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

TM 1-1520-251-10

4.36.9 Priority Scheme Selections. FCR target in-

ranges, if loaded, are selected using the FCR UTIL page

formation is prioritized by the FCR and used to direct the

FCR LETHAL RANGES button.

selected weapon against targets and to enhance situa-

4.36.11 MISSION Button. This button toggles between

tional awareness in the area of operations. Seven priority

1 and 2. It is used to determine which mission is used

schemes are used by the FCR; 3 schemes are resident in

when loading Priority schemes D through G. This load

the FCR (options A, B, and C), and 4 are available for

takes place when Priority schemes D through G are

loading via the DTC (options D through G) if programmed.

selected using the SCHEME button. This button will auto-

All priority schemes give higher priority to targets merged

matically switch to 1 or 2 when the Master, Mission 1, or

with RFI emitters and vary only with respect to how un-

Mission 2 ALL uploads are commanded.

merged targets are prioritized. Prestored FCR priority

schemes (A, B, and C) are summarized as follows:

4.36.12 TERRAIN Button. The TERRAIN button is

used to select the radar clutter threshold consistent with

a. Priority scheme A emphasizes airborne and sta-

anticipated terrain or other features in the area of opera-

tionary ground targets.

tions.

b. Priority scheme B emphasizes stationary ground

NOTE

targets.

In the Ground Targeting Mode (GTM) only,

c. Priority scheme C emphasizes airborne and mov-

selecting the reserved terrain selection en-

ing ground targets.

ables a Moving Target Indicator (MTI) only

mode in the FCR P8 software load and sub-

The 4 priority scheme options available for loading

sequent. The Stationary Target Indicator

through the DTC and are programmed into the DTC via

(STI) target detection processing is dis-

the AMPS. All 7 priority schemes, if loaded, are selectable

abled. This selection will cause an FCR fault

using the FCR UTIL page SCHME button.

message on the UFD/EUFD and an FCR

4.36.10 FCR Lethal Ranges Selections. FCR lethal

STI FAIL indication on the DMS page. To re-

range data is processed with with the selected priority

turn to STI detected targets, select any oth-

scheme to determine FCR target priority. One of two lethal

er terrain selection. The new selection will

range files is used by the FCR; one is resident in the FCR

take effect at the beginning of the next scan.

(DEFAULT file), and one is available for loading via the

4.36.13 Terrain Sensitivity Setting. The terrain sensi-

DTC (MODIFIED file) if programmed. The lethal range is

tivity setting is selectable using the FCR UTIL page TER-

the maximum effective range for the specific threat or tar-

RAIN SENSITIVITY button. This provides the crewmem-

get type and is used in the FCR prioritization algorithm to

ber the capability to select the proper radar clutter

determine if ownship is within lethal range of a given tar-

threshold setting for correct processing of STI detections.

get.

The crewmember has a choice of 8 selectable sensitivity

Like priority scheme options D through G, the modified le-

options that is consistent with the anticipated terrain or

thal ranges available for loading through the DTC are pro-

other features in the area of operation, These selectable

grammed into the DTC via the AMPS. Modified lethal

options are found in table 4-19.

Table 4-19. Terrain Sensitivity Settings

OPTION

TERRAIN SELECTION

AUTO

FCR automatically selects terrain.

RESERVED

In the FCR P7 software load and previous, selecting RESERVED, the FCR automatically se-

lects terrain and false alarm control (Pd is not assured). In the FCR P8 software load and sub-

sequent, selecting the RESERVED, enables the MTI only mode and disables the STI.

Eastern U.S. coastal plains region.

Valleys, mountains, sparse trees.

Combination of coastal plains and desert (light vegetation).

Similar to setting 3 with different decision thresholds.

Desert vegetation and arroyos (water carved gully or channel).

Similar to setting 5 with sparse vegetation.

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

4-50

Change 3

TM 1-1520-251-10

4.37 FCR OPERATION

4.39 FCR SYSTEM STATUS

In certain cases, status windows are displayed on the

FCR page and the FCR UTIL page when the FCR is in

The FCR, in combination with the RF missile, provides a

other than a ready state:

fire-and-forget capability. An integrated mast-mounted

RFI provides threat emitter warning and azimuth direction

FCR NOT INSTALLED

The FCR is not installed.

finding/cueing. RFI detected emitter signals may be corre-

lated with FCR target data to derive the identity and loca-

FCR NOT POWERED

The FCR is set to OFF.

tion of a particular threat. Target information is sent to the

FCR BIT

The FCR is performing

weapons processor for the determination of target loca-

IN PROGRESS

BIT.

tion coordinates and is used to direct the selected weapon

FCR FAIL

The FCR has been de-

against targets. FCR target information is displayed on

tected as failed.

the FCR page targeting format and the TSD page. The

FCR ZEROIZED

The FCR has been de-

FCR page targeting format may also be displayed on the

tected as zeroized.

ORT HOD/HDD. In addition, the information is processed

for the generation of FCR target symbology for overlay

4.40 IDM STATUS

onto TADS/PNVS sensor video.

Status windows are also displayed on the FCR page and

the FCR UTIL page when certain IDM transmissions are

4.38 FCR PAGE CONTROLS

received:

RF HANDOVER Valid RF handover target has

been received and accepted.

FCR page controls are dependent upon the states of the

sight select function and of the FCR mode function. The

IDM TARGET

Valid FCR target has been re-

following is a general description of controls available:

DATA

ceived and accepted for display.

4.41 FCR MODES OF OPERATION

• When the FCR is not the selected sight in either

crew station, selecting the FCR subsystem bezel

The FCR is employed in one of three operational modes

button or the FCR page button from the MENU

to perform ground targeting (GTM and RMAP), air target-

page calls up the FCR page in the format as last

ing (ATM), and terrain profiles mode (TPM). Modes are

selected at the FCR mode switch (in either crew

selected using the FCR mode switch on the LHG or col-

station).

lective mission grip. Momentarily positioning the FCR

mode switch to RMAP, after RMAP is initially selected,

• Selecting the sight select switch to FCR esta-

displays target symbols without radar video. GTM is the

blishes control of the FCR to that crew station in

FCR default mode. The last-to-select rule remains in ef-

the mode/format last selected at the FCR mode

fect for the mode switch. Radar clutter threshold, that is

switch (from either crew station). If the FCR page

consistent with the anticipated terrain or other features in

is not currently displayed on either MPD or the

the area of operation, is selected using the FCR UTIL

ORT HOD/HDD (CPG station) or TDU (CPG

page TERRAIN sensitivity button.

station), it is automatically called up on the left

MPD (in that crew station). All controls are

4.41.1 FCR Ground Targeting. Ground targeting is ac-

available. Sight selection of the FCR between the

complished using one of two modes: the Ground Target-

crew stations is based on last-to-select logic.

ing Mode (GTM) or the Radar Map (RMAP). These

ground scan modes are used to detect, classify and priori-

tize both moving and stationary ground targets and low

• When the FCR is the selected sight in the opposite

flying air targets. Targets are presented on the targeting

crew station, selecting the FCR subsystem bezel

format at the current range/azimuth location.

button or the FCR button from the MENU page

calls up the FCR page in the format as last

4.41.2

FCR Air Targeting. Air targeting is accom-

selected at the FCR mode switch (in either crew

plished using the ATM. It is an air scan mode used to de-

station). Only the FCR UTIL page button, the TGT

tect, classify and prioritize air targets. Targets are pres-

button (and associated controls) and the ACQ

ented on the FCR targeting format at the current

button is available.

range/azimuth location.

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

Change 3

4-51

TM 1-1520-251-10

used in conjunction with a terrain profiles format displayed

WARNING

with IHADSS video.

The terrain profiling mode of the FCR

shall not be relied upon for primary pilot-

WARNING

age information.

Low radar cross section objects such as

4.41.3 FCR Terrain Profiles. Terrain clearance is ac-

telephone or power poles or isolated

complished using the TPM. It is a ground scan mode used

leafless trees cannot be accurately mea-

to provide pilotage information to either the pilot /CPG. It

sured by the FCR. The clearance plane

provides an FCR sector ground clearance plane format

should be set to exceed the height of all

displayed (fig 4-53) on an MPD or ORT display which is

anticipated hazards.

ÓÓÓÓÓÓÓÓÓ

ÓÓÓÓÓÓÓÓÓÓÓÓ

LIGHT GRAY

ÓÓÓÓÓÓÓÓÓ

UNKNOWN

ÓÓÓÓÓÓÓÓÓÓÓÓ

BLACK SAFE

ÓÓÓÓÓÓÓÓÓ

TO FLY

ÓÓÓÓÓÓÓÓÓÓÓÓ

ÓÓÓÓÓÓÓÓÓ

WHITE

ÓÓÓÓÓÓÓÓÓÓÓÓ

HAZARDOUS

ÓÓÓÓÓÓÓÓÓ

DARK GREY

ÓÓÓÓÓÓÓÓÓÓÓÓ

SOME RISK

ÓÓÓÓÓÓÓÓÓ

ÓÓÓÓÓÓÓÓÓÓÓÓ

ÓÓÓÓÓÓÓÓÓ

ÓÓÓÓÓÓÓÓÓÓÓÓ

OBSTACL

ÓÓÓÓÓÓÓÓÓ

ÓÓÓÓÓÓÓÓÓÓÓÓ

ÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓ

ÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓPRESENT ALTITUDEÓÓÓÓÓÓÓÓÓ

20, 50, 100, 200 FT

ÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓ

CLEARANCE PLANE

ÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓ

ÓÓÓ

ÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓ

LBA2585

ÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓ

Figure 4-53. FCR Terrain Profiles

a. Clearance Planes. Options of 20, 50, 100, or

• DARK GRAY represents an area that is potentially

200 feet below the helicopter wheels are available for

hazardous and does not guarantee the expected

selection. Four shades of gray will be displayed to repre-

clearance. Terrain measured is between the

sent terrain information as follows:

helicopter present altitude and the clearance

plane. Flying into a dark gray area presents some

• LIGHT GRAY represents unknown terrain. Terrain

risk depending on TADS/PNVS video quality.

has areas in radar shadow or areas where

sufficiently accurate measurements CANNOT be

• BLACK represents terrain measured below the

made. This can occur in a ring near the radar or in

selected clearance plane.

a ring where ground cannot be reached at the

• WHITE represents a hazardous area that must be

radar slant range. A light gray area without a

avoided. Terrain measured is above the helicopter

characteristic shadow edge can be an indication of

wheel height.

heavy rain or low reflectivity terrain. The FCR is

capable of detecting and reporting heavy rain.

However, there is no discrete symbology for this

information.

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

4-52

TM 1-1520-251-10

b. Profile Lines. Terrain profile data (fig. 4-54) is

symbols are not displayed in a wiper fashion as with tar-

collected in range intervals that are based on the FCR

geting data. The symbols are displayed at one time each

page profile (PROF) button selection. The highest eleva-

time the data is updated at the completion of a TPM scan.

tion points within a range interval are detected and com-

TPM obstacle symbols are displayed in YELLOW. A maxi-

bined into a single profile line. FCR page range interval

mum of 64 symbols may be displayed on the FCR page

selections are geometric (GEOM), arithmetic (ARITH), or

TPM format or IHADSS C - Scope formats at any one time.

TEST. The number of profile lines displayed can be se-

lected using the FCR page LINES button. Selecting the

LINES button will display options; 1, 2, 3, and 4.

LINE 4

LBA2566

LINE 3

Figure 4-55. TPM Obstacle Symbol

LINE 2

4.42 FCR FUNCTIONS

LINE 1

OBSTACLE SYMBOL

LBA2595

4.42.1 FCR Scan Size. The FCR scan size default is

wide for all targeting modes. If a new scan size is se-

Figure 4-54. Terrain Profile Data

lected, the new scan size selection will be used at the be-

ginning of the next scan. In TPM, the FCR determines

scan size based on helicopter ground speed. In cued

Lines and obstacles are displayed as follows:

search, the FCR determines scan size based on the des-

ignated emitter frequency and whether the emitter was

detected in the coarse or fine area of coverage.

Option 0

Display obstacles only

Option 1

Display line 1 with obstacles

4.42.2 FCR GTM/RMAP Scan. Characteristics of an

Option 2

Display lines 1 and 2 with obstacles

FCR scanburst depend on the type of scanburst (single or

Option 3

Display lines 1, 2, and 3 with obstacles

continuous) and the selected scan size. Scan bursts also

use multiple detections of moving targets to calculate

Option 4

Display lines 1, 2, 3, and 4 with obstacles

cross range velocity.

Range interval settings are:

a. Single Scanburst. When the FCR scan switch is

momentarily positioned to S-SCAN the FCR will complete

GEOM

Line 1

100 - 300 meters

a single scan or, based on the selected FCR scan size, a

Line 2

300 - 500 meters

scanburst. If the FCR scan switch is momentarily posi-

Line 3

500 - 1000 meters

tioned to S-SCAN or C-SCAN before the scanburst is

Line 4

1000 - 2500 meters

complete, the FCR will stop the scan, deactivate the trans-

ARITH

Line 1

100 - 700 meters

mitter, and return the FCR antenna to the azimuth start

Line 2

700 - 1300 meters

position for the selected mode and scan size. In GTM, a

Line 3

1300 - 1900 meters

near bar and a far bar equals one scan. A single scanburst

Line 4

1900 - 2500 meters

consists of multiple scans, based on the selected scan

size, as listed below:

TEST

Line 1

500 meters

Line 2

1000 meters

Line 3

1500 meters

Scan Size Number of Scans Per Scanburst

Line 4

2000 meters

Wide

Medium

4.41.4

TPM Obstacle Symbol. The TPM obstacle

Narrow

symbols represent objects or terrain features which the

FCR has derived as obstacles to flight (fig 4-55). These

Zoom

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

4-53

TM 1-1520-251-10

b. Continuous Scanburst. When the FCR scan

b. RMAP Wiper Symbol. In the RMAP format, the

switch is momentarily positioned to C - SCAN, the FCR will

scan wiper symbol is displayed as a vertical line and

start a continuous scanburst. Continuous scanburst ap-

moves left to-right-covering the near bar and right - to - left

pears as a series of scanburst. The FCR will continue to

covering the far bar.

scan until the FCR scan switch is momentarily positioned

to C - SCAN or S - SCAN again. When the continuous

c. Near Bar/Far Bar. A bar (sweep) is the move-

scanburst is deactivated, the MMA is returned to the start

ment of the radar from one scan limit to the other. The

position for the selected mode and scan size.

near bar begins on the left limit of the scan width and

sweeps left-to-right through the search area to the right

limit. The antenna, during turnaround, adjusts elevation

4.42.3 FCR Display Zoom. Targeting information for

up for far bar and sweeps right-to-left through the search

any scan size can be viewed at approximately 6:1 zoom

area to the left limit. This completes 1 scan. The radar

display ratio. The border of the zoomed format is dis-

beamwidth in the near bar overlaps the beamwidth of the

played in WHITE.

far bar. Targets in the overlap area will be scanned twice

during a single radar scan. This provides the FCR with

a. RHG ZOOM Switch. If zoom is selected by

more information to be used during the classification/

pressing the RHG ZOOM switch, the display zoom area

prioritization process and improves P_D.

will be centered on the NTS target. The ZOOM button will

not select zoom if there is no NTS target.

d. Blanking Symbol. The FCR blanking symbol (fig

4-56) is displayed within the selected scan sector to indi-

cate that the FCR transmitter has been set to OFF for sys-

b. FCR Page ZOOM Button. If zoom is selected

tem calibration or to avoid scanning directly toward the

using the FCR page ZOOM button, the LHG or collective

vertical stabilizer and tailboom. Each side of this polygon

mission grip CURSOR control is used to select the area to

is made up of azimuth lines where blanking begin and

be displayed. When the display cursor is positioned within

where blanking ends. The remaining lines of the polygon

the FCR target area, the display cursor symbol is changed

connect the line end points at the maximum and minimum

to a WHITE zoom area box with corner to corner cross-

azimuth lines. Two additional criss-crossing lines are dis-

hairs. The size of the zoom area box is determined by the

played in the last 30% of the polygon to form a large “X”

selected scan size. If the zoom area box is moved within

symbol.

the area of active button selections, the zoom area box

will change to the normal display cursor symbol and cur-

sor enter operation. Pressing the LHG or collective mis-

sion grip CURSOR control or RHG cursor enter switch will

enter the cursor selection and the display will zoom on the

designated area. Geometric fidelity with respect to relative

target positions (and radar video in RMAP format) is re-

tained in the zoom area format. Deselecting zoom using

the FCR page ZOOM button will return the FCR to the last

selected format.

4.43 FCR PAGE SYMBOLOGY

4.43.1 Scan Wiper Symbol. A scan wiper symbol is

displayed within the scan sector on the FCR page when

the FCR is transmitting. It is displayed in WHITE during

single scan bursts and in GREEN during continuous scan.

a. GTM Wiper Symbol. In the GTM PPI format, the

scan wiper symbol is displayed as a line and moves right-

to-left covering the near bar and left-to-right covering the

LBA2586A

far bar. The line appears to move or wipe across the scan

sector pivoting about the sector origin in conjunction with

the actual radar antenna movement.

Figure

4-56.

FCR Blanking Symbol

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

4-54

TM 1-1520-251-10

e. ATM Wiper Symbol. In ATM PPI format, the

Target symbols appear virtual in position on the display as

scan wiper symbol appears to move or wipe across the

the selected sensor is moved about. Only those symbols

sector scan, pivoting about the center of the sector, with

within the sensor FOV will appear on the format.

FCR antenna movement. During continuous scanning,

the wiper symbol moves back and forth across the scan

sector until the FCR is commanded to stop scanning. This

symbol is visible in ATM and GTM/RMAP.

f. TPM Wiper Symbol. In TPM PPI format, the

scan wiper symbol appears to move or wipe across the

sector scan, pivoting about the center of the sector, with

FCR antenna movement. As it reaches the right boundary

of the selected scan sector it moves back toward the left

boundary of the scan sector and continues to cover the

entire area in front of the helicopter.

