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

TM 1-1520-251-10

set-up and shut-down of loading operations. Their use re-

pylon and the ballistic ejector for stores jettison. The PIU

quires that the MODE Switch be placed in the AUTO posi-

provides the interface between the weapons processor

tion and the OPERATE Switch be placed in the OFF posi-

and pylon discrete signals. The pylons can be articulated

tion.

in elevation by hydraulic power in response to pointing

commands from the weapons processor. The pylons are

d. MODE Switching. This three position latching

equipped with hydraulic and electrical quick-disconnect

toggle switch provides three command modes. Center

provisions and contain electrical aircraft interfaces for the

position is OFF, prohibiting any S/MC loading operations.

2.75 in. Aerial Rocket Subsystem, auxiliary fuel tanks,

The down position is used for MANUAL operations which

Hellfire Modular Missile System and servo control of rack

is used only as needed by the operator to address non-

position.

standard operating conditions. The up position is the AU-

4.69.2 Wing Stores Jettison. Each pylon is equipped

TO mode for which Sideloader system use is optimized. In

with an electrically operated ballistic ejector circuit to jetti-

the AUTO mode, the operator is freed from control inputs

son the attached wing store. Refer to Chapter 2, para-

while uploading of ammunition is accomplished. Down-

graph 2.28 for operation.

loading in all operating modes requires the operator to

maintain pressure on the OPERATE toggle switch, in the

4.70 WING STORES PYLON SUBSYSTEM

downward direction, to accomplish the DOWNLOAD op-

OPERATION

eration.

The weapons processor commands the pylons to the re-

e. OPERATE Switching. This three position toggle

quired elevation angles for the various fire control modes.

switch provides three operational states. Center position

The modes include ground stow, flight stow, and articula-

is OFF, prohibiting all Loader Assembly operations except

tion mode.

AUTO ENGAGE and DISENGAGE. The DOWNLOAD

position operates the Sideloader system in the download

4.70.1

Ground Stow. The ground stow mode com-

direction as long as the operator maintains pressure on

mands the pylons to a stow position ( - 5°) so that the wing

the toggle switch. The toggle switch latches in the up

stores are parallel with the ground (level terrain). The

(UPLOAD) position only during AUTO MODE operation.

ground stow mode is automatically commanded when the

While in the MANUAL MODE, operator pressure must be

squat switch indicates GROUND and either a rocket

maintained in either the UPLOAD or DOWNLOAD posi-

launcher or a hellfire launcher is present. The pylons can

tion for continued operation.

be manually ground stowed while in flight using the WPN

UTIL page.

4.68.2 Turret Control Box. The TCB serves as the gun

turret assembly controller performing BIT, mode control,

4.70.2 Flight Mode. The flight mode commands the py-

and turret servo loop closure in response to commands

lons to a single fixed position (+4°). The flight mode is au-

received from the Weapons Processors. The TCB pro-

tomatically commanded ON at takeoff when the squat

vides intermediate power outputs to the Gun Control Box

switch indicates airborne for more than 5 seconds.

(GCB) as well as the Train Rate Sensor (TRS) and eleva-

4.70.3 Articulation. In flight the pylons remain in the

tion actuator located in the gun turret assembly. The TCB

flight mode until missiles or rockets are actioned. Pylons

outputs arming and firing signals to the GCB to control

are independently controlled through a range of +4° to

gun firing. The TCB also processes bolt position status

- 15° in elevation.

from the GCB to derive rounds decrement status which is

output to the Weapons Processors.

