and FLIR is on, the DVO FOV will

rounds the target with tracker gates, sizes the gates

default to NFOV and the TEU will use FLIR

based on target edge detection techniques, and initiates

video for tracking the target. DTV video will

automatic tracking. The track number will be displayed

be displayed on the HOD. Since FLIR video

below and to the right of the gates. Pressing and holding

is used to track the target and DVO does not

the switch in the IAT position for longer than 0.6 seconds

display IAT tracker gates, impending break-

will initiate manual sizing control of the tracking gates.

locks cannot be detected and IAT track crite-

Gates will start near the LOS recticle center, then expand

ria cannot be evaluated by the CPG.

and shrink back down, and then begin the growth cycle

again. Sizing will continue until the switch is released at

4.26.2 IAT. IAT automatically tracks targets detected

the desired size. Size will not exceed 50% of the FOV.

with DTV or FLIR. Operation is basically the same using

Once a primary track is established, the TADS LOS may

either sensor. IAT should be used to track, designate, and

be manually slewed to acquire additional tracks or to allow

engage targets when there is sufficient target-to-back-

for offset lasing during Hellfire missile engagements/rang-

ground contrast. IAT is selected by setting the LHG IAT/

ing. The amount of slewing (offset tracking) allowed is lim-

OFS switch to IAT. IAT identifies a target by contrast, sur-

ited to the extent that the primary track cannot be forced

rounds the target with tracker gates, and calculates the

out of the current FOV.

difference between target centerline and selected FOV

center point. Good track criteria (video parameters eva-

Setting the IAT/OFS switch to IAT, when the TADS LOS is

luated by IAT) must be established for proper IAT opera-

within the primary tracking gates, will adjust the ’aim point’

tion. When IAT tracker gates start to flash, an impending

symbol to the desired location on the target/object. Setting

IAT breaklock condition exists. While the impending

the IAT/OFS switch to IAT when the TADS LOS is not

breaklock condition exists, IAT will try to reacquire the tar-

within the primary tracking gates will cause the MTT to at-

get. If IAT does not reacquire the target, within a required

tempt a primary target track as described above.

period of time, IAT enters a stop mode. In the stop mode,

Selecting a second target track will establish that track as

IAT gates change to 4 solid rectangles. When in the stop

the primary track and the previous track will become a

mode, the CPG has manual track control of the TADS

secondary track. A unique flag and flag post symbol will

LOS. If LMC is off when the IAT enters the stop mode,

be displayed in conjunction with the secondary track. The

LOS will stop. If LMC is on, the LOS will continue to move

track number will be displayed within the flag symbol. In

at the last commanded slew rate. Once IAT is selected,

addition, the total number of target tracks will be displayed

setting the IAT/OFS switch to OFS will engage the IAT off-

in the upper right area of the weapon format when the

set tracking capability. In this mode, the MAN TRK thumb-

MTT is in use.

force controller is re-enabled so the TADS may be manu-

ally tracked away from the target to allow for offset lasing

When the TADS LOS is not within the primary tracking

during Hellfire missile engagements/ranging. Actioning

gates, setting the IAT/OFS switch to OFS for less than 0.5

the IAT/OFS switch again to OFS will disengage offset

seconds will disengage offset tracking and slew the TADS

tracking and the TADS will resume automatic tracking of

LOS to the primary track. At this point, the TADS LOS may

the target. Actioning the IAT/OFS switch again to IAT will

again be manually slewed as required. Placing the TADS

disengage automatic tracking and re-enable the MAN

LOS on a primary or secondary track (symbol bolds) and

TRK thumbforce controller for manual tracking.

setting the IAT/OFS switch to OFS will delete that track. If

the primary track is deleted, the previously selected sec-

[

MTT. The TADS multi - target tracker is capable of

ondary track will become the primary track. Pressing and

tracking one primary and two secondary targets using

holding the switch in the OFS position for longer than 0.5

DTV or FLIR. Operation is basically the same using either

seconds anywhere within the FOV will delete all target

sensor, however, tracks can be maintained in only one

tracks. Track delete messages will be displayed in the

sensor at a time. The sensor may be changed between

HAD Weapon Inhibit message field.

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

Change 4

4-35

TM 1-1520-251-10

When tracking multiple targets, the RHG SPARE Switch

smaller boxes after 5 seconds of inertial tracking. The

may be used to select sequentially through multiple target

track will be dropped after 10 seconds.

tracks. Pressing forward moves the TADS LOS to the next

5. Inertial Bar An inertial bar symbol with a small

secondary track in sequence and promotes it to the prima-

bracket at the end and associated track number will be

ry track. Pressing aft moves the TADS LOS to the pre-

displayed at the edge of the FOV when an inertial track is

vious secondary track in sequence and promotes it to pri-

out of the FOV.

mary

6. Low Confidence Bar A low confidence dashed

If the selected sight is changed to HMD or FCR when the

bar/bracket and associated track number will be displayed

MTT is in use, tracks will continue to be maintained until

at the edge of the FOV after 10 seconds of inertial tracking

dropped. It is possible to change the selected sight back

out of the FOV. The track will be dropped after 15 sec-

to TADS and resume tracking tasks. If the SLAVE or LINK

onds.

functions are activated, all tracks will be deleted.

b. Secondary Track Symbols. Secondary Track

Primary tracking gates and secondary track symbols are

Symbols (fig 4-32B) are described below.

symbol coded to provide feedback for various track

states.

a. Primary Track Gates. Primary Track Symbols (fig

4-32A) are described below. Primary track gates will flash

when approaching 50% of the FOV, limited at FOV edge,

or when the gates are extremely small.

