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UNITED STATES ARMY AVIATION CENTER OF EXCELLENCE

FORT RUCKER, ALABAMA

14 June 2011

STUDENT HANDOUT

TITLE: AH-64D LONGBOW HELLFIRE MODULAR MISSILE SYSTEM

FILE NUMBER: 011-0923-9

Proponent For This Student Handout Is:

COMMANDER, 110TH

AVIATION BRIGADE

ATTN: ATZQ-ATB-AD

Fort Rucker, Alabama 36362-5000

FOREIGN DISCLOSURE STATEMENT: (FD6) This product/publication has been reviewed by the product developers in coordination with the USAACE Foreign Disclosure Authority. This product is releasable to students from foreign countries who have purchased the AH-64D model, but the IETM is not releasable.

D-4

TERMINAL LEARNING OBJECTIVE:

NOTE: Inform the students of the following Terminal Learning Objective requirements.

At the completion of this lesson, you (the student) will:

ACTION: Identify missiles, launcher components, operations, icons, symbology, controls,

displays, and safety features of the AH-64D Longbow Hellfire Modular Missile

System (LBHMMS).

CONDITIONS: In a classroom environment, given an AH-64D Operator's Manual, Aircrew

Training Manual (TC 1-251), a computer with IMI software lesson, and a student

handout.

STANDARD: Identify the missiles, launcher components, operations, icons, symbology,

controls, displays, and safety features of the AH-64D Longbow Hellfire Modular

Missile System (LBHMMS) and receive a “Go” by answering 15 of 20 questions

on scoreable unit 3 of criterion referenced test 011-1081 IAW the SEP.

D-5

A. ENABLING LEARNING OBJECTIVE 1

ACTION: Identify the Hellfire SAL and RF missiles.

CONDITIONS: Given a written test without the use of student notes or references.

STANDARD: In accordance with TM 1-1520-251-10-2, TC 1-251, and FM 3-04.140 (FM 1-

140).

1. Learning Step/Activity 1

Identify the Hellfire SAL and RF Missiles.

Figure 1. Hellfire Air-to-Ground Missile.

(a) AGM-114 series

1) There are Semi-Active Laser (SAL 1 and SAL 2), and Radio Frequency (RF) models of the

Hellfire tactical Air-to-Ground-Missile (AGM) currently in the Army inventory.

2) The missiles are 7 inch diameter, anti-armor munitions with a wingspan of 12.9 inches and,

depending on the missile model, weigh 99.2 to 107 lbs with an overall length of 64 to 71

inches.

3) The Hellfire missile is an extremely reliable missile with a Probability of Kill (PK) above 90%.

4) With the new programmable laser codes, dual warheads, and virtually smokeless motors, the

Hellfire is among the best AGMs in the world.

5) The guidance section is the main difference between the SAL and RF missiles.

D-6

Figure 2. Hellfire Missiles.

(b) Missile types

1) AGM-114A. The A-model is the original Hellfire missile, which is no longer purchased by the

Army.

2) AGM-114C. This missile has an Improved Low Visibility (ILV) capability that allows it to fly

lower trajectories than the AGM-114A and contains a minimum-smoke rocket motor (less

smoke than the AGM-114A). The missile is 64 inches long and weighs 100 pounds.

3) AGM-114B. This missile is the same as the AGM-114C except it contains a Safe and Arm

Device (SAD), which provides electrical and mechanical blockage in the rocket motor firing

train, making it approved for U.S. Navy shipboard use.

4) AGM-114F. This missile is the same as the AGM-114C but features dual warheads for

improved performance against reactive armor. The missile is 71 inches long and weighs

107 pounds.

5) AGM-114K. One of the newest missiles in the Hellfire family, this missile features dual

warheads, electro-optical countermeasure immunity, and a programmable guidance section

for trajectory shaping/seeker logic changes. This missile is referred to as the Hellfire II

missile. The missile is 64 inches long and weighs 100 pounds.

6) AGM-114L. The RF Hellfire missile uses an active RF signal to detect and track targets. It

emits RF energy and homes-in on the reflected RF energy. It is an active (emitting) missile

that is inertially guided and radar assisted. The missile is 69 inches long and weighs 108

pounds.

D-7

Figure 3. Hellfire Dummy and SAL Training Missile.

a) The Hellfire missile is also available as a dummy or training missile.

1 M34 dummy missile

NOTE: The M34 missile will not show up on the aircraft inventory.

a The M34 dummy missile has the same external shape and length as the

AGM-114C.

b Internally, it contains no explosives or electronics but has ballast to simulate the

weight and center of gravity of the AGM-114C.

c It is used to train armament personnel in uploading and downloading, and also to

simulate a prescribed load of missiles for a specific training flight.

2 M36 SAL training missile

a The M36 SAL training missile is used for captive flight training and cannot be

launched.

b It has an operational laser seeker that can search for and lock on laser energy.

c The M36 contains no explosives but should be treated as a live tactical missile.

NOTE: If an M36 training missile is on a launcher rail, live missiles will be coded N/A (Not Available) and

cannot be launched.

D-8

Figure 4. Hellfire Missile Common Components.

b) Hellfire missile common components. The AGM-114 missile contains a shaped charge

warhead that is capable of defeating any known-fielded tank. The maximum velocity of

the missile is 475 m/sec (Mach 1.4). The missile is comprised of four major assemblies;

the guidance section, the warhead group, the control section, and the propulsion section.

1 Guidance Section. The control interface group includes the missile autopilot,

pneumatic accumulator, battery, and displacement gyros used to compute steering

command data. The laser seeker converts reflected laser energy from the target into

electronic guidance signals.

2 Warhead group

a The warhead group houses the warhead and fuse.

b The fuze, located behind the warhead, contains the ARM/SAFE device that arms

the missile when its launch acceleration exceeds 10 G between 150 and

300 meters in front of the aircraft.

c The AGM-114C possesses a single shape charge to provide the explosive and

piercing force necessary to destroy the target.

d The AGM-114F, 114K, and 114L use the same shape charge warhead but

contain an additional small warhead forward of the main warhead to provide

enhanced performance against reactive armor.

3 Control section. The control section, located just aft of the rocket motor, receives

tracking commands from the guidance section and provides stabilization with a

pneumatic actuation system to convert steering commands into mechanical fin

movement.

D-9

4 Propulsion section

a The propulsion section provides the thrust to launch and accelerate the missile.

b It consists of a single-stage, single-thrust, star-shaped, minimum-smoke, solid-

propellant rocket motor; a motor squib; and cruciform wings.

c When thrust exceeds 500 to 600 pounds the missile leaves the rail.

d Thrust duration is approximately 2 to 3 seconds.

Figure 5. Environmental Protective Cover.

c) Environmental Protective Cover (EPC)

1 The EPC is a frangible glass dome that provides protection for the missile seeker

from environmental elements that can degrade seeker performance. The EPC is

removed by a command signal from the Weapons Processor (WP) prior to missile

launch. The RF and SAL missile EPCs are not interchangeable.

2 When an EPC is installed on the RF missile, the cover must be removed prior to

radar transmission.

3 Pressing the DEICE button will send a squib signal to remove the frangible dome on

the next missile in the launch sequence.

4 The DEICE button is only presented when the missile type is SAL, the aircraft is

armed, the missile system is actioned, and EPCs are installed.

5 Both missile types have very similar EPCs, with the connectors to the launcher rails

being slightly different.

D-10

CHECK ON LEARNING

1. What is the major difference between the SAL and RF missiles?

ANSWER: ______________________________________________________________________

______________________________________________________________________

2. How will a live missile be coded if there is a M36 training missile loaded on a launcher rail?

ANSWER: ______________________________________________________________________

______________________________________________________________________

3. The fuze contains the ARM/SAFE device that arms the missile when its launch acceleration

exceeds ________ g’s between _______ to ______ meters in front of the aircraft.

ANSWER: ______________________________________________________________________

______________________________________________________________________

4. When thrust exceeds _____ to _____ pounds the missile leaves the rail?

ANSWER: ______________________________________________________________________

______________________________________________________________________

5. The thrust duration is approximately two to three seconds and the maximum velocity of the

missile is _____________.

ANSWER: ______________________________________________________________________

______________________________________________________________________

D-11

B. ENABLING LEARNING OBJECTIVE 2

ACTION: Identify the components of the M299 missile launcher.


STANDARD: In accordance with TM 1-1520-251-10-2, TC 1-251, and FM 3-04.140 (FM 1-140).


Identify the components of the M299 missile launcher.

Figure 6. M299 Missile Launcher.

(a) M299 Hellfire missile launcher

1) The LBHMMS is the primary armament of the AH-64D.

2) All variants of the SAL missile and the RF missile can be employed by the aircraft.

3) The LBHMMS consists of M299 launchers mounted on any of the four wing stations. One

electrical connector on the hardback connects the launcher with the Pylon Interface Unit

(PIU).

4) The PIU interfaces the launcher to the WP.

(b) M299 Launcher components. The launcher consists of a hardback, removable Launcher

Electronics Assembly (LEA), and four or two low-insertion-force rails.

1) The hardback houses the LEA, the 14-inch spacing bomb lugs, and the mounting points for

the four missile rails.

2) The LEA performs the following functions:

a) Processes commands from the aircraft to provide missile launch control.

b) The ARM/SAFE switch provides for manually safing the launcher. The switch is manually

safed and electronically armed via the WPN Utility (UTIL) page LNCHR (launcher) ARM

selection.

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c) A Training Missile Emulator (TME) that can simulate up to four RF missiles on the

launcher for training. Live missiles will be coded NA when operating in the train mode.

CIU provides launch audio for simulated missile engagements.

Figure 7. Pylon Articulation.

(c) Pylon Articulation.

1) Pylon Limits.

a) The Flight mode commands the pylons to a single fixed position (+4°).

b) Flight mode is automatically commanded at takeoff when the squat switch indicates

airborne for more than 5 seconds.

c) In flight, the pylons remain in the Flight Mode until missiles or rockets are actioned.

Pylons are independently articulated through a range from +4.9° to –15°.

d) Upon landing, with squat switch activated, pylons move to Ground Stow position of -5º.

e) GROUND STOW VAB can be selected on the WPN UTIL page.

2) SAL

a) When firing SAL missile the pylons are commanded to 6° above the target.

b) This will allow A/C pitch angles of greater than 10° before the pylon limit inhibit is

invoked, which is a performance inhibit in flight.

3) RF

a) Pylon position is dependent upon range and altitude.

b) Minimum altitude for launch of RF missile is 66 feet (20 meters) before the pylons can be

articulated down in order to prevent missile from striking ground if radar altitude becomes

invalid.

D-13

CHECK ON LEARNING

1. Can the M299 fire all variants of the Hellfire missile?

ANSWER: ______________________________________________________________________

______________________________________________________________________

2. What component contains the Training Missile Emulator (TME) that simulates RF missile

training?

ANSWER: ______________________________________________________________________

______________________________________________________________________

3. What MPD page can you electronically arm the M299 missile launcher?

ANSWER: ______________________________________________________________________

______________________________________________________________________

4. What are the normal pylon articulation limits when the missiles or rockets are actioned?

ANSWER: ______________________________________________________________________

______________________________________________________________________

D-14

C. ENABLING LEARNING OBJECTIVE 3

ACTION: Identify the icons and symbology of the Hellfire SAL and RF missile system.



140).


Identify the icons and symbology of the Hellfire SAL and RF missile system.

Figure 8. Hellfire Launcher Icons.

(c) Hellfire missile launcher icons

1) Hellfire missile launcher rail icons will be displayed to indicate that a launcher is present on

that wing station. The top missile icons represent missiles on the upper rails; the bottom

missile icons represent missiles that are on the lower rails.

2) The launcher rail icons indicate that no missile is at that station or that a dummy missile may

be loaded. Dummy missiles (M34) do not show because there is no umbilical connection

between the launcher and the missile. All of the launcher status icons will display either a

normal or inverse mode, based on weapon system selection or actioned.

3) When a launcher ARM/SAFE switch is in the SAFE position, the white SAFE icon will replace

the launcher rail and missile icons on that launcher. This SAFE icon may also be present

with the ARM/SAFE switch in the ARM position.

4) If a launcher fails, a yellow FAIL icon will replace the launcher rail and/or missile icons on that

launcher.

5) When the launcher is performing BIT, a white BIT launcher icon will be displayed around the

launcher icon. The power lever does not need to be positioned in the off position in order for

Hellfire on Bit to execute.

6) The white launcher load icon is displayed when the loading of key words to the launcher is in

progress.

D-15

Figure 9. Hellfire Missile Icons.

(d) Missile icons. The missile icons are presented in their relative position on the aircraft wings and

the missile status will be displayed within each missile icon.

1) The SAL missiles have a straight seeker line across the nose of the icon.

2) The RF missiles have a “V” seeker line across the nose of the icon.

3) The upper missiles are depicted as forward (on top) of the lower missiles.

4) Missile status and inventory codes are displayed within each missile icon.