4.71 AERIAL ROCKET SUBSYSTEM DESCRIPTION

4.69 WING STORES PYLON SUBSYSTEM

The 2.75 in. Aerial Rocket Subsystem consists of light-

DESCRIPTION

weight rocket launchers mounted on any of the four wing

stations. Remote fuzing capability is incorporated and ac-

The Wing Stores Pylon Subsystem consists of four pylon

commodates use of both penetration and air burst fuze

assemblies, a Selectable Stores Jettison panel, and an

types. Penetration fuzes permit use of variable detonation

Emergency Jettison button.

timing to defeat bunkers and targets masked by forest

canopy. Air burst fuzes permit deployment of payloads at

4.69.1 Wing Store Pylons. The wing store pylon con-

optimum range and height offsets.

sists of a pylon frame, the ejector rack, Pylon Interface

Unit (PIU), pylon actuator, and pylon fairings. The ejector

4.71.1 Rocket Launcher. The M261 lightweight rocket

rack contains attaching lugs for securing the store to the

launcher consists of 19 tubes in a cylindrical configuration

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

4-95

TM 1-1520-251-10

and a hardback with 14 inch lug spacing. Each tube con-

struction may be reduced to 350 ft. Fir-

tains a mechanical detent for holding the rocket until fired.

ing this combination with the

Two electrical interface connectors are provided: one for

ballistics for the M151 warhead will re-

providing firing signals to the rocket motor igniters and the

sult in reduced rocket range.

other for externally setting the rockets fuze circuitry.

• Firing MK66 in a hover or low speed at

4.71.2

2.75 Inch Folding Fin Aerial Rockets. The

a height of less than 7 ft AGL, and for

rocket system is compatible with the MK-66 rocket type.

all other flight conditions of 5 ft AGL,

Available warhead and rocket motor types are listed be-

is not authorized.

low:

• Do not fire rockets with the M433 fuse

MK-66 Rocket Motor/Warheads

in situations where they might fly

closer than 51m from other airborne

• 6PD

- Point Detonation, High Explosive

helicopters. This restriction comes

• 6RC

- Penetration, High Explosive

from Safety of Usage Message, U. S.

• 6MP

- Time, Multi-purpose Submunition

Army Industrial Operations Command

(SOUM IOC) #2-97.

• 6IL

- Time, Illumination

• 6SK

- Time, Smoke

• Due to the possibility of surging the

• 6FL

- Flechette

engines, do not fire rockets from in -

board stations. Fire no more than

4.72

AERIAL ROCKET SUBSYSTEM OPERATION

pairs with two outboard launchers ev-

ery three seconds, or fire with only

one outboard launcher installed with-

CAUTION

out restrictions (ripples permitted).

These are the only conditions per-

Firing of 2.75 inch Hydra-70 rocket con-

mitted.

figuration (fuse/warhead/motor) flight

conditions as follows:

• Use of the MK66 MOD 2 rocket motor

NOTE

is prohibited.

• Re - inventory and attempting to fire 6MP,

• Rockets with jericho nozzles are pro-

6FL, and 6SK rocket types, after a NO -

hibited.

FIRE event is not recommended due to

significant impact on accuracy. The rock-

• Do not use a MK66 rocket motor which

ets should not be used for at least 10

has been continuously stored above

days to allow the M439 fuse to reset.

140° F (60° C).

• Discard any rocket which has been

• The minimum range to target when firing

dropped.

Flechette rocket is 800 meters. The effec-

tive range with MK66 rocket motors is 1

• M439/M261/MK66 at ranges less than

to 3 Km. Effectiveness is reduced with

1000 meters and/or speeds greater

ranges greater than 3 Km.

than 90 kts are not authorized.

• When forward airspeed exceeds 10

KTAS, do not use M229/M423 war-

The Aerial Rocket Subsystem can be employed indepen-

head/fuse combination for engage-

dently by either crewmember or in the cooperative mode

ment of targets under 450 ft distance,

when the active sight is HMD, TADS, or FCR

. The sub-

and ensure the line of fire is clear of

system permits the crewmember to select the warhead

obstruction (trees/buildings) for at

and quantity desired. Articulating wing pylons move in

least 450 ft. When at a hover or for-

elevation based on the selected sight and weapons pro-

ward airspeed is less than 10 KTAS,

cessor ballistics calculations, while the crewmember

engagement distance and the require-

aligns helicopter heading based on steering symbols pro-

ment for line of fire to be clear of ob-

vided on cockpit displays.