4.43.2 ATM Centerline Symbol. The FCR centerline

symbol for ATM is a partial intensity line displayed, when

medium, narrow, or zoom scan sizes are selected, within

the ATM format. The centerline symbol is not displayed

when wide scan is selected. It is a partial intensity line

which extends from the first range arc to the outer range

arc of the selected scan size. The FCR centerline symbol

is dynamic and represents the relative FCR centerline

position within the ATM format.

LBA2600A

4.44 FCR TARGET INFORMATION

FCR target information is prioritized by the FCR and used

Figure

4-57.

C-Scope Presentation on Weapons

to direct the selected weapon against targets. Seven

Symbology

priority schemes are used by the FCR: 3 schemes are res-

ident in the FCR (options A through C), 4 are available

from the DTC (options D through G). The information can

4.44.2 GTM Target Processing/Prioritization. GTM

be processed for FCR target symbology overlay on flight

target symbols are displayed in any given scanburst. Tar-

and weapon symbology formats with the C-SCP se-

get data is correlated from scan-to-scan during a scan-

lected. When FCR target data is displayed, switching from

burst to derive priority target characteristics (velocity and

RMAP to GTM will display information in the selected for-

classification). Scan-to-scan correlation improves STI

mat. Selecting ATM or TPM will eliminate all ground tar-

detection and classification and Moving Target Indicator

geting data. Eliminated ground targeting data cannot be

(MTI) classification. Scan-to-scan correlation is also used

recalled for display. All target information is sent to the dis-

to measure cross range velocity, and differentiate cross

play processor for target symbology presentation on the

range moving targets from stationary targets. When a new

FCR page (highest priority) or TSD (all targets).

scan is commanded, the FCR will clear its target file. Tar-

get types and location which are not stored in the threat

4.44.1 C-SCOPE Processing. FCR target symbology

file are lost. If single scan is selected, targets are corre-

is processed for overlay on the TADS/PNVS video by se-

lated from scan-to-scan but not from scanburst-to-scan-

lecting the FCR page C-SCOPE (fig 4-57) or by pressing

burst. As soon as a new scanburst is initiated, the priority

the RHG C-SCOPE switch. GTM and ATM provide a tar-

and total target lists and total target count are cleared, re-

get symbol overlay display on TADS/PNVS video in C -

initiated, and updated during the scan. In continuous

scope format on the IHADSS, ORT or TDU. Target sym-

scan, targets are correlated from scan-to-scan and from

bols are displayed in geometric fidelity over sensor video.

scanburst-to-scanburst.

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

Change 3

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TM 1-1520-251-10

4.44.3 Scanbursts. The processing and display of tar-

• Priority target data is correlated from scanburst to

get data is unique to the type of scanburst, single or con-

scanburst.

tinuous. The scan burst supports scan-to-scan correlation

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

without appreciably increasing timelines. Scan-to-scan

updated by the WP as target information is

correlation is a process which maintains track of detected

prioritized by the FCR.

targets between each scan. Correlating a burst of scans

while keeping the timelines short is referred to as a single

• To avoid re-engagement, shot-at target data is

scanburst operation. Continuous scanburst operation pro-

tagged.

vides various scan-to-scan correlations.

•

Stationary target symbols are added and updated

for classification during the final scan. Threats are

a. Single Scanburst.

added during any scan.

• Priority target data, total target count, total targets,

• Targets blank as they exit the scan sector except

and map are purged at the start of each single

for the NTS. NTS will become dashed and partial

scanburst and updated during the scanburst.

intensity when NTS is at the edge of sector scan

(crew member may select new NTS).

• Radar video is generated on the first scan in a

wiper fashion.

4.44.4 FCR Target Symbols. A maximum of 16 FCR

• Priority target data is correlated from scan to scan.

target symbols (fig 4-58) are displayed in any given scan.

These symbols represent the highest priority targets de-

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

tected and classified for that scan or scan burst. Target

updated by the WP as target information is

data is correlated from scan to scan during a scanburst to

prioritized by the FCR.

derive priority target characteristics (velocity and classifi-

cation). Symbols are displayed in YELLOW by type target,

• To avoid re-engagement, shot-at target data is

type of anticipated missile launch (LOAL or LOBL), and a

tagged.

condition of moving or stationary. RFI detected emitters

• Stationary target symbols are displayed on the first

which have been correlated with radar target information

scan, added during intermediate scans (threats

is displayed by class and type within the scan sector of the

added), and updated for classification during the

format to indicate the threat/target location. Target sym-

final scan.

bols are dimmed after a period of time to indicate that the

target data is stale. Moving target symbols become stale

• Symbols are displayed in a wiper fashion during

after 5 seconds and stationary target symbols become

the first and last scan of a scanburst. During

stale after 30 seconds. Low priority targets are displayed

intermediate scans, only changes are displayed in

in partial intensity YELLOW on the TSD page as a half-

azimuth order.

size icon.

• Moving target symbols are displayed on the first

scan and updated for classification during the final

FCR TARGET SYMBOLS

scan. Moving air defense units will always be

LOAL

LOBL

displayed.

(STATIONARY

(MOVING

)

• RFI target merges are displayed during any scan.

TRACK

WHEEL

b. Continuous Scanburst, first scan. Target data

AIR DEFENSE

is displayed essentially the same as during a single scan-

UNIT

burst.

UNKNOWN

MERGED

c. Continuous Scanburst, subsequent scans:

AIR DEFENSE

• Priority target data, total target count and total

HELICOPTER

targets are purged at the start of each scanburst

FLYER

and updated during the scanburst.

LBA2012

• Radar video is generated on the first scan in a

wiper fashion.

Figure 4-58. FCR Target Symbols

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

4-56

TM 1-1520-251-10

4.44.5 Priority of Fire Symbols. Unique symbols (fig

• The symbol is displayed beneath target symbols

4-59) are designated to indicate the 2 highest priority tar-

during/after a scan burst and prior to a Hellfire

gets: the NTS target and the alternate next-to-shoot

missile launch.

(ANTS) target. FCR priority of fire indicators include the

• The symbol is displayed on top of a target symbol

NTS symbol and the ANTS symbol.

following a Hellfire missile launch at that target.

PRIORITY OF FIRE INDICATORS

NEXTTOSHOOT

LBA2567

(#1 PRIORITY TARGET)

Figure 4-60. Shot - At Symbol

ALTERNATE

(#2 PRIORITY TARGET)

4.44.7 Priority Fire Zone Symbol. Priority fire (PF)

LBA2013

zones are displayed in WHITE as a convex or concave

quadrilateral to indicate a geographic area in which target

priority is established as highest for the processor prioriti-

Figure 4-59. NTS/ANTS Symbols

zation and display. It will be displayed in the GTM mode

(not presented in the RMAP mode). Only 1 PF zone will be

a. NTS Symbol. The NTS symbol is displayed in

active and displayed at a time as selected by the crew-

YELLOW around the highest priority target symbol within

member. This zone is constructed on the TSD page and

the sector scan to indicate the most significant target or

displayed on the FCR page (described in chapter 3).

threat information derived by the FCR. It will be initially

displayed at the completion of the first scan of a scan

4.44.8 No Fire Zone Symbol. No fire (NF) zone is dis-

burst. In addition, it is displayed around a priority target

played in YELLOW as a convex or concave quadrilateral

symbol as selected by the crewmember. The symbol is a

to indicate a geographic area in which target priority is es-

dashed symbol when the crewmember has not actioned a

tablished as prohibited for the processor prioritization and

weapon system. When FCR is the selected sight and the

display. Only 1 NF zone will be active and displayed at a

weapon system is actioned, the NTS target is frozen and

time as selected by the crewmember. This zone will be

the NTS symbol will become solid.

constructed on the TSD page and displayed on the FCR

page (described in chapter 3).

b. ANTS Symbol. The ANTS symbol is displayed in

4.45 RFI OPERATION

YELLOW concurrently with the NTS symbol to indicate

the alternate NTS target, or #2 priority target in the auto-

RFI targeting is accomplished using the GTM, RMAP, and

matic target selection sequence. The ANTS target is up-

ATM modes. It occurs through the normal employment of

dated at the end of each far bar and is not frozen, i.e., may

the FCR or by performing a cued search.

change as per the selected priority scheme algorithm.

Once the NTS target is frozen, and a target is detected

4.45.1 Normal FCR Modes. RFI targeting data is pro-

that out - prioritizes the NTS target, the ANTS symbol will

cessed and displayed as part of the normal operation of

be automatically displayed on that target symbol and flash

any FCR targeting mode. Uncorrelated RFI threat (out-

for 3 seconds. The operator may select the ENTER func-

side FCR search area or not merged with a candidate

tion to choose this target as the NTS. If the operator has

FCR target) symbols are displayed, in azimuth, on the out-

not selected ENTER at the 3 second time limit, the ANTS

er periphery of FCR GTM and ATM modes described

symbol will remain over the target as it has become the

above. RFI symbols are displayed in full intensity during

new ANTS target.

the period when the RFI emitters are active. RFI symbols

will be displayed in partial intensity after the emitters be-

4.44.6 Shot-At Symbol. The shot - at icon (fig 4-60) is

come inactive. The highest priority threat symbol, or #1

displayed within the selected scan sector to indicate the

emitter as determined by the system, is displayed in con-

locations at which Hellfire missiles have been launched

junction with the RFI Box symbol. RFI emitters, detected

(actual or simulated) by the ownship or received IDM

within the fine coverage area of the RFI antenna, will be

BDA. Shot at target data is stored to the shot target file for

displayed by emitter type modifier symbol. RFI emitters

display on the TSD page as described in chapter 3 and for

detected within the coarse coverage area of the RFI an-

display on the FCR page. This icon provides shot-at in-

tenna will be displayed by the type modifier number. Cor-

formation for two situations on the FCR page.

related threats are displayed within the selected format

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

4-57

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scan sector by class and type and threat/target location.

Status Field of the HAD for a minimum of 10 seconds un-

Correlation may occur during or following a scan and is a

less the FCR is sooner commanded to another function.

product of target prioritization and priority weight standing.

If a second scanburst is desired, the LHG or collective

After correlation, an RFI threat symbol displayed on the

mission grip FCR scan switch is momentarily positioned to

outer periphery of the scan sector is removed.

S-SCAN to complete another scanburst in an attempt to

correlate the location of the emitter. Pressing the CUED

switch a second time will orient the FCR antenna to the

4.45.2 Cued Search. The cued search function is used

next priority emitter. Continuing to press and release the

to rapidly position the FCR centerline to the line of bearing

CUED switch will continuously cycle the cued search

of an emitting threat as detected by the RFI. The search

through the existing list of detected emitters. If the CUED

may be performed on targets which have been detected

switch is pressed during a normal FCR scan, the scan-

within the fine or coarse coverage regions of the RFI an-

burst will be discontinued and a cued search will be initi-

tenna to correlate the location of an emitting threat.

ated.

If the FCR is operating in ATM and the detected emitter is

b. Cued Search Display Cursor. Selecting a RFI

ground based, the FCR will default to GTM/RMAP to con-

detected target symbol on the periphery of the targeting

duct the cued search. If the FCR is operating in GTM/

format using the display cursor will command the FCR

RMAP and the detected emitter is airborne, the FCR will

centerline to the line of bearing of the selected emitter and

default to ATM to conduct the cued search. An FCR scan-

set the scan sector to the appropriate cued search scan

burst is completed in an attempt to correlate the location

size. The Selected RFI Box symbol will be displayed in

of the emitter as described below. After entering the cued

conjunction with the selected threat symbol on each

search mode, selecting any FCR control function other

selection. When the LHG or collective mission grip FCR

than threat selection with the display cursor, rotary threat

scan switch is momentarily positioned to S-SCAN the

selection with the CUED switch, or activation of the scan

FCR will complete a scanburst in an attempt to correlate

switch will cause an exit from the cued search mode and

the location of the emitter.

revert to normal FCR control in current mode.

4.45.3 ACQ Select RFI. With TADS or HMD as the se-

a. Cued Search Using CUED Switch. An FCR

lected sight, cueing or slaving to the azimuth of RFI emit-

cued search is initiated by pressing the LHG or collective

ters is available for visual target acquisition. Selecting RFI

mission grip CUED switch. This orients the FCR antenna

as the ACQ source, provides cueing or slaving of the RFI

to the highest priority emitter or a selected emitter, sets

#1 emitter. If cueing or slaving to other than the #1 emitter

the appropriate cued search scan size, and conducts a

is desired, then the emitter must be selected using the

cued search to correlate the location of the RFI detected

CAQ feature on either TSD or ASE top level page. Selec-

emitter. When an emitter selected for cued search is a

tion of other than #1 emitter with CAQ enabled, places an

ground vehicle, the FCR is commanded into a GTM mode

inverse video homeplate (selected emitter symbol) over

and the FCR centerline is commanded to the azimuth of

that emitter. The selected emitter symbol is for display ref-

that emitter. If the emitter is located beyond the azimuth

erence only, and does not change the ranking of emitters

limits of the GTM ("

90° off the aircraft nose GTM Wide),

in the RFI emitter list. The selected emitter symbol will be

the FCR will not perform a cued search. If this condition

displayed only in the crewstation that has made the

occurs, a LIMITS message will be displayed in the Sight

selection.

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

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4.45.4 RFI Detected Emitters. RFI threat symbols (fig

THREAT SYMBOLS

(DISPLAYED IN PERIPHERY OF THE FCR FOOTPRINT)

4-61) represent jammers and emitters. Up to 10 symbols

can be displayed with the highest priority emitter identified

RFI COARSE DETECTED THREAT

X X

by class and type. Friendly RFI emitters are displayed in

CYAN and enemy/gray emitters are displayed in YEL-

X X

RFI FINE DETECTED THREAT

LOW. The RFI targets are further defined by coarse and

fine bearing detection, and emitter classification. Tic

marks in the RFI display area indicate the RFI coarse area

X X

RFI BOX NO. 1 EMITTER INDICATOR

of coverage in FCR wide scan. Prioritization and display

criteria for RFI emitters are described as follows:

SELECTED RFI BOX

X X

• Emitters that indicate immediate danger to the

SELECTED EMITTER INDICATOR

aircraft are always the highest priority.

(BACKGROUND SHADED)

• Emitters that indicate potential danger to other

FCR DETECTED JAMMER (IN BAND)

aircraft are the next lower priority. Sidelobes of a

tracking radar that may be illuminating other

THREAT SYMBOLS

aircraft are an example of this type.

(NO.1 EMITTER)

WITH FINE OR COARSE DETECT

• Emitters that indicate potential danger to the

aircraft are the next lower priority. Surveillance

ICON

radars are used to locate aircraft and hand over

data to missiles. The FCR is an example of this

type.

ICON

ACQUISITION TRACKING

• Any emitter that is known to be associated with the

enemy air defense system that is engageable by

LAUNCH

ICON

the immediate helicopter team is the next lower

priority.

(FLASHING)

• Any emitter that is known to be associated with the

enemy air defense system that is not engageable

THREAT SYMBOLS

by the immediate helicopter team is the next lower

(OTHER THAN NO. 1 EMITTER)

WITH FINE OR COARSE DETECT

priority.

ICON

After RFI emitters have ceased radiating for 30 seconds,

the symbols will change to partial intensity. After 90 se-

conds of no transmission receipt, the symbols will blank.

ACQUISITION TRACKING

ICON

Correlated threats are displayed within the selected for-

mat scan sector by class, type, and threat/target location.

RFI emitters, detected within the fine coverage area of the

LAUNCH

ICON

RFI antenna, will be displayed by emitter type modified

(FLASHING)

symbol. RFI emitters detected within the coarse coverage

LBA2592

area will be displayed by the type modifier number.

Figure 4-61. RFI Threat symbols

4.45.5 RFI Mode. The RFI can be switched to display

all emitter detections or only hostile emitter detections.

The FCR page RFI MODE button is used to select ALL or

HOSTILE detected emitters.

4.45.6 RFI Train Mode. An RFI training mode can be

selected using the RFI TRAIN button. The RFI training

mode produces FCR generated RFI emitters which are

displayed and processed the same as real RFI detected

emitters.

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

4-59

TM 1-1520-251-10

Cued searches can be performed, and if GTM or ATM tar-

new offset scan value into the WP. Once stored, the new val-

gets are displayed, the FCR will attempt to correlate and

ue is displayed at the bottom mode of the OFFSET button.

merge the data. While RFI train is selected, normal RFI

operation is inhibited and no real threats will be detected

4.46.3

BPS Button. The BPS Button provides the

or displayed.

maintenance pilot with a means of conducting the blade

position sensor boresight on the aircraft. The BPS mode is

an FCR mode that detects the time (angle) of offset be-

4.46 BORESIGHT POSITION SYNCHRONIZATION

tween the rotor blade sensor and the FCR beam. The

(BPS) PAGE

scan calculation characterizes the dynamic interference

condition between the rotor blades and the FCR beam. A

4.46.1 BPS BORESIGHT Page Description. The BPS

blade position indicator angle (offset value) can be then

page (fig 4-62) provides the maintenance pilot with a

provided to the WP, once the crewmember decides to ac-

means of boresighting the rotor system with the FCR scan

cept the new value. The intended effect is to maximize the

beam. It also provides the operating crew a means to

overall FCR performance by synchronizing rotor blade

verify the displayed BPS OFFSET value.

position with FCR emission and reception.

4.46.4 Conditions For Use. The BPS boresight can

only be performed if certain specified dynamic air data

conditions and aircraft sensor conditions are met. These

conditions are:

a. The FCR is powered ON and operational with BIT

complete.

b. The aircraft is between 200 and 300 ft AGL.

c. The aircraft velocities are less than 5 km/hr in all

axes.

d. The blade tracker is locked.

e. The radar altimeter is operational and producing

valid data.