5) FAIL is displayed in yellow when the launcher is inoperable.

6) SAFE is displayed when the launcher ARM/SAFE switch is set to SAFE.

7) NA will be displayed for missiles detected as not available.

8) When no missile is loaded on a rail the Empty Launcher Rail Icon will be displayed.

D-16


Identify the icons and symbology of the Hellfire SAL and RF missile system.

Figure 10. WPN Page Missile Format.

(a) WPN page missile selection

1) If the missile, button is selected, the missile icons will become inverse video, and missile

controls will be displayed.

2) The missile legend becomes boxed.

3) Selecting the missile button again will deselect the missiles.

4) If the missile system is actioned, the missile icons will become inverse video, and missile

controls will be displayed.

5) The missile legend becomes boxed and nonselectable (barriered), and the other weapons

selections (GUN and RKT) will blank.

6) The WAS must be used to deselect the missile system.

D-17

Figure 11. Missile Constraint Boxes.

(b) Missile constraints

1) Constraints boxes

a) The missile constraint boxes are dynamic boxes displayed in two sizes. Constraint

symbology will be displayed only when the missile system is actioned.

b) The boxes apply to both SAL and RF missile launches.

c) The missile constraints boxes are displayed in the same manner for SAL or RF missiles,

with the inhibits covered under LBHMMS safety features.

d) The LOBL constraints box (20°) will be displayed when the missile system is in a LOBL

missile launch mode.

1 For SAL missile engagements, the Laser Range Finder Designator (LRFD) must be

designating in order for it to be considered a LOBL missile shot.

2 For RF missile engagements, the RF missiles onboard radar must be tracking the

target.

e) The LOAL constraints box (7.5°) will be displayed when the missile system is in a LOAL

missile launch mode.

1 For SAL missile engagements in the LO or HI trajectory, constraints are calculated

based on the acquisition source chosen from the COORD page. This does not have

to be the active acquisition source, but it must be selected as the target source.

2 For RF missile engagements, the RF missile’s onboard radar is not tracking the

target.

NOTE: If the RF missile is tracking and the target range is ≥1 km, the allowable angle is 20º. IF the RF

missile is tracking and the target range is <1km, the allowable angle is 5º.

D-18

Figure 12. Missile Constraints Symbology.

2) Missile constraints symbology

a) In the horizontal plane, the symbology presentation represents a total of 40 (±20 about

the center, referenced to the sight reticle).

b) The LOBL constraint box is approximately three times larger than the LOAL box. The

box position provides steering cues to help align the aircraft with the target. This allows

the aircraft to meet the target-offset limits for the type of engagement.

3) LOBL engagements

a) The LOBL out-of-constraints symbol is a large dashed box. The missile should not be

launched when the constraint box is dashed.

b) The LOBL in-constraints symbol is a large solid box.

c) The horizontal position represents a ±20 constraints from the aircraft ADL.

d) The box is directional; turn toward the symbol to align the aircraft with the target line.

e) The box is referenced to the missile seeker LOS with respect to the aircraft ADL.

f) The constraints box is driven by the missile seeker.

g) When the target is within ±20 of the aircraft ADL, and a missile seeker on the designated

PRI CHAN is locked on and tracking reflected laser energy, the symbol will change to a

solid box. This indicates in constraints and the missile may be launched.

D-19

h) At very short LOBL ranges, it is important to adhere to the tighter azimuth alignment

requirements. This requirement is not reflected in the LOBL constraint box indication. At

these shorter ranges, the pilot should turn the aircraft toward the box, reducing the launch

offset angle to less than 5.

i) During autonomous LOBL operation, an additional requirement must be met to be within

constraints: the tracking missile seeker must be within ±2 of the TADS sensor line of

sight to the target to obtain a solid LOBL box. If the TADS LOS and seeker LOS are not

within 2º, the message BACKSCATTER will be displayed in the WPNS INHIBIT section

of HAD and the missile cannot be launched. To correct the condition turn the laser off

and use LOAL DIR with at least 2 seconds delayed designation from missile launch.

4) LOAL engagements

a) The LOAL out-of-constraints symbol is a small dashed box. The missile should not be

launched when the constraint box is dashed.

b) The horizontal position indicates ±7.5 constraints from the aircraft ADL, the box will be

dashed when it is positioned greater than approximately one-third of the distance to

either the left or right display edge.

c) The box is directional. Turn toward the symbol to align the aircraft ADL with the target.

d) For LOAL DIR autonomous or remote, the constraints box is driven by the TADS LOS.

For LOAL LO and LOAL HI, the constraints box is referenced to the target coordinates

stored in the WP, as selected on the target/Navigation (NAV) in the Acquisition (AQC)

selection, with respect to the aircraft's present position and heading.

e) The LOAL in-constraints symbol is a small solid box with the same characteristics as the

LOAL out-of-constraints symbol, except that the box is solid.

f) When the target is within ±7.5 of the aircraft ADL, the box will be solid, indicating in

constraints.

g) If visibility is less than 5 km and/or laser delays near the recommended maximum are

used, then a +5 offset is recommended.

D-20

Figure 13. Weapon Action Switches (WAS)

5) Weapon Action Switch (WAS)

a) Purpose. The WAS are used to select (action) a weapon system for operation from a

specific crewstation.

b) Location. WAS is located on both cyclics and on the TEDAC Left Handgrip (LHG).

c) Description

1 The WAS is a five-position spring-loaded switch with the missile position designated

by a M on the cyclic WAS and MSL on the TEDAC LHG WAS.

2 The missile is selected, from any crewstation, at the 3 o’clock position of the WAS.

d) Function. Placing the WAS momentarily to the desired position actions the weapon.

Placing the WAS to the selected weapon again will deselect the weapon system.

Actioning any other weapon position will deselect the current weapon and action the

newly selected weapon.

1 The WAS used in the CPG station must be associated with the intended trigger.

a If the weapon is actioned on the cyclic, the cyclic trigger must be used.

b If the weapon is actioned on the TEDAC LHG, the trigger on the TEDAC LHG

must be used.

2 The last crewmember to action missiles will have control.

D-21

Figure 14. Weapons Triggers

6) Weapons triggers

a) Purpose. The weapons triggers are used to fire the selected weapon system.

b) Location. The weapons triggers are located on both cyclics and on the TEDAC LHG.

c) Description. The weapons triggers are a three-position, two detent switch that are

protected from accidental weapons firing by a cover which must be raised to gain access

to the trigger.

d) Function. The weapons triggers are active in a crewstation only when the ARM/SAFE

switch is armed and a weapon has been actioned by that crewmember. Each trigger has

two detents.

1 Pressing the trigger to the first detent with no weapon inhibits, the missile will be

launched 1 second after trigger pull.

2 Pressing the trigger to the second detent will override weapon performance inhibits

and fire the missile.

NOTE: Safety inhibits can never be overridden.

D-22

CHECK ON LEARNING

1. A SAL missile icon that has not been coded will display ______.

ANSWER: ______________________________________________________________________

______________________________________________________________________

2. RF missiles have a _____ instead of a straight line at the seeker.

ANSWER: ______________________________________________________________________

______________________________________________________________________

3. An RF missile that has an overtemp condition will display _______.

ANSWER: ______________________________________________________________________

______________________________________________________________________

4. A hangfire will display ________ in the missile icon.

ANSWER: ______________________________________________________________________

______________________________________________________________________

5. If a missile has failed, the icon will display _________.

ANSWER: ______________________________________________________________________

______________________________________________________________________

D-23

D. ENABLING LEARNING OBJECTIVE 4

ACTION: Identify the Hellfire SAL missile controls and displays.


STANDARD: In accordance with TM 1-1520-251-10-2 and TC 1-251.


Identify the Hellfire SAL missile controls and displays.

Figure 15. Missile PRI and ALT CHAN CODE.

(a) SAL missile controls

1) PRI or ALT CHAN buttons

a) The PRI or ALT CHAN buttons are used to designate the PRI or ALT CHAN for coding

SAL missiles.

b) The ALT button is not selectable when there is no PRI CHAN selected.

c) Selecting the PRI or ALT button provides the CHAN options displayed in the CHANNELS

status window.

d) When PRI and ALT CHANs are selected, the quantity defaults to three for both CHAN if

sufficient missiles are available.

e) In the NORM mode, the PRI CHAN is allocated the maximum number of missiles before

any are allocated to the ALT CHAN. In the MAN mode only the selected missile is

coded. Only missiles on the PRI CHAN can be launched.

f) In RIPL mode, the quantity is evenly divided between the two channels, with the PRI

CHAN assigned the extra missile in the case of an odd number of missiles available.

g) As missiles are launched in the RIPL mode, the PRI and ALT labels alternate or switch

positions within the PRI and ALT buttons to indicate the automatic PRI and ALT

selections on the WPN page.

h) PRI and ALT CHAN selections are common to both crewstations.

D-24

Figure 16. SAL Missile Select.

2) SAL SEL

a) The SAL SEL button is used to select the type of SAL missile as follows:

1 AUTO allows for automatic selection of a SAL 1 or SAL 2 missile. If the code type is

PRF the missile will select SAL 2 first, if available, over SAL 1 missiles. If the code

type is PIM the system will select only SAL 2.

2 SAL 1 allows for firing of only SAL 1 missiles. SAL 1 missiles are only capable of

PRF laser code operation.

3 SAL 2 allows for firing of only SAL 2 missiles. SAL 2 missiles are capable of PRF and

PIM laser code operations.

3) TYPE button

a) The TYPE button selection allows for selecting SAL or RF–type missiles.

b) If the selected sight is FCR, the missile TYPE will be barriered, and the mode will default

automatically to RF.

c) TYPE selections are independent in each crewstation.

D-25

Figure 17. SAL Missile Mode.

4) MODE button

a) The MODE button is used to select the operational mode of the missile system.

b) Missile MODE selections are common in each crewstation.

c) Missile MODE selections include:

1 The NORM mode will maintain three PRI CHAN missiles ready until the SAL missiles

are depleted.

2 The RIPL mode automatically will alternate between the PRI CHAN and the ALT

CHAN for missile engagements. The RIPL mode will not be selectable when no

missile channel is selected as alternate.

3 The MAN mode allows the crewmember to use the MAN Advance (ADV) switch to

select and ready a single missile to the PRI CHAN for firing.

D-26

Figure 18. SAL Missile Trajectory.

5) Trajectory (TRAJ) button

a) The TRAJ button is used to select the desired missile launch LOAL trajectory.

b) DIR will select the direct LOAL trajectory.

c) LO will select the low LOAL trajectory.

d) HI will select the high LOAL trajectory.

e) If the missile is locked-on before launch, it will default to LOBL and fly the LOBL

trajectory.

f) TRAJ selections are independent in each crewstation.

D-27

Figure 19. Range Logic.

6) In either crewstation, the crew will be unable to enter a manual range (from NAV range) when

employing SAL missiles with missile trajectory set to LO or HI. The missile constraints box for

LOAL LO and LOAL HI engagements are driven from target data located at (B5) except when

TRN is the ACQ selection. When TRN is the ACQ selection the missile constraints box is

driven by the TRN point.

Figure 20. Deice Controls.

7) Deice controls

a) The missile DEICE button is used to manually remove the EPC’s protecting the SAL

missile seekers in preparation for missile launch.

D-28

b) The DEICE button is only presented when the missile type is SAL, the aircraft is armed,

the missile system is actioned, and EPCs are installed. The missile to have the EPC

removed when the DEICE button is selected are as follows:

1 MAN mode. The selected missile EPC will be removed.

2 NORM mode. The next missile in the firing sequence on the PRI CHAN will have its

EPC removed.

3 RIPL mode. The next missile in the firing sequence on the PRI and ALT CHANs will

have their EPCs removed.

NOTE: A signal command to remove the missile seeker deice cover is part of any missile launch

sequence regardless of the above deice functions.

8) Missile Counter-Counter Measure (MSL CCM) button

a) The MSL CCM button enables the CCM routine within the laser missile.

b) This selection narrows the Pulse Repetition Frequency (PRF) number of Pulses Per

Second (PPS) tracking capability of the missile to the precise PRF of the selected laser

code.

Figure 21. MSL CHAN Set Page.

9) Laser codes

a) Laser codes available for SAL missile coding are presented in the CHANNELS status

window located below the aircraft icon.

b) The SAL missile CHANNELS status window displays four missile channels for rapid

selection.

c) The codes selected for the PRI and ALT CHANs are identified with a box around the PRI

and ALT CHANs.

d) The CHAN page button allows for selection of 16 different missile channel codes.

e) Use one of the four CHANNEL buttons to select the code CHANNEL to be changed.

When selected, the CHANNEL number will appear in the upper center of the display.

D-29

f) Press the desired code button to assign that code to the selected channel.

g) When all selections are made, pressing the CHAN button will return the display to the

WPN page.

h) The new codes will be displayed in the missile CHANNELS status window.

Figure 22. CODE Page.