LBA - 5997

Figure 4-32B. Secondary Track Gates

1. Normal Gate The normal flag symbol is dis-

LBA - 5996

played just above the track aim point.

2. Bold Gate The flag symbol becomes bold

Figure 4-32A. Primary Track Gates

when the TADS LOS is within the symbol’s selectable

area.

1. Normal Gate The normal gates are displayed

3. Inertial Gate The inertial flag symbol is dis-

around the target image; updated based on image proc-

played in dashed lines when the track is being maintained

essing.

inertially because of an obscuration within the FOV.

2. Bold Gate The gates become bold when the

4. Low Confidence Gate The low confidence flag

TADS LOS is within the gates selectable area.

symbol is displayed in small dotted lines after 5 seconds

3. Inertial Gate Inertial gates are displayed as

of inertial tracking. The track will be dropped after 10 sec-

four box symbols when the track is being maintained iner-

onds.

tially because of an obscuration within the FOV.

5 Inertial Bar An inertial bar symbol and associ-

4. Low Confidence Gate Low confidence gates

ated track number will be displayed at the edge of the

are displayed as four box symbols segmented into 4

FOV when an inertial track is out of the FOV.

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

4-36

Change 4

TM 1-1520-251-10

6. Low Confidence Bar A low confidence dashed

is adjusted internally, then outfront boresight must be per-

bar and associated track number will be displayed at the

formed following the cue update. Cue update procedure is

edge of the FOV after 5 seconds of inertial tracking out of

contained in para 4.55.

the FOV. The track will be dropped after 15 seconds.]

4.30 TADS INTERNAL BORESIGHT

4.26.3 Laser Spot Tracker (LST). The LST provides

The internal boresight aligns the DTV and FLIR sensors to

the CPG with the capability of searching for and tracking

the laser and the DVO (ORT only) to the DTV sensor line of

reflected laser energy of the selected code. The LT mode

sight. Internal boresight shall be performed as part of preflight

switch on the RHG is used to select the desired LST

procedures prior to any firing of laser or weapons when

mode: Automatic (A), Off (O), or Manual (M). Placing the

TADS is used as imaging sensor. Internal boresight can also

LT switch to the A position arms the LST and commands

be performed in flight to ensure boresight accuracy without

the TADS into an automatic 4-bar scan around the TADS

requiring outfront boresight as a follow-up. Internal boresight

LOS at the point of engagement. Placing the LT switch to

procedure is contained in para 4.55.

the M position arms the LST and allows for manual track-

ing of the TADS to search in the area of interest. In either

[

Internal boresight shall be performed as part of pre-

mode, when laser energy of the selected code is detected

flight procedures prior to any firing of laser or weapons when

by the LST, it will auto-track the TADS about the laser en-

TADS is used as imaging sensor. Internal boresight can also

ergy spot. Placing the LT switch to O will turn the LST off

be performed in flight. Internal boresight errors can develop

and release the TADS to normal control. The LST is only

in-flight due to temperature changes within the internal com-

PRF code capable and therefore will not track PIM coded

ponents of TADS (thermal drift). It is recommended that an

laser energy.

internal boresight be accomplished 2 times per 2.5 hour flight.

4.27 TADS DRIFT NULL

TADS internal boresight is an automated process which inde-

The TADS system has the capability to null the turret ser-

pendently boresights the DTV and FLIR sensors. The DTV

vo drift by either auto or manual drift null. Servo drift can

boresight must be performed successfully before the FLIR

be identified as happening whenever the TADS turret is

boresight can be performed. Once the FLIR boresight is

under manual control, the CPG is not making any inputs

complete, the internal boresight is complete. If an ORT is

with the thumbforce controller and the reticle appears to

installed, the DTV boresight must be performed successfully

drift off the aim point. The aim point should remain within

prior to boresighting the DVO.

the narrow FOV of the DTV for 30 seconds. If it does not,

or a lesser amount of drift is desirable, perform Manual

Initiating an internal boresight automatically sets the CPG se-

Servo Drift Null (para 4.55.5 or 4.55.5A). Auto Drift Null is

lected sight to TADS, the sensor to TV and the FOV to nar-

active from the time the TADS is first turned on. It is only

row. A standby prompt is displayed while the TADS turret

inactive when the manual servo drift procedure is being

slews to the boresight position and prepares for the process.

performed. Auto Drift Null is not as precise as Manual Ser-

At initial powerup, the system will conduct an automatic cue

vo Drift Null so some residual servo drift will always be

search which will take less than 90 seconds before indicating

present when it is active.

it is ready for boresight. Subsequent attempts to perform an

internal boresight under the same powerup will include a

Paragraphs 4.27.1 and 4.27.2 deleted

preparation time of less than 15 seconds as it will not involve

a cue search. During these waits, boresight target images will

4.28 TADS BORESIGHT OPERATION

appear and disappear in TADS video. These images do not

necessarily align with weapon symbology and are not manip-

Boresight aligns TADS sensors to a coincident LOS. Bore-

ulated in any way by the CPG.

sight includes an internal and outfront boresight. TADS

When the system is ready, a laser warning window and bore-

boresight is initiated by selecting the weapon page

sight procedure prompt will be displayed. The CPG will be re-

BORESIGHT button and selecting the internal or outfront

quired to arm the laser and pull the laser trigger during DTV

boresight button. Boresight procedures are contained in

internal boresight, otherwise, no action is required by the

paragraph 4.55.