4.46.5 OFFSET Button. The BPS OFFSET button dis-

LBA2595

plays the currently stored (last stored) blade position off-

set value. Depressing the button provides the crewmem-

ber with the capability to manually edit the currently stored

Figure

4-62.

BPS Page

blade position sensor value via the KU.

4.47 SIGHT SELECTION

The BPS page contains the following unique buttons:

The right handgrip (RHG) or collective mission grip sight

• T6

UTIL button

select switch is a momentary contact switch used to select

the helmet mounted display (HMD), TADS, or FCR

• L2

STORE button

the active LOS for weapons processing. The sight select

• R1

BPS button

switch also incorporates a LINK

function. Sight select

functions are as follows:

• R2

OFFSET button

4.46.2 STORE Button. The BPS STORE button is dis-

4.47.1 Sight Select HMD. When HMD is the selected

played only when the BPS has provided a valid scan feed-

sight, HMD is the active line of sight for weapons proces-

back. It allows the crewmember to automatically store the

sing. Selecting any other sight will deselect the HMD.

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

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4.47.2 Sight Select TADS. When TADS is the selected

c. f the CPG selected sight is FCR and LINK is se-

sight in the CPG station, TADS is the active line of sight for

lected, selecting the RHG SLAVE switch allows the CPG

weapons processing. Selecting FCR will deselect TADS

to manually offset the TADS LOS from the NTS. This can

and the TADS will be commanded to FXD unless FCR

be used to view the area surrounding the NTS or to keep

was linked to TADS. In this case, the TADS LOS will re-

the target centered when going to narrower Fields of View

main at its current position. The TADS position of this

on the TADS. Re-selecting the RHG SLAVE switch forces

switch is not active in the pilot station.

the TADS back to the NTS position.

d. The link function is ignored when the selected sight

is helmet mounted display (HMD) or when both TADS and

4.47.3 Sight Select FCR

When FCR is the selected

FCR are sight and acquisition selects.

sight, FCR (NTS) in that crew station is the active line of

sight for weapons processing. This selection also calls up

e. The link function is set to off when a sight or ac-

the FCR page targeting format for the selected mode on

quisition selection is made that does not comply with the

the left MPD (if not already displayed). Selecting TADS

conditions mentioned above.

will deselect FCR and the FCR will be commanded to FXD

unless TADS was linked to FCR. In this case the FCR

f. Either crewmember has the ability to LINK the FCR

(centerline) will remain at its current position. Selection of

or TADS away from the other crewmember. For example,

the FCR from either crew station is based on a last-to-se-

if the CPG’s selected sight is TADS and the pilot selects

lect logic. If accepting an RFHO while sight select is FCR,

LINK, the CPG’s sight will automatically change to HMD.

then targeting data will be provided from the IDM data and

If the CPG then reselects TADS, the pilot’s link function

not ownship radar.

will be set to off.

g. If the pilot selected sight is FCR and LINK is se-

lected, the TADS FOV will automatically change to wide if

4.47.4 Sight LINK Function

The link function is

DVO (ORT only) or DTV is the selected sensor, or me-

used to set the FCR centerline to the TADS LOS when the

dium if FLIR is the selected sensor. Subsequently, sensor

selected sight is TADS or to set the TADS LOS to the FCR

and FOV selections can be made by the CPG.

NTS LOS when the selected sight is FCR in the CPG sta-

4.48 ACQUISITION SOURCE SELECTION

tion. In the pilot station, it is used only to set the TADS

LOS to the FCR NTS LOS. Placing the switch momentari-

An acquisition source is selected by the pilot or CPG, us-

ly down to the LINK position will toggle the LINK mode al-

ing the WPN page, the FCR page

, or TSD page ACQ

ternately between ON and OFF in either crew station. The

button. This selection is independent in each crew station.

link function operates as described below:

When an acquisition source is selected, the selected sight

can be slaved or provide cueing to the acquisition source

LOS/coordinate point. After a sight and an acquisition

a. If TADS is the selected sight and LINK is selected,

source are selected, slaving and/or cueing in the CPG sta-

the FCR azimuth scan centerline is aligned to the TADS

tion is selected by pressing the RHG SLAVE switch. Se-

LOS. If a single or continuous scanburst is selected, the

lecting a different acquisition source or pressing the RHG

FCR scan centerline will not follow TADS movement until

SLAVE switch again in the CPG station deselects slave.

the scan is complete. A continuous scanburst must be de-

In the pilot station, slaving and/or cueing is in effect on

selected before the scan centerline is realigned to the

selection of an acquisition source. If an invalid acquisition

TADS LOS.

LOS condition is created, the acquisition source is de-

faulted to FXD. Acquisition options are not displayed

when that acquisition source is not available (not powered

or failed). In addition, an acquisition option will not be dis-

b. If the FCR is the selected sight and LINK is se-

played when the option is not valid based on the selected

lected, the TADS LOS is aligned to the FCR next-to-shoot

sight.

(NTS) target at the completion of a single scanburst or at

the completion of each scanburst within a scanburst. Dur-

4.48.1 Available Acquisition Sources.

ing continuous scanburst, the TADS LOS is set to the FCR

NTS target at the completion of a scanburst. When the RF

a. Pilot Acquisition Sources. The pilot receives

missile seeker is in a track state, the TADS LOS is aligned

cueing data upon selection of an acquisition source when

to the seeker LOS. When no NTS is detected, the LINK

the sight selected is HMD. The slaving of the FCR is pro-

selection is ignored.

vided when the FCR is the selected sight. Cueing can be

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

Change 3

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TM 1-1520-251-10

turned off in pilot’s crewstation via the WPN UTIL page.

SLAVE switch to on. The CPG may use as an acquisition

Slaving of the FCR can not be turned off. The pilot may

source:

use as an acquisition source:

• PHS - Pilot’s HMD LOS.

• PHS - Own HMD (available only when the sight is

• GHS - Own HMD (when it is not the selected sight).

FCR.)

• SKR - Tracking missile seeker.

• GHS - CPG helmet sight.

(1) Hellfire laser seeker is tracking laser energy ei

• SKR - Tracking missile seeker

ther ownship or remote designator.

(1) Hellfire laser seeker is tracking laser energy ei

(2) RF Hellfire is tracking a next-to-shoot target.

ther ownship or remote designator.

• RFI - Highest priority RFI detected emitter azi-

(2) RF Hellfire is tracking a next-to-shoot target.

muth.

• FCR - The next-to-shoot target LOS (when the

• RFI - Highest priority RFI detected emitter azi-

sight is either TADS or HMD).

muth.

• FXD - Fixed forward (centerline of the aircraft with

• FCR - The next-to-shoot target LOS.

an elevation relative to the airframe of negative

• FXD - Fixed forward (centerline of the aircraft with

4.9°).

an elevation relative to the airframe of negative

• TADS (when it is not the selected sight).

4.9°).

• W01, C51, T01 - One of the stored waypoints,

• TADS.

hazards, control measures, or target/threat points.

• W01, C51, T01 - One of the stored waypoints

Both the pilot and CPG have the added feature of being

hazards, control measures, or target/threat points.

able to LINK the TADS to the FCR LOS via a single action.

b. CPG Acquisition Sources. The CPG is required

This feature allows the visual confirmation of targets,

to manually “slave” the selected sight to the acquisition

helping in the reduction of potential fratricide.

LOS via the RHG Slave control. The CPG has the added

capability, via a single action, to LINK the FCR to the

4.48.2 Sight Selection Acquisition Source. The fol-

TADS LOS in order to obtain more detail on the acquired

lowing matrix (table 4-20) provides an indication of what

target. If the CPG selects (changes) an acquisition

cueing and/or slaving is provided for each crewmember

source, the slave function is automatically set to off. Slav-

based on the selected sight and the selected acquisition

ing and/or cueing will be in effect upon actuating the

source.

Table 4-20. Sight Selection/Crewstation/Acquisition Source Matrix

Selected

Crewstation

Acquisition

Slaving

Cueing

Not Valid/

Notes

Sight

Source

Provided

Not Available

TADS

PLT

PHS

GHS

SKR

RFI

FCR

FXD

TADS

Txx

TRN

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Table 4-20. Sight Selection/Crewstation/Acquisition Source Matrix (cont)

Selected

Crewstation

Acquisition

Slaving

Cueing

Not Valid/

Notes

Sight

Source

Provided

Not Available

HMD

CPG

PHS

1,3

GHS

SKR

1,3,7

RFI

1,3,8

FCR

1,3,9

FXD

1,3

TADS

1,3

Txx

1,3

TRN

1,3

NOTE: TADS is not available for sight selection if either crewmember is using it as a sensor (i.e. NVS MODE switch in

NORM or FXD). Pilot can not sight select TADS.

NOTES:

When the RHG SLAVE switch is actuated to slaved, cueing dots and the cued LOS reticle will be dis-

played on the ORT or TEDAC displays and the HMD to provide cueing to the selected acquisition LOS.

When the RHG SLAVE switch is actuated to not slaved, the TADS LOS is controlled by the manual

tracker and no cueing is displayed.

When the RHG SLAVE switch is actuated to not slaved, no cueing is displayed.

When the RHG SLAVE switch is actuated to slaved, the FCR centerline will be set to the selected ac-

quisition LOS. When the SLAVE switch is actuated to not slaved, the FCR centerline is controlled by

the manual tracker and/or the arrow buttons on the FCR page.

When selected, the FCR centerline will be set to the PHS LOS unless the pilot has manually moved the

centerline using the MPD arrow buttons on the FCR page.

When selected, cueing dots and the cued LOS reticle will be displayed on the HMD providing cueing

to the selected acquisition LOS.

The tracking priority missile seeker LOS will be the selected acquisition LOS with the tracking priority

missile seeker defined as follows: SAL - tracking the priority laser channel, RF - tracking the NTS tar-

get, or ATA - uncaged and tracking.

The #1 RFI or selected RFI emitter is the selected acquisition LOS, with slaving and/or cueing provided

to the azimuth of the RFI emitter and 0° elevation (local horizontal).

The FCR NTS is the selected acquisition LOS. If no valid NTS target exists, the slaving and/or cueing

is not provided. The data used for the FCR NTS LOS can be derived from autonomous FCR target

data or from FCR target data received via the IDM.

10.

If FCR is the selected sight or if the FCR is linked to the TADS LOS.When the ORT SLAVE switch is

actuated to slaved, the FCR centerline will be set to the FXD forward position.

11.

When the RHG SLAVE switch is actuated to not slaved, the FCR centerline will be controlled by the

manual tracker and the FCR centerline will be commanded to the start scan position (offset to the left)

to reduce the time to start scan.

12.

If TADS is the selected sight or the TADS is linked to the FCR NTS LOS.

13.

Not available if TADS is linked to the FCR NTS LOS.

14.

Cued search is used to rapidly scan RFI detected targets with the FCR.

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4.49 RANGE AND RANGE SOURCE SELECTION

b. Automatic Range. Entering A on the KU selects

automatic range for the weapons processor. The weap-

The weapons processor uses the last range obtained (laser,

ons processor calculates range of the selected sight LOS

FCR

, coordinate point, manual, or automatic). The range

at intercept with the target, which is assumed to be at zero

will be used by the weapons processor until another valid

radar altitude. The display range is 0.1 to 50.0 in km and

range source is selected or data from the current range

tenths of km increments (AXX.X).

source becomes invalid. A default range is used when no

4.49.5 Default Range. A default range is used when no

range is in memory or when range cannot be computed from

range is in memory at power-up, or when range cannot be

the existing source. An automatic or manual range source

computed from the existing source. Default range for the

can be selected from the weapon page; however, a manual

CPG is 3.0 km. Default range for the pilot is 1.5 km. The

range cannot be entered when FCR is the selected sight.

weapons processor will use the default range until a valid

Range and range source is displayed in the HAD on the

range source is used or until a valid range can be calcu-

IHADSS flight and weapons symbology formats as well as

lated from the original range source.

the FCR page

4.49.6 HMD - Gun Default Range. If the aircraft is

4.49.1 Laser Range. When the CPG fires the laser us-

equipped with MTADS provisions, range will default to

ing the RHG laser trigger, laser becomes the range

manual range when HMD is the selected sight and the

source. Squeezing the laser trigger switch to the first det-

gun system is actioned. If the manual range is zero, the

ent fires 3 burst of laser energy in 1 second for target

default range for that crew station will be used.

ranging. Squeezing the laser trigger to the second detent

4.50 SIGHT SUBSYSTEM - DEGRADED MODES OF

fires a continuous burst of laser energy for target designa-

OPERATION

tion and continuous range updates. The display range is

500 to 9999 in 1m increments (XXXX).

4.50.1 TEU Fail. If the TEU fails, PNVS is commanded

to direct mode by the weapons processor. When PNVS is

4.49.2 Radar Range

. When FCR transmit is activated

in direct mode, PNVS turret movement is controlled by

using the collective mission grip or LHG scan select

IHADSS and the PNVS electronic unit (PEU). In PNVS di-

switch, radar becomes the range source. Radar range is

rect, azimuth coverage is limited to ± 75° with degraded

entered when the pilot or CPG activates the FCR scan se-

LOS accuracy. PNVS turret movement may become errat-

lect switch. The weapons processor uses the NTS target

ic beyond ± 75°.

range as pilot or CPG range as appropriate. If the aircraft

4.50.2 IHADSS Fail. If IHADSS video or position control

is equipped with MTADS provisions, and a manual range

commands fail, the pilot/CPG NVS MODE switch should

has been entered, radar range may be reestablished by

be set to FIXED. The PNVS turret is commanded to fixed

selecting a NTS target or conducting a new scan. The dis-

forward and the PNVS image is displayed on an MPD

play range is 0.0 to 9.9 in km and tenths of km increments

without azimuth or elevation correction.

(RXX.X).

4.50.3 IHADSS Single DP Operation. During single DP

4.49.3 Target Range. Target range is the navigation

operation both crewstations share common symbology

range from the helicopter present position to a coordinate

and imagery on their HMDs. Symbology brightness is

point. Target range is entered automatically when a coor-

controlled by the crewmember whose symbology and

dinate point (TXX, WXX, CXX or [

BLK 2

TRN] ) is se-

imagery is presented on both HMDs. Control of the HMD

lected as the acquisition source and the RHG SLAVE is

presentation is as follows: If the NVS MODE switch is OFF

pressed to select slave. If the aircraft is equipped with

in both crewstations the pilot’s symbology and imagery

MTADS provisions, and a manual range has been en-

will be presented on both HMDs. If only one crewmem-

tered, target range may be reestablished by again select-

ber’s NVS MODE switch is NORM or FIXED, that crew-

ing the coordinate point as the acquisition source. The dis-

member’s symbology and imagery will be presented on

play range is 0.1 to 32.0 in tenths of km increments

both HMDs. If both crewmembers’ NVS MODE switches

(NXX.X).

are NORM or FIXED, the symbology and imagery of pilot

4.49.4 Manual Range Entry. Selecting the WPN page

will be displayed. Subsequent selection of the NVS switch

MANRNG button and entering a numeric range (manual)

will select the crewmember’s symbology and imagery.

or entering an alphabetic letter A (automatic) on the KU

The HMD FORMAT OWNER CUE (Figure 4-27) will be

initially selects a range source for the weapons processor.

displayed with the appropriate format while operating in

a. Manual Range. Entering a numeric range for se-

single DP. The HMD FORMAT OWNER CUE will flash for

lected sight ranging on the KU selects an initial range for

three seconds and then remain displayed in a solid mes-

the weapons processor to use. The range entry is from

sage layout when the format ownership is changed and

100m to 50,000m in 1m increments. The display range is

DP operation changes from normal to single. The HMD

0.1 to 50.0 in km and tenths of km increments (MXX.X).

FORMAT OWNER CUE will flash for three seconds when

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

Change 4

4-65

TM 1-1520-251-10

DP operations changes from single to normal operation

SHUTDOWN HOT message will be displayed on the DMS

and then extinguish. In single DP operation the crewmem-

page.

ber viewing the opposite format is inhibited from firing the

4.50.6 FCR Useable Range

FCR usable range can

weapon systems.

be reduced by transmitter, receiver, or LPRF failures. Re-

MPD VIDEO Page presentation of PILOT HMD or CPG

ceiver and LPRF failures usually result in an FCR not op-

HMD underlay selections will continue to display dual DP

erational fault. One of the messages described below will

format and imagery. Therefore, the MPD may display a

be displayed only on the DMS page. The transmitter is the

video and format that does not match the HMD display.

highest failure rate item. The transmitter failure rate is

This may be used to the crewmenbers advantage, as it

dominated by 4 identical multipliers. The multiplier outputs

enables the crewmember to observe the video/format of

are summed together to produce the desired transmitter

their sensor on the MPD during single DP operation.

power output. Each multiplier has a BIT monitor. If one

multiplier is bad, an FCR RANGE 10% DEGR message is

4.50.4 PNVS Fail. In the event of a PNVS failure, TADS

displayed. If 2 multipliers are bad, an FCR RANGE 20%

FLIR can be switched to pilot control as emergency back-

DEGR message is displayed. If three multipliers are bad,

up. The pilot sets the collective flight control grip night vi-

an FCR RANGE 35% DEGR message is displayed. If all

sion select switch to TADS. The TADS assembly is slaved

4 multipliers are bad, the FCR is not operational.

to the pilot helmet LOS and FOV is set to WFOV. The slew

4.50.7 RFI Only Operational with FCR Not Operation-

rate of the TADS turret assembly is slower than the PNVS

If the radar fails, the FCR can be configured for

turret assembly.