10) CODE page

a) Selecting the SET button on the CODE page will alternate between Laser Spot Tracker

(LST) and LRFD.

b) With the desired system (LST or LRF/D) selected, selecting one of the code (A through

R, excluding I and O) buttons will assign that code.

c) When the desired codes are selected, pressing the CODE button will return the display to

the WPN page.

d) The CODE RANGE, and keyword status window is located in the center of the CODE,

FREQ, and CHAN pages.

e) CODE RANGES indicates the laser code ranges that are supported by the laser

keywords resident on the Data Transfer Card (DTC).

1 It is capable of supporting the tri-service PRF laser codes and USAF, Hellfire, and

Copperhead Pulse Interval Modulation (PIM) laser codes.

2 In order for the LRFD and Hellfire subsystem to use a PIM laser code, the

appropriate keyword for the specific code range is required:

a 1111-1788 Tri-Service, PRF

b 2111-2888 USAF, PIM

c 4111-4288 Hellfire-A, PIM

d 4311-4488 Hellfire-B, PIM

e 4511-4688 Hellfire-C, PIM

D-30

f 4711-4888 Hellfire-D, PIM

g 5000 through 8888 reserved for Copperhead and SAL2 missiles.

f) The STATUS area indicates the code range status for the LRFD and Hellfire subsystem.

1 FAIL: indicates the DTC laser keyword for this code range has a checksum error.

2 N/A: indicates that the LRFD and the Hellfire subsystem are not capable of using this

code range.

3 MSL ONLY: indicates that only the missile subsystem is capable of using this code

range.

4 LRFD ONLY: indicates that only the LRFD is capable of using this code range.

Figure 23. CODE FREQ Page.

11) CODE FREQ page

a) The frequency of the laser codes may be modified through the CODE FREQ page.

b) Selecting the FREQ button on the CODE page will display the CODE FREQ page.

c) Selecting a laser code button will enable the Keyboard Unit (KU) to accept a new

frequency to be assigned to the selected laser code.

d) When the frequencies have been set as desired, pressing the FREQ button will return the

display to the CODE page.

e) Frequencies of the laser codes may be reviewed by selecting the CODE button and

edited by selecting the FREQ button.

D-31

Figure 24. Laser Keyword Fail.

12) PIM FAULT Advisory

a) A PIM FAULT Advisory will be displayed on the UFD and MPD if the WP has determined

that Laser code keywords are resident on the DTC, but no PIM LEU is installed or that

anomalies exist in at least one of the following:

1 LEU upload errors.

2 Individual HF launcher errors.

3 LST upload errors.

b) This message will be removed from the EUFD when the CODE page is selected.

D-32

CHECK ON LEARNING

1. The ALT CHAN button is only selectable after a _____ CHAN has been entered.

ANSWER: ______________________________________________________________________

______________________________________________________________________

2. The quantity defaults to _______ for both channels if sufficient missiles are available.

ANSWER: ______________________________________________________________________

______________________________________________________________________

3. What is the sequence to edit a laser code?

ANSWER: ______________________________________________________________________

______________________________________________________________________

4. What is the tri-service pulse repetition frequency (PRF) code range?

ANSWER: ______________________________________________________________________

D-33

E. ENABLING LEARNING OBJECTIVE 5

ACTION: Identify the Hellfire SAL missile operation.


STANDARD: In accordance with TM 1-1520-251-10-2, TC 1-251, and FM 3-04.140(FM 1-140).


Identify the Hellfire SAL missile operation.

Figure 25. SAL Missile Laser Seeker.

(b) SAL Hellfire missile laser seeker functions and operational characteristics

1) The SAL Hellfire missile detects reflected laser energy that is of the same code as set into

the seeker.

2) It is a passive (non-emitting) missile.

3) The SAL seeker produces steering signals to the missile guidance section when tracking

laser energy (target).

4) The signals are acted on by the control section when the missile is in flight, which results in

precise homing of the missile body to the laser spot.

NOTE: The laser code determines the laser pulse FREQ. Prior to launch, the missile is programmed to

receive a specific code. If the designator’s code and the code programmed into the missile are

not the same, the missile will not acquire or track the target.

5) The seeker detects properly coded laser energy and provides Line-Of-Sight (LOS)

information to the WP while on the rail and to the missile autopilot after launch.

6) The seeker detector is gimbal-mounted and gyro-stabilized with a mass composed of the

mirror, balance wheel, and a permanent magnet rotor spinning at 4200 rpm.

7) The detector, which does not rotate, has a ±30 gimbal limit from the missile centerline.

D-34

(c) Operational seeker modes

1) Scan

a) The seeker is moved in a predetermined scan pattern (box scan) to help it acquire and

lock-on to a laser spot.

b) This mode is employed prior to launch for Lock-On Before Launch (LOBL) remote mode

and after launch for Lock-On After Launch (LOAL) mode.

2) Stare

a) The seeker is commanded to look straight ahead along the missile body axis.

b) All missiles, with the exception of the AGM-114K, can acquire and lock on if laser energy

is detected.

c) This mode is employed prior to launch for LOAL Direct (DIR), LO, or HI remote modes.

3) Slave

a) The seeker is commanded to follow external LOS commands. It can acquire and lock on

if laser energy is detected.

b) This mode is employed prior to launch for all autonomous modes.

4) Track

a) The seeker is commanded by the seeker electronics assembly to maintain the reflected

laser energy centered on the detector/preamplifier assembly so that the optics assembly

is pointed at the target.

NOTE: How the missile reacts to loss of designation (loss of pulse correlation) depends on whether the

missile is captive or launched and the mode of missile after launch.

5) Captive missile

a) For all missiles, the seeker will revert to its selected pre-designation mode if loss of pulse

correlation occurs before launch.

6) After launch.

a) For all missiles, the seeker gimbal becomes inertially stable upon loss of pulse

correlation. The seeker gimbal will continue to point to the same pitch and yaw angle

relative to horizontal.

D-35

Figure 26. Autonomous/Remote Designation.

(d) LBHMMS launch modes

1) The LBHMMS may be operated in several different modes or a combination of modes based

on the tactical situation and the battlefield environment.

2) When selecting a launch mode for a SAL Hellfire missile engagement, cloud ceiling,

battlefield obscurants, range to target, designation delay times, and terrain features must be

considered. The combination of these factors will influence the mode that the crew chooses

for the SAL missile launch mode.

3) When the crew is engaging a target using SAL missiles, the following modes must be

decided upon before the missile is launched.

a) LOBL. LOBL modes are used when the SAL missile seeker has already locked onto

return laser energy from the target before launch. This return energy can be from the

onboard Target Acquisition and Designation Sight (TADS) laser or a remote laser

designator.

b) LOAL. LOAL modes are designed to allow the missile to be launched without a seeker

being locked-on to return laser energy.

c) Autonomous engagement. Autonomous designation occurs when the launching aircraft

designates its own target. This method of designation may be used in either the LOBL or

LOAL modes. For autonomous engagements the sight must be TADS, PRI channel must

match the LRFD, and the Laser must be on.

d) Remote engagement

1 Remote engagement occurs when the target is designated by an aircraft, other than

the launching aircraft, or by a remote, ground-based designator.

2 This designation technique can be used in either the LOBL or LOAL modes.

3 Remote designation allows the launching aircraft to fire from a masked position with a

longer standoff range than is possible with autonomous designation.

CAUTION

During remote designation, the remote designator should not be within a ±30° fan from the

gun to target line.

D-36

(e) Target illumination requirements. The Hellfire missile has a high probability of hitting and killing a

target when, the following target designation conditions are met:

1) Illuminating the target by a laser designator that is set to the same code as the missile with

sufficient beam intensity that the seeker can detect the reflected energy.

2) Only the laser spot should illuminate the target.

3) When the missile is in its last few seconds of flight before impact, it is critical that the entire

laser spot be placed on the target. Even a momentary placement of laser energy on adjacent

terrain can prevent the missile from hitting the target if the beam misplacement were to occur

during the final few seconds of flight.

4) Once the seeker is tracking, the designator should not be turned off before all in-flight

missiles have impacted. The seeker will not reinitiate box scan once the laser energy is lost.

Figure 27. Negative Illuminating Factors.

(f) Negative factors when illuminating targets

1) Underspill

a) Underspill is caused by placing the laser spot too low on the target so that the spot, or a

portion of the spot, spills onto the foreground.

b) This can cause foreground false target, becoming more severe at long designation

ranges.

2) Spot jitter

a) The result of motion of the designator or of the beam developed by the designator around

the intended aim point.

b) This can give the laser spot a bouncing movement on the target, which increases with

designator distance from the target.

D-37

3) Attenuation

a) A portion of the laser beam energy that is "scattered" by obscurants along the laser-to-

target LOS and the missile-to-target LOS resulting in reduced laser energy to the seeker.

b) If attenuation is severe, the seeker will not detect the laser energy from the target.

4) Beam divergence

a) The farther the laser designator is from the target, the wider the spot will be on the target.

b) The amount of beam divergence will vary between types of designators.

Figure 28. Effects of Overspill and Underspill.

5) Overspill

a) Overspill is caused by placing the laser spot too high on the target so that beam

divergence and jitter cause the spot or a portion of the spot to spill over onto the terrain

behind the target.

b) This can cause intermittent background false target, becoming more severe at longer

designation ranges.

6) Boresight error. The laser spot is not properly aligned with the TADS reticle, producing an

error in the location of the spot on the target.

NOTE: Even a small number of overspilled or underspilled laser pulses can cause the missile to follow

false signals. If this occurs just before missile impact, the probability of a hit is significantly

degraded.

D-38

Figure 29. Backscatter

7) Backscatter

a) Backscatter is a term that applies to a portion of the laser beam energy reflected off

atmospheric particles in the laser path back toward the designator.

b) Backscatter energy competes with the reflected energy from the target, so that the

seeker may lock-on to the backscatter rather than the target.

c) Obscurants (fog, haze, rain, snow, smoke, dust, etc) in the laser-to-target LOS will also

produce strong backscatter pulse returns.

d) Backscatter can also occur in clear weather.

e) Backscatter is much more likely to occur with autonomous lasing because of the

proximity of the laser beam to the seeker even in clear (high visibility) conditions.

f) If a target return is not detected, the seeker may track the backscatter return. If the

seeker is tracking backscatter, the seeker LOS and TADS LOS will differ by more than

2, and the LOBL constraints box will be dashed, indicating an out-of-constraints

condition with the message BACKSCATTER displayed in the weapons inhibit.

g) Anytime the constraints box indicates an out-of-constraints condition, the crewmembers

must correct the condition prior to launch.

h) The seeker generally does not track backscatter after track has been established on the

true target.

i) Backscatter affects LOBL but can also affect LOAL if lock-on occurs too early in flight

before the missile has time to climb above the laser beam.

D-39

(g) Backscatter avoidance technique

1) If the launching aircraft is designating the target, and autonomous operation prerequisites are

met, all seekers on the Priority (PRI) Channel (CHAN) will be slaved to the TADS LOS,

pointed at the target when TADS is tracking the target.

2) Generally poor target reflectivity, co-located obscurants, or excessive designation cause

invalid ranges.

3) If this occurs and the seeker LOS diverges from the TADS LOS by 2° or more, the LOBL

constraints symbology will indicate out-of-constraints.

4) If the LOBL constraints box is intermittently switching in and out of constraints, a marginal

target condition exists, and the missile should not be launched.

NOTE: If primary CHAN track is achieved, and symbology indicates out of constraints, the missile cannot

be launched. BACKSCATTER is a safety inhibit.

5) To eliminate a backscatter lock-on, stop lasing the target. Switch to LOAL DIR and use a

minimum of 2 seconds of delayed designation from separation (3 seconds from trigger pull).

Figure 30. LOBL Autonomous Launch Offset.

6) It is possible for the seeker to switch to tracking backscatter during the first second after

missile separation in the LOBL autonomous mode if the target return is lost before the missile

has climbed above the laser beam.

7) The aircraft heading should be moved 3° to 5° in the direction of the missile to be launched to

ensure that the missile does not fly across the TADS LOS and degrade the TADS imagery.

D-40

8) False target avoidance techniques

a) Erratic range readings by the designating aircraft indicates that the seeker is tracking

false targets.

b) Backscatter, overspill, and underspill are the primary causes of this targeting error.

c) If accurate designation does not correct the problem, the solution is to:

1 Change to a different designator.

2 Change to a different target.

3 Relocate the designator to a new position.

(h) Rules for operation in obscurants

1) The launch envelopes defined earlier showed engagement capabilities in a clear

environment.