CPG during FLIR internal boresight. If the TADS FLIR is not

4.29 TADS CUE UPDATE

cooled upon completion of DTV boresight, a not cool status

will be displayed and the process will be ended. In addition,

Performance of cue update ensures that the TADS turret

status windows will be displayed to indicate when the bore-

is in proper position relative to the boresight assembly

sight(s) are in progress, complete, or failed. Internal boresight

prior to firing the laser for internal boresight. If cue update

procedure is contained in para 4.55.]

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

Change 4

4-36.1

TM 1-1520-251-10

4.31 TADS OUTFRONT BORESIGHT

4.32 TADS MANUAL BORESIGHT

The purpose of the TADS manual boresight is solely to re-

WARNING

capture or center the laser spot. This boresight procedure

should not be considered acceptable for normal flight op-

erations. The manual boresight procedure is contained in

The narrow and zoom FOV TADS FLIR

para 4.55.

imagery has inaccuracies for lasing or

weapons direction following TADS inter-

4.33 TADS ANTI-ICE

nal boresight. TADS outfront boresight

When the pilot or CPG selects anti-ice using the aircraft

validation and adjustment (if necessary)

UTIL page ANTI-ICE SENSOR button and the helicopter

shall be performed prior to using the

is off the ground, 115 Vac is applied to the TADS shroud

TADS FLIR imagery for laser or weapons

window and a shroud frame heater. TADS anti-ice can be

operations.

selected when the aircraft is on the ground by using the

GND button.

Performance of outfront boresight ensures FLIR LOS is in

4.34 FCR DESCRIPTION

coincidence with laser LOS. Outfront boresight should be

NOTE

checked prior to any firing of laser or weapons when

TADS FLIR is used as the imaging sensor. Outfront bore-

The FCR will provide reliable data while ma-

neuvering up to 20° in roll and +20° to - 15°

sight must be performed after a cue update adjustment.

in pitch. Flight outside these parameters

Target requirements for the outfront boresight procedure

may result in degraded FCR performance.

are as follows:

The FCR is an integrated radar system with a mast-

A target a minimum of 0.5 km away from the he-

mounted transmitter and receiver. The FCR detects, lo-

licopter is required. Target must be clearly vis-

cates, and classifies ground and airborne targets and pro-

ible and trackable through both FLIR and TV

vides terrain profile signatures when operating in limited

sensor NFOV. Target must have the same cen-

adverse weather or obscured visibility conditions. The

ter as viewed in both FLIR and TV sensors.

FCR augments the helicopter’s weapon delivery capabili-

ty through the use of a target acquisition fire control radar,

Outfront boresight procedure is contained in

coupled with a Radar Frequency (RF) guided seeker ver-

para 4.55.

sion of the Hellfire missile. A Radar Frequency Interferom-

eter (RFI) is incorporated to provide threat emitter warn-

ing, direction finding, and cueing. These coordinates are

sorted and sent to the display processor for target symbol-

ogy presentation on the FCR page or TSD page. Non-vol-

atile memory is zeroed-out using the MASTER ZEROIZE

Switch described in chapter 2.

4.34.1 Mast Mounted Assembly (MMA). The MMA

(fig 4-33) is mounted to the aircraft on a pedestal tube

which contains a derotation assembly. Electrical power

and signal/RF transmissions pass through the mast by

way of a slipring/rotary joint assembly. The slipring as-

sembly transfers prime power and signal information be-

tween the two portions of the assembly as they are rotated

with respect to each other. The slipring housing also con-

tains the accelerometer sensor assembly for the pedestal.

A rotary joint coupler provides a path for four RF channels.

The MMA to aircraft interface is a blindmate connector.

The MMA dome and baseplate are made of a honeycomb

core sandwiched between carbon graphite fiber/epoxy

prepreg composite. The composites reduce weight and

provide structural integrity. The MMA stands 32 in. high

and weighs 257 lb. The MMA is cooled by air drawn from

the surrounding environment.

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

4-36.2

Change 4

TM 1-1520-251-10

RADOME

AFT DOME

RFI ANTENNA

AZIMUTH

ELECTRONICS

UNIT

MAIN

QUARTZ

POWER

COOLING

RAT

SUPPLY

SENSOR

CONTROLLER

ELEVA−

GIMTB

RFI RECEIVER

AS−

AZIMUTH ACTUATOR

SEMBLY

TRANSMITTER

RECEIVER

AZIMUTH

INERTIAL

ELECTRONICS

PARTICLE

UNIT

SEPARATOR

LBA2582

Figure 4-33. MMA Major Components

4.34.2 MMA Components. The MMA is made up of the

4.35 FCR PAGE

following major components:

The FCR page is used to present the display of radar in-

• Power Supply Controller

formation and to functionally control much of the FCR and

RFI moding. It provides the controls, graphics, and sym-

• Transmitter

bols required to operate the selected FCR mode.

• Receiver

4.35.1 FCR Page Selection. The FCR page can be ac-

cessed in one of three ways in either crew station: 1) se-

• Main Cooling Fan

lecting the FCR subsystem bezel button, 2) selecting the

• Inertial Particle Separator

FCR page button from the MENU page, or 3) selecting the

sight select switch to FCR.