RFI only mode operation. To configure the FCR for RFI

4.50.4A Video Fail Conditions

only operation, the MMA is mechanically pinned to fixed

forward and the RFI processor is connected to multiplex

a. Frozen Video Frozen video occurs due to loss of

bus 3A/B (TM 1-1520-251-CD). When aircraft power is

video link communications. The result of this failure will be

applied, the MMA mode is set to PINNED on the WPN or

frozen video and a VIDEO FROZEN status message. Vid-

FCR UTIL page, which subsequently allows selection of

eo will be removed if it remains frozen for more than four

the RFI ON/OFF button. With RFI selected ON, RFI de-

seconds.

tected emitters will be displayed on the ASE page and

b. Degraded Video Degraded video occurs when

TSD page.The flight crew can select BIT ORIDE anytime

errors are detected in the video signal. The result of this

during the BIT sequence. When FCR BIT ORIDE is se-

condition may be degradation of all or a portion of the vid-

lected from the FCR utility page, Initiated BIT (IBIT) will

eo image and a VIDEO DEGR status message. Video will

only conduct critical item BIT and will terminate early (after

not be removed in this condition.

a minimum run time of approximately 25 - 45 seconds),

c. Loss of Bus Communications In the event bus

and the FCR will go directly to the selected mode of op-

communications is lost, the turret (TADS or PNVS) will

eration. Continuous BIT will still provide notification of

move to fixed forward in five seconds. Video will switch to

FCR functional status but will not detect faults that require

FLIR if DTV or DVO is selected and the sensor will switch

intrusive testing. It is recommended that IBIT is selected

to run the entire BIT when the situation permits.

to WFOV if not currently selected.

4.50.8 FCR BIT Override

The flight crew can select

4.50.5

FCR Overtemperature

The FCR MMA,

BIT ORIDE anytime during the BIT sequence. When FCR

LPRF, and PSP contain temperature sensors which are

BIT ORIDE is selected from the FCR utility page, Initiated

located near heat producing or heat sensitive compo-

BIT (IBIT) will only conduct critical item BIT and will termi-

nents. When any temperature sensor detects 80 - 90% of

nate early (after a minimum run time of approximately 25

an overheat threshold, an FCR HOT message is dis-

- 45 seconds), and the FCR will go directly to the selected

played on the HAD and the DMS page. If the FCR is al-

mode of operation. Continuous BIT will still provide notifi-

lowed to operate until the maximum temperature thresh-

cation of FCR functional status but will not detect faults

old is reached, the FCR will automatically shut down. The

that require intrusive testing. It is recommended that IBIT

FCR overtemperature shutdown can be inhibited by se-

is selected to run the entire BIT when the situation per-

lecting the FCR utility page FCR TEMP ORIDE button af-

mits.

ter receiving the FCR HOT message prior to reaching the

maximum temperature threshold. With the automatic

4.50.9

Degraded FCR Modes

Partial failure of

shutdown inhibited, the FCR will continue to operate (with

ATM, GTM, or TPM functions, directed by BIT, will cause

possible degraded system performance) until permanent

FCR MTI DEGR, FCR STI DEGR, FCR STI FAIL, or FCR

damage occurs. If the FCR detects a maximum tempera-

TPM DEGR messages to be displayed on the DMS page.

ture threshold without override command, the FCR will be

The FCR will continue to operate without all of the operat-

powered down by the weapons processor and an FCR

ing mode features available for use.

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

4-66

Change 4

TM 1-1520-251-10

4.50.10 Degraded FCR Azimuth Servo

. Faults de-

message displayed while the FCR remains in operation indi-

tected in azimuth rate sensing circuits can cause a FCR AZ

cates that maintenance should be performed as soon as pos-

SERVO DEGR message to be displayed on the DMS page.

sible.

The effects of the degraded azimuth servo condition can be

reduced by minimizing yaw motion of the aircraft during scan-

ning. This degraded condition could occur at the same time

Table 4-21. DMS Page FCR Functional Loss

as a degraded elevation servo (para 4.50.11). If degraded

Messages

azimuth and elevation servo indications occur at the same

time, minimize yaw, pitch, and roll motion of the aircraft during

scanning. If the azimuth servo is detected as not operational,

a FCR FAIL message will be displayed.

Message

Description

4.50.11 Degraded FCR Elevation Servo

. Faults de-

FCR AZ SER-

Indicates that the FCR azimuth scan

tected in elevation rate sensing circuits can cause a FCR EL

VO DEGR

capability is degraded. Refer to para-

SCAN DEGR message to be displayed on the DMS page.

graph 4.50.10 for corrective action.

The effects of the degraded elevation servo condition can be

FCR BIT LOG

Indicates that the FCR has lost the

reduced by minimizing pitch and roll motion of the aircraft

INOP

ability to store BIT data. FCR mission

during scanning. This degraded condition could occur at the

capabilities are still fully functional.

same time as a degraded azimuth servo (para 4.50.10). If

FCR BIT LOG

Indicates that the FCR has reached a

degraded azimuth and elevation servo indications occur at

LIMIT

BIT data storage limit. FCR mission

the same time, minimize yaw, pitch, and roll motion of the air-

capabilities are still fully functional.

craft during scanning. If the elevation servo is detected as not

FCR BPI

Indicates that the FCR has detected a

operational, a FCR FAIL message will be displayed.

DEGR

BPI failure. FCR target information

may be unreliable.

4.50.12 FCR to Missile Target Assignment Status

FCR CALS

Indicates that the FCR can not recali-

. Faults detected in FCR hardware that could cause azi-

DEGR

brate. System accuracy will degrade

muth or elevation pointing errors during RF missile target as-

over time.

signments will cause a FCR HANDOVER DEGR message to

be displayed on the DMS page. This fault could direct the

FCR CAL

Indicates that the FCR may be

JAMMED

jammed during calibration (para

missile (LOBL recommended for this fault condition) to a LOS

4.50.13).

that will not allow the missile to acquire the target or will direct

the missile to acquire the wrong target. The TADS/PNVS

FCR FDI

Indicates that FCR fault detection/

DEGR

isolation capability has been de-

LOS should be aligned to the FCR NTS or the tracking seek-

graded.

er LOS for desired target verification.

FCR EL

Indicates that the FCR elevation scan

4.50.13 Potential Jamming of FCR Calibrations

. The

SCAN DEGR

capability is degraded. Refer to para-

effects of a potential jammer on FCR calibrations cause a

graph 4.50.11 for corrective action.

FCR CAL JAMMED message to be displayed on the DMS

FCR FAIL

Indicates that the FCR has been shut-

page. The effect of a potential jammer on calibrations can be

down as non-operational. RFI only op-

reduced by changing the start position of a sector scan. Dur-

eration may be possible (para 4.50.7).

ing a circular scan, reposition the aircraft in yaw.

Message will be cleared if power is ap-

plied to the FCR.

4.50.14 RFI Degraded

. Degraded RFI operation is indi-

FCR HAND-

Indicates that FCR to missile target

cated by an RFI DEGR message displayed on the DMS

OVER DEGR

assignment is degraded (para

page. When this message is displayed, RFI information may

4.50.12).

be unreliable.

FCR HOT

Indicates that FCR has detected

4.50.15 FCR Functional Loss Messages

. The follow-

80 - 90% of an overtemperature thresh-

ing DMS page fault messages indicate that the FCR/RFI has

old (para 4.50.5).

lost some or all operational capability. There may not be a

FCR INOP

Indicates that FCR nonvolatile has

HAD message related to functional losses that degrade op-

ZEROIZED

been zeroized. The FCR is not opera-

eration without complete loss of operation. Table 4-21 list the

tional. The FCR PSP nonvolatile

DMS page FCR functional loss messages, description, and

memory ECA must be removed and

corrective action (if any) for possible continued operation. Any

reprogrammed or replaced.

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

Change 4

4-67

TM 1-1520-251-10

Table 4-21. DMS Page FCR Functional Loss

Messages

Message

Description

FCR VIDEO

Indicates that FCR RMAP/TPM radar

DEGR

video generation capability is de-

graded.

Message

Description

FCR VID

Indicates that FCR RMAP radar video

FCR MMA

Indicates that the FCR MMA cooling

ZOOM DEGR

may be degraded in display zoom op-

COOL DEGR

fan is not operational. An overtemper-

eration.

ature condition could be the result

FCR VOLT-

Indicates that an FCR power supply

(para 4.50.5).

AGE DEGR

voltage is out of tolerance. FCR in-

FCR

Indicates that MTI is degraded. Mov-

formation may be unreliable.

MTI DEGR

ing targets may not be detected or

RFI BPI

Indicates that the RFI has detected a

may be shown with the wrong classifi-

DEGR

BPI failure. RFI information may be

cation. FCR operation in other modes

unreliable.

may still be possible (para 4.50.9).

RFI DEGR

Indicates that RFI information may be

FCR RADAR

Indicates that any FCR data could be

unreliable (para 4.50.14).

DEGR

invalid (symbol position in azimuth or

RFI FAIL

Indicates that the RFI is not operation-

elevation, classification, etc.

al.

FCR RANGE

Indicates that FCR range is 90% of full

10% DEGR

capability (para 4.50.6).

4.51 VIDEO SUBSYSTEM

FCR RANGE

Indicates that FCR range is 80% of full

20% DEGR

capability (para 4.50.6).

The Video Subsystem provides real time composite video

for the MPDs VIDEO page and VCR. Composite video is

FCR RANGE

Indicates that FCR range is 65% of full

composed of TADS FLIR, TADS DTV, PNVS FLIR with

35% DEGR

capability (para 4.50.6).

Flight/Weapon format symbology, or FCR

imagery with

FCR

Indicates that the FCR has lost the

symbology. The MPDs can display real-time sensor video

RESTART

ability to initiate a warm start se-

underneath all other MPD format symbology. Each crew

DEGR

quence.

station can select the VIDEO page for independent dis-

FCR

Indicates that the FCR has been shut-

play on either of their MPDs. Either crewmember can ac-

SHUTDOWN

down as a result of a detected over-

cess the video recorder controls to select what is to be re-

HOT

temperature condition. Message will

corded, to start and stop recording, and to play recorded

be cleared if power is applied to the

video. Sensor information does not have to be displayed

FCR.

to be recorded.

FCR STI

Indicates that STI is degraded. Sta-

DEGR

tionary targets may not be detected or

Only one sensor can be recorded at a time. Once se-

classified. FCR operation in other

lected, the video recorder will record the selected system

modes may still be possible (para

in the format it would be presented to the crewmember.

4.50.9).

FCR STI FAIL

Indicates that STI has failed. Station-

4.51.1 [

BLK 1

Video Recorder. The video record-

ary targets may not be detected or

er records 875 line video, and is located in the right aft

classified. FCR operation in other

avionics bay. The recorder controls are available to both

modes may still be possible (para

crewmembers through the VCR page. Tape length control

4.50.9).

is also available through the LMP.]

FCR TPM

Indicates that TPM is degraded. Ob-

DEGR

stacle symbol or profile line elevation

4.51.2 [

BLK 2

Video Recorder. The video recorder

position may be wrong. FCR operation

records 525 line video, and is located in the right aft avion-

in other modes may still be possible

ics bay. The recorder controls are available to both crew-

(para 4.50.9).

members through the VCR page.]

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

4-68

Change 2

TM 1-1520-251-10

4.52 CONTROLS AND DISPLAYS

controlled with the VCR rotary knob on the COMM panel.

If any radio is operating in a secure mode, no audio is re-

Controls and displays are integrated into the following ma-

corded. Monitored radio and other headset audio for the

jor Video Subsystem components:

crewmember that selected VCR recording is recorded at a

constant volume.]

• Video recorder controls

• [

BLK 1

Load Maintenance Panel controls]

4.52.5

[

BLK 2

Communications (COMM) Panel

Controls. Audio playback volume within each headset

• Communications Panel controls

can be independently controlled with the VCR rotary knob

• Multipurpose displays (MPDs)

on the COMM panel. If any radio is operating in a secure

mode, no audio is recorded. Monitored radio and other

4.52.1 Left Hand Grip. The LHG Video Record push-

headset audio for the crewmember that selected VCR re-

button (fig 4-63) toggles the VCR between its default

cording is recorded at a constant volume.]

mode (STOP or STANDBY), and RECORD modes.

4.53 VIDEO PAGE

The VIDEO page (fig 4-64A) is used to select VCR for

real-time video display, select IMAGE for still pictures, se-

VIDEO

RECORD

lect G/S for display optimization, and mode operation for

BUTTON

the VIDEO page in that crew station. If the VIDEO page

underlay buttons are set to NO VIDEO, and the pilot se-

lects the VIDEO page, the pilot’s HMD underlay will be se-

lected by default. This gives the pilot the ability to quickly

access his active NVS underlay (PNVS or TADS) in the

event of HMD failure. If there is no real-time video pres-

ented on an MPD, and the CPG selects the VIDEO page,

the CPG’s sight video underlay will be selected by default.

LBA2040

Figure 4-63. Left Hand Grip Control

4.52.2 Video Recorder Controls. Recorder controls

are provided through the crew station VCR page.

4.52.3

[

BLK 1

Load Maintenance Panel Con-

trols.

The Load Maintenance Panel can be used by the

ground personnel to indicate what tape length has been

loaded.]

4.52.4

[

BLK 1

Communications (COMM) Panel

Controls. The VCR provides a short tone when the

crew commands an event mark. This tone and audio play-

back volume within each headset can be independently

Figure 4-64.

[

BLK 1

VIDEO Page]

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

Change 3

4-69

TM 1-1520-251-10

4.53.1 VCR Button. The VCR button is provided on the

VIDEO page. Selection of the VCR button from the VIDEO

page calls the VCR page.

4.53.1A IMAGE Button. The IMAGE button is provided

on the VIDEO page. Selection of the IMAGE button from

the VIDEO page calls the IMAGE page.

4.53.2 Declutter Button. Selection of the VIDEO page

Video Select button initiates decluttered mode operation

on the VIDEO page for that crew station.

The button label changes to indicate the video symbolgoy

to be selected for presentation. The label is either C - FLT,

P-FLT, TADS, C-FCR, or P-FCR. Pilot or CPG owner-

ship is indicated by the initial P - or C - . TADS is always

owned by the CPG, and presents weapons symbology.

FLT indicates flight symbology, and FCR indicates FCR

targeting symbology. During decluttered mode operation,

the display is cleared of all button labels other than the

boxed VIDEO VSEL button, and abbreviated versions of

VIEW (W, N, Z) and the SHARP buttons presenting video

imagery and associated Flight, Weapon, or FCR

symbology. Although the menu button label is not shown

Figure 4-64A.

[

BLK 2

VIDEO Page]

when VSEL is selected, the menu button continues to

function normally. The default VIDEO page presentation is

with this button selected.

The following buttons can be found on the VIDEO page:

• T2

VCR button

4.53.3

VIEW Buttons. The VIEW buttons provide

selection of the video view modes for all non - FCR

vid-

• T3

IMAGE button

eo underlay beneath the MPD formats. When FCR sym-

• T6

Video Symbology Select button

bols are not presented, the VIEW buttons also affect FCR

(C-FLT, P-FLT, TADS, C-FCR, or

video. The default VIEW mode is NORM, in which the

P-FCR)

center 75% of the video image is presented. The WIDE

VIEW presents the center 95% of the image, with black

• L1

VIEW WIDE Button

bars filling blank video area on the top and bottom of the

• L2

VIEW NORMal button

underlay. The ZOOM VIEW presents a 2:1 electronic

• L3

VIEW ZOOM button

zoom of the WIDE image. The VIEW buttons are abbrevi-

ated to W, N, and Z and their surrounding bracket is re-

• L4

SHARP scroll up button

moved when VIDEO VSEL is selected.

• L5

SHARP scroll down button

4.53.4 SHARP Buttons. The SHARP buttons allow the

• L6

COLOR WHITE/GREEN button

crew to amplify presentation of fine detail information. The

• R1

UNDERLAY TADS button

optimal SHARP setting may vary with changing sensors

• R2

UNDERLAY CPG SIGHT button

or scene content. Applying SHARP to video containing

noise may make that noise more visible. The default is for

• R3

UNDERLAY CPG HMD button

no sharpness to be applied. When VIDEO VSEL is se-

• R4

UNDERLAY PLT SIGHT button

lected, the scale showing SHARP status is removed, but

the arrow buttons remain.

• R5

UNDERLAY PLT HMD button

• R6

UNDERLAY NO VIDEO button

4.53.5 COLOR Button. The COLOR button allow the

• B2

SYMB button

crew to choose either green or white video color for that

MPD’s video underlay. This button’s state does not impact

• B3

RESET button

the Day/Night/Mono knob or symbology presentation. The

• B6

G/S (Grayscale) button

default video color is WHITE.

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

4-70

Change 3

TM 1-1520-251-10

4.53.6 DISPLAY Buttons. The DISPLAY buttons pro-

vide selection of the video source to be displayed (under-

laid) beneath the MPD pages. Video underlay is overrid-

den by selection of the VCR playback, and FCR page

presentation on that MPD. Once these conditions change,

the previously selected video underlay returns to that

MPD. If the selected sight is FCR and FCR is operating in

terrain profiles or RMAP mode, FCR imagery is pres-

ented. During single DP operation, the VIDEO PAGE

selection of PILOT HMD or CPG HMD will continue to

present dual DP display format and imagery (see para

4.50.3).

4.53.7

RESET Button. The reset button allows the

crew to quickly return the VIEW, SHARP, and COLOR

buttons to their default conditions of NORM, no SHARP,

and color WHITE.

4.53.8 SYMB Button. The SYMB button is used to se-

lect between NORM and BOOST to optimize symbol con-

trast. Video performance is best when set to NORM. Set-

LBA−2031

ting the SYMB button to BOOST will darken the video

Figure

4-65.

[

BLK 1

VCR Page]

underlay to boost the apparent symbol brightness.

4.53.9 G/S (Grayscale) Button. Selection of the G/S

button temporarily overrides the VIEW button setting, and

presents VIEW WIDE video with gray scale bars filling the

top and bottom blank video area. If there is currently no

video underlay presented, an additional grayscale pattern

is generated by the CDP for presentation in the center

area. The G/S is useful for understanding the affect the

VID enhancement knob has on video.