2) Performance is reduced when obscurants degrade the seeker's lock-on range or create false

targets. The following rules indicate how to determine if the situation supports a missile

launch:

a) The designating crew must have a clear image of the target for accurate placement of the

laser spot on the target, without overspill or underspill.

b) When the launch aircraft has a line of sight to the target, it must have a sufficient image in

its TADS for the aircrew to recognize the general shape of the target. If the launch

aircraft is masked, the designating aircraft must have a sufficient image in its TADS for

the aircrew to recognize the general shape of the target. Otherwise, the seeker will

probably not be able to achieve a true target lock-on, even after launch.

c) Laser rangefinder readings must be taken by the designating aircraft (especially if FLIR is

required to recognize the target), and the missile should not be launched unless steady,

plausible range readings are indicated.

d) For LOBL autonomous launches, constraints symbology must show “in constraints.”

Otherwise, the seeker is locked-on to backscatter and LOAL DIR should be used with

delay designation (2-second minimum from separation).

3) When the previous rules support LOAL launch, the launch aircraft should be aligned as

closely as possible toward the target, if designation is remote. For autonomous designation,

to assure that the missile does not fly across the TADS LOS, move the aircraft heading 3° to

5° toward the missile to be launched.

D-41

Figure 31. LOBL.

(i) LOBL requirements and launch strategies

1) LOBL mode requirements

a) LOBL mode may be used when the target is within the missile LOS prior to launch, with

either autonomous or remote designation.

b) In this mode, the missile laser seeker has acquired and locked-on to the reflected laser

energy from the target prior to launch.

c) Missile constraints box is driven by the missile seeker.

d) The LOBL mode may be used when the following conditions are present:

1 Direct LOS to the target exists.

2 The visibility conditions allow seeker lock-on at the launch range.

3 The cloud ceiling is higher than the LOBL maximum trajectory altitude for the

required range.

4 The threat to the launch platform does not warrant the use of delay designation or

launch from a defilade position.

D-42

Figure 32. LOBL Launch Envelope.

2) LOBL autonomous launch envelope

a) The minimum effective engagement ranges with a 0° or 20° target offset angle from the

aircraft Armament Datum Line (ADL) are as follows:

1 AGM-114K

a 500 meters with a 0° target offset angle.

b 700 meters with a 20° target offset angle.

2 AGM-114C



3 AGM-114F



D-43

Figure 33. LOBL Trajectories Versus Cloud Cover. (K-Model)

3) Nominal LOBL trajectories

a) The trajectories of the LOBL missile are dependent on range.

b) As the range increases, the trajectory altitude will increase as follows:

1 AGM-114K the missile will climb to an altitude of approximately 300 feet for a 3 km

target, 500 feet for a 5 km target, and 600 feet for a 7 km target.

2 AGM-114C/F the missile will climb to an altitude of approximately 400 feet for a 3 km

target, 1000 feet for a 5 km target, and 1700 feet for a 7 km target. The AGM-114F

will be approximately 100 feet lower in this trajectory than the numbers listed.

c) The AGM-114K is shown for reference.

d) Example: For a maximum-range (7km) LOBL SAL missile engagement, the crew must

ensure that they have a minimum of 600 feet above the aircraft launch altitude to ensure

cloud clearance for the entire missile time of flight.

e) Cloud cover is a major consideration when using SAL missiles. If a K-Model missile

enters the clouds, laser tracking is lost. However, the missile seeker will continue to point

at the target and the missile will be commanded to turn in the same direction as the

seeker, resulting in the missile flying out of the clouds towards the target. This maximizes

the probability of target reacquisition for the K-Model missile. Once the SAL 1 (F-Model)

missile enters the clouds reacquisition will be unlikely.

D-44

Figure 34. LOBL Remote Horizontal Distance Scan.

4) LOBL Field Of View (FOV)

a) The LOBL FOV depends on whether LOBL remote or LOBL autonomous is selected.

b) LOBL remote

1 If LOBL remote operation is selected, the seeker or seekers are scanning and the

FOV covered depends on the number of seekers.

2 The FOV of the scanning seekers are controlled by the WP by offsetting the pattern

of adjacent missiles. As the range increases, the horizontal distance searched, in

kilometers, increases.

3 In the LOBL remote mode, the scan time limits of the seeker are as follows:

a No time limit for continuous-scan operations

(1) AGM-114C/F temperatures below 90F (32C)

(2) AGM-114K temperatures below 125F (52 C)

b 30 minute continuous-scan limit

(1) AGM-114C/F missiles for temperatures above 90F

(2) AGM-114K for temperatures above 125F

(3) The missiles must be either deselected or placed in the LOAL mode to allow

the seekers to cool. The seeker should be allowed to cool for 30 minutes if

the tactical situation permits.

NOTE: No time limit on the AGM-114C/F/K missiles in any LOAL mode.

D-45

NOTE: The LOAL discussion will be general and not specific to either autonomous or remote

engagements. The data applies to both types.

Figure 35. LOAL.

(j) LOAL requirements and strategies

1) LOAL launch considerations

a) The seeker scans and locates the reflected laser energy after launch.

b) This capability allows target designation to be delayed until the missile is closer to the

target or to operate in low-visibility conditions, which shorten the seeker's lock-on range.

c) It also allows the missile to be launched from an Apache that is hidden from the target by

a terrain mask.

d) For either remote or autonomous modes, if LOAL DIR, LO, or HI is selected, and properly

coded laser energy is received prior to launch, the following occurs:

1 AGM-114C/F/K missile will default to LOBL, and the LOAL constraint box will change

to a LOBL box.

e) There are three LOAL modes which differ in the trajectory shape and seeker scan

pattern.

1 LOAL-Direct (LOAL DIR)

2 LOAL-Low (LOAL LO)

3 LOAL-High (LOAL HI)

D-46

Figure 36. LOAL Direct Mode.

2) LOAL modes

a) LOAL DIR: LOAL DIR mode provides the lowest missile trajectory. The LOAL DIR mode

may be used when any of the following conditions exists:

1 Direct LOS. Direct LOS to target exists.

2 Low ceiling/visibility. Bad weather (low cloud ceilings and/or visibility) exists.

3 Laser detector on threat. The available threat data indicates, the target may have

laser detectors.

4 Backscatter condition. Backscattered laser energy prevents the seeker from locking-

on to the proper target before launch in the LOBL autonomous mode.

5 Constraints box is driven by the selected LOS.

D-47

Figure 37. LOAL Direct Launch Envelope.

b) LOAL Direct Missile launch parameters

1 The minimum effective engagement ranges with a 0° or 7.5° target offset angle from

the aircraft ADL are as follows:

a AGM-114K

(1) 1500 meters with a 0° target offset angle.

(2) 1700 meters with a 7.5° target offset angle.

b AGM-114C



c AGM-114F



2 Due to seeker look down limits, the minimum engagement range should be increased

as follows:

a Increase minimum range by 500 meters for launch altitudes of 50 to 400 feet

above the target.

b Increase minimum range by 1000 meters launch altitudes of 401 to 800 feet

above the target.

3 The maximum effective engagement range that the missile can be launched from is

limited by the TADS ability to accurately maintain the laser spot on the target and the

seeker's ability to lock-on to the reflected laser energy.

4 The maximum effective engagement range for all missiles is 7 kilometers in the direct

mode.

D-48

5 Ranges beyond the maximum effective range will cause the probability of the missile

hitting the target to decrease but does not mean that the missile will not hit the target.

Figure 38. LOAL Direct Trajectories

c) LOAL DIR trajectories: The maximum effective engagement range for all missiles is 7

km. The nominal LOAL DIR trajectories.

1 The trajectories of the LOAL DIR missiles are dependent upon designation delay and

range to target. Longer designation delay times will result in lower trajectories. The

AGM-114K is shown for reference.

2 The LOAL DIR mode provides the lowest trajectory and requires an LOS to the

target.

3 LOAL DIR is used when low clouds prohibit the use of higher trajectories. It is used

in low-cloud conditions and should be used when backscatter is detected in a LOBL

autonomous mode.

a AGM-114K. With either a 4 or 12-second laser delay time, the missile will climb

to an altitude of approximately 400 feet for a 7 km target.

b AGM-114C/F. With a 12-second laser designation delay time, the missile will

climb to an altitude of approximately 400 to 800 feet with a 4-second delay for a 7

km target.

4 The missile flies lower trajectories for closer target.

5 Changing the laser delay time will change the AGM-114C/F missile trajectories.

Short delays will produce higher trajectories than long delays. The AGM-114K

trajectory is designed to be low for all laser delay times.

D-49

Figure 39. LOAL LO Launch Envelope.

d) LOAL LO: The minimum effective engagement ranges with a 0° or 7.5° target offset

angle from the aircraft ADL are as follows:

1 AGM-114K


b 2500 meters with a 7.5° target offset angle.

2 AGM-114C



3 AGM-114F


b 3500 meters with a 7.5° target offset angle


as follows:


above the target.


above the target.

5 The maximum effective engagement range for all missiles is 8 kilometers in the LO

mode.

6 The missile constraints box for LOAL LO and LOAL HI engagements are driven from

target data located at (B5) except when TRN is the ACQ selection. When TRN is the

ACQ selection the missile constraints box is driven by the TRN point.

D-50

Figure 40. Nominal LOAL LO Trajectories Nominal LOAL LO trajectories

e) Nominal LOAL LO Trajectories

1 The trajectories of the LOAL LO missiles are dependent on designation delay and

range to the target. Trajectory for an 8 km target:

a AGM-114K with a 4 or 15 second laser designation delay time, the missile will

climb to an altitude of approximately 800 feet.

b AGM-114C/F with a laser designation delay of 15 seconds , the altitude is

approximately 800 feet. With a delay of 4 seconds, the altitude is approximately

1400 feet. AGM-114F flies about 100´ lower than the AGM-114C

c The missile flies lower trajectories to closer targets.

2 The LOAL LO mode may be used when the missile is required to clear a low mask,

which may have been selected by the crew for aircraft protection.

Figure 41. LOAL LO Mode.

D-51

a Mask may not be higher than 260 feet above aircraft altitude.

b Minimum standoff distance from the mask is 600 meters.

3 The maximum effective engagement range is 8 km, when the remote designator is

close enough for accurate target designation.

Figure 42. LOAL HI Launch Envelope.

f) LOAL HI. The minimum effective engagement ranges with a 0° or 7.5° target offset angle

from the aircraft ADL are as follows:

1 AGM-114K



2 AGM-114C and AGM-114F




as follows:


above the target.


above the target.

4 The maximum effective engagement range for all missiles is 8 kilometers in the HI

mode.

D-52

Figure 43. Nominal LOAL HI Trajectories

g) Nominal LOAL HI trajectories

1 The trajectories of the LOAL HI missiles are dependent on designation delay and

range to the target. Trajectory for an 8 km target:

a AGM-114K with a 4 or 15 second laser designation delay time, the missile will

climb to an altitude of approximately 1400 feet.

b AGM-114C/F with a laser designation delay of 15 seconds , the altitude is

approximately 1300 feet. With a delay of 4 seconds, the altitude is approximately

1600 feet.

c The missile flies lower trajectories to closer targets.

2 The LOAL HI mode may be used when the missile is required to clear a high mask,

which may have been selected by the crew for aircraft protection.

D-53

Figure 44. LOAL HI Mode.

a Mask may not be higher than 1000 feet above aircraft altitude.

b Minimum standoff distance from the mask is 1500 meters.

3 The maximum effective engagement range is 8 km, when the remote designator is

close enough for accurate target designation.

3) Missile approximate flight time

Range (km) T=–25 F

(–32 C)

T = 70 F

(21 C)

T= 125 F

(52 C)

1

2

3

4

5

6

7

8

3

7

11

16

20

27

35

44

3

7

10

14

19

24

29

36

3

6

10

13

17

22

27

33

Figure 45. Hellfire Approximate Time Of Flight (TOF) (seconds)

NOTE: These flight times are from launch separation. An additional 1 second is required from trigger pull

to launch separation. The flight times are also applicable to all missile configurations and launch

modes.

D-54

a) Flight time will vary significantly with air temperature. For example:

1 On a 70 F (21 C) day, missile flight time to an 8 km target is 36 seconds.

2 At –25 F (–32 C), flight time at the same distance is 44 seconds.

3 At 125 F (52 C), flight time at the same distance is 33 seconds.

b) Note that this is a spread of 11 seconds. At shorter ranges, the TOF differences are less

but can be significant.

c) If the target is suspected of having a laser detector, the amount of time that the

designator is held on the target should be kept to a minimum.

d) This can be accomplished by delay and/or offset designation.

e) The allowable delayed and/or offset designation time depends on the missile TOF to the

target at various ranges.

f) The time the designator can be delayed is limited by the amount of time the missile must

be able to track the target in order to impact on the target.

g) For example, at a 7 km target range, the missile TOF on a 70 F (21 C) day is 29

seconds. The designator should illuminate the target between 4 and 13 seconds after

missile separation and continue until impact.

h) At this range, a period of 7 seconds of steady on-target time (terminal guidance) is

required prior to impact.