• Elevation Gimbal Assembly (EGA)

4.35.2 FCR Page Formats. The FCR page provides in-

• Quartz Rate Sensor (QRS)

formation to the aircrew based on the selected mode of

the radar: Ground Targeting Mode (GTM), Radar Map

• Radome

(RMAP), Air Targeting Mode (ATM), or Terrain Profiles

Mode (TPM). The format of the FCR page is displayed in

• Aft Dome

the Plan Position Indicator (PPI) or B Scope format ac-

cording to the selected FCR mode:

• Azimuth Actuators

• Ground Targeting Mode (PPI format)

• Azimuth Electronics Unit

• Radar Map (B Scope format)

• RFI Antenna

• Air Targeting Mode (PPI format)

• RFI Receiver

• Terrain Profiles Mode (PPI format)

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

4-37

TM 1-1520-251-10

4.35.3 FCR Page Formats on ORT HDD/HOD. The

a. GTM Scan Sector Symbol. The scan sector

FCR page is available on the ORT HOD/HDD by the use

symbol is displayed in the mode selected by the crew-

of the VID SEL switch and the HDD switch. Selections

member (Wide, Medium, Narrow or Zoom). Current mode

from the FCR formats ORT HOD/HDD are accomplished

is displayed in full intensity with other modes displayed in

solely by use of the display cursor ENTER function. Mod-

partial intensity, if applicable. FCR Page - GTM Format

ing of these selections are the same as for FCR page op-

scan sectors function as follows:

erations described in the paragraphs to follow. Control

and placement of the display cursor is described in chap-

b. FCR Footprint. The GTM targeting scan sectors

ter 2.

are displayed in full intensity and are based on the se-

lected scan size: Wide, Medium, Narrow, and Zoom.

4.35.4 FCR Page - GTM Format. The GTM format

(fig 4-34) is displayed in the PPI format made up of a scan

The wide scan sector symbol represents a 90°

sector outline with partial intensity range arc lines and azi-

scan sector (45° either side of centerline). The

muth tic marks which correspond to each scan size. The

wide scan sector displays in partial intensity

scan sector is overlaid onto radar map video. The FCR

when any other scan size is selected.

page buttons function identically in either GTM or RMAP

format.

The medium scan sector symbol represents a

45° scan sector (22.5° either side of centerline).

The wide scan sector displays in partial intensi-

ty.

The narrow scan sector symbol represents a 30°

scan sector (15° either side of centerline). The

wide and medium scan sectors displays in par-

tial intensity.

The zoom scan sector symbol represents a 15°

scan sector (7.5° either side of centerline).The

wide, medium and narrow scan sectors displays

in partial intensity.

RFI tic marks. A single RFI tic mark is displayed

along the outer left and right boundary line of the

GTM and RMAP wide sector scan symbols. The

tic marks represent a reference point 90° left

and right of scan centerline relative to the dis-

play of RFI threat symbols along the perimeter

of the sector scan (helicopter).

LBA2587A

Arcs and tics. Each arc represents a 2 km dis-

tance in even increments (2, 4, 6 and 8) and

each tic mark represents a 2 km distance in odd

Figure

4-34.

FCR Page - GTM Format

increments (1, 3, 5, and 7).

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

4-38

TM 1-1520-251-10

A view of all scan sector modes is shown in figure 4-35.

WIDE SCAN

MEDIUM SCAN

NARROW SCAN

ZOOM

LBA0486A

LBA2591A

Figure 4-36. FCR Page - RMAP Format

a. RMAP Scan Sector Symbol. The scan sector

Figure 4-35. GTM Scan Sectors

symbol is displayed in the mode selected by the crew-

member (Wide, Medium, Narrow or Zoom). Current mode

4.35.5 FCR Page - RMAP Format. The RMAP format

is displayed in full intensity with other modes displayed in

(fig

4-36) provides radar information within a B-scope

partial intensity, if applicable. FCR Page - RMAP Format

(rectilinear format) scan sector outline with partial intensi-

scan sectors function as follows:

ty range lines and azimuth tic marks which correspond to

b. FCR Footprint. The GTM targeting scan sectors

each scan size. The scan sector is overlaid onto radar

are displayed in full intensity and are based on the se-

map video. The FCR page buttons function identically in

lected scan size: Wide, Medium, Narrow, and Zoom.

either GTM or RMAP format.

1. The wide scan sector symbol represents a 90°

scan sector (45° either side of centerline). The

wide scan sector displays in partial intensity

when any other scan size is selected.

2. The medium scan sector symbol represents a

45° scan sector (22.5° either side of center-

line).The wide scan sector displays in partial in-

tensity.

3. The narrow scan sector symbol represents a 30°

scan sector (15° either side of centerline). The

wide and medium scan sectors displays in par-

tial intensity.

4. The zoom scan sector symbol represents a 15°

scan sector (7.5° either side of centerline). The

wide, medium and narrow scan sectors displays

in partial intensity.

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

4-39

TM 1-1520-251-10

5. RFI tic marks. A single RFI tic mark is displayed

• R4

RFHO button

along the outer left and right boundary line of the

• R6

ACQ button

GTM and RMAP wide sector scan symbols. The

a. C-SCP Button. The C-SCP button is used to call

tic marks represent a reference point 90° left

and right of scan centerline relative to the dis-

up the C-scope target symbols for display on the flight and

play of RFI threat symbols along the perimeter

weapons symbology format. Selecting the C-SCP button

of the sector scan (helicopter).

will cause the display of virtual FCR target symbols on the

HMD in the pilot station, on the HMD and ORT HOD/HDD

in the CPG station, and on the MPDs when the appropri-

6. Lines and tics. Each line represents 2 km dis-

ate video is selected.

tance in even increments (2, 4, 6 and 8) and

each tic mark represents a 2 km distance in odd

b. FCR UTIL Page Button. The FCR UTIL page

increments (1, 3, 5, and 7).

button is used to access FCR system utility functions.