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

4-96

Change 4

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4.73 LONGBOW HELLFIRE MODULAR MISSILE

4.74.4 RF Missile Transfer Alignment. Transfer align-

SYSTEM DESCRIPTION

ment (transfer of aircraft inertial data to missile inertial

platform) occurs automatically, whether in - flight or not, at

missile powerup with no pilot action required. The “R” in

The Longbow Hellfire Modular Missile System is the pri-

the missile icon on the WPN page indicates that the mis-

mary weapon on the AH-64D. The system consists of mis-

sile is ready to receive the target.

sile launchers mounted on any of the four wing pylons.

The system employs SAL 1 and SAL 2 and RF Hellfire

4.74.5 RF Missile Target Handover. The missile re-

missiles. The SAL portion of the missile system is capable

ceives targeting information, to include North, East, and

of both PRF and PIM laser code operation.

Down data, from the acquisition source:

4.73.1 Missile Launcher. The M299 missile launcher

• TADS

consists of a hardback, a removable Launcher Electronics

Assembly (LEA), and four missile rails. The launcher is

• FCR

capable of firing all Hellfire missile types.

•

IDM

4.73.2 Hellfire Missile. The missile is comprised of

four major assemblies; the guidance section, the warhead

Handover will occur when the WAS is actioned during a

group, the control section, and the propulsion section.

scan or if WAS is actioned prior to a scan, handover will

Currently the missile system employs two types of SAL

occur after the first scanburst of the scan is completed.

missiles:

• Basic (SAL 1)

4.74.6

RF Missiles Launch. RF missiles may be

• Hellfire II (SAL 2)

launched after target acquisition using targeting data from

the FCR

or the aircraft’s fire control system, TADS, and

targeting data received through the IDM. Automatic mis-

The SAL 1 missile is capable of only PRF laser codes.

sile firing selection from alternating sides of the aircraft is

SAL 2 missiles are capable of both PRF and PIM laser

performed by the WP to minimize the possibility of missile

codes.

radars from interfering with each other. Targets will be as-

signed by the WP to missiles on opposite sides of the air-

4.74 LONGBOW HELLFIRE MODULAR MISSILE

craft, with only one missile per side possessing a target at

SYSTEM OPERATION

any given time. If missiles are only present on one side,

only one missile will be assigned a target.

4.74.1 Target Designation Modes. Laser target desig-

nation may be autonomous or remote. Autonomous is

NOTE

when the target is designated by the aircraft. Remote is

when the target is designated by a remote laser source.

Operation of tactical missiles is not possible

while the training mode is enabled. All tacti-

4.74.2 Missile Launch Types. The aircrew has the ca-

cal missile icons will be coded as NA on the

pability of two types of missile launches; Lock-On-Before

WPN page.

Launch (LOBL) where the missile is tracking prior to

launch, and Lock-On-After Launch (LOAL) where the

4.74.7 TRAIN Mode. The TRAIN mode enacts a soft-

missile acquires and tracks the target after launch.

ware component (Training Mission Emulator [TME])

loaded in the missile launcher that provides the capability

4.74.3 RF Missile Loading. Loading of RF missiles

of simulating missile operations. The TME can simulate

should be balanced between both sides of the aircraft, pri-

the functioning of 4 RF missiles for each launcher. The

marily on outboard launchers. This allows automatic mis-

TME emulates the missile control decision making pro-

sile firing selection from alternating sides of the aircraft to

cess, replicates the missile launch mode selection pro-

minimize the possibility of missile radars from interfering

cessing, target acquisition and tracking function, BIT rou-

with each other. Outboard launcher loading also mini-

tines and thermal management characteristics (fig 4-92).

mizes missile-to-target masking by the aircraft fuselage

During simulated Hellfire missile launch, rocket launch, or

by selecting missiles from alternating sides. Missile-to-tar-

if gun fire occurs, the Communications Interface Unit will

get masking by the fuselage increases crew workload

provide the respective weapons launch/firing audio effect.

associated with keeping missiles within launch

for additional TRAIN mode functionality, refer to para-

constraints.

graph 4.76.