D-55

4) Flight, designation delay, and on target times

Range

(km)

Approx. Time of Flight from

Launch Separation at 70F

(21C) ** (seconds)

Laser delay after

Separation *** (seconds)

Steady on-Target

Time (prior to

impact) (seconds)

2

3

4

5

6

7

*8

7

10

14

19

24

29

36

****

2-3

3-6

4-8

4-11

4-13

4-16

6

6

6

6

6

7

8

Hellfire Approximate Time of Flight

NOTE: *Indirect fire only

** Additional 1 second is required to allow for the time from launch trigger pull to separation

***Laser designation must be initiated during this time interval.

****Not recommended: Delay times under 2 seconds may cause backscatter lock-on.

a) The designation delays indicated are selected so as to maximize the effectiveness of the

missile for launches in any LOAL mode.

b) Earlier designation will result in higher trajectories for AGM-114C/F but not for AGM-

114K.

c) Later designation could cause the missile to fly past the target without locking on.

d) To offset-designate while manually tracking, place the M-TADS reticle on a target of at

least tank size, about 50 to 100 meters to the front or side of the intended target, while

keeping the intended target within the selected TADS sensor FOV.

e) To offset-designate while in IAT, the primary target is first tracked using the IAT and then

reposition the M-TADS line of sight out of the tracking gates in front or to the side of the

target to be designated.

f) When maximum delay time is reached, the CPG can select offset to return M-TADS LOS

to the primary target to continue designation until missile impact.

g) To determine maximum delay time: Take TOF ÷ ½ and subtract 2.

D-56

CHECK ON LEARNING

1. What negative factor during target illumination will cause the laser spot to spill over the

target?

ANSWER: ______________________________________________________________________

______________________________________________________________________

2. What are the three LOAL trajectory modes?

ANSWER: ______________________________________________________________________

______________________________________________________________________

3. When the TADS LOS and the seeker LOS differ by more than _____ degrees a

BACKSCATTER message will display in the weapons inhibit section of the HAD.

ANSWER: ______________________________________________________________________

______________________________________________________________________

4. The safety inhibit backscatter is generally caused by ____________, ______________, and

____________.

ANSWER: ______________________________________________________________________

______________________________________________________________________

5. If the aircraft is 50 to 400 feet above the target you would increase the minimum range for

LOAL launch by _________ meters.

ANSWER: ______________________________________________________________________

______________________________________________________________________

6. Your target is 5000 meters away and you need to clear a mask that is 900 feet above the

aircraft, what trajectory would you select to engage that target?

ANSWER: ______________________________________________________________________

______________________________________________________________________

7. For a 5000 meter hellfire engagement the last _____ seconds needs to be steady-on-target

time (terminal guidance).

ANSWER: ______________________________________________________________________

______________________________________________________________________

D-57

F. ENABLING LEARNING OBJECTIVE 6

ACTION: Identify the SAL missile designation modes.




Identify the SAL missile designation modes.

Figure 46. Designation Strategy.

(k) Designation strategy

1) The Hellfire missile can operate with different designators and operating modes.

2) The selection of the designator and missile modes must be based on the specific mission,

enemy, troops, terrain, and time factors for the particular engagement.

3) The following guidelines are suggested:

a) Autonomous designation

1 Maximum standoff range

a The launching aircraft should designate the target when the aircraft can fire from

a position close enough to the target for accurate designation without extensive

exposure of the launching aircraft to the enemy threat.

b Maximum autonomous designation range, in a clear atmosphere, is limited by the

TADS ability to maintain the total laser spot on the target.

D-58

2 Manual tracking method

a When manually tracking a target, the TADS reticle should be maintained as close

as possible on the base of the turret in elevation and centered laterally, using

smooth, deliberate reticle movement with the MAN tracker, avoiding overspill and

underspill.

b Smooth tracking of a steadily moving target can be improved by engaging the

Linear Motion Compensator switch on the TADS Electronic Display And Control

(TEDAC) Left Hand Grip (LHG).

c Because MAN track usually produces larger jitter errors than IAT, the maximum

autonomous designation standoff ranges with MAN track should be less than

with IAT.

3 IAT tracking method

a A target can be tracked using the M-TADS either by manually using the MAN

tracker or by using the MTT mode.

b The IAT generally produces more stable tracking (less jitter) than the MAN mode.

c Therefore, IAT is less likely to illuminate false target or degrade the missile

accuracy than a less-stable MAN designation.

d However, under some target conditions, the IAT can provide a more-stable laser

spot on the wrong portion of the target, such as the bottom of the tank hull due to

the digital tracker which locks on to specific features of a target.

e In such cases, if the CPG can recognize that the MTT is tracking the wrong part

of the target, the aim point should be adjusted inside the tracking gates reposition

M-TADS LOS to desired point and press IAT.

f If desired aim point is outside tracking gates place M-TADS LOS inside tracking

gates and press IAT/OFS to IAT and hold for greater than 0.6 seconds to activate

the manual sizing to cover the desired aim point and then release the IAT switch.

Position M-TADS to the desired aim point and momentarily select IAT.

g During daytime and in a clear atmosphere, the Day Television (DTV) provides

better tracking than the FLIR.

4 LOBL/LOAL (autonomous)

a If the missile is to be launched from the left side, turn the aircraft left; if the

missile is to be launched from the right side, turn the aircraft right, past center,

until there is a 3-5 offset.

b The purpose of this offset is to cause the missile to fly an arc outside the TADS

target LOS.

c This will aid in the prevention of both TADS break lock and video washout out in

FLIR and smoke obscuration in DTV.

d Whenever possible, select a missile from the side of the aircraft such that the

wind will blow the smoke away from the TADS.

D-59

Figure 47. Remote Designation.

b) Remote designation

1 The portion of the target that is illuminated must be “seen” by the missile. This

requirement imposes a 60 limit on the angle between the gun target line and the

remote designator to target line.

2 The probability of killing a target depends on the missile flight path at impact and

target attack azimuth but generally is maximized if the laser spot can be held stable

on the base of the tank turret.

3 Maximum designation range. Remote designation allows the launch aircraft to stand

off at greater distances from the target. This standoff range can be out to the

maximum missile effective engagement ranges defined earlier. Remote designation

also allows the launch aircraft to be masked from the target, using the LOAL HI or

LOAL LO launch modes.

4 Remote designation also allows a single Apache to provide the weapons for other

designators. Remote designators may include another AH-64A/D aircraft, OH-58D,

Ground Laser Target Designator (GLTD), or one of the various designators of other

services or foreign allies

5 Remote designators must be within their maximum designation range from the target,

as determined by their laser beam divergence and aiming errors (spot jitter which

leads to overspill and underspill).

6 This can vary from one designator type to another. For remote designation by an

Apache, the maximum designator standoff ranges are the same as the maximum

autonomous Apache standoff ranges defined earlier.

D-60

Figure 48. Remote Designation.

c) Remote designator safety

1 When the remote designator is located in an offset position in azimuth from the

launch aircraft, care must be taken to assure that the laser spot is on a section of the

target that is visible to the missile. The remote designator should not be displaced

more than ±60 in azimuth from the launch aircraft to target line.

2 The remote designator should take precautions to prevent possible injury, which

could result from the missile tracking backscatter from the remote designator.

3 The designator should not be positioned within the ±30° fan either side of the

launching aircraft to target line or outside the ±60° designator offset angle.

NOTE: Offset angles greater than 45 degrees may significantly reduce the missiles ability to acquire laser

energy reflected off the target and should be avoided to assure a higher probability of hit.

D-61

Figure 49. Rapid Fire.

(l) Multiple-missile launch techniques

1) Rapid-fire engagements

a) Rapid fire is a mode of fire controlled by the PLT or CPG, as opposed to the WP, which

involves firing multiple SAL missiles with the same laser code.

b) The rapid-fire technique allows a single aircraft to engage several targets with less total

exposure time than required for sequential single-target engagements.

c) Rapid fire engagements may be employed for autonomous or remote engagements

(LOBL/LOAL).

d) The first missile is launched at the first target; a second missile is launched (on the same

laser code) 8 seconds after the first, and a third missile could be launched 8 seconds

after the second.

e) Subsequent missiles launched will be flying to the same target as the previous missile or

to the spot transitioning over the foreground to the next target.

f) When the first missile impacts on the first target, the laser spot is moved to the second

target and held until the second missile impacts.

g) A single Apache in one engagement may fire the entire load of missiles, each with 8-

second spacing, using the rapid-fire mode.

h) To use this technique, the targets should be relatively close (approximately 100 meters

maximum separation for missiles launched 8 seconds apart).

i) This will allow time for the second missile and subsequent missiles to correct their flight

path to the new target.

j) When manually tracking, the MAN tracker is used to slew the designator from the first

target to the second target.

D-62

k) The spot movement must be smooth and deliberate over a 1 to 3 second interval.

l) During the movement, the spot must continuously illuminate the foreground between the

targets (not a background tree line or hill that could be a considerable distance behind

the target).

m) The closest target should be engaged first, unless smoke from the first missile impact

would obscure the second target.

NOTE: In rapid fire, if designation commences before the second missile is launched, the second missile

will fly the LOBL flight trajectory even if LOAL was previously selected.

Figure 50. Ripple Fire.

2) Ripple (RIPL) fire engagements

a) When two designators are available (which may or may not include the launch aircraft),

two missiles may be fired against two targets (both targets within the missile’s footprint)

without the 8-second launch delay.

b) This is accomplished by using the RIPL fire technique.

c) With RIPL fire, the SAL mode option on the WPN page is set to RIPL, the PRI CHAN is

set to the laser code of one of the designators, and the Alternate (ALT) CHAN is set to

the code of the second designator.

d) One missile from the PRI CHAN may be launched, then a missile from the ALT CHAN

may be launched 1.5 seconds later.

e) Each pair of missiles is actually the result of two trigger pulls, so that the second missile

may be fired 1.5 seconds after the first.

f) Each missile will fly toward its own target.

g) Performing multiple launches in this mode is quicker than in rapid fire and does not

involve the process of slewing laser spots while the tracking missiles are in flight.

h) Prelaunch coordination between the launch platform and the remote designator is

required.

D-63

CHECK ON LEARNING

1. What is the maximum offset limit between the gun target line and the remote designator to

the target line?

ANSWER: ______________________________________________________________________

______________________________________________________________________

2. Maximum autonomous designation range is limited by the ________.

ANSWER: ______________________________________________________________________

______________________________________________________________________

3. During remote designation, the remote designator should not be within a ±___° fan from the

gun to target line.

ANSWER: ______________________________________________________________________

______________________________________________________________________

4. During rapid fire engagement the maximum separation between targets should not exceed

_________ meters, with at least an ______ second separation between missile launches.

ANSWER: ______________________________________________________________________

______________________________________________________________________

5. In the Ripple mode, after the primary channel missile is launched the alternate channel

missile may be launched after ______ seconds separation.

ANSWER: ______________________________________________________________________

______________________________________________________________________

D-64

G. Enabling Learning Objective 7

ACTIONS: Identify the Hellfire RF missile controls and displays.


STANDARD: In accordance with TM 1-1520-251-10-2, TC 1-251, FM 3-04.140 (FM 1-140).


Identify the Hellfire RF missile controls and displays.

Figure 51. RF Missile Mode.

(a) RF missile controls

1) Missile mode

a) The MODE button is used to select the operational mode of the missile system.

b) Missile MODE selections is common in both crewstations.

c) Missile MODE selections include the following:

1 The NORM mode powers RF missiles according to the missile PWR selection.

2 The MAN mode allows the crewmember to use the MAN ADV switch on the TEDAC

right handgrip or collective to select and power a single RF missile for firing. This

mode also allows the crew to advance manually through the RF missiles to select a

desired missile for power application.

3 When the MAN mode is selected, the missile PWR selections are removed.

D-65

Figure 52. RF Missile Power Options.

2) Missile POWER options

a) The missile POWER grouped option buttons are used to manage the power requirements

of the RF missiles.

b) The RF missiles could go into an over temperature condition if they stay powered

continuously.

c) The missiles also can overheat if they are radiating (tracking) a target for more than 3

minutes.

d) This is a cumulative time that will overheat a missile if adequate time for cooling is not

allowed.

1 The ALL button will power-up all available RF missiles. There is no automatic power

management in the ALL mode; missile can overheat and display the OT in the missile

icon.

2 The NONE button will remove power from all RF missiles.

3 The AUTO button will enable automatic power management. The number of missiles

powered is based on the total RF missile inventory available. In the AUTO mode,

missiles will be powered up at 10-minute intervals. This does not occur when the

missiles are actioned.

D-66

e) RF missile PWR selection is common to both crewstations.

Missiles Available Missiles Powered

8 or more 4

4 to 7 2

2 to 3 1

1 0

Automatic RF Missile Power Management

Figure 53. LOBL Inhibit and 2ND

Target Inhibit.

3) LOBL INHIBIT button

a) The LOBL INHIBIT button will inhibit the missile from radiating prior to launch.

b) Selecting the LOBL INHIBIT button will mode the RF missile system to fire the RF

missiles in a LOAL mode.

c) This capability reduces or eliminates the RF signature on the battlefield and allows for

firing missiles at FCR LOBL targets from a defilade position.