4.54 VCR PAGE

The VCR page ( [

BLK 1

fig 4-65] and [

BLK 2

fig

4-65A] ) is used to control the selection of sources for tape

recording, and the VCR operating mode controls.

[

BLK 1

During single DP operation, the video recorder

is off and not selectable. When in single DP operation, or

if the VCR has been identified as failed, the VCR page will

blank, presenting a center status window stating VCR

NOT AVAILABLE and showing the VCR power button on

L6 as OFF.] [

BLK 2

During single DP operation, the vid-

eo recorder is not selectable. When in single DP opera-

tion, or if the VCR has been identified as failed, the VCR

page will blank, presenting a center status window stating

VCR NOT AVAILABLE.]

Figure

4-65A.

[

BLK 2

VCR Page]

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

Change 3

4-71

TM 1-1520-251-10

The following selections are found on the VCR page

(VSEL not selected) for all modes of operation:

• T1

VIDEO button

• T6

VSEL button

• L1

[

BLK 1

VCR RECORD button]

• L2

[

BLK 1

VCR PLAY button]

• L2

[

BLK 2

VCR RECORD button ]

• L3

[

BLK 1

VCR STANDBY button]

• L3

[

BLK 2

VCR PLAY button]

• L4

[

BLK 1

VCR STOP button]

• L4

[

BLK 2

VCR STANDBY button]

• L5

VCR REWIND button

• B5

[

BLK 1

TAPE button]

4.54.1 VIDEO Button. Selection of the VIDEO button

from the VCR page calls the VIDEO page.

4.54.2 VSEL Button. Selection of the VCR VSEL (vid-

LBA−5246

eo select) button ( [

BLK 1

fig 4-66] and [

BLK 2

fig

4-66A] ) selects video and its symbology for primary dis-

Figure 4-66A.

[

BLK 2

VCR Page, VSEL Selected]

play, and hides the MPD button labels from display for the

selecting crew station. This button is useful for viewing de-

4.54.3 [

BLK 1

VCR Mode Buttons. The VCR mode

cluttered VCR Playback information on the MPD.

buttons allow moding of the VCR for RECORD, PLAY,

STANDBY, STOP, and REWIND. They are presented

whenever the VCR is available (not failed) during normal

DP operations, and the VCR page is not operating in de-

cluttered mode. The default selection is VCR MODE

STOP (the tape is unthreaded) when operating under ex-

ternal power, and STANDBY (the tape is threaded), when

operating under aircraft power. If at any time the VCR is

unable to enter the commanded state, it will enter an un-

threaded STOP condition from which the crew can send it

to PLAY, RECORD, REWIND, or the threaded STANDBY

condition.]

4.54.3A [

BLK 2

VCR Mode Buttons. The VCR

mode buttons allow moding of the VCR for RECORD,

PLAY, STANDBY, and REWIND. They are presented

whenever the VCR is available (not failed) during normal

DP operations, and the VCR page is not operating in de-

cluttered mode. The default selection is VCR MODE

STANDBY (the tape is unthreaded) when operating under

external power, and STANDBY (the tape is threaded),

when operating under aircraft power. If at any time the

LBA−5070

VCR is unable to enter the commanded state, it will enter

an unthreaded STOP condition from which the crew can

Figure

4-66.

[

BLK 1

VCR Page, VSEL Selected]

send it to PLAY, RECORD, or REWIND.]

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

4-72

Change 3

TM 1-1520-251-10

4.54.4 [

BLK 1

TAPE Length Button. Selection of

NOTE

the TAPE button toggles between 40 minutes and 60 min-

Voice playback may not be audible to crew

utes. Tapes record for approximately twice their labeled

and/or maintenance personnel following re-

length. Tape length can also be set at the Load Mainte-

placement/reinstallation of the CIU until the

nance Panel. This button affects the elapsed time indica-

VCR volume ON/OFF knob has been

tion and does not alter actual recording speed or time

cycled.

available.]

4.54.6

VCR Playback Operations. Selecting the

4.54.5

VCR Recording Operations. The following

PLAY button initiates play of video tape at normal speed

additional selections can be found on the VCR page (fig

to any MPD presenting the VCR page. If at the end of the

4-65) during all VCR modes of operation except PLAY.

tape, the VCR will mode to [

BLK 1

play reverse] [

When commanded, the VCR records the selected image

BLK 2

play fast reverse] in response to crewmember

source with its symbology overlay. In addition, the approx-

play request by selecting the PLAY button, labelled PLAY

imate zulu time and a format ownership cue (C - FLT, P -

REVERSE at that point in time. The following selections

FLT, TADS, C - FCR, or P - FCR) are also recorded in the

can also be found on the VCR page during VCR Playback:

upper left corner of the format.

• L6

[

BLK 1

Mark (MK) button (VCR ON/

• L6

[

BLK 1

Mark (MK) button (VCR ON/

OFF button)]

• L6

[

Mark (MK) button]

• L6

[

BLK 2

Mark (MK) button]

BLK 2

• R1

RECORD TADS button

• R1

PLAY Fast Forward (>>) button

• R2

RECORD CPG SIGHT button

• R2

PLAY Forward (>) button

• R3

RECORD CPG HMD button

• R3

PLAY Pause (*) button

• R4

RECORD PLT SIGHT button

• R4

[

BLK 1

PLAY Reverse (<) button]

• R5

RECORD PLT HMD button

• R4

[

BLK 2

PLAY Reverse (<<) button]

• R6

RECORD FCR button

• R5

[

BLK 1

PLAY Fast Reverse (<<)

button]

• B2

EVENT PAUSE/IGNORE button

• R6

[

BLK 1

ORT PLAYBACK button

a. RECORD Buttons. Composite video, containing

(CPG Station Only)]

both imagery and flight, weapon, or FCR

symbology is

recorded in accordance with the RECORD buttons. Zulu

• R6

[

BLK 2

CTR DISP button (CPG

time is also recorded in the upper left area of the format.

Station Only)]

The default selection for these buttons is RECORD CPG

• B2

EVENT PAUSE/IGNORE button

SIGHT. VCR recording can also be commanded on the

left hand grip. See section 4.52.1.

a. ORT PLAYBACK Button. Selection of this but-

ton sends VCR playback to the ORT head-out and head-

[

BLK 1

MARK (MK) Button. Activation of the

down displays ( [

BLK 1

fig 4-67] and [

BLK 2

fig

MARK button marks a particular event on the video tape.

4-67A] ) when the VCR page is presented on either CPG

An event marker tone ( para 4.54.6.c) can be heard at this

MPD.

location when operating in the playback mode.]

b. Center Display

(CTR DSPL) Button (TE-

b1. [

BLK 2

MARK (MK) Button. Activation of the

DAC). Selection of the CTR DSPL button sends VCR

MARK button marks a particular event on the video tape.

playback to the TDU (fig 4-67A) when the VCR page is

(See para 4.54.6.c) ]

presented on either CPG MPD.

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

Change 4

4-72.1

TM 1-1520-251-10

PAUSE, the recorder pauses during tape playback at

each event marker. When set to IGNOR, the recorder ig-

nores event marks during tape playback.

NOTE

When the VCR is operated in the [

BLK 1

STBY Mode] [

BLK 2

STBY threaded

Mode] , the VCR is commanded to PLAY for

one second every five minutes (This is an

auto-advance command that reduces po-

tential damage to the VCR tape/head.) Any

previously recorded audio that is on the tape

is subject to being heard by the flight crew

for that one - second - time period. (If the re-

spective crewmember’s communication

(COMM) panels VCR volume control knob

is pushed in.) To preclude hearing any pre -

recorded audio when operating the VCR in

the STBY mode, pull out the VCR volume

control knob.

LBA3012A

4.54.7 VCR Standby Operations.

[

BLK 1

Selection

Figure

4-67.

[

BLK 1

CPG VCR Page - Play Mode]

of the VCR Mode STANDBY button sets the VCR to

standby. In this mode, the tape is threaded and prepared

for recording or playback.]

[

BLK 2

Selection of the VCR Mode STANDBY button

sets the VCR to either standby or stop depending on the

following conditions. In this mode, the tape is threaded

and prepared for recording or playback.]

• the aircraft is on the ground

• throttles are in OFF

• TADS is OFF

• PNVS is OFF

If all of the above conditions are met, then the VCR is

moded to stop. In this mode, the tape is unthreaded and

will require approximately 3 seconds to thread and begin

to operate as commanded. Otherwise, selection of the

VCR Mode STANDBY button sets the VCR mode to

standby. In this mode, the tape is threaded and prepared

for recording or playback (within half a second).

[

BLK 1

VCR Power Button. The VCR button

allows the crew to power the recorder on and off. The

LBA5072A

VCR will power on automatically unless external power is

applied. The VCR will be commanded to STOP when the

last of the following conditions are met:

Figure

4-67A.

[

BLK 2

CPG VCR Page - Play

• the aircraft is on the ground

Mode]

• throttles are in OFF

• TADS is OFF

c. EVENT Button. Selection of the EVENT button

toggles it between IGNOR and PAUSE. When set to

• PNVS is OFF

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

4-72.2

Change 3

TM 1-1520-251-10

Prior to shut-down of the aircraft, the crewmember should

• [

BLK 2

STOP (VCR mode indicated as STAND-

mode the VCR to OFF.]

BY - tape unthreaded) ]

• RWND

b. Video Tape Counter. A video tape counter, dis-

• [

BLK 1

OFF]

playing tape elapsed time or tape position, and VCR mode

and error messages is presented in the lower right corner

If the state is unknown, a WHITE “?” is presented.

of the VCR page. This counter is not removed during de-

c. VCR Real-Time Video Cue. When real-time vid-

cluttered operation. The counter outline is WHITE whenever

eo underlay is visible on the VCR page, the Video Cue

its interior text strings are white or alternate with white text.

data field, located next to the VIDEO button or VIDEO la-

NOTE

bel on the Menu button, shows which video is being un-

derlaid. This data field is presented to distinguish between

Priority for the presentation of the top line

playback and real-time video. Real-time video cues are:

Counter messages is:

•

CPG SIGHT (CPG)

• FAIL (VCR not responding or failed)

• PLT SIGHT (PLT)

• WET (alternating with other message)

• CPG HMD (CHMD)

• PLT HMD (PHMD)

• CHK (Check VCR)

• TADS (TADS)

• BOT (Beginning of Tape)

4.54A IMAGE PAGE

• EOT (End of Tape)

The IMAGE page (fig 4-67B) allows selection of a data

• Elapsed Time

frame (scanned image). The image selection is used to

view a loaded image (e.g. radar site target).

(1)

[

BLK 1

Top Line. The elapsed time in-

dication provides the same number for the same tape

position consistently (assuming the same tape length

selection), and can be used as a reference during play-

back. When starting from BOT, it may take up to 5 minutes

for the count to change upon initiating RECORD or PLAY.

The VCR can record when moisture is detected (WET).

However, continued operation could damage the VCR.

FAIL, WET, and CHK are displayed as WHITE in color.]

(2)

[

BLK 2

Top Line. The elapsed time indi-

cation can be used as a reference during playback. The

VCR can record when moisture is detected (WET). How-

ever, continued operation could damage the VCR. FAIL,

WET, and CHK are displayed as WHITE in color.]

(3) Bottom Line. The counter also displays a

second data field reflecting the state of the recorder:

• PLAY

• RCD

• [

BLK 1

STBY ]

• [

BLK 2

STBY (VCR mode STANDBY - tape

threaded) ]

• [

BLK 1

STOP]

Figure 4-67B. IMAGE Page

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

Change 3

4-72.3

TM 1-1520-251-10

The following unique selections are found on the IMAGE

4.54A.1 Image ROTATE Button Left. The Image RO-

page (ISEL not selected) for all modes of operation:

TATE Button Left (T4) is used to rotate the backg2round

image counterclockwise. Selecting the Image ROTATE

Button Left will cause the image to rotate 1 degree. If the

• T3

IMAGE button

Image ROTATE Button Left is selected and held for more

• T4

Image ROTATE button Left

than 0.5 seconds, the image will rotate at 40 degrees per

second after the initial 1 degree rotation.

• T5

Image ROTATE Data Entry button

4.54A.2 Image ROTATE Data Entry Button. The

• T6

Image ROTATE button Right

Image ROTATE Data Entry Button (T5) is used to rotate

• L6

Image LIST button

the image via a crewmember input on the KU. Rotation

angles from 1 through 360 degrees may be used.

• R1

Image Zoom Out button

4.54A.3 Image ROTATE Button Right. The Image

• R2

Image Zoom In button

ROTATE Button Right (T6) is used to rotate the back-

• R3

Image MOVE button

ground image counterclockwise. Selecting the Image RO-

TATE Button Right will cause the image to rotate 1 de-

• R4

Image RESET button

gree. If the Image ROTATE Button Right is selected and

held for more than 0.5 seconds, the image will rotate at 40

• R6

Image STORE button

degrees per second after the initial 1 degree rotation.

• B2

Image view option 1

4.54A.4 LIST Button. The LIST maintained option button

• B3

Image view option 2

(L6) (fig 4-67C ) is used to select which image is to be

viewed. When the list button is selected up to 20 image files

• B4

Image view option 3

will be available from the DTC. Page buttons are displayed if

more than 10 image files are found on the DTC. The first 22

• B5

Image view option 4

characters of the individual file names for each image will be

• B6

ISEL button

displayed. Selection of a file name will load the image.

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

4-72.4

Change 3

TM 1-1520-251-10

4.54A.9 STORE Button. Selecting the STORE button

(R6) allows the crewmember to store the current image

settings (location, rotation, and zoom) into view.

4.54A.10 Image View Buttons. Selecting any of the

Image View buttons (B2 - B5) allows the crew member to

select up to 4 stored views of the image. Each view con-

tains a specified zoom factor, location, and rotation of the

image. A view is created using the STORE button and se-

lecting the store location 1 - 4.

4.54A.11 ISEL Button. Selection of the ISEL (image

select) button (B6) (fig 4-67D) allows the crew member to

select a decluttered view of the image. All symbols and

controls are removed from the IMAGE page with the ex-

ception of the cursor controller symbol and the image view

buttons 1 - 4.

Figure 4-67C. IMAGE Page / LIST Selected

4.54A.6 ZOOM Buttons. The ZOOM scroll buttons

(R1 - R2) are used to zoom the image in or out. Selecting

an arrow will fine tune the zoom. Holding the arrow button

will change the zoom at a variable rate. Valid zoom range

is from 50% to 400%.

4.54A.7 MOVE Button. Selecting the MOVE button

(R3) allows the crewmember to move the image with the

cursor thumb - force controller.

4.54A.8 RESET Button. Selecting the RESET button

(R4) allows the crewmember to restore the image to the

default (non - stored) view. The default view restores the

image to 100% zoom, 360 rotation angle (image top to

MPD top) and the image will be recentered on the MPD.

Figure 4-67D. IMAGE Page / ISEL Selected

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

Change 3

4-73

TM 1-1520-251-10

4.55 SIGHTING SUBSYSTEM OPERATING

3. PLRT B/S switch - Check polarity reversal.

PROCEDURES

4. NVS MODE switch - NORM.

4.55.1 IHADSS Boresight - Pilot and CPG.

5. Registration - Check.

WARNING

a. Align crewmembers LOS forward to the 12

o’clock position ±5°.

OFFSET boresight is not authorized.

b. Select a reference object approximately 90

NOTE

ft in front of the aircraft.

Checks herein are in addition to those listed

c. Check registration (alignment differential)

in chapter 8. Except for safety, chapter 4

between the thermal image and reference

does not duplicate chapter 8 checks.

object in azimuth and elevation.

Sight select switch - HMD.

d. The allowable registration error is 1 ft of azi-

muth at 90 ft. The center open position of

WPN page - GRAYSCALE button - Select.

the LOS reticle is equivalent to 1 ft at 90 ft.

BRT and CONT knobs - Adjust as desired.

e. Unity Magnification - Check. Ensure 1:1 ra-

a. Sizing and centering - Verify.

tio with selected object.

6. Alternate sensor - Check.

b. Infinity focus - Check.

4.55.3 TADS Operational Checks - CPG (ORT).

WPN Page - GRAYSCALE button - Deselect.

SYM BRT Control (ORT and pilot) or SYM

CAUTION

brightness (TEDAC) - Adjust as desired.

The FLIR zoom field-of-view shall not be

WPN page - BORESIGHT button - Select.

activated for more than one minute of

continuous operation to prevent exces-

IHADSS button - Select.

sive after - image or raster burn. Any use

of the FLIR zoom FOV will result in some

PRI INT LT knob - Adjust as desired.

amount of after-image or raster burn.

The after - image tends to fade out over

HMD reticle - Align with BRU.

operating time in other FLIR FOV’s. How-

ever, prolonged use of FLIR zoom FOV

10.

PLRT B/S switch - B/S and release.

will result in an increased amount of

B/S NOW button (aircraft equipped with MTADS

after image or raster burn.

provisions) - Select.

1. NVS MODE switch - OFF

11.

BORESIGHT button - Deselect.

2. Sight select switch - TADS.

12.

PRI INT LT knob - Adjust as desired.

3. VID SEL switch - TADS.

4.55.2 NVS Operational Check (Pilot and CPG).

4. GS switch - Press.

1. NVS MODE switch - FIXED or NORM.

2. GAIN and LVL knob (ORT and pilot) or GAIN

5. BRT and CONT knob - Adjust as desired on

and LEV (TEDAC) - Adjust for optimum image.

heads - up and heads - down displays.

Verify capability to select the various modes of

flight symbology.

6. VID SEL switch - TADS.

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

4-74

Change 4

TM 1-1520-251-10

Sensor Select switch - DTV.

4.55.3A TADS Operational Checks - CPG (TEDAC).

SLAVE switch - Press and release to initiate

CAUTION

manual track.

The FLIR zoom field-of-view shall not be

activated for more than one minute of

MAN TRK thumbforce controller - Exercise tur-

continuous operation to prevent exces-

ret.

sive after - image or raster burn. Any use

of the FLIR zoom FOV will result in some

amount of after-image or raster burn.