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

Change 2

4-97

TM 1-1520-251-10

(3) Upon actioning the missile system, the TME

transitions to the prelaunch mode and target assignments

from the FCR are passed to the firing missile. In the pre-

launch mode the TME will replicate target acquisition and

tracking characteristics.

(4) HAD Messages and WPN page icons will be

displayed in conjunction with the TME track processing.

(5) A centered “T” (fig 4-93) will be displayed in the

missile constraints box when the training mode is enabled

and the weapon system is actioned.

LBA2555

Figure 4-92. WPN Page with TRAIN ON

1 LOAL OUT−OF−CONSTRAINTS MISSILE BOX

a. Training Mode BIT Functions. The training

2 LOAL IN−CONSTRAINTS MISSILE BOX

mode will replicate PBIT and IBIT functions with appropri-

ate delays built in for simulation accuracy. IBIT may be ini-

3 LOBL OUT−OF−CONSTRAINTS MISSILE BOX

tiated when the system has completed PBIT and is not ac-

4 LOBL IN−CONSTRAINTS MISSILE BOX

tioned. IBIT can be commanded on an aircraft power up,

LBA2585

but will not function until PBIT is complete.

Figure 4-93. Missile Constraints Boxes

b. Thermal Management. A training mode missile

(Training Mode)

is allowed an elapsed ON time of 30 minutes. If this time is

exceeded, an overtemperature (OT) symbol will appear

on the affected missile icon on the WPN page. The timer

(6) The weapon inhibit field will display “SAFE”

can be reset by turning the missile OFF and then back

when the training mode and missile system is actioned

ON.

and the weapon system is safed. Upon arming the weap-

on system, the weapon inhibit field will change to “TRAIN-

c. TME Operational Sequence.

ING”.

NOTE

(7) Upon determining that the firing missile has

met all prelaunch constraints, it will notify the WP, which

The TRAIN button is not displayed until mis-

will display the “in constraints” box on the weapons

sile power is applied.

symbology display. The trigger may then be actioned to

initiate launch commands. The training mode will display

(1) Missile system power is selected in the normal

a successful launch by signalling the WP to blank the fir-

manner.

ing missile icon from the WPN page. The WP will also

cause the target on the FCR page to change to the “shot

at” icon.

(2) When in the training mode, empty launcher

rails will indicate an RF missile present and rails with SAL

training missiles installed will indicate SAL missiles pres-

(8) Successive target engagements may then pro-

ent. Tactical missiles will indicate NA.

ceed as per the tactical system design.

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

4-98

TM 1-1520-251-10

4.75 TACTICAL ENGAGEMENT SIMULATION

type entries are only changed by administrative input to

SYSTEM (TESS)

the TECU and subsequent transmission to the Weapons

Processor or by simulated gun/rocket fire. Simulated in-

ventory is not considered in aircraft gross weight and per-

The TESS is an interactive simulation system that allows

formance calculations.

aircrew training for all of the AH - 64D sight and weapons

systems. The system provides real time casualty assess-

4.75.2 Symbology/HAD Indications. A centered “T”

ment (RTCA) for force - on - force (FOF) training for Com-

(fig 4-94) will be displayed in the Hellfire constraints and

bat Training Center - Instrumentation (CTC - I) and home

rocket steering cursor symbols when TESS training is en-

station instrumentation (HSI). The TESS will interface with

abled and either of these weapons are actioned. The HAD

the ground instrumentation at CTCs and HSI. TESS is ap-

weapon inhibit field will display “SAFE” when the training

portioned into two component systems. The A Kit is com-

mode and missile system is actioned and the weapon sys-

prised of modifications to the AH - 64D software and fixed

tem is safed. Upon arming the weapon system, the weap-

hardware required to interface with the removable B - Kit.

on inhibit field will change to “TRAINING”.