4) 2ND target INHIBIT button

a) The 2ND target INHIBIT button prevents the FCR from assigning secondary target data

to the missile during FCR target handover.

b) When receiving stationary LOAL target assignments in the prelaunch mode, a missile will

receive two target positions. This will provide the missile with an additional target in the

event it loses track of the initial target.

D-67

c) This feature could be necessary when friendly targets are possibly near the engagement

area. If friendly vehicles are in the vicinity of the target being engaged, it is possible that

the missile could target the friendly vehicle if missile tracking is lost.

d) Normally, the missile will search for a second target if it loses tracking on a primary STI

and cannot reacquire it within a prescribed time period.

5) Loading of RFmissiles should be balanced between both sides of the aircraft, primarily on

outboard launchers. The WP determines missile selection and firing order. No more than two

RF missiles are allowed to actively track targets simultaneously. The WP will always keep

the NTS and ANTS missiles on opposite sides of the aircraft to avoid interfering with each

other when radiating. If missiles are only present on one side, only one missile will be

assigned a target

D-68

CHECK ON LEARNING

1. The missile MODE selections are __________ in each crewstation.

ANSWER: ______________________________________________________________________

______________________________________________________________________

2. In the AUTO power mode, the missiles are powered-up at _____ minute intervals.

ANSWER: ______________________________________________________________________

______________________________________________________________________

3. 2ND

Target INHIBIT selection is used for _________ targets?

ANSWER: ______________________________________________________________________

______________________________________________________________________

4. The RF missiles can overheat (OT) if it is radiating (tracking) a target for more than ______

minutes.

ANSWER: ______________________________________________________________________

______________________________________________________________________

5. How many missiles will be powered with 6 missiles on board with the AUTO power mode

selected?.

ANSWER: ______________________________________________________________________

______________________________________________________________________

D-69

H. ENABLING LEARNING OBJECTIVE 8

ACTION: Identify the RF Hellfire Missile Operation.




Identify the RF Hellfire missile operation.

Figure 54. RF Missile Operation.

(a) RF missile modes

1) The RF missile operates in three modes:

a) Standby

b) Prelaunch

c) Postlaunch

D-70

Figure 55. RF Missile Operation.

2) Standby mode

a) On aircraft power up, the missiles begin a startup process. During startup, the missiles

initiate a power-up sequence; initialize in the standby mode; perform a Power on Built-in-

Test (PBIT); and inform the WP that startup is complete and they are in the standby

mode. When the outside air temperature is below -20 degrees C, the system will perform

a power cycling of the missiles to prevent an under-temp condition. The AUTO missile

power mode will prevent an overtemp condition by cycling power in 10 minute intervals.

b) The missile will remain in the standby mode until it receives target handover data from

the WP.

D-71

Figure 56. RF Missile Transfer Alignment

c) A Transfer Alignment (TA) is completed immediately after the PBIT sequence. TA allows

the missile to receive continuously updated inertial position (present position),

acceleration, and velocity data from the aircraft to align its own Inertial Navigation Unit

(INU).

d) The TA process accounts for known mechanical alignments between the systems, pylon

articulation, and communications delays.

e) The attitude and velocity of the aircraft are maintained during the TA function. While the

missile is in the standby mode and transfer alignment is complete, it will display an “R” in

its missile icon.

f) TA compares attitude and velocity measurements from the aircraft Embedded GPS

Inertial (EGI) to the missile Inertial Navigation System (INS) and updates it to the aircraft

reference.

g) Information included in the TA message is as follows:

1 Pitch and roll angle

2 True heading angle

3 Aircraft longitudinal, lateral, and vertical velocity

4 Inertial Navigation Unit (INU) time tag

5 Pressure and density altitude

6 Static temperature

7 Pylon position relative to Armament Datum Line (ADL)

8 Pylon position time tag (articulation with ACFT (aircraft) pitch and roll rates)

9 Aircraft pitch, roll, and yaw rate

10 Aircraft estimated heading error

D-72

Figure 57. RF Prelaunch.

3) Prelaunch mode

a) Actioning the missile system Weapons Action Switch (WAS) with acceptable target data

will initiate the missile prelaunch mode.

b) Prelaunch mode occurs from the time the WP transfers target data to the missile until the

missile is either launched or returned to the standby mode.

Figure 58. FCR Target Handover

D-73

c) The WP provides the missile target data three ways:

1 From the aircraft own FCR

a When the selected sight is FCR, and the 2ND target INHIBIT mode is not

selected, the WP transfers target data for both a primary and secondary target

when the targets are detected.

b If the primary target is stationary, a second stationary target may be supplied to

the missile. This is the only mode of the three that supplies a secondary target.

c If the Hellfire system is actioned prior to an FCR scan, the WP initiates the target

handover data at the completion of the scan.

d If the Hellfire system is actioned during an FCR scan, the WP immediately

initiates target handover data of the Next-To-Shoot (NTS) target based on the

targets detected up to that point, with subsequent Alternate Next-To-Shoot

(ANTS) target data occurring after completion of the scan.

Figure 59. TADS Target Handover

2 From the TADS

a When TADS is the selected sight, and the actioned missile type is RF, the

TARGET DATA? will be displayed I the sight status section of the HAD.

b The target must be designated for approximately 3 seconds to receive the target

handover data and remove the TARGET DATA? message.

c If the laser data is erratic, the message will not be removed, and the target

handover data will not occur until, valid range is acquired.

d Upon TADS target handover to the RF missile, target velocities will be zeroed if

the target velocities are under a specific threshold. This will more accurately

reflect a stationary target.

D-74

Figure 60. IDM Handover

3 From the Improved Data Modem (IDM) in the form of an RFHO

a When the RFHO is received via the IDM RFHO, and the mission is accepted, the

target handover data represents the target North-East-Down (NED) grid

coordinates relative to the receiving aircraft.

b To receive an IDM RFHO in an aircraft with or without radar, you must have the

FCR as your selected sight, and the missiles actioned. In a non-FCR aircraft,

you must press the REC (receive) BTN (button) on the Tactical Situation Display

(TSD) page prior to selecting the FCR as your sight; if not, the message FCR

NOT INSTALLED will be displayed when selecting FCR prior to pressing the

REC BTN. In this case, you will not receive the RFHO.

c The only timeout associated with a handover is the receiving aircraft must

receive the RHFO within six minutes of the of the RFHO target data being

received in the aircraft’s IDM buffer. DATA INVALID message will be displayed in

the HAD.

d) Target handover data contains the following information:

1 Target status: ID, target type (air/ground), LOBL inhibit (on/off)

2 Target detection time: Time from initial detection until current update

3 Target update time: Time since last update

4 Target NED position: NED at time of detection

5 Updated NED position: NED position at update time

6 Target NED velocity

7 Crossrange: target handover data for crossrange

8 Height: target handover data for height

9 Range: target handover data for range

D-75

10 Range rate: target handover data for radial velocity

11 Cross-range: target handover data for crossrange velocity

12 Aircraft time at request

Figure 61. Target Assignment.

e) Target assignment

1 The Longbow RF missile is capable of engaging moving and stationary targets at a

range between 0.5 and 8 km.

2 After the WP transfers target NED data to the missile, the missile determines the

launch mode, either LOBL or LOAL, based on target velocities (moving or stationary)

and range to target.

3 The FCR target symbols that are displayed do not determine the type of missile

mode for launch (that is, LOBL or LOAL). Therefore, it is possible to launch a LOBL

missile at a LOAL target symbol and vice versa.

4 If the missile determines the target requires a LOBL acquisition, it will attempt to

acquire it by radiating three times for approximately 3 seconds each.

5 During LOBL engagement, if the missile radar fails to acquire the target after three

attempts, the radar will transition back to standby, but the inertial tracking of the

target will continue.

6 Actioning the missile system again would allow for three more scan attempts on the

same PRI target.

f) RF missile LOBL and LOAL determination

1 Although the RF missile has the final authority whether it should be launched LOAL

or LOBL, it generally follows a predetermined set of rules.

a Moving target. All moving target are processed as Moving target Indicator (MTI)

target and should be assigned as LOBL engagements from the minimum range

of 500 meters to the maximum range of 8000 meters.

D-76

b Stationary target. Stationary target assignments are processed as Stationary

Target Indicator (STI) and are broken into three range areas, which include the

following:

1. 500 to 1000 meters

a. Targets are too close for an LOAL engagement and must be made a

LOBL engagement. (out-of-constraints LOBL box).

b. When the missile to target range or target motion requires a LOBL

trajectory and a NO TRK occurs, the “NO ACQUIRE” message will

appear in the weapons inhibit section of the HAD and this safety inhibit

will preclude the missile from being launched.

2. 1000 to 2500 meters

a. An RF missile will try to acquire while displaying an LOAL box for targets

between 1000 and 2500 meters.

b. If the missile acquires the target, it becomes LOBL box and will be made

LOBL engagement. If no acquisition is made, the LOAL is authorized.

This range uses High Range Resolution (HRR) for STIs

3. 2500 to 8000 meters

a. Targets between 2500 and 8000 meters will be LOAL using Doppler

Beam Sharpening (DBS).

b. RF missiles can only receive a target handover data from the TADS or

via RFHO for a target between 6000 and 8000 meters because the FCR

is unable to process stationary targets at ranges greater than 6000

meters.

.

Figure 62. RFHO Delay.

D-77

g) Target handover delays

1 Missile performance against moving and stationary target is a function of many

factors. The most important factor is the RFHO error at the start of the target

acquisition process.

2 The target handover data error grows as the time between FCR detect and the

missiles receipt of the target handover data increases.

3 In the example above, the time between accepting the IDM RFHO and the time the

actual target handover data occurs (WASing) could cause an acquisition attempt in

the wrong area.

4 It is very important to minimize this handover latency for best performance; however,

the missile does optimize its performance by selecting the appropriate acquisition

mode and submode for best target detection and tracking performance based on

handover latency and initial target RFHO error.

Figure 63. RF Postlaunch Mode.

4) Postlaunch mode

a) The postlaunch mode is initiated when the firing command (weapon trigger pull) occurs.

b) The WP verifies launch constraints (safety and performance inhibits, launcher and missile

Built-In-Test (BIT) status, missile gimbal angles, and RF tracking status for LOBL missiles

and, if no constraints are active, issues the release consent message to the launcher.

c) Once the release consent message is received, the launcher issues the launch command

to the designated missile and, at the same time, issues commands to enable the missile

battery and pneumatic actuator control system.

D-78

d) When the launch commands are received by the missile, the system mode transitions to

postlaunch.

e) The launcher verifies battery power and, if valid, digital communication with the missile

ceases and the motor fire command is sent to the missile.

f) The missile achieves separation and leaves the rail approximately 1 second after the

launch command is issued.

g) The warhead is armed when the missile achieves 10 G acceleration (150 to 300 meters).

D-79


Identify the RF Hellfire missile radar modes.

Figure 64. RF Missile Radar Modes.

(a) RF missile radar modes

1) The target acquisition and tracking modes are terms used to explain the different ways the

missile seeker improves its chances of locating and hitting LOBL and LOAL targets.

2) The missile radar has three target acquisition modes tailored to specific target characteristics.

All modes require target handover data from the WP.

3) The missile has three acquisition modes:

a) Terminal Track Acquisition (TTA) Used for short-range stationary target LOAL and LOBL.

b) Preterminal Acquisition (PTA) Used for long-range stationary targets LOAL.

c) Moving Target Acquisition (MTA) Used for moving target LOBL.

4) The missile has two tracking modes:

a) Preterminal Track (PTT). Used for tracking of medium-to-long-range stationary and

moving targets.

b) Terminal Track (TT). Performs the final phase tracking of stationary and moving targets.

D-80

Figure 65. High Range Resolution.

(b) Missile acquisition modes. The two stationary-target acquisition modes (TTA and PTA) use

different types of processing to separate targets from the surrounding clutter, based on range.

1) TTA

a) The TTA mode utilizes HRR to process target from 0.5 to 2.5 km for both LOBL and

LOAL short-range targets.

b) The missile cannot perform DBS trajectory on short-range targets under 2.5 km.

c) HRR is utilized to detect stationary targets in ground clutter by providing much tighter

range bins per range gate.

d) This technique produces a much better resolution of the designated target.

e) With smaller range bins, this mode assists target detection by measuring the size of the

radar return for comparison with target handover classification.

f) The LOAL mode is exercised at ranges greater than 1 km to meet performance

requirements for longer-range HRR operations and reduced Radar Cross Section (RCS)

targets.

g) For targets between 1 and 2.5 km a LOAL status will be supplied to the launch platform;

however, the radar will immediately attempt to acquire and track the target LOBL.

h) This is why between the ranges of 1 and 2.5 km the missile mode can be either LOAL or

LOBL.

D-81

Figure 66. Doppler Beam Sharpening.