10.

TADS FOV switch - Evaluate various FOVs.

The after - image tends to fade out over

operating time in other FLIR FOV’s. How-

ever, prolonged use of FLIR zoom FOV

11.

IAT/OFS switch - Engage. Check for proper

will result in an increased amount of

function.

after image or raster burn.

NVS MODE switch - OFF.

12.

Sensor Select switch - DVO.

Sight select switch - TADS.

13.

TADS FOV switch - Evaluate various FOVs. If

TAD - selected.

scene is not vertical in both FOVs, perform

Pechan Alignment.

G/S - selected.

14.

Sensor Select switch - FLIR.

BRT ans CON buttons - adjust as desired.

TAD - selected.

15.

GAIN and LVL knob - Adjust for optimum image

then engage ACM as desired.

Sensor select switch - DTV.

SLAVE switch - Press and release to initiate

16.

TADS FOV switch - Select. Evaluate various

manual track.

FOV’s.

MAN TRK thumbforce controller - Exercise tur-

ret.

17.

IAT/OFS switch - Engage image auto tracker.

Check for proper performance.

10.

TADS FOV switch - Evaluate various FOVs.

11.

IAT/OFS switch - Engage. Check for proper

18.

FLIR PLRT button - Check polarity.

function.

12.

Sensor Select switch - FLIR.

19.

Sensor Select switch - DTV or FLIR.

13.

GAIN and LEV knobs -Adjust for optimum

image, then engage ACM as desired.

NOTE

14.

TADS FOV switch - Select. Evaluate various

If Auto Drift Null does not reduce drift to

FOV’s.

desired level, perform Manual Servo Drift

Null Procedure. Manual Servo Drift Null may

reduce TADS turret slew rates by up to 50%.

15.

IAT/OFS switch - Engage image auto tracker.

Check for proper performance.

20. Drift null - Perform if required.

16.

FLIR PLRT button - Check polarity.

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

Change 3

4-75

TM 1-1520-251-10

17. Sensor Select switch - DTV or FLIR.

11. Right Thumbwheel Control - Adjust as required

to align horizontal crosshair with horizon.

NOTE

12. Boresight Enable switch - CENTER.

If Auto Drift Null does not reduce drift to

desired level, perform Manual Servo Drift

13. TADS FOV switch - N.

Null Procedure. Manual Servo Drift Null may

reduce TADS turret slew rates by up to 50%.

14. NFOV - Reverify alignment.

18. Drift null - Perform if required.

NOTE

If satisfactory, procedure is complete. If not

satisfactory, repeat steps 5 through 14 as

If satisfactory, procedure is complete. If not

required.

satisfactory, repeat steps 5 through 14 as

required.

4.55.5 TADS Manual Servo Drift Null (ORT).

4.55.4 TADS Pechan Realignment (ORT).

1. Sight select switch - TADS.

2. SLAVE switch - Press to verify TADS turret

slews to fixed forward position by observing

2. Sensor Select switch - DVO.

dashed reticle in center of display.

3. TADS FOV switch - N.

3. SLAVE switch - Press.

4. TADS turret - MANUAL control.

4. Sensor select switch - DTV or FLIR (for greatest

accuracy use DTV).

5. Boresight Enable switch - UP.

5. TADS FOV switch - N.

6. Left Thumbwheel Control - Adjust as required to

align horizontal crosshair with horizon.

6. Reticle - Aim at easily observed object.

7. Boresight Enable switch - CENTER.

7. Boresight Enable switch - UP. Wait 5 seconds

then adjust left and right thumbwheel controls

8. TADS FOV switch - W.

for drift null.

9. Crosshair and horizon - Recheck alignment.

8. Boresight Enable switch - CENTER.

NOTE

If satisfactorily aligned, select desired oper-

If the manual procedure was accomplished,

ating mode. If not satisfactorily aligned, go

the auto drift null may may be reactivated by

to step 10.

placing the Boresight Enable switch in UP

position for 2 seconds and then placing it

10. Boresight Enable switch - UP.

back to CENTER position.

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

4-76

Change 3

TM 1-1520-251-10

4.55.5A TADS Manual Servo Drift Null (TEDAC).

4.55.6 TADS Internal Boresight (ORT).

WARNING

1. Sensor select switch - FLIR or TV.

Proper laser safety procedures shall be

followed.

NOTE

2. TADS FOV switch - N.

• Boresighting of the DTV and FLIR occur

independently and the actual order is not

critical. However, DTV must be bore-

3. SLAVE switch - Press and release to initiate

sighted prior to boresighting the DVO.

manual track. Observe TADS drift.

• Internal boresight errors can develop in

flight due to temperature changes within

the internal components of the TADS

(thermal drift). It is recommended that an

NOTE

internal boresight be accomplished 2

times per 2.5 hour flight. Generally, the

more recent the internal boresight, the

To set TEDAC Display Unit (TDU) default

more accurate the system will be.

brightness and contrast levels, press AZ/EL

button on TDU.

Sight select switch - TADS.

WPN UTIL - LASER on.

4. AZ/EL button - Press to activate servo drift null.

WPN page - BORESIGHT - Select.

AZ/EL will appear boxed above button. After five

seconds, AZ and EL buttons become active.

INTERNAL - Select. Internal boresight mes-

sage present - Verify.

LASER - ARM.

NOTE

Sensor select switch - DTV.

If elevation and azimuth servo drift is not

TADS FOV switch - N.

corrected, go to step 5. Otherwise, go to

step 7.

IAT polarity switch - W.

LRFD trigger - Press and hold, observe pres-

ence of laser spot.

5. Adjust AZ and EL buttons to center target on

TADS reticle.

10.

Boresight Enable switch - UP. Observe tracking

gates capture laser spot. Continue to fire laser

until tracking gates disappear. If tracking gates

fail to capture laser spot, perform manual bore-

6. AZ/EL button - Press. AZ/EL display box above

sight (para 4.55.9) as required. If tracking gates

button will extinguish.

enter STOP mode, Boresight Enable switch to

CENTER position, then back to UP position.

11.

Boresight Enable switch - CENTER.

7. SLAVE switch - Press to deactivate manual

track.

12.

LRFD trigger - Release.

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

Change 3

4-77

TM 1-1520-251-10

13.

TADS FOV switch - Z.

29. Boresight Enable switch - CENTER.

14.

Z FOV - Repeat steps 9 through 12, then pro-

30. LASER - SAFE.

ceed to step 15.

31. BORESIGHT button - Deselect.

15.

Sensor select switch - FLIR.

32. WPN UTIL Page - Deselect LASER if desired.

16.

TADS FOV switch - N.

4.55.6A TADS Internal Boresight (TEDAC).

17.

LVL - Adjust fully counterclockwise.

18.

GAIN - Adjust to mid-range.

WARNING

19.

LRFD trigger - Press and hold.

Proper laser safety procedures shall be

Observe laser spot, and optimize FLIR for white

followed.

laser spot. If laser spot is not visible, perform

FLIR Cue Update Procedure

1. DTV Boresight NFOV

(para 4.55.7).

a. WPN page - Laser ON.

20.

Boresight Enable switch - UP. Observe tracking

gates capture laser spot. Continue to fire laser

b. WPN page - Select Boresight.

until tracking gates disappear. If tracking gates

fail to capture laser spot, perform manual bore-

c. TADS BORESIGHT page - TADS INTER-

sight (para 4.55.9). If tracking gates enter STOP

NAL - select.

mode, Boresight Enable switch to CENTER

position, then back to UP position.

WARNING

21.

Boresight Enable switch - CENTER.

Do not allow personnel forward of the

22.

LFRD trigger - Release.

TADS interface bulkhead while the laser

is being fired. Direct exposure to or re-

23.

TADS FOV switch - Z.

flections from the laser beam could

cause blindness or serious eye injury.

24.

Z FOV - Repeat steps 19 through 22, then pro-

ceed to step 25.

NOTE

25.

Sensor select switch - DVO.

To set TEDAC Display Unit (TDU) default

brightness and contrast levels, press * but-

26.

TADS FOV switch - N. Observe position of DVO

ton on TDU.

crosshairs. If the DVO crosshairs are not clearly

visible, perform DVO CUE update procedure

d. LASER - ARM.

(para 4.55.8). Observe position of DVO cross-

hairs. If coincident with DTV reticle, go to step

29.

e. Laser Trigger switch - Press and hold at

second detent. Verify laser spot is visible on

27.

Boresight Enable switch - DOWN.

TDU.

28.

DVO BRSIT - Adjust DVO crosshairs into coin-

f. AZ/EL button - press to enable boresight.

cidence with DTV reticle.

AZ/EL will appear in box above button.

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

4-78

Change 3

TM 1-1520-251-10

g. On TDU, observe that the tracker gates

f. On TDU, observe that tracker gates capture

capture the laser spot and center it in the

laser spot and center it in the display aiming

display aiming reticle. If laser spot is not

reticle. If laser spot is not centered on the

centered on the display and cannot be cap-

display and cannot be captured by tracking

tured by tracking gates, press AZ/EL button

gates, press AZ/EL button to enable AZ/EL

and continue firing laser. Wait five seconds

buttons and continue firing the laser. Wait

and adjust AZ and EL controls to center la-

five seconds and adjust AZ and EL controls

ser spot in display. Release laser trigger and

to center laser spot in display. Release laser

repeat steps e through i. If tracker enters the

trigger switch and repeat steps d through f.

STOP mode, press AZ/EL switch and re-

If tracker enters the Stop Mode, press AZ/

peat steps e through i.

EL switch and repeat steps d through f.

h. When tracker gates disappear, press AZ/EL

button to disable boresight. AZ/EL display

g. When tracking gates disappear, press AZ/

box above button will extinguish.

EL button to disable boresight. AZ/EL box

above button will extinguish.

i. Laser trigger - Release.

DTV boresight ZFOV.

h. Laser trigger - Release.

a. TADS FOV switch - Z.

b. Repeat steps - 1.e through 1.12 to bore-

FLIR Boresight ZFOV.

sight zoom FOV.

FLIR Boresight NFOV.

CAUTION

a. Sensor select switch - FLIR.

b. FLIR polarity switch - Press to select white

FLIR zoom FOV shall not be actuated for

hot.

more than two minutes of continuous

operation in order to prevent excessive

c. TADS FOV switch - N.

raster retention. Permanent damage may

occur if it is engaged for more than five

d. Laser trigger

- Press and hold at second

minutes.

detent. Adjust GAIN and LEV controls for

brightest laser spot with least backg2round

noise. If laser spot is not visible or if laser

spot is visible and cannot be captured in

a. TADS FOV switch - Z.

step f below, perform FLIR CUE Update

Procedure (para 4.55.7A) and select a dif-

ferent aiming reticle position within the CUE

b. Repeat steps 3.d through 3.22.

update target boundaries.

e. AZ/EL button - Press. AZ/EL will appear

boxed above switch.

c. TADS FOV switch - FOV other than Zoom.

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

Change 3

4-78.1

TM 1-1520-251-10

4.55.6B [

MTADS Internal Boresight].

5. Laser WARNING and prompts - observe safety

procedures and boresight procedure prompts.

WARNING

6. LASER - ARM.

Proper laser safety procedures shall be

7. LRFD trigger - Press and hold, observe pres-

followed.

ence of laser spot on the TDU or ORT HOD.

Continue lasing until spot disappears or DTV

NOTE

boresight is complete.

• Automatic internal boresighting of the

DTV and FLIR occur independently with

8. Internal Boresight Status - Observe

DTV being accomplished prior to FLIR. If

an ORT is installed, DTV must be bore-

a. Verify DTV BORESIGHT COMPLETE sta-

sighted prior to boresighting the DVO.

tus.

• If DTV boresight is complete, then FLIR

boresight will be performed. If DTV bore-

b. Continue to monitor FLIR BORESIGHT IN

sight fails, then FLIR boresight will not be

PROGRESS - Verify FLIR BORESIGHT

performed.

COMPLETE status.

• When FLIR boresight is complete, the in-

ternal boresight is complete.

c. If unable to successfully complete bore-

sight, exit internal boresight mode.

• Internal boresight errors can develop in

flight due to temperature changes within

9. BORESIGHT button - Deselect.

the internal components of TADS (ther-

mal drift). It is recommended that an in-

4.55.7 FLIR CUE Update Procedure (ORT).

ternal boresight be accomplished 2 times

per 2.5 hour flight. A HAD sight status

message will be displayed to indicate an

1. Sight select switch - TADS.

internal boresight is required at system

powerup and every 50 minutes thereaf-

2. Sensor select switch - DTV.

ter.

3. TADS FOV switch - W.

WPN UTIL - LASER on.

4. WPN Page - BORESIGHT button - Select.

WPN page - BORESIGHT - Select.

Sensor select switch - DTV or FLIR.

5. INTERNAL button - Select.

INTERNAL - Select. Internal boresight mes-

6. SLAVE switch - Actuate. Verify INTERNAL BS

sage present - Verify.

message replaced by CUE UPDT message.

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

4-78.2

Change 4

TM 1-1520-251-10

NOTE

7. AZ/EL button - Press.

Reticle should appear within the black

8. SLAVE switch - Press to select internal bore-

cross. If not, execute the following steps:

sight. Verify that INTERNAL BORESIGHT is

displayed in lower left corner of TDU.

7. Boresight Enable switch - UP.

4.55.8 DVO CUE Update Procedure (ORT).

8. DTV reticle - Use thumbforce controller to posi-

tion within black cross.

NOTE

9. Boresight Enable switch - CENTER.

The DVO CUE Update should be accom-

plished whenever the DVO crosshairs are

10. SLAVE switch - Actuate. Verify CUE UPDT

not visible during Internal Boresight. If the

message replaced by INTERNAL BS.

crosshairs are still not visible after accom-

plishing the DVO CUE Update, then pro-

11. WPN Page - BORESIGHT button - Deselect.

ceed with maintenance troubleshooting.

Note that there are symbology indications to

4.55.7A FLIR CUE Update Procedure (TEDAC).

the operator.

1. Sensor select switch - TV.

1. Sight select switch - TADS.

2. TADS FOV switch - W.

2. Sensor select switch - DVO.

3. TADS FOV Switch - W.

NOTE

To set TEDAC Display Unit (TDU) default

4. SLAVE Switch - Press.

brightness and contrast levels, press * but-

5. Manual Thumb Force Controller - Adjust light to

ton on TDU.

center of crosshairs.

3. SLAVE switch - Press to select cue update.

6. TADS FOV Switch - N.

Verify that message CUE UPDT is displayed in

lower corner of TDU.

7. Observe DVO crosshairs. If the visual presenta-

tion is still not optimum - fine tune for best pre-

NOTE

sentation with the Thumb Force controller.

All four cue update target position indicators

8. SLAVE Switch - Press.

may not be visible on the display simulta-

neously.

9. Continue with Internal Boresight.

4.55.9 Manual Boresight (ORT).

4. Observe position of cue update target position

indicators around aiming reticle. If aiming reticle

is not within boundary line or the laser spot is not

NOTE

visible or not useable during FLIR internal bore-

The manual boresight adjust procedure is

sight, go to step 6 , If aiming reticle is within

used only to recapture or center the laser

boundary line go to step 8.

spot. It is not an acceptable boresight pro-

cedure for normal flight operations.

5. AZ/EL button - Press. AZ/EL will appear boxed

above switch.

1. Sight select switch - TADS.

NOTE

2. WPN UTIL page - LASER on.

Do not drive cue update target from the

3. WPN Page - BORESIGHT button - Select.

FOV.

4. INTERNAL button - Select.

6. MAN TRK control - Operate to move aiming re-

ticle within cue update target boundary.

5. LASER button - ARM.

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

Change 4

4-78.3

TM 1-1520-251-10

Sensor select switch - FLIR or DTV as required.

NOTE

If the target is between 0.5 km and 1.5 km,

FLIR PLRT button - White hot.

the range entered on the KU must be within

10m. If the target is between 1.5 km and 5

TADS FOV switch - N.

km, the range entered on the KU must be

within 50m. If the target is greater than 5

GAIN knob - Adjust to mid-range.

km, the range entered on the KU must be

within 1 km.

10.

LVL knob - Adjust fully counterclockwise.

3. NFOV FLIR - Adjust GAIN and LVL. Observe

11.

LRFD trigger - Press and hold. Observe laser

outfront boresight target for optimum autotrack-

spot and optimize FLIR.

er image. Engage IAT. If tracker enters stop

mode, disengage IAT, then re-engage IAT.

12.

Boresight Enable switch - UP for 1 second, then

move to CENTER position. After 5 seconds the

left and right thumbwheel controls will be active;

4. Sensor select switch

- DTV, observe light

adjust laser spot in elevation and azimuth.

source.

13.

LRFD trigger - Release.

If FLIR and DTV reticles do not strike the bore-

sight target in precisely the same spot, perform

14.

Boresight Enable switch - CENTER.

the following:

15.

LASER - SAFE.

16.

WPN Page - BORESIGHT button - Deselect.

WARNING

17.

WPN UTIL page - Deselect LASER, if desired.

Do not allow personnel forward of the

4.55.10

TADS Outfront Boresight (ORT).

TADS interface bulkhead while the laser

WARNING

is being fired. Direct exposure to or re-

flections from the laser beam could

TADS Outfront Boresight validation and

cause blindness or serious eye injury.

adjustment (if necessary) shall be per-

formed prior to using the TADS FLIR

5. WPN Page - BORESIGHT button - Select.

imagery for laser or weapons opera-

tions, after performing a Cue update, a

TADS component change, or if the heli-

6. OUTFRONT - Select.

copter experiences an abnormal electri-

cal shutdown.

1. Helicopter - Position on the ground over identi-

7. Boresight Enable switch - UP.

fied location for this procedure.