A view of all scan sector modes is shown in figure 4-37.

c. NTS Button. The NTS button is used to select

the next valid target in the priority target list as the NTS

WIDE SCAN

MEDIUM SCAN

target. Selecting an FCR target symbol with the display

cursor will designate that target as the FCR NTS. The

MPD display cursor will automatically be placed in the ac-

tive area of this button at the completion of the first scan of

a scan burst. This allows rapid NTS target selection using

the cursor ENTER function. The cursor operation on the

FCR page is described in chapter 2. This button is only

displayed when valid target data is present.

NOTE

If the Pilot’s selected sight is FCR, the cent-

NARROW SCAN

ZOOM

erline is commanded to the selected acquisi-

tion source. If a left/right arrow button is se-

lected, the centerline is offset as described

below. To force the centerline back to the ac-

quisition LOS, the Pilot must reselect the

FCR sight select switch on the collective.

d. Left/Right Arrow Buttons. The left/right arrow

buttons are only displayed if the FCR is the selected sight.

LBA2590A

They are used to rapidly position the FCR centerline to the

left or right of the helicopter centerline. Selecting the left or

Figure 4-37.

RMAP Scan Sectors

right centerline buttons will cause the FCR centerline to be

adjusted to the left or right based on the selected scan

size. The centerline will be adjusted to the right or left so

4.35.6

FCR Page - GTM/RMAP Format pages. Each

as to effect total scan width coverage of the area adjacent

of the GTM/RMAP pages contains the following unique

to the previously selected area. The FCR centerline will

buttons:

remain heading stabilized at each position until comman-

ded to a new position. If the FCR is slaved, the left/right

• T1

C-SCP button

arrow buttons are barriered in the CPG crewstation. In

• T6

FCR UTIL button

addition, the MAN state allows the antenna azimuth posi-

• L1

NTS button

tion to be manually adjusted using the MAN TRK thumb

force controller.

• L2

Left Arrow button

• L4

TGT button

e. TGT Button. The TGT button is used for the

selection of FCR target data (fig 4-38) to be stored into the

• L5

ELEV button

permanent Target/Threat file. Selecting the TGT button

• R1

ZOOM button

sets the display cursor for selecting/storing any FCR tar-

• R2

Right Arrow button

get symbol and calls up the store status window in the

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

4-40

TM 1-1520-251-10

right area of the FCR page. In addition, it calls up the ALL

f. ELEV Button. Antenna elevation control is se-

button. Selecting an FCR target symbol with the display

lected using the ELEV button (fig 4-39) on the FCR page

cursor will store that target data to the target/threat file.

GTM format. Two options are available to the crewmem-

Again selecting the TGT button will exit the target select

ber: AUTO or manual. Depressing the ELEV button while

function and return the format to normal operation. This

in the AUTO mode will remove the AUTO placard and

button is only displayed when valid target data is present.

present up and down arrows on the display for manual

control. Selecting the up arrow button will cause the an-

tenna position to elevate up one setting or to the next

higher setting when starting between settings. Selecting

the down arrow button will cause the antenna to move

down one setting or to the next lower setting when starting

between settings. When the antenna is at the uppermost

setting, the up arrow symbol will not be available. Con-

versely, when the antenna is at the lowest setting, the

down arrow symbol will not be available. If TADS power is

applied, selecting manual will allow the CPG to slew an-

tenna elevation using the RHG MAN TRK control. The de-

grees shown in figure 4-39 are lower bar elevations. The

upper bar elevation will vary with altitude.

18.75

12.5

6.25

(Default)

6.25

LBA2011A

12.5

18.75

Figure 4-38. TGT Store Selection

ELEVATION SCALE

(1) ALL Button. The ALL button is used to rap-

LBA2596

idly store all of the displayed FCR target data. Selecting

the ALL button stores all of the top priority FCR target

Figure 4-39. GTM Elevation Setting

data to the target/threat file and calls up a larger status

window.

g. Display ZOOM Button. Selection of the ZOOM

(2) Store Status Window. The store status win-

button activates the zoom function. When the display cur-

dow provides the file address of the next target to be se-

sor is positioned within the FCR target area, the display

lected/stored (boxed) and the list of file addresses of tar-

cursor symbol is changed to a ZOOM cursor (para

gets stored during the current iteration of TGT selection.

2.21.4). Placement of the ZOOM cursor represents the

This data is displayed for reference by the crew member

area to be zoomed allowing better viewing of target arrays

for future use.

where the targets are in close proximity to each other.

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

Change 3

4-41

TM 1-1520-251-10

h. RFHO Button. The RFHO button is used for rap-

(2) SEND Button. The SEND button is used to

id transmission of the FCR next-to-shoot (NTS) (fig 4-40)

activate the IDM and transmit the RF handover target data

target information via the IDM to another LBA system for

to the selected subscriber.

engagement. Selecting the RFHO button will select the

FCR NTS target data for transmission and call up the Sub-

(3) ACQ Button. The ACQ button is described

scriber Identifier buttons based on the selected IDM net-

in Section I of this chapter.

work on the right side of the FCR page. Selecting a Sub-

scriber Identifier button will call up the IDM SEND button

4.35.7 GTM Antenna Elevation Control when MMA is

on the right side of the FCR page. This button is only dis-

Masked. In automatic elevation control (fig 4-41), anten-

played when valid target data is present.

na elevation is set to cover FCR minimum and maximum

range based on radar altimeter altitude. In situations

where the FCR is scanning behind a hill or mountaintop,

the radar altitude may be such that the automatic setting

will not cover the desired area of interest. A suggested

method of overcoming this situation requires manual ad-

justment of antenna elevation and multiple scans to

bracket the area of interest.