2) PTA. PTA is designed to acquire long-range stationary target in the LOAL mode at ranges

between 2.5 to 8 km using a technique called DBS.

a) DBS

1 DBS uses a curved trajectory to induce relative motion between a stationary target

and its background by flying an off-axis flight path to the target. DBS significantly

enhances the probability of detection and tracking stationary targets at long ranges.

2 Standard Doppler processing (missile flying direct to the target) would cause a

stationary target to be included in the same Doppler bin as all of the main lobe clutter

return since both types of return exhibit the same relative range rate.

3 DBS, due to the angular difference between the missile’s forward velocity vector and

the target LOS, causes the relative range rate of the target to be different than that of

the background, spreading the return over many Doppler bins.

4 The resulting spread increases the target signal-to-clutter ratio in the target Doppler

bin, enabling the radar to identify and locate the target.

5 DBS is selected for ground-clutter rejection during stationary-target PTT or when a

target that was initially an MTI has become an STI during flight. If this occurs, the

missile would switch from a straight trajectory to a DBS trajectory in flight.

6 There are two constraints involved when the missile evokes the in-flight DBS option:

a First, the switch is not allowed near the terminal phase, where missile kinematics

cannot support the trajectory switch.

b Second, the trajectory will not switch from DBS back to a straight trajectory. The

probability of an in-flight DBS is very low.

D-82

Figure 67. DBS Trajectory.

b) DBS trajectory

1 The missile does not always turn in the same direction when DBS occurs. The

direction of the turn is determined at umbilical separation as a function of the LOS to

the target. Missiles launched from either side of the aircraft will follow the same

trajectory, based on the following data:

a If the target is right of the missile centerline, the missile trajectory curve will be a

left DBS trajectory to the target.

b If the target is left of the missile centerline, the missile trajectory curve will be a

right DBS trajectory to the target.

c Targets close to the zero bearing may yield either a left or a right DBS trajectory.

2 In the event the missile loses radar track of the target, it will shift to DBS in an

attempt to reacquire the target.

3 The primary parameters used to determine the extent of the DBS trajectory are the

inertial guidance data of the missile (where it is at that instant), the last known point

of the target (point the missile is tracking to), and, for moving targets, the last known

velocity of the targets.

4 In the event the missile does not reacquire the target, it will use inertial guidance to

fly to the calculated target location.

D-83

Figure 68. Step Scanning.

c) Step scanning

1 If a break lock occurs after launch against an STI, the PTA will exercise the

reacquisition mode.

2 The reacquisition mode includes several PTA attempts over a series of azimuth

antenna positions and range positions (step scanning).

3 The reacquisition sequence is repeated until the target is acquired or until the

terminal track phase range is reached.

4 Azimuth scanning is required for LOAL operation in order to provide an adequate

probability of the target being in the seeker angular FOV.

D-84

Figure 69. Secondary Target Handover.

d) Secondary target handover

1 During stationary target handovers , the FCR has the capability to handover two

targets to the same missile. If the FCR acquires two targets with zero velocity within

a certain footprint, it may supply both target vectors to the missile.

Figure 70. Secondary Target Symbol.

2 A second target symbol will be displayed on the FCR and TSD page to indicate the

second target was passed to the missile.

3 The secondary target will only be used if postlaunch acquisition or reacquisition of the

primary target fails.

D-85

4 The secondary-target position data, which is sent from the platform through the

launcher via the secondary-target message, is a NED vector from the primary-target

location.

5 This can only occur with stationary targets; the missile cannot calculate positions for

two separate target handovers if either the primary or secondary targets are moving.

6 Once a reacquisition cycle (step scanning) is complete, the primary target was not

found, and if a secondary target has been assigned, the missile will shift trajectory to

the secondary target position.

7 In the event the missile does not acquire the second target, it will use inertial

guidance to fly to the calculated location of the second target.

8 Do not confuse the primary and secondary target handover with the FCR NTS and

ANTS target.

Figure 71. Spotlight and Scan Submodes.

3) MTA

a) MTA performs acquisitions on all moving targets. This mode uses Doppler processing

created by the target velocity and operates from 500 to 8000 meters.

b) Spotlight and Scan are both sub-modes of the MTA radar mode. The missile

automatically selects the spotlight or scan submodes for MTA, based on the quality of the

target handover data.

c) RFHO data quality is the estimate of how well the aircraft acquisition sensor (FCR,

TADS, IDM) was able to measure the position of the target.

D-86

1 Spotlight submode

a The spotlight submode is selected when precision RFHO data is provided along

with minimum handover latency.

b This submode acquires moving targets by maintaining the center of the antenna

beam and range gates over the inertially tracked target position while collecting

several dwells of radar data.

2 Scan submode

a The scan submode is selected when a nonprecision target handover data (based

on RFHO quality and latency) is received.

b This submode acquires targets by collecting radar data while scanning over a

scan width in azimuth that is calculated to encompass the crossrange region

most likely to contain the target.

Figure 72. Missile Track.

d) Radar missile track modes. There are two radar track modes which use different signal

processing to track targets. Both modes track moving and stationary targets; however,

PTT employs DBS, while TT uses HRR.

1 PTT

a Performs tracking of medium-to-long-range stationary and moving targets

b Operates on the rail out to the TT mode and uses multiple trajectories and DBS

to maximize target detection

D-87

2 TT

a Performs the final phase tracking of stationary and moving targets

b Uses HRR processing to improve the aimpoint accuracy through missile impact

c If the missile is unable to acquire the primary target, it will continuously cycle

through the reacquisition mode until it either reacquires the target or reaches a

minimum range.

d Once the minimum range is reached without reacquisition, the missiles will

transition into the TT mode and fly to the target last-known point.

D-88


Identify the RF Hellfire missile trajectories.

Figure 73. RF Missile Elevation Flight Profiles.

(a) RF missile trajectories

1) Elevation flight profiles for moving LOBL and stationary LOAL targets:

a) The RF missile flies a trajectory that is optimized for radar performance while maintaining

lethality. The LOBL and LOAL elevation flight profiles are similar.

b) The RF missile generally flies a higher trajectory than the SAL missile. Clouds are not a

factor when employing an RF missile. The missile has its own onboard radar system that

allows it to “see through” clouds.

c) If the missile is tracking an STI and loses radar track, reacquisition failures may result in

the missile changing its target to a secondary target passed to it in the prelaunch mode.

D-89

Figure 74. Direct Trajectory for RF LOBL/20 Degree Offset.

(b) LOBL moving target azimuth flight profiles

1) The missile flies a very direct azimuth flight profile for LOBL operations.

2) If the target becomes stationary after launch, the missile may fly an off-axis trajectory in an

attempt to reacquire the target (DBS).

3) The illustration shows a direct trajectory relative to a trajectory with a 20° offset angle. The

missile can fly out to 100 meters with an extreme offset angle because of the missile’s initial

energy before the guidance section can get the missile headed toward the target.

4) As the offset angle decreases, the trajectory is closer to the armament datum line.

D-90

Figure 75. Stationary LOAL RF Missile Trajectories.

(c) LOAL stationary target azimuth flight profiles

1) The LOAL azimuth flight profile is driven by a DBS trajectory, which is used for medium-to

long-range stationary targets. This illustration shows trajectories with 1° and 20 offset

angles.

NOTE: Increasing the offset angle will slightly increase the distance of the trajectory from the armament

datum line.

D-91

CHECK ON LEARNING

1. What are the three RF missile modes?

ANSWER: ______________________________________________________________________

______________________________________________________________________

2. Transfer alignment occurs in the ______ missile mode.

ANSWER: ______________________________________________________________________

______________________________________________________________________

3. In the pre-launch mode what are the three methods of target handover data to the RF

missile?

ANSWER: ______________________________________________________________________

______________________________________________________________________

4. Doppler Beam Sharpening (DBS) uses a curved trajectory to induce a relative motion for

stationary targets (STI) to enhance the probability of detection and tracking between what

ranges?

ANSWER: ______________________________________________________________________

______________________________________________________________________

5. At a range of _______ to _______ meters, targets are too close for a LOAL engagement and

must be a LOBL engagement or a “NO ACQUIRE” message will be displayed.

ANSWER: ______________________________________________________________________

______________________________________________________________________

6. The three RF missile acquisition modes are ________________, ________________, and

________________.

ANSWER: ______________________________________________________________________

______________________________________________________________________

D-92

I. Enabling Learning Objective 9

ACTION: Identify the LBHMMS safety features.



140).


Identify the LBHMMS safety features.

Figure 76. RF Radiation Hazard Area.

NOTE: During missile operation, the RF radiation hazard area should be avoided. This area extends

from the missile nose outward 1-meter and 45° polar from the missile centerline.

(a) LBHMMS safety features. The performance inhibits can be overridden by a trigger pull to the

second detent, but the safety inhibits cannot be overridden. When applicable, the associated

HAD message follows the inhibit description.

1) Missile Inhibits. Missile inhibits are organized into missile system safety inhibits and missile

performance inhibits.

D-93

SAFETY PERFORMANCE GENERIC

ACCEL LIMIT YAW LIMIT SAFE

ALT LAUNCH PYLON ANGLE TRAINING

DATA INVALID PYLON LIMIT (AIR)

GUN OBSTRUCT RATE LIMIT

LOS INVALID ROLL LIMIT

PYLON ERROR SKR LIMIT

PYLON LIMIT (GND)

BACKSCATTER

LASER RANGE?

MSL NOT RDY

Figure 77. Missile Inhibits.

2) Missile system safety inhibits

a) ACCEL LIMIT: Aircraft vertical Acceleration (ACCL) is less than 0.5 G.

b) ALT LAUNCH: Within 2 seconds of a rocket launch.

c) DATA INVALID: The FCR is the active sight, and the RFHO data (position error taken

from both aircraft and/or FCR range deviation error) has exceeded optimum parameters

to a magnitude that a safety inhibit is implemented. (RFHO in MSG REC file for more

than 6 minutes)

d) GUN OBSTRUCT: If the gun is out of coincidence, the WP will inhibit launch of missiles

from the inboard stations of the inboard pylons. The inboard missiles will be coded NA.

e) LOS INVALID: Indicates the selected LOS is either failed or invalid.

f) PYLON ERROR: Indicates the aircraft is on the ground, and the pylons position is

unknown, or the pylons are positioned such that the missile may strike the ground near

the aircraft.

g) PYLON LIMIT: Indicates that the commanded pylon position exceeded the pylon

articulation limits (+4 to –5 on the ground), (+4 to –15 in the air). Performance or safety

inhibit is dependant upon air/ground status.

h) BACKSCATTER: Based on missile seeker versus TADS LOS, indicates the seeker is not

tracking the TADS laser designation.

i) LASER RANGE?: Indicates the ST/UPDT switch on the TEDAC LHG has been selected

to the UPDT position, and the current range source is other than laser.

j) MSL NOT RDY: Indicates that no hellfire missiles are ready for launch, and no SAL

missile priority channel is selected, or that RF missile TA is not complete.

D-94

3) Missile performance inhibits. The WP will inhibit missile firing if a performance constraint is

detected, and the weapons trigger is not depressed to the second detent.

a) YAW LIMIT: indicates yaw position of the aircraft with respect to the target is excessive;

applies to LOAL mode only.

1 SAL missile LOAL LO or LOAL HI selected and any of the following conditions exists:

a Azimuth angle between the target and the ADL is greater than 7.5°.

b Selected target data is invalid.

c True heading data from the EGI is invalid.

2 SAL missile LOAL DIR selected and azimuth angle between the selected sight LOS

and the ADL is greater than 7.5°.

3 RF missile engagements when the target to be handed over has a LOS angle greater

than 20° from the ADL.

b) PYLON ANGLE: Indicates the pylon position is greater than 10° from the optimum launch

position or that the pylon position is unknown.

c) PYLON LIMIT: Indicates (either/or) that the commanded pylon position exceed the pylon

articulation limits (+4 to -5 on the ground)(+4 to 15 in the air). Performance or safety

inhibit is dependent upon air/ground status.

d) RATE LIMIT: Indicates the aircraft pitch, roll, or yaw rate or acceleration is excessive.

e) ROLL LIMIT: Indicates the aircraft roll position is excessive.

1 RF missile selected and roll magnitude is greater than 20°.

2 SAL missile in LOBL mode and roll magnitude is greater than 20°.

3 SAL missile in LOAL mode and roll magnitude is greater than 10°.

f) SKR LIMIT: indicates the missile seeker azimuth or elevation gimbal limit has been

reached.

1 If the priority SAL missile is tracking and the seeker azimuth or elevation angle is

greater than 20° from the missile body axis.

2 If the priority RF missile is tracking, the seeker azimuth angle is greater than 20° from

the missile body axis, and the range is equal to or greater than 1 km.

3 If the PRIORITY RF missile is tracking, the seeker azimuth angle is greater than 5°

from the missile body axis, and the range is greater than 1 km.

4) Other weapon inhibit status field messages:

1 SAFE: Indicates the weapon system has not been armed through the Armament Control

panel.