NOTE

8. Adjust azimuth and elevation knobs to center

If on an approved laser firing range, fire la-

the target on the reticle.

ser to obtain range. Otherwise, enter manu-

ally the range from the helicopter to the out-

front boresight target by selecting MAN

9. Boresight Enable switch - CENTER.

RNG on WPN page and entering range in

KU.

2. RANGE - Enter.

10. WPN Page - BORESIGHT button - Deselect.

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

4-78.4

Change 4

TM 1-1520-251-10

4.55.10A TADS Outfront Boresight (TEDAC).

11. Observe boresight target light source. if not cen-

tered on TADS reticle, complete steps 12

through 18.

WARNING

TADS Outfront Boresight validation and

adjustment (if necessary) shall be per-

Do not allow personnel forward of the

formed prior to using the TADS FLIR

TADS interface bulkhead while the laser

imagery for laser or weapons opera-

is being fired. Direct exposure to or re-

tions, after performing a Cue update, a

flections from the laser beam could

TADS component change, or if the heli-

cause blindness or serious eye injury.

copter experiences an abnormal electri-

cal shutdown.

12. WPN page - BORESIGHT - Select.

NOTE

13. WPN page - TADS OUTFRONT - Select.

Wait 30 minutes after the FLIR NOT

14. AZ/EL button - Press. AZ/EL becomes boxed

COOLED message on the TEDAC Display

above button.

Unit (TDU) disappears before performing

outfront boresight. This allows the FLIR sys-

15. AZ and EL buttons - adjust to center target on

tem to stabilize for a more accurate outfront

TADS recticle.

boresight.

16. AZ/EL button - Press. AZ/EL display box above

button will extinguish.

1. NVS switch - OFF.

17. IAT switch - OFF.

2. WPN page Range button - enter manual range

from helicopter to boresight target on KU.

18. WPN page - BORESIGHT - Deselect.

4.55.11 FCR Operational Check

NOTE

A target, a minimum of 0.5 km away from

• Wait for magnetic heading scale to ap-

the helicopter is required. The target must

pear before proceeding to power-up the

have the same center as viewed in both

FCR. INU must be aligned before reliable

FLIR and TV sensors.

FCR target information is available.

•

The FCR will not accept DTU loads for

modes and lethal ranges or FCR UTIL

3. Sight select switch - TADS.

page (DTU source) priority schemes D, E

F, or G until the FCR has completed pow-

4. Sensor select switch - FLIR.

er - up BIT and the FCR power button is

not OIP.

5. FLIR LEV and GAIN knobs - Adjust as neces-

• This operational check verifies correct

sary.

operation of the crewstation switches

used to employ the FCR. If it is antici-

6. TADS FOV switch - N.

pated that both the pilot and CPG will op-

erate the FCR during the mission, then

7. Slave button - Press to enable manual track.

this task should be completed in both

crewstations.

8. Exercise TADS Turret with MAN TRK controller

• A WEAPONS/SIGHTS DTU load only

to acquire boresight target.

needs to be performed one time by either

the PLT or CPG.

9. IAT/OFS switch - IAT. Engage boresight target

FCR UTIL page - Select.

with auto tracker.

MMA button - NORM (1st power up, if pinned,

10. Sensor select switch - TV.

or select FCR or RFI power ON).

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

Change 4

4-78.5

TM 1-1520-251-10

Section II. ARMAMENT SYSTEMS

4.56 GENERAL

controlled by redundant weapon processors which man-

age gun, rocket and missile functions. The weapon sys-

This section provides a description of the armament sys-

tems consists of the following:

tems and respective operating procedures. It includes a

description of weapons components, the controls and dis-

• M139 Area Weapons System (AWS) (M230E1

plays, systems operation, and armament checklists.

Automatic Gun)

4.57 INTRODUCTION

• Rocket Management Subsystem (2.75 Inch Aerial

Rocket)

The armament systems (fig 4-68) provide the aircrew with

a means of quick response delivery of ordnance to se-

• Longbow Hellfire Modular Missile System

lected targets. The armament systems provide for weap-

on selection, control moding, and firing, for close-in, me-

dium and long-range targets. The armament systems are

• Wing Stores Pylon Subsystem

PYLON

INTERFACE UNITS

SIDELOADER

LOAD MAINTENANCE PANEL

MAGAZINE CONTROLLER

WEAPONS

PROCESSORS

HIADC

SYSTEM

PROCESSOR

GUN CONTROL BOX

EG1 2

TURRET

CONTROL

BOX

2.75 INCH

ROCKETS

EG1 1

SYSTEM

PROCESSOR

HELLFIRE/

PYLON

30mm GUN

RF & LASER

INTERFACE UNITS

LBA0094

Figure 4-68. Armament Systems

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

4-79

TM 1-1520-251-10

4.58 ARMAMENT SYSTEM ARCHITECTURE

attitudes, rates, and accelerations to the WP for use in

ballistic computations and weapons constraint calcula-

4.58.1 PRIMARY POWER CONTROL. Prime power is

tions.

applied to the Hellfire weapon stations when the subsys-

tem is enabled via the WPN UTIL page. The gun prime

4.58.5 Air Data System (ADS). The ADS provides air

power is applied during aircraft powerup and the rocket

data to the WP for use in computing ballistics and weapon

subsystem does not require prime power. The weapon

constraint calculations.

subsystem enable/disable functions on the WPN UTIL

page allow for positive safeing of the weapons suite for

4.58.6 Pylon Interface Units (PIU). Each pylon con-

rearming or other activities that require absolute safeing

tains one PIU. The PIU communicates via the MUX bus to

measures.

control pylon positioning and control, status information

and management of pylon stores.

4.58.2

Arm Power Control. Weapon stations are

armed only after a weapon is selected, via the WAS, and

4.58.7 Weapons Processor (WP). During normal op-

the aircraft has been armed from the ARMAMENT panel

eration, one WP actively provides weapon computations

A/S button.

and control while the second WP is maintained in a readi-

ness state. The WP performs the tasks of weapon initial-

a. The SP controls the application of arm power inde-

ization, selection, inventory, moding, positioning, and fir-

pendent of the WP, in that the aircraft must be armed as

ing for all aircraft weapons.

determined by the SP, before WP station arm power re-

quests are acted upon.

CAUTION

b. Station arm power is applied via the ELCs under

SP control. Electromagnetic relays are used for all weap-

There is no indication in the cockpit

on power load switching. The SP determines the aircraft

when the SQUAT ORIDE switch is in the

state based on the ARMAMENT panel selections and the

AIR position. The possibility exists that

squat switch. The SP commands the ELCs to apply sta-

the AWS could inadvertently be driven

tion arm power when requested by the WP.

into the ground.

c. The WP requests station arm power, via the SP,

4.58.8 Load Maintenance Panel (LMP). The LMP (fig

when the aircraft is armed and a weapon is selected and

4-69) provides the ground crew with the capability to man-

arming constraints are satisfied. Station arm power is

ually enter and display AWS and external stores muni-

used for rocket and missile squib ignition as well as gun

tions load data. The LMP provides the aircrew the capabil-

bolt-pulse relay control.

ity to check/verify rocket type within each of the rocket

zones and gun rounds loaded on pre-flight. A weapon

4.58.3 System Processor (SP). The SP provides the

load page is provided on the MPD to permit aircrews to

SAFE/ARM control and the corresponding primary power

modify (override) the LMP zone inventory in the event an

and arm power control to the weapons.

entry error is made by the load crew during munition load-

ing or LMP failure occurs. The LMP also permits position-

4.58.4 Embedded Global Positioning Inertial Naviga-

ing of the pylons to either +4° (Up) or - 5° (down) positions

tion System (EGI). The EGI provides aircraft position,

for munitions loading.

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

4-80

TM 1-1520-251-10

LBA2559

Figure 4-69. Load Maintenance Panel

4.59 ARMAMENT PANEL

between SAFE and ARM. The button light indicates

SAFE or ARM as appropriate in both crew stations. On

The ARMAMENT Panel (fig 4-70) is located on the instru-

aircraft powerup, the default setting is SAFE. There is no

ment panel in both crew stations.

OFF position for the ARM/SAFE button.

4.59.2

Ground Override (GND ORIDE). The GND

ORIDE button is a lighted pushbutton used to override

squat switch inhibits when on the ground. Activating the

GND ORIDE button enables ARM/SAFE control in all

modes and the button light indicates ON in both crew sta-

tions. Activating the button a second time will mode the

GND ORIDE button to OFF and extinguish the ON indica-

tor.

4.60 CYCLIC CONTROL GRIP

The following weapons system controls are located on the

BA0071

cyclic control grip (fig 4-71) in each crew station.

Figure 4-70. ARMAMENT Panel

4.60.1 Weapon Action Switch (WAS). The WAS is a

five-position spring-loaded switch. Placing the switch mo-

4.59.1 ARM/SAFE (A/S) Button. The A/S button is a

mentarily to a desired position selects (actions) a weapon

lighted pushbutton used to control ARM/SAFE power of

for firing. Reselecting the actioned weapon will deselect

the aircraft. The button controls application of power to

the weapon. If a weapon has been selected, actioning an

weapon firing circuits. Activating the A/S button from ei-

alternate weapon will deselect the current selection and

ther crew station will mode the aircraft status alternately

action the newly selected weapon.

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

4-81

TM 1-1520-251-10

the first detent will fire a weapon if no inhibits exist. Press-

WEAPONS

ing the trigger to the second detent will override weapons

ACTION

SWITCH

performance inhibits and fire a weapon. Safety

constraints can never be overridden.

4.61 COLLECTIVE CONTROL

Weapon switches on the collective control grip (fig 4-72)

include the emergency stores jettison (JETT) switch on

the flight control grip and the missile advance (MSL ADV)

WEAPONS

switch on the mission control grip.

TRIGGER

SWITCH

MISSION

MISSILE

CONTROL

ADVANCE

GRIP

ÓÓÓ

LBA1039

ÓÓÓ

Figure 4-71. Cyclic Control Grip

JETTISON

SWITCH

FLIGHT

CONTROL

GRIP

a. WAS Selections. WAS selections are as follows:

• G (Gun). Actions the AWS and slaves the gun to

the selected sight.

• M (Missile). Actions the Hellfire missile system;

allows the pylons to articulate and displays the

launch constraints symbol.

• A (Air-To-Air). Growth position; not active.

• R (Rocket). Actions the Rocket Management

LBA0759

Subsystem; allows the pylons to articulate and

displays the rocket steering symbol.

Figure 4-72. Collective Control Grips

b. WAS Logic. A weapon can be actioned from ei-

ther crewstation via the cyclic. Additionally, the CPG can

4.61.1 Missile Advance (MSL ADV) Switch. The MSL

action weapons via the LHG. The last crewmember to ac-

ADV switch is used to manually advance or select the

tion a weapon has control of that weapon. Exception: If

next missile in the firing sequence. When the Hellfire mis-

the CPG has rockets actioned via the ORT/TEDAC WAS

sile system is actioned in the manual mode, the MSL ADV

and the pilot actions rockets, cooperative moding is in ef-

switch on the collective mission grip is active. When the

fect. The active LOS will be the CPG’s LOS. The CPG’s

SAL missile mode is NORM or RIPL, the MSL ADV

rocket moding selections will be active in cooperative

switch is not active.

mode. The pilot’s type, quantity, and penetration selec-

tions will default to the CPG’s selections.

4.62 ORT/TEDAC HANDGRIPS

4.60.2 Weapons Trigger Switch. The weapons trigger

Armament system controls located on the ORT/TEDAC LHG

switch is a three position, two detent, guarded switch used

(fig 4-73) include the WAS and the weapons trigger switch.

to fire an actioned weapon. The switch is active when the

The MSL ADV switch is located on the ORT/TEDAC RHG.

A/S switch is in the ARM position. Pressing the trigger to

(fig 4-74)

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

4-82

Change 3

TM 1-1520-251-10

• RKT (Rocket)

• ATA (Air to Air) (Inactive)

Functionally it is identical to the WAS located on the cyclic

control grip.

CURSOR

4.62.2

Weapons Trigger Switch. Functionally, this

weapons trigger switch is identical to the trigger switch lo-

L/R

WEAPONS

cated on the cyclic control grip.

TRIGGER

SWITCH

4.62.3 Missile Advance (MSL ADV) Switch. Func-

WEAPONS

ACTION

tionally, this MSL ADV switch is the same as the MSL

SWITCH

ADV switch located on the collective control grip.

4.63 WEAPONS (WPN) PAGE

The WPN page (fig 4-75) is used to functionally control

sight and weapons moding. Various sight and weapons

subsystem status windows, icons, and control selections

LBA1024

are included on the format to reduce workload and en-

hance situational awareness. Sight subsystem descrip-

tions are provided in Section I. The WPN page contains

Figure

4-73. LHG

the following weapons buttons:

C−SCOPE

SLAVE

MAN TRK

ZOOM

HDD

ADV

MISSILE

ADVANCE

LBA2014

LBA0433A

Figure 4-74. RHG

Figure 4-75. WPN Page

4.62.1 Weapon Action Switch (WAS). The WAS is a

• T1

Missile CHAN button

5-position spring-loaded switch used to select a weapon

• T6

WPN UTIL button

for firing:

• B2

GUN button

• GUN (Gun)

• B3

MSL button

• MSL (Missile)

• B5

RKT button

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

Change 3

4-83

TM 1-1520-251-10

4.63.1

CHAN Button. The missile CHAN button is

used to access missile channels and stored laser codes

for missile channel coding.

4.63.2 WPN UTIL Button. The WPN UTIL button is

used to access weapons subsystem utility functions.

4.63.3 TRAIN Button. The TRAIN button is used to ac-

tivate and deactivate the weapon training mode (refer to

paragraph 4.74.7). The TRAIN button is displayed with a

barrier when armament control is in the ARM state or

when a weapon system is actioned in either crew station.

This button is not available when the Tactical Engagement

Simulation System (TESS) is enabled.

4.63.4 AKI Button. The AKI button is used to set the

Aircraft Kill Indicator (AKI) to off in order to avoid crew dis-

orientation when operating at night in heavy obscuration

(i.e., fog, dust, precipitation, etc.). It is displayed only

when operating in the TESS mode with an active kill, hit,

or near miss casualty indication (external AKI flashing

LBA1974A

light activated).

Figure 4-76. Gun System Controls

4.63.5 GUN Button. The GUN button is used to access

a. MODE Button. The gun MODE button is used to

gun system controls and system status. Selecting the

select operational mode of the gun system: NORM or

GUN button causes the gun icon to become inverse video

FXD. The NORM mode allows the gun to follow the se-

and calls up the gun controls around the edges of the dis-

lected sight while the FXD mode fixes the gun to the cent-

play (fig 4-76).

erline of the aircraft. Gun mode selections are indepen-

dent in each crew station.

b. BURST LIMIT Buttons. BURST LIMIT defines

the number of rounds to be fired with each trigger pull: 10,

20, 50, 100, or ALL. Burst limit selections will not exceed

turret control box burst limit selection.

c. HARMONIZE Button. The HARMONIZE button

is used to perform the gun system dynamic harmonization

procedure. This function is provided only in the CPG crew

station.

d. Gun Icon and Rounds Counter. The gun

rounds counter displays within the gun icon and will de-

crease in real time to reflect the number of rounds remain-

ing as the gun is fired. When all rounds have been fired,

the gun symbol displays zero.

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

4-84

TM 1-1520-251-10

• L1

PRI button

e. MSL CCM Button. The MSL CCM button is used

to enable the counter-countermeasures within the SAL

• L2

ALT button

missile.

• L3

SAL SEL button

f. TYPE Button. The missile TYPE button is used

• L5

DEICE button

to set the desired missile type: SAL or RF. Missile TYPE

• L6

MSL CCM button

selections are independent in each crewstation.

• R1

TYPE button

g. MODE Button. The missile MODE button is used

to select the operational mode of the missile system in the

• R2

MODE button

SAL missile format: NORM, RIPL, and MAN. The NORM

• R3

TRAJ button

allows for firing missiles coded to the priority (PRI) chan-

nel. The RIPL mode allows for firing of missiles coded to

a. PRI Button. The PRI button is used to designate

both the priority channel and the alternate channel. The

the priority missile channel for coding SAL missiles. Prior-

MAN mode allows selection of a single missile for firing.

ity channel is common to both crewstations. Selecting the

SAL missile mode selections are common to both crew

PRI button will provide the channel options as set up on

stations.

the CHAN page. PRI button must be selected before se-

lecting ALT. A PIM (pulse interval modulation) or PRF

h. TRAJ Button. The TRAJ button is used to select

(pulse repetition frequency) label is displayed adjacent to

the desired missile launch trajectory: DIR, HI, or LO. DIR

the button label to indicate the type of laser code in the

is used when the aircraft has direct line of sight to the tar-

priority channel.

get. HI/LO are used when a high altitude trajectory is re-

quired. Trajectory mode selections are independent in

each crew station.

b. ALT Button. The ALT button is used to desig-

nate the alternate missile channel for coding SAL mis-

i. SAL Missile Status Window. The SAL missile

siles. Alternate channel is common to both crewstations.

status window in the lower center area of the format indi-

Selecting the ALT button will provide the channel options

cates the current status of missile channel coding and

as set up on the CHAN page. A PIM (pulse interval modu-

priority/alternate channel selections for all 4 SAL missile

lation) or PRF (pulse repetition frequency) label is dis-

channels. The priority channel label, laser code and box

played adjacent to the button label to indicate the type of

are displayed in WHITE.

laser code in the alternate channel.

j. SAL Missile Icons. When the missile system in-

ventory detects SAL missiles present on the launcher

c. SAL SEL Button. The SAL SEL button is used

rails, unique SAL missile icons (fig 4-78) display to reflect

to select the type of SAL missile when in the SAL missile

this condition. Missile type, status, and fault condition in-

format: AUTO, SAL1, and SAL2. For missile system op-

formation is displayed within the icon symbol. Icons may

erations Basic Hellfire missiles will be identified as SAL 1

be displayed in normal or inverse video depending on

missiles and Hellfire II missiles will be identified as SAL 2

whether the MSL button is selected or the missile system

missiles. SAL 1 missiles are only capable of PRF laser

is actioned. The icon will be displayed in WHITE and flash

code operation. SAL 2 missiles are capable of both PRF

between a bold and normal line when that missile is se-

and PIM laser code operations. The AUTO allows for au-

lected as the next missile to be launched in the firing se-

tomatic selection of a SAL 1 or SAL 2 missile. If the code

quence, regardless of these selections.

type is PRF the missile system will select SAL 2 missiles

first, if available, over SAL 1 missiles. If the code type is

k. RF Missile Icons. When the missile system in-

PIM the system will select only SAL 2. The SAL1 selection

ventory detects RF missiles present on the launcher rails,

allows for firing of only SAL 1 missiles. The SAL2 selec-

unique RF missile icons (fig 4-79) display to reflect this

tion allows for firing of only SAL 2 missiles.

condition. Missile type, status, and fault condition informa-

tion is displayed within the icon symbol. Icons may be dis-

d. DEICE Button. The missile DEICE button is

played in normal or inverse video depending on whether

used to manually de-ice SAL missile seekers in prepara-

the MSL button is selected or the missile system is ac-

tion for missile launch. The DEICE button (L5) is only

tioned. The icon will be displayed in WHITE, normal video

presented when the aircraft state is ARM and the missile

when that missile is selected as the next missile to be

system is actioned. Selecting the button causes the se-

launched in the firing sequence, regardless of these

lected missile seeker’s protective de-ice cover to jettison.

selections.