The B - kit contains an eye safe laser rangefinder/MILES

laser designator that physically replaces the TADS laser

rangefinder/designator and laser spot tracker. The eye

safe laser rangefinder and MILES laser designator func-

tionally replace the TADS laser rangefinder/designator.

Laser spot tracking is simulated during TESS training.

The B kit also adds a TADS internal boresight adapter.

Simulated weapons inventory is used to provide realistic

interaction between aircrew, aircraft and targets. TESS in-

corporates the capability to interact with ground based Af-

ter Action Review (AAR), Executive Control (EXCON),

and targeting systems. Information is provided from the

1. INHIBITED CURSOR

2. ARTICULATING CURSOR

aircraft systems to the B Kit for processing and transmis-

sion to the ground instrumentation systems. The ground

instrumentation system elements can provide real - time

LBA3013

status display, administrative control, data archiving, tar-

get position tracking, and real time casualty assessment

(RTCA) of targets. If the TESS electronic control unit

(TECU) is installed without the TESS training missile

(TTM), the aircraft enters a live fire instrumentation config-

(1)

(2)

uration and transmits tactical weapon event data to the

TECU for recording and transmission to ground instru-

mentation systems.When the TECU is installed without

the TTM, the aircraft will enter a live fire instrumentation

configuration that will be used for training. When in this

configuration, the Weapons Processor will transmit tacti-

cal weapon event data to the TECU for recording and

transmission to ground instrumentation systems.

(3)

(4)

LBA3014

4.75.1

Simulated Weapons Inventory. For TESS

training, weapon stores inventory is simulated by adminis-

trative input to the TECU and subsequent transmission to

Figure 4-94. TESS Training Indication

the Weapons Processor. Simulated inventory is uploaded

upon TESS B kit power up and by subsequent administra-

tive input. If any Hellfire missile or rocket is detected dur-

4.75.3

Weapons Effects. When during TESS training

ing the initial stores inventory or if a gun rounds inventory

a simulated Hellfire missile launch, rocket launch, or gun

of greater than 0 is stored, a“LIVE AMMO” indication will

fire occurs, the communications interface unit (CIU) will

be displayed in the HAD weapon inhibit field and TESS

provide the respective weapon launch/firing audio effect

training will not be enabled. The specific type ammunition

and the TESS B kit will provide an external visual effect

will be indicated on the UFD. Gun rounds count and rocket

(firing flash).

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

4-99

TM 1-1520-251-10

4.75.4

Real Time Casualty Assessment. During

• In the event the flashing AKI creates a hazard to

TESS training the TECU determines, either from the laser

flight due to adverse weather conditions, the

warning receiver (LWR) or administrative input, that an

capability to turn off the AKI is available to the

RTCA event has occurred, the TECU will transmit the

aircrew via the WPN Page AKI button (R4) ( fig

RTCA status (hit, near miss or kill) and a weapon ID code

4-96 ). The weapons TRAIN button is not available

to the aircraft and the following will occur:

when TESS is enabled.

• The CIU will provide the aircrew with an RTCA

audio effect (tone with voice messages):

“ding, YOU HAVE BEEN KILLED”

“ding, YOU HAVE BEEN HIT”

“ding, NEAR MISS”

• The RTCA status will be displayed on the UFD (hit

and near miss for 8 seconds, kill continously):

“SIM KILL”

• The RTCA status and weapon ID code will be

made available on the WPN UTIL Page (Fig 4-95).

LBA3016

Figure 4-96. AKI Button on WPN Page

When 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 and the follow-

ing will occur:

• The CIU will provide the aircrew with resurrect or

reset audio effect:

“SIMULATION IS RESET”

“SIMULATION IS RESURRECTED”

•

The RTCA status will be removed from the UFD.

• The RTCA status and weapon ID code will be

LBA3015

removed from the WPN UTIL Page.

• The resurrect or reset status will be displayed on

the UFD for 8 seconds:

Figure 4-95. RTCA Status on WPN UTIL Page

• “SIM RESET” - TESS has commanded the aircraft

to a reset state.

• If a kill status is received, the aircraft will be

inhibited from firing any weapon.