4.35.8 GTM Manual Elevation Control Operations.

a. Select RMAP with radar video.

b. Set antenna elevation manually to an angle esti-

mated to cover the area of interest or the lowest setting.

c. Conduct a single scanburst and observe RMAP

display.

d. Conduct the following steps until RMAP video

shows ground returns at minimum range with one eleva-

tion setting lower than a blank area presentation.

LBA2010A

(1) If the display presents ground returns at mini-

mum range, set the elevation angle up one setting and

conduct a single scanburst.

Figure

4-40.

RFHO Selection

(2) If the minimum range area still displays ground

returns, set the elevation angle up one setting and con-

• T5 - T6, R1 - R5 Subscriber buttons

duct a single scanburst.

• R6

SEND button

(3) If the minimum range area is blank, set the

(1) Subscriber Identifier Button.

The Sub-

elevation angle down one setting and conduct a single

scriber Identifier buttons are used to select the desired

scanburst. A blank area indicates the main beam is set to

subscriber to which the RF handover target data will be

an angle which does not provide coverage at the minimum

transmitted.

range.

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

4-42

TM 1-1520-251-10

POSITION OF MAIN BEAM WITH AUTO SETTING AT LOW RADAR ALTITUDE

APPARENT GROUND PLANE BASED ON RADAR ALTITUDE

POSITION OF MAIN BEAM WITH AUTO SETTING

AT HIGH RADAR ALTITUDE

MANUAL SETTING REQUIRED TO DETECT TARGET

AT STEEP LOOKDOWN ANGLE

GROUND PLANE

OF INTEREST

LBA2599

Figure 4-41. Manual Elevation Control Considerations

4.35.9 GTM/RMAP SYMBOLOGY. The following sym-

1. Scan Sector Symbol. The scan sector symbol is

bols (fig 4-42) are displayed on the GTM and RMAP for-

displayed in the mode selected by the crewmember

mats.

(Wide, Medium, Narrow or Zoom). Current mode is dis-

played in full intensity with other modes displayed in par-

tial intensity, if applicable.

2. Elevation Scale. The moving antenna elevation

pointer is displayed along the right side of the antenna

elevation scale located in the lower left area of the format.

The pointer moves up and down along the scale to indi-

cate the elevation setting of the FCR antenna. The long tic

mark within the scale provides indications with reference

to the zero setting.

3. Heading Scale and Symbols. The heading

scale and associated symbols are as described in chapter

4. Total Target Count Status Window. The total

target count status window appears when targets are se-

lected. It provides a total number of targets selected by

the radar within a scanburst. The status window digital

readout is from 1 to 1023 in GTM/RMAP.

5. RFI Threat Symbols. RFI threat symbols repre-

LBA2587A

senting RFI detected emitters are displayed on the periph-

ery of the radar scan sector to indicate the direction to the

threat. Up to 10 RFI threat symbols can be displayed at a

Figure

4-42. GTM/RMAP Symbology

time.

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

4-43

TM 1-1520-251-10

6. FCR Priority Target Symbols. FCR target prior-

4.35.11 ATM Target Processing/Prioritization. ATM

ity symbols represent the highest priority targets detected

target symbols are displayed in any given scan. Target

and classified for a scanburst. Up to 16 FCR target sym-

data is displayed and updated as it is detected during the

bols can be displayed for any given scanburst (Refer to

scan to derive priority target characteristics (velocity and

4.44.5 for target symbol descriptions).

classification). The symbols represent the highest priority

target detected and classified for that scan. The target

7. High Action Display. The High Action Display is

classification process is:

as described in paragraph 4.16.

• Priority target data, total target count, and total

targets are purged at the start of each single scan

8. FOR Symbols. The Field of Regard and

and updated during the scan.

associated symbols are described in paragraph 4.14.

• Symbols are displayed during the scan.

4.35.10 FCR Page ATM Format.. The ATM format (fig

• NTS is displayed at the end of the first scan and is

4-43) provides radar information within a plan PPI circular

updated by the WP as target information is

sector scan outline with partial intensity range arc lines

prioritized by the FCR.

and azimuth tic marks at 90° increments. The ATM pro-

vides the same functional controls as the GTM and RMAP

• RFI target merges are displayed during any scan.

formats except that is does not include the ZOOM button

or automatic control of the antenna elevation. In addition,

a. ATM Scan Sector Symbol. The ATM scan sec-

there is no FOR symbology displayed in the ATM format.

tor is displayed in full intensity and is based on the se-

lected scan size: Wide, Medium, Narrow, and Zoom. Cur-

rent mode is displayed in full intensity with other modes

displayed in partial intensity, if applicable. FCR Page -

ATM Format scan sectors function as follows:

• The wide scan sector symbol represents a 360°

scan sector. The wide scan sector remains

displayed in partial intensity when any other scan

size is selected.

• The medium scan sector symbol represents a

180° scan sector (90° either side of centerline).

• The narrow scan sector symbol represents a 90°

scan sector (45° either side of centerline). The

wide and medium scan sectors remains displayed

in partial intensity.

• The zoom scan sector symbol represents a 45°

degree scan sector (22.5° either side of center-

line). The wide, medium, and narrow scan sectors

remains displayed in partial intensity.