2 TRAINING: Indicates the training mode is active, or the TESS is enabled, and the

Armament Control is in the ARM state, and a weapon is actioned in either crew station.

D-95

CHECK ON LEARNING

1. What inhibits can be overridden, and how is this accomplished?

ANSWER: ______________________________________________________________________

______________________________________________________________________

2. Is the message “BACKSCATTER” a safety or performance inhibit?

ANSWER: ______________________________________________________________________

______________________________________________________________________

3. What does the message “ALT LAUNCH” mean?

ANSWER: ______________________________________________________________________

______________________________________________________________________

4. What is the RF missile radiation hazard area to be avoided?

ANSWER: ______________________________________________________________________

______________________________________________________________________

D-96

J. ENABLING LEARNING OBJECTIVE 10

ACTION: Identify the Training Missile Emulator (Tme) operation.



140).


Identify the Training Missile Emulator (TME) operation.

Figure 78. Training Missile Emulator.

(a) TME

1) The TRAIN button enables the TME LEA. There is one TME in each launcher.

2) The TME is a software program loaded in the LEA, which provides the capability of simulating

RF missile operations.

3) The TME can replicate the functioning of four LBHMMS missiles on each launcher.

4) The TRAIN mode emulates the control decision making process of the RF missile.

5) The TME will also replicate the missile’s launch mode selection processing, target acquisition

and target tracking functions, missile BIT routines, and thermal management characteristics.

(b) TME BITs

1) Selecting the TRAIN mode will emulate PBIT and IBIT functions with appropriate delays built

in for accurate simulation.

2) IBIT can be initiated when the system is in the standby or prelaunch modes.

3) It may be commanded at power on, but cannot be acted upon until startup is complete.

4) Emulated IBIT will run in 17 seconds.

5) Due to the manner in which the emulator deals with memory, the startup routine will rerun

upon completion of the IBIT.

D-97

6) This will cause an additional 9-second delay for the restart, resulting in a 26-second delay to

run IBIT.

(c) TME thermal management

1) The TME provides for thermal management monitoring and control.

2) The TME is allowed a cumulative ON time of 30 minutes.

3) If this time is exceeded, an Over Temperature (OT) symbol will appear on the affected missile

icon on the WPN page.

4) Turning the missile system off and back on from the WPN UTIL page can reset the timer.

(d) TRAIN mode

1) Operation of tactical missiles is not possible while the TRAIN mode is enabled and all tactical

missiles will be coded as NA. However, while in the TRAIN mode with the ARM/SAFE switch

set to ARM, the laser is fully functional.

2) TRAIN mode functions include the following:

a) Off. This is the default function of the missile when the emulator is first turned on. It

simulates the missile system in a no power condition.

b) Standby

1 This function is established by a power-on command from the launcher, which is

initiated from the missile system power selection on the WPN UTIL page.

2 The emulator will simulate the delay (9 seconds) that occurs during missile spin-up

and PBIT routines when power-up is commanded.

3 TA will also be initiated during this function, and will run continuously through the pre-

launch function.

c) Prelaunch

1 The TRAIN mode will transition from standby to prelaunch when a target assignment

is received.

2 The TME will then simulate prelaunch radar (MTA, TTA) and launch mode control

decisions (LOAL versus LOBL) based on target characteristics, relative position,

handover accuracy (TADS versus FCR), whether the target is in the seeker FOV, and

the number of previous acquisition attempts

d) Acquisition and track radar modes

1 The TRAIN mode will simulate the appropriate acquisition and track modes based on

the target assignment. Target-to-aircraft location is continuously updated to provide

the TME with the proper data with which to make the mode and launch decisions.

e) TME operation

1 The LOBL/LOAL decision will be based primarily on target range and the MTI/STI

indicator. If LOBL becomes the designated launch mode, the TME will exercise

acquisition attempts based on FOV limits and range.

2 Once acquisition has occurred, the radar mode will transition to an appropriate track

mode and continuously update the aircraft and target positions to determine if the

TME is still capable of tracking the target.

3 If the track is lost due to the target going outside the FOV or crossing the LOAL/LOBL

range boundaries, reacquisition will be attempted every 2.7 seconds after the break.

D-98

4 The TME will remain in the track mode until after the third reacquisition cycle, after

which the TME will cease target processing and revert to the prelaunch mode.

f) TRAIN mode operational sequence

1 When the TME is in the Standby mode, all empty rails will show an RF missile

present and all rails with Hellfire SAL training missiles loaded will show SAL missiles

present.

2 When the missile system is actioned, the TME transitions to the prelaunch mode and

target assignments from the FCR are passed to the firing missile.

3 In the prelaunch mode, the TME will replicate the acquisition and track characteristics

identified above.

4 The appropriate messages in the High Action Display (HAD) (for example, RF MSL

TRACK, LOAL NORM, NO ACQUIRE) will be displayed along with the appropriate

missile icons (for example flashing R or T).

5 The missile constraints box will be presented with a "T" centered in the box when the

weapon system is actioned.

6 The weapon inhibits field will display SAFE when the aircraft is in the safe mode and

TRAINING when the aircraft is armed.

7 When the TME calculates that the firing missile has met all prelaunch constraints, it

will notify the WP, which will display the in-constraints box on the weapons

symbology display.

8 The crewmember can then pull the weapons trigger to initiate launch commands.

9 The TME will then display a successful launch by signaling the WP to blank the firing

missile icon from the WPN page.

10 The WP will also cause the target on the FCR page to change to the "shot-at" icon.

Figure 79. Training Missile Emulator.

D-99

g) Tactical Engagement Simulation System (TESS)

1 TESS is an interactive simulation system that allows aircrew training for all of the AH-

64D sight and weapon systems.

a This provides Real Time Casualty Assessment (RTCA) for Force-On-Force

(FOF) training for Combat Training Center–Instrumentation (CTC-I) and Home

Station Instrumentation (HSI). TESS will interface with the ground

instrumentation at CTCs and HSI.

b TESS is apportioned into two component systems.

1. The A-Kit is composed of modifications to the AH-64D software and fixed

hardware required to interface with the removable B-Kit.

2. The B-Kit

a. The B-Kit contains an eye safe laser rangefinder/MILES laser designator

that physically replaces the TADS laser rangefinder/designator and laser

spot tracker.

b. The eye-safe laser rangefinder/MILES laser designator functionally

replaces the TADS laser rangefinder/designator. The laser spot tracking

is simulated during TESS training.

c. The B-Kit also adds a TADS internal boresight adapter.

3. Simulated weapons inventory is used to provide realistic interaction between

aircrew, aircraft, and targets.

a. TESS incorporates the capability to interact with ground-based After

Action Review (AAR), Executive Control (EXCON), and targeting

systems.

b. Information is provided from the aircraft systems to the B-Kit for

processing and transmission to the ground instrumentation systems.

c. The ground instrumentation system elements can provide real-time

status display, administrative control, data archiving, target position

tracking, and RTCA of targets.

4. When the TESS Electronic Control Unit (TECU) is installed without the TESS

Training Missile (TTM):

a. The aircraft enters a live-fire instrumentation configuration and transmits

tactical weapon event data to the TECU for recording and transmission

to ground instrumentation systems, which is used for training.

b. When in this configuration, the WP will transmit tactical weapon event

data to the TECU for recording and transmission to ground

instrumentation systems.

2 Simulated weapons inventory for TESS training:

a Weapons inventory is simulated by administrative input to the TECU and

subsequent transmission to the WP.

b Simulated inventory is uploaded upon TESS B-Kit power up and by subsequent

administrative input.

c If any Hellfire missile or rocket is detected during the initial stores inventory or if a

gun-rounds inventory of greater than zero is stored:

D-100

a. A LIVE AMMO indication will be displayed in the HAD weapon-inhibit field,

and TESS training will not be enabled.

b. The specific type of ammunition will be indicated on the Up-Front Display

(UFD).

d Gun-rounds count and rocket-type entries are only changed by administrative

input to the TECU and subsequent transmission to the WP or by simulated

gun/rocket fire.

e Simulated inventory is not considered in aircraft gross weight and performance

calculations.

Figure 80. Missile Constraint Boxes.

3 Symbology/HAD indications:

a The Hellfire missile constraints boxes are used to indicate the delivery mode and

direction to orient the aircraft for the Hellfire missile launch.

1. A dashed line type indicates the missiles are out of constraints.

2. A solid line indicates the missiles are within constraints.

b Constraint boxes are displayed in two sizes and will be displayed only when the

missile system is actioned. Boxes apply to SAL and RF missile launches.

1. LOBL constraint box (20º):

a. The LOBL constraint box will be displayed when the missile system is in

a LOBL missile launch mode.

b. For SAL missile engagements, the LRFD must be designating in order

for it to be considered a LOBL missile shot.

2. LOAL constraints box (7.5º):

D-101

a. The LOAL constraint box will be displayed when the missile system is in

a LOAL missile launch mode.

b. For SAL missile engagements in the LO or HI trajectory, constraints are

calculated based on the acquisition source chosen from the COORD

page (Txx, Cxx, Wxx, TRN, or Hxx). (ACQ B5)

c. LOAL does not have to be the active acquisition source, but it must be

selected as the target source.

1. A centered "T" will be displayed in the Hellfire constraints cursor

symbols when TESS training is enabled and the missiles are actioned.

2. The HAD weapon inhibit: Whether the aircraft is ARMed or SAFE with

TRAIN mode selected the weapons inhibit field (HAD) will display

TRAINING.

Figure 81. RTCA Status.

4 Weapons effects during TESS training:

a With a simulated Hellfire missile launch, rocket launch, or gun firing, the

Communications Interface Unit (CIU) will provide the respective weapon

launch/firing audio effect.

b The TESS B-Kit will provide an external visual effect (firing flash).

5 During TESS training the TECU determines, either from the Laser Warning Receiver

(LWR) or administrative input, that an RTCA event has occurred, and the TECU will

transmit the RTCA status and a weapon Identification (ID) code to the aircraft.

6 The CIU will provide the aircrew with an RTCA audio effect (tone with voice

messages):

a Tone, “YOU HAVE BEEN KILLED.”

b Tone, “YOU HAVE BEEN HIT.”

c Tone, “NEAR MISS.”

D-102

7 The RTCA status will be displayed on the UFD hit and near miss for 8 seconds; kill

continuously:

a "SIM KILL."

b "SIM HIT."

c "SIM MISS."

Figure 82. Aircraft Kill Indicator (AKI).

8 The RTCA status and weapon ID code will be made available on the WPN UTIL

page.

9 If a kill status is received:

a The aircraft will be inhibited from firing any weapon.

b The TTM will power the external Aircraft Kill Indicator (AKI) to indicate the RTCA

status. If the flashing AKI indication creates a hazard to flight, the capability to

turn off the AKI is available to the aircrew via the WPN page AKI button.

10 The weapons TRAIN button is not available when TESS is enabled.

11 During TESS training the TECU determines that an RTCA kill event has been

revoked by administrative input of a resurrect or reset status, the TECU will transmit

the resurrect or reset command to the aircraft.

a The CIU will provide the aircrew with resurrect or reset audio effect:

1. "SIMULATION IS RESET."

2. "SIMULATION IS RESURRECTED."

b The RTCA status will be removed from the UFD.

c The RTCA status and weapon ID code will be removed from the WPN UTIL

page.

D-103

d The resurrect or reset status will be displayed on the UFD for 8 seconds.

1. SIM RESET indicates that TESS has commanded the aircraft to a reset

state.

2. SIM RESURR indicates that TESS has commanded the aircraft to a resurrect

state.

e The aircraft will be permitted to fire any weapon, and the TTM will power off the

external AKI.

f If a resurrect signal is received, the TECU will update the weapon stores

inventory with the same inventory that was available before the kill was

processed.

g If a reset signal is received, the TECU will update the weapon stores inventory

with the initial inventory that was available upon power up.

D-104

CHECK ON LEARNING

1. How many TMEs are on each aircraft?

ANSWER: ______________________________________________________________________

______________________________________________________________________

2. Tactical missiles will be coded ______ while in the training mode.

ANSWER: ______________________________________________________________________

______________________________________________________________________

3. The TME allows for thermal management of the missiles by allowing for a cumulative time

ON of ______ minutes.

ANSWER: ______________________________________________________________________

______________________________________________________________________

4. With the TRAIN mode selected and a weapon system is actioned the weapons inhibit field

will display ____________.

ANSWER: ______________________________________________________________________

______________________________________________________________________

5. The constraints box will display a _______ centered in the box when the weapon system is

actioned in the training mode.

ANSWER: ______________________________________________________________________

______________________________________________________________________

D-105

D-106

D-107

D-108

D-109

Figure 1. Remote HF Chart

1) Left column, read up to Shooting Aircraft NAV Range to TGT

2) Right to OFFSET angle column

3) Shooting gun-target-line designator LTL. Must be within 60º.

4) Displayed Range is DESIGNATORS MIN RANGE to TGT. If designators range is

less, consider possible max laser delay or reposition aircraft.

D-110

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