• “SIM RESURR” - TESS has commanded the

aircraft to a resurrect state.

• The TTM will power the external aircraft kill

indicator (AKI) to indicate the RTCA status.

• The aircraft will be permitted to fire any weapon.

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

4-100

TM 1-1520-251-10

• The TTM will power off the external AKI.

• 19 rockets for each installed and inventoried M260

launcher

• If a resurrect is received, the TECU will update the

weapon stores inventory with the same inventory

that was available before the kill was processed.

• 888 gun rounds

• If a reset is received, the TECU will update the

weapon stores inventory with the initial inventory

that was available upon power up.

Resident Hellfire launchers will be placed in the TME

mode resulting in the simulation of RF missiles on each

4.76 WEAPON TRAINING MODE

launch rail in which no missile was inventoried during ini-

tial missile inventory. The TME operation is described in

The weapon training mode is an emulation of weapon sys-

paragraph 4.74.7.

tems operation that allows aircrew training for all AH - 64D

weapon systems. The weapon training mode is activated

and deactivated using the TRAIN button (R4) on the WPN

page (Fig 4-97). This mode is not available when TESS is

Simulated inventories will decrement in response to valid

enabled. The aircrew can enter and exit the weapon train-

firing requests. Inventories are restored each time the

ing mode only when the armament control is in SAFE and

weapon training mode is activated. When SAL training

no weapon system is actioned. Weapon systems opera-

missiles are installed on a Hellfire launcher, all tactical

tions in the weapon training mode are as per the tactical

missiles will be made unavailable. Simulated inventories

design. Any faults or failures experienced by the systems

are not considered in aircraft gross weight and perfor-

will impact the weapon systems operation in the training

mance calculations. A data entry change to the gun

mode as it does in the tactical mode.

rounds count or the use of rocket ’spoofing’ devices will

adversely impact aircraft gross weight.

4.76.2 Symbology/HAD. A centered “T” will be dis-

played in the Hellfire constraints and rocket steering cur-

sor symbols when operating in the weapon training mode

and either of these weapons are actioned (same as

TESS, Figure 4-94). The HAD weapon inhibit field will dis-

play “SAFE” when in the training mode, a weapon system

is actioned and the armament control set to SAFE. Upon

setting the armament control to ARM, the weapon inhibit

field will change to “TRAINING”.

4.76.3 Sound Effects. When operating in the weapon

training mode, and a simulated Hellfire missile launch,

rocket launch, or gun fire occurs, the communications in-

terface unit (CIU) will provide the respective weapon

LBA1977A

launch/firing audio effect.

Figure 4-97. WPN Page TRAIN Button

4.76.4 Safety Considerations. The weapon training

4.76.1 Simulated Weapons Inventory. The armament

mode may be operated with live ammunition at the weap-

subsystem will adopt the following simulated weapon in-

on stations. As such, the weapon training mode employs

ventory when the weapon training mode is selected for

multiple safety features to minimize hazards associated

use:

with its use:

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

4-101

TM 1-1520-251-10

• Application of arm power to weapon stations is

9. CPG WAS - MSL. (Observe HAD messages

inhibited by both the SPs and WPs when the

and WPN page configuration/fault indications.)

weapon training mode is active. In addition,

existing continuous BIT algorithms ensure that

10. Pilot WAS - MSL. (Observe HAD messages

arm power and discrete firecommands are absent

and WPN page configuration/fault indications.)

at these stations when the weapon training mode

is in use. Detection of hazardous conditions via

11. GND ORIDE switch - OFF.

CBIT results in non - availability of the affected

weapon station.

4.78 AWS OPERATING PROCEDURES

• Launch events are simulated; no tactical launch/

firing command are issued to stores or to the gun

WARNING

when the weapon training mode is in use.