LBA0487A

• The ATM blanking symbol will appear whenever

the FCR is looking towards the tail section of the

Figure

4-43.

FCR Page - ATM Format

aircraft.

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

4-44

TM 1-1520-251-10

A view of all scan sector modes is shown in figure 4-44.

WIDE SCAN

MEDIUM SCAN

23 º

18 º

13 º

8 º

(DEFAULT) 3 º

NARROW SCAN

ZOOM

ELEVATION SCALE

LBA2597

Figure 4-45. ATM Elevation Setting

4.35.13 ATM Azimuth Scan Centerline Control. Left

(

) or right (

) FCR page buttons are used to rapidly

position the FCR azimuth scan centerline to the left or

LBA2592A

right of the current FCR azimuth scan centerline. The FCR

azimuth scan centerline will be set to the left or right to

Figure 4-44. ATM Scan Sectors

give total scan width coverage of the area adjacent to the

previously selected area. The new centerline selection will

4.35.12 ATM Elevation Control. The up/down arrow

be displayed as shown in figure 4-46. The FCR azimuth

buttons are displayed continuously in the ATM. They are

scan centerline will remain heading stabilized until com-

used to manually adjust the antenna elevation up or down

manded to a new azimuth position. If TADS power is ap-

incrementally during air targeting. Selecting the up arrow

plied, the CPG can slew antenna azimuth using the RHG

button will cause the antenna position to elevate up one

MAN TRK control. If the FCR is slaved to an acquisition

setting or to the next higher setting when starting between

source in the CPG station, manual controls (arrow buttons

settings. Selecting the down arrow button will cause the

and MAN TRK controller) will be inhibited. Pilot station left

antenna to move down one setting or to the next lower

or right arrow button selection, after the FCR is sight se-

setting when starting between settings. When the antenna

lected, will deselect FCR slave to the acquisition source.

is at the uppermost setting, the up arrow symbol will not

For the pilot to slave the FCR to the acquisition source

be available. Conversely, when the antenna is at the low-

again, the FCR must be deselected as sight and selected

est setting, the down arrow symbol will not be available.

again.

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

Change 3

4-45

TM 1-1520-251-10

1. Scan Sector Symbol. The ATM scan sector

WIPER MOVEMENT

symbology is displayed in full intensity and is based on the

LEFT AND RIGHT

selected scan size: Wide, Medium, Narrow, and Zoom.

Current mode is displayed in full intensity with other

modes displayed in partial intensity, if applicable.

2. Elevation Altitude Status Window. The eleva-

tion altitude status window is displayed in the lower center

area of the format. The upper and lower altitude digital

readouts represent the upper and lower altitude of FCR

coverage at maximum range and is referenced from the

aircraft and antenna elevation setting. Each altitude value

for digital readout is from - 32,767 feet to +32,768 feet, in

one foot increments.

3. Elevation Scale. The moving antenna elevation

pointer is displayed along the right side of the antenna

elevation scale located in the lower left area of the format.

The pointer moves up and down along the scale to indi-

cate the elevation setting of the FCR antenna. The long tic

LBA2598

mark within the scale provides indications with reference

to the zero setting.

Figure 4-46. ATM Azimuth Scan Centerline Control

4. Total Target Count Status Window. The total

4.35.14 ATM Symbology. The ATM scan sector

target count status window (fig 4-48) appears when tar-

symbology (fig 4-47) is displayed in full intensity and is

gets are detected. It provides a total number of targets de-

based on the selected scan size: Wide, Medium, Narrow,

tected by the radar within a scanburst. The status window

and Zoom. Current mode is displayed in full intensity with

digital readout is from 1 to 1023 in ATM.

other modes displayed in partial intensity, if applicable.

LBA2589A

LBA0487A

Figure 4-47. ATM Symbology

Figure 4-48. Total Target Count Status Window

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

4-46

TM 1-1520-251-10

4.35.15 FCR Page - TPM Format. The TPM format (fig

• Arcs. Each arc represents the following: first arc =

4-49) provides radar information within a PPI sector scan

100m, second arc = 1000m, third arc = 2000m and

outline with partial intensity range arc lines. Two scan sec-

fourth arc = 2500m.

tor sizes are automatically displayed based on ground

speed. The FCR centerline is set to the aircraft centerline

A view of all scan sector modes is shown in figure 4-50.

in this mode. The scan sector is overlaid onto radar map

video converted to shades of gray. Line distances are 100

m, 1000 m, 2000 m, and 2500 m. Obstacle symbols and

NARROW SCAN

WIDE SCAN

radar video are displayed in geometric fidelity within a

sector scan. The TPM format provides the following selec-

tions, status windows, and graphics:

LBA2594A

Figure 4-50. TPM Scan Sectors

The FCR page - TPM format contains the following

unique buttons:

• T1

C-SCP button

• T6

UTIL button

• L1

PROF button

• L2

LINES button

• R1

CLEARANCE button

• R2

ELEV button

LBA0488A

b. C-SCP Button. The C-SCP button is used to call

up the C-scope radar information for display on the crew

Figure 4-49. FCR Page - TPM Format

member’s HMD. Selecting the C-SCP button will cause

the display of virtual profile lines and obstacle symbols on

the HMD in the pilot station and on the HMD and ORT

4.35.16 TPM Scan Sectors Symbols. The TPM scan

HOD/HDD or TDU in the CPG station.

sectors symbols are displayed in full intensity and are

based on the scan size: Wide or Narrow.

c. FCR UTIL Page Button. The FCR UTIL page

button is used to access FCR system utility functions.

a. Scan Sector Modes. The mode of the TPM sec-

tor is based on aircraft airspeed.

d. PROF Button. The PROF button is used to se-

• The TPM wide format is displayed as a 180° scan

lect the setting for the display of profile line intervals. Se-

sector (90° either side of centerline) when the

lecting the PROF button will call up the profile setting op-

ground speed decreases below 45 knots and until

tions: GEOM, ARITH, and TEST.

increasing above 55 knots.