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

4-86

TM 1-1520-251-10

SAL 1

LASER MISSILE PRESENT

RF MISSILE PRESENT

RF MISSILE POWERED

SAL 2

LASER MISSILE PRESENT

BUT NOT YET ALIGNED

LASER MISSILE POWERED

BUT NOT YET CODED

RF MISSILE HAS BEEN DETECTED

IN AN OVER−TEMPERATURE

STATE

PRIORITY SAL MISSILE,

RF MISSILE READY

NEXT MISSILE LOAL

TO RECEIVE

TARGET

MISSILE SEEKER IN

TRACK MODE

MISSILE HAS BEEN DETECTED

AS NOT AVAILABLE

AS NOT

AVAILABLE

MISSILE IS

LAUNCHER

MISSILE IS UNLATCHED

ON LAUNCHER

MISSILE LAUNCHER

HAS

FAILED

HASTION

FAILED

MISSILE HAS FAILED BIT

MISSILE HAS FAILED BIT OR

HAS BEEN DETECTED AS

FAILED SUBSEQUENT TO

BIT

MISSILE HAS BEEN

MISSILE HAS BEEN REPORTED

HANGFIRED

AS HANGFIRED

MISSILE LAUNCH SEQUENCE HAS

ABORTED OR MISSILE HAS MISFIRED

LBA2576

LBA2577

Figure 4-78. SAL Missile Icons and Status

Messages

Figure 4-79. RF Missile Icons and Status Messages

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

4-87

TM 1-1520-251-10

Table 4-22. MSL Available/MSL PWR

(AUTO MODE)

Missiles Available

Missiles Powered

8 or more

4-7

2-3

* Unless missiles are actioned, then 1 is powered.

Selecting the NONE button removes power to all RF mis-

siles. When the RF missile MODE is MAN the MSL PWR

buttons are not displayed. MSL PWR selection is common

to both crew stations.

m. LOBL INHIBIT Button. The Lock On Before

Launch LOBL INHIBIT button inhibits the RF missile

LBA1976

seeker from transmitting and attempting to track the se-

lected target while on the rail during an RF engagement.

LOBL INHIBIT selection is common to both crew stations.

2ND TARGET INHIBIT Button. The 2ND TAR-

GET INHIBIT button is used to prevent secondary target

information from being handed over from the FCR to the

primary RF missile during a stationary target engage-

Figure

4-80.

RF Missile System Controls

ment. 2ND TARGET INHIBIT is common to both crew sta-

tions.

o. MODE Button. The MODE button is used to de-

• L1 - L3

MSL PWR buttons

termine how control of power to the RF missiles will occur.

The MODE button toggles between NORM and MAN

• L5

LOBL INHIBIT button

modes and will power the RF missiles according to MSL

PWR selection. The MAN MODE allows the operator to

• L6

2ND TARGET INHIBIT button

use the Manual Advance (MAN ADV) switch to to select

and power a single RF missile for firing. It also allow the

• R2

MODE button

crew to manually advance through the RF missiles to se-

• R4

TRAIN button

lect a desired missile for power application. When the

MAN MODE is selected, the MSL PWR selection is re-

moved. RF missile MODE is common to both crew sta-

l. MSL PWR Buttons. MSL PWR buttons are used

tions.

to select the desired method of RF missile management:

ALL, AUTO, and NONE. Selecting the ALL button com-

p. Missile Launcher Rail Icons. Missile launcher

mands power to all RF missiles. Selecting the AUTO but-

rail icons (fig 4-81) indicate launcher present and missile

ton automatically manages power to the missiles to pre-

inventory status. Like the individual missiles icons, the

vent overheating. The number of missiles powered is

launcher rail icons become inverse video when selected

based on the total missile inventory (table 4-22) available.

or when the missile system is actioned.

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

4-88

TM 1-1520-251-10

MISSILE LAUNCHER PRESENT

4.63.7 RKT Button. The RKT button is used to access

(FOUR RAIL SYMBOLS)

rocket system controls and system status. Selecting the

RKT button causes the rocket launcher icons to become

inverse video and calls up the rocket system controls

around the edges of the display (fig 4-83).

NORMAL

INVERSE

LBA0434

Figure 4-81. Missile Launcher Rail Icons

q. Missile Launcher FAIL/SAFE/BIT/LOAD

Icons. Unique missile launcher status icons (fig 4-82)

are displayed under certain conditions: the WHITE

launcher SAFE icon is displayed when the launcher

SAFE/ARM switch is in the SAFE position; the WHITE

launcher BIT icon is displayed when launcher IBIT is in

progress; the WHITE launcher LOAD icon is displayed

when the loading of keyword(s) to the launcher is in prog-

ress; the YELLOW FAIL icon is displayed when a fail

condition is detected that affects missile operation. These

LBA1977B

icons are displayed around the missile icons of the af-

fected launcher.

Figure 4-83. Aerial Rocket System Controls

• L1 - L5

INVENTORY Buttons

• R1

QTY button

• R2

PEN button

a. INVENTORY Buttons. The INVENTORY buttons

are used to select the desired rocket warhead and type to

be fired. Rocket INVENTORY type and warhead selec-

tions are independent in each crew station.

NORMAL

INVERSE

NORMAL

INVERSE

b. QTY Button. The QTY button is used to select

the desired number of rocket pairs to be fired with each

trigger pull: 1, 2, 4, 8, 12, 24, and ALL. When QTY is 1, a

single rocket will be fired with each trigger pull. For the re-

maining QTY options, rockets will be fired in pairs with

each trigger pull. Rocket Quantity selections are indepen-

dent in each crew station.

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

NORMAL

INVERSE

NORMAL

INVERSE

the desired warhead fuse penetration setting. The PEN

LBA0435

button displays when warheads which require a penetra-

tion selection, such as RC4 or 6RC (M433 fuze), are

loaded. Warhead penetration selections are independent

Figure 4-82. Missile Launcher Status Icons

in each crew station.

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

4-89

TM 1-1520-251-10

d. Total Rockets Status Window. The TOTAL

4.63.10 CHAFF Status. The CHAFF status displayed

ROCKETS status window in the inventory format area in-

in the center area of the WPN page provides the remain-

dicates the total rockets remaining for the type warhead

ing number of chaff cartridges decremented by the system

selected when the total and available quantities are not

processor and the current chaff dispenser status: SAFE or

equal. This status window is displayed in WHITE.

ARM. The dispenser status is displayed in GREEN when

the status is SAFE; it is displayed in YELLOW when the

e. Rocket Launcher Icons. Rocket launcher icons

status is ARM.

are displayed at the appropriate station. The inventory

type and warhead selected is presented within the launch-

4.64 WPN UTILITY (UTIL) PAGE

er icons.

The WPN UTIL page (Pilot) (fig 4-85) is used to enable

f. Rocket Launcher Degraded Icons. When the

weapon systems and provide access to the LOAD page.

rocket system has been detected as degraded, a YEL-

Although many utility functions may be premoded by use

LOW DEGR icon will be displayed around the rocket

of the Data Transfer Cartridge (DTC), this page provides

launcher icon.

access to utility functions while in flight. The CPG’s WPN

UTIL page (fig 4-85) provides the same functions. Sight

g. Rocket Launcher Fail Icons. When the rocket

subsystem control descriptions are provided in Section I.

system has been detected as failed, the station will be un-

available and a YELLOW FAIL icon will be displayed

around the rocket launcher icon.

4.63.8 ARM/SAFE Status Window. The ARM/SAFE

status window displayed in the upper area of the WPN

page provides the current aircraft status: SAFE or ARM. It

is displayed in GREEN when the status is SAFE; it is dis-

played in YELLOW when the status is ARM. Cross-hatch

symbol coding is added to the status window when a

weapon is actioned (fig 4-84). ARM/SAFE status is com-

mon to both crew stations.

WEAPON NOT

ACTIONED

(COMMON)

WEAPON

ACTIONED

(INDEPENDENT)

LBA2584

LBA1978

Figure 4-85. WPN UTIL Page (Pilot)

Figure 4-84. ARM/SAFE Status Window

• T6

WPN UTIL button

• R2

LNCHR ARM button

4.63.9 Weapon Actioned Format. When a weapon is

• R5

GROUND STOW button

actioned for firing, the respective weapon controls will be

• B2

GUN On/Off button

available as previously discussed, and all icons

associated with the actioned weapon will become inverse

• B3

MSL On/Off button

video. Weapon system buttons (GUN, RKT, MSL) are not

• B5

RKT On/Off button

available when a weapon has been actioned. WAS status

is independent in each crewstation.

• B6

LOAD button

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

4-90

TM 1-1520-251-10

4.64.7 Casualty Status Window. The casualty status

window is displayed in the upper area of the format to pro-

vide the casualty indication status and the opposing

weapon type/identification code for the most recent en-

gagement event when operating in the TESS mode. This

status window is displayed only when a casualty status is

active (figure 4-95). The casualty “INDICATION” status

shall be one of three messages:

• “NEAR MISS”

• “HIT”

• “KILL”

The opposing “WPN IDCODE” shall be one of 37 two - dig-

it codes in a range from 00 to 36. The aircrew must refer to

the appropriate technical manual for the description of

these codes.

4.65 WEAPONS LOAD PAGE

The weapons LOAD page (fig 4-87) is used to access the

GUN ROUNDS and RKT INV zone buttons to manually

LBA0432

override the data loaded at the LMP or the DTC. The

weapons LOAD page provides the following button selec-

tions:

Figure

4-86.

WPN UTIL Page (CPG)

4.64.1 LNCHR ARM Button. The LNCHR ARM button

is used to arm the Hellfire missile launchers. Selecting this

button will command the Remote Launcher Safe/Arm

switch on all Hellfire missile launchers to the ARM posi-

tion.

4.64.2

GROUND STOW Button. The GROUND

STOW button is used to stow the wing pylons to achieve

optimum ground clearance.

4.64.3 GUN Button. The GUN button is used to en-

able/disable the gun system.

4.64.4 MSL Button. The MSL button is used to to en-

LBA1979

able/disable the missile system.

Figure 4-87. LOAD Page

• R1

GUN ROUNDS button

4.64.5 RKT Button. The RKT button is used to enable/

• R2 - R6 RKT INV ZONE buttons

disable the aerial rocket system.

4.65.1

GUN ROUNDS Button. The GUN ROUNDS

button is used to manually enter the number of rounds

4.64.6 LOAD Button. The LOAD button is used to ac-

loaded. This entry overrides the value entered at the LMP.

cess the controls required to manually override the data

The range value entry will be from 0 to 1200 rounds in 1

loaded at the maintenance load panel.

round increments.

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

4-91

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4.66 MISSILE CHANNEL (CHAN) PAGE

4.66.2 CHAN Code Buttons. The missile CHAN Code

buttons are used to select the code for the current missile

The missile CHAN page (fig

4-90) is used to select the

channel as indicated by the selected CHANNEL option

laser codes to be loaded into the four missile channels.

button. A missile CHAN code button will be displayed with

a barrier when that code is not available.

4.66.3

Code Range and Keyword Status Win-

dow.

The information displayed in this status window is

described in paragraph 4.9.5.

4.67 AREA WEAPON SYSTEM (AWS) DESCRIPTION

The AWS consists of the M230E1 30mm Automatic Gun,

Gun Control Box, Gun Turret, Turret Control Box, and am-

munition handling system.

4.67.1 M230E1 30mm Automatic Gun. The M230E1

is an externally powered, chain driven weapon mounted in

a hydraulically driven turret which is mounted on the un-

derside of the helicopter forward fuselage. Gun major

components are: receiver assembly, index drive assem-

bly, bolt carrier assembly, forward track assembly, recoil

mechanisms, drive motor, flash suppressor, and barrel. It

incorporates positive cook-off safety (open bolt) and

double ram prevention. The rate of fire is 625 ±25 rounds

per minute. The gun turret is capable of azimuth move-

ment of 86° left or right of the helicopter centerline, +11°

LBA1980

elevation (+9° elevation within ±10° of centerline), and

- 60° depression.

Figure

4-90.

CHAN Page

4.67.2 Ammunition Handling System. The ammuni-

tion handling system receives and stores 30mm linkless

The CHAN page provides the following button selections:

ammunition and delivers the rounds through fixed and

flexible feed chutes to the 30mm gun on demand. The am-

• T2 - T5

CHANNEL buttons

munition handling systems maximum capacity is 1200

rounds. The amount of rounds will be reduced with the

• L1 - L6

CHAN Code buttons

installation of the IAFS. The quantity will be approximately

• R1 - R6 CHAN Code buttons

94 rounds, with the 130 gal fuel cell, if utilizing the upload-

• B2 - B5

CHAN Code buttons

er/downloader or approximately 58 rounds using the side-

loader. The 100 gal fuel cell includes a 242 round am-

4.66.1

CHANNEL Buttons. The missile CHANNEL

munition storage magazine, making the maximum

buttons are used to code SAL missile channels 1 through

capacity about 300 rounds. The system can accommo-

4 using CHANNEL option buttons. Selecting the desired

date a variety of 30mm ammunition including high explo-

channel determines to which missile channel subsequent

sive dual purpose (HEDP M789), ADEN/DEFA, HEI

CHAN Code selections apply.

(M799), and TP (M788).

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

Change 2

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TM 1-1520-251-10

4.68 AWS SYSTEM OPERATION

The S/MC provides the discrete interface link between the

Turret Control Box, Carrier Drive, LH and RH tensioners,

GSE Loader, Loader Assembly, and Weapons Processor.

CAUTION

The AWS will continue to follow IHADSS

LIGHTING

LOS when operating in NVS FIXED mode.

FUNCTION

ROUNDS

COUNT

DISPLAY

NOTE

In the event of power loss, the gun is spring

driven to +11° elevation to prevent dig-in

during landing.

LOADER

The AWS can be directed by either crewmember in the

SWITCHING

ENTERING

NORM mode when the active sight is HMD, TADS or FCR

ROUNDS

COUNT

. The system can also be employed in the FIXED (+6° in

MODE

elevation) mode which aligns the gun forward in azimuth to

SWITCHING

OPERATE

the helicopter centerline. The software limit is 4200 meters.

SWITCHING

LBA2588

Figure 4-91. Sideloader/Magazine Controller

WARNING

The S/MC operational interface can be grouped into five

Failure to adhere to the published gun

functional areas:

duty cycle may result in a catastrophic

failure, loss of aircraft, injury or death.

a. Lighting functions. When powered, the S/MC

sets display lighting to the maximum night time intensity.

Successive button pushes of the NIGHT button will se-

The gun duty cycle is as follows:

quentially cycle the intensity to the minimum night time in-

• Six 50 round bursts with 5 seconds between bursts

tensity in five steps, and then back to the maximum inten-

followed by a 10 minute cooling period.

sity on the sixth button press. A momentary press of the

DAY/TEST button provides maximum display lighting in-

• For BURST LIMITER settings other than 50, the

tensity for readability under direct sun light. Pressing the

cycle can be generalized as no more than 300

NIGHT button after selecting DAY lighting will return the

rounds fired within 60 seconds before allowing the

display intensity to the maximum night time intensity.

gun to cool for 10 minutes, after which the cycle

Pressing and holding the DAY/TEST button for longer

may be repeated.

than 3 seconds will initiate a lamp test routine which illumi-

nates all display segments, legend lamps, and indicators

to confirm that all lighting circuits are functional. When the

4.68.1 Sideloader/Magazine Controller (S/MC). The

squat switch status indicates that the aircraft is airborne,

S/MC (fig 4-91) is an LRU with control features provided

the S/MC disables the display indicators to extend service

for direct operator interface during loading operations.

life.

The S/MC is mounted in the RH FWD Avionics Bay adja-

cent to the Loader Assembly for one-man operation.

b. Rounds Count Management. Four momentary

push button switches are used for manually editing the

The S/MC performs three distinct ammunition handling

displayed numeric value of rounds count which is stored in

system functions:

the S/MC non-volatile memory. This data is not down-

loaded to the aircraft and must be loaded via the LMP or

• counting of 30mm rounds

LOAD page.

• control of the Carrier Drive Assembly

c. Loader Switching. This function is provided by

• control the Loader Assembly for uploading and

two momentary push buttons labeled ENGAGE and DIS-

downloading 30mm ammunition

ENGAGE. These push buttons provide for the automatic

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

4-94

HELICOPTER, ATTACK, AH-64D LONGBOW APACHE. TECHNICAL MANUAL (2002) - page 11