• The crew interface imposes a barrier on the

• If 300 or more rounds have been fired

weapon TRAIN button to minimize the potential for

in the preceding ten minutes, and a

inadvertent entry into the weapon training mode

stoppage occurs, personnel must re-

during a live - fire engagement. Likewise, the

main clear of the aircraft for 30 mi-

barrier logic minimizes the potential for accidental

nutes. Aircraft crewmembers should

exit of the weapon training mode during a simu-

remain in the aircraft and continue

lated engagement.

positive gun control.

4.77

WEAPONS OPERATIONAL CHECK

• Failure to adhere to the published gun

duty cycle may result in a catastrophic

NOTE

failure, loss of aircraft, injury or death.

Weapons initialization is used to verify go/

4.78.1 M230E1, 30mm Gun - FIRE GUN.

no-go status of the weapons using fault in-

dications and symbolic messages. It also

WPN page - Select.

places the weapons in a condition that will

require minimal switch selection prior to en-

gagement.

GUN button - Select.

1. SIGHT SELECT - (pilot - HMD) (CPG - TADS).

GUN MODE and BURST LIMIT buttons - Select

As desired.

2. GND ORIDE switch - ON ( required on ground).

Sight Select switch - Select as desired.

3. ARM/SAFE switch - ARM. (Arm power and in-

dications verified by both pilot and CPG.)

Target - Acquire and track.

4. ARM/SAFE switch - SAFE.

WAS - GUN.

5. CPG WAS - GUN. (Observe HAD messages

A/S button - ARM.

and WPN page configuration/fault indications.)

Range - Establish to target.

6. PLT WAS - GUN. (Observe HAD messages and

WPN page configuration/fault indications.)

HAD messages - Observe.

7. CPG ORT WAS - RKT. (Observe HAD mes-

10.

Weapons trigger switch - Press, continue to fire

sages and WPN page configuration/fault indica-

as required.

tions.)

8. PLT WAS - RKT. (Both seats observe COOP

11.

WAS - Deselect as desired.

HAD messages and WPN page configuration/

fault indications.)

12.

A/S button - As desired.

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

4-102

TM 1-1520-251-10

4.78.2 M230E1, 30mm Gun - Dynamic Harmonization

5. Sight Select switch - Select as desired.

(CPG Only).

6. CPG - Acquire and track target.

NOTE

7. ORT WAS - RKT.

Harmonization procedures should be ac-

8. Pilot WAS - RKT.

complished between 500 to 1000 meters

from the target.

9. A/S button - ARM.

WPN page - Select.

10. Range - Establish to target.

GUN button - Select.

11. Pilot - Align rocket steering cursor.

12. HAD messages - Observe.

HARMONIZE button - Select.

13. Pilot Weapons trigger switch - Press.

Sight Select switch - TADS.

14. ORT WAS - Deselect as desired.

Target - Auto track in NFOV DTV/FLIR.

15. Pilot WAS - Deselect as desired.

WAS - GUN.

16. A/S button - As desired.

A/S button - ARM.

4.79.2 Fire Rockets - PILOT OR CPG ONLY MODE.

Range to target - Establish Laser or Manual.

1. WPN page - Select.

2. INVENTORY button - As desired.

Weapons trigger switch - Press. Observe Mean

Point of Impact (MPI) of rounds.

3. QTY button - As desired.

10.

MAN TRK thumbforce controller - Position

4. PEN button - As desired.

dashed reticle over MPI.

5. Sight Select switch - Select as desired.

11.

STORE/UPDATE switch - Store.

6. Target - Acquire and track.

12.

GUN DH NOT VALID status window - Verify not

7. WAS - RKT.

displayed. If present repeat steps 3 through 12.

8. A/S button - ARM.

13.

WAS - Deselect as desired.

9. Range - Establish to target.

14.

A/S button - As desired.

10. Rocket steering cursor - Align.

15.

Sight Select switch - Select as desired.