• The TPM narrow format is displayed as a 90° scan

e. LINES Button. The LINES button is used to se-

sector (45° either side of centerline) when the

lect the number of profile lines displayed when C SCP is

ground speed increases above 55 knots and until

selected. Selecting the LINES button will call up the op-

decreasing below 45 knots.

tions: 0, 1, 2, 3, or 4.

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

Change 3

4-47

TM 1-1520-251-10

f. CLEARANCE Button. The CLEARANCE button

1. TPM Scan Sector Symbols. The scan sector

is used to select the clearance plane setting of the TPM.

symbology is displayed in full intensity and is

Selecting the CLEARANCE button will call up the clear-

based on the selected scan size: Wide or Nar-

ance plane setting options: 20, 50, 100, and 200. These

row. The format of the TPM sector is based on

values represent the number of feet below the helicopter

aircraft airspeed.

(wheels) at which the clearance plane exists.

2. Heading Scale and Symbols. The heading

g. ELEV Button. The FCR page ELEV button alter-

scale and associated symbols are as described

nately selects two different antenna elevation positions to

in chapter 2.

obtain the desired radar information. Pressing the ELEV

button to select FAR sets the antenna elevation at - 0.5° to

3. High Action Display. The High Action Display

give information for the earliest warning of high terrain out

is as described in paragraph 4.16.

to 2500m. Pressing the ELEV button to select NEAR sets

the antenna elevation at - 3° to measure terrain in rain or

4. FOR Symbols. The Field of Regard and

obtain radar information out to minimum range (approxi-

associated symbols are as described in para-

mately 1000m).

graph 4.14.

4.35.17 TPM Symbology. A view of the TPM Symbolo-

gy is shown in figure 4-51.

5. Total Obstacle Count Status Window. The to-

tal obstacle count status window appears when

obstacles are detected.

LBA2593A

Figure 4-51. TPM Symbology

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

4-48

Change 3

TM 1-1520-251-10

4.36 FCR UTIL PAGE

CAUTION

The FCR UTIL page (fig 4-52 ) is used to enable the FCR

Continued operation with the FCR TEMP

and RFI, override BIT, and set various FCR and RFI

ORIDE button selected may cause per-

modes. On initial aircraft powerup, the MMA button de-

manent damage to FCR components.

faults to the pinned position. Subsequent FCR powerup/

powerdown operations are conducted through the FCR or

4.36.1 FCR TEMP ORIDE Button. The FCR TEMP

WPN UTIL page.

ORIDE button is used to prevent overtemperature protec-

tion shutdown of the FCR when it has been detected in an

overtemperature state (FCR HOT). This button is dis-

played only when an overtemperature state has been de-

tected.

CAUTION

FCR BIT ORIDE selection in extreme cold

weather ( - 105 C or colder) could result in

damage to the FCR.

4.36.2 FCR BIT ORIDE Button. The FCR BIT ORIDE

button is used to override the FCR built-in-test sequence.

This button is displayed only when the FCR is in BIT.

4.36.3 FCR LETHAL RANGES Button. The FCR LE-

THAL RANGES button is used to select the desired lethal

ranges data to be used by the FCR for target classifica-

tion. Selecting the FCR LETHAL RANGES button alter-

nately toggles between DEFAULT and MODIFIED. The

default data file is resident in the FCR and the modified

LBA3009A

data file is available from the DTC (if programmed)

4.36.4 ELEV Button. The ELEV button is used to set

Figure

4-52.

FCR UTIL Page

the state of FCR antenna elevation control to AUTO. Se-

lecting the AUTO state automatically adjusts the elevation

value passed to it by the weapon processor for the given

acquisition LOS.

The FCR UTIL page provides the following unique selec-

tions:

4.36.5 RFI TRAIN Button. The RFI TRAIN button is

used to activate the training mode of the RFI subsystem.

• L1

FCR TEMP ORIDE button

Selecting the RFI TRAIN button modes the system to pro-

• L4

FCR BIT ORIDE button

vide an on - board emulation of RFI detected emitters for

aircrew training exercises. This is a contrived set of

• L4

FCR LETHAL RANGES button

threats preprogrammed solely for training purposes.

• L5

ELEV button

4.36.6 RFI MODE Button. Refer to Section III, para

• L6

TERRAIN button

4.90.8 for description.

• R1

RFI TRAIN button

4.36.7 FCR STOW Button. The FCR STOW button is

used to stow the FCR antenna.

• R2

RFI MODE button

4.36.8 SCHEME Button. The SCHEME button is used

• R3

FCR STOW button

to select the desired prioritization scheme to be used by

• R4

SCHEME button

the FCR for target classification. Selecting the SCHEME

• R5

MISSION button

button calls up options of A through G. Three priority

schemes are resident in the aircraft (FCR) and another 4

• R6

MMA button

are available from the DTC.

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

4-49

HELICOPTER, ATTACK, AH-64D LONGBOW APACHE. TECHNICAL MANUAL (2002) - page 10