11. HAD messages - Observe.

4.79 AERIAL ROCKET SUBSYSTEM OPERATING

12. Weapons trigger switch - Press.

PROCEDURES

13. WAS - Deselect as desired.

4.79.1 Fire Rockets - COOPERATIVE MODE.

14. A/S button - As desired.

1. WPN page - Select.

4.80 LONGBOW HELLFIRE MISSILE SYSTEM

OPERATING PROCEDURES

2. INVENTORY button - As desired (CPG).

NOTE

3. QTY button - As desired (CPG).

If FCR was sight selected during this proce-

dure, ensure the MSL TYPE option is reset

4. PEN button - As desired (CPG).

to SAL.

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

4-103

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4.80.1 SAL Missile Engagement (NORMAL - LOBL).

3. TYPE button - SAL.

WPN page - Select.

4. PRI button - Select primary channel as desired.

5. ALT button - Select alternate channel as desi-

MSL button - Select.

red.

TYPE button - SAL.

6. SAL SEL button - Select type of SAL missile as

desired.

PRI button - Select primary channel as desired.

7. MODE button - NORM or MAN.

ALT button - Select alternate channel as desi-

red.

NOTE

SAL SEL button - Select type of SAL missile as

If trajectory is set to LO or HI, ensure that

desired.

ACQ select is the desired target.

8. TRAJ button - Select as desired.

MODE button - NORM or MAN.

9. WAS - MSL.

WAS - MSL.

10. A/S button - ARM.

A/S button - ARM.

11. WPN page or AND - Observe for missile selec-

10.

WPN page or AND - Observe for missile selec-

tion, coding, and ready status.

12. Aircraft - Establish in constraints.

11.

Target - Lase, observe for proper missile track

status.

13. HAD messages - Observe.

12.

Pilot - Establish aircraft in constraints.

NOTE

If performance constraint criteria are not

13.

HAD messages - Observe.

met, the 2nd detent of the weapons trigger

switch may be used to override constraint

NOTE

inhibits and fire missile. Safety inhibits can-

If performance constraint criteria are not

not be overridden.

met, the 2nd detent of the weapons trigger

switch may be used to override constraint

14. Weapons trigger switch - Press.

inhibits and fire missile. Safety inhibits can-

not be overridden.

15. Target - Lase or call for remote designator in ad-

equate time for terminal guidance.

14. Weapons trigger switch - Press.

16. WAS - Deselect as desired.

15. LRFD trigger - Release on missile impact.

17. A/S button - As desired.

16. WAS - Deselect as desired.

4.80.3 SAL Missile Engagement (RIPPLE - LOBL).

17. A/S button - As desired.

1. WPN page - Select.

4.80.2 SAL Missile Engagement (NORMAL - LOAL).

2. MSL button - Select.

1. WPN page - Select.

3. TYPE button - SAL.

2. MSL button - Select.

4. PRI button - Select primary channel as desired.

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

4-104

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5. ALT button - Select alternate channel as desi-

4.80.4 SAL Missile Engagement (RIPPLE - LOAL).

red.

WPN page - Select.

6. SAL SEL button - Select type of SAL missile as

MSL button - Select.

desired.

TYPE button - SAL.

7. MODE button - RIPL.

PRI button - Select primary channel as desired.

8. TRAJ button - Select as desired.

ALT button - Select alternate channel as desi-

9. WAS - MSL.

red.

SAL SEL button - Select type of SAL missile as

10. A/S button - ARM.

desired.

11. WPN page or AND - Observe for missile selec-

MODE button - RIPL.

tion, coding, and ready status.

TRAJ button - Select as desired.

12. Pilot - Establish aircraft in constraints.

WAS - MSL.

13. HAD messages - Observe.

10.

A/S button - ARM.

NOTE

11.

WPN page or AND - Observe for missile selec-

If performance constraint criteria are not

tion, coding, and ready status.

met, the 2nd detent of the weapons trigger

12.

Pilot - Establish aircraft in constraints.

switch may be used to override constraint

inhibits and fire missile. Safety inhibits can-

13.

HAD messages - Observe.

not be overridden.

NOTE

14. Weapons trigger switch - Press and release.

If performance constraint criteria are not

met, the 2nd detent of the weapons trigger

15. Target - Lase and continue lasing until missile

switch may be used to override constraint

impact.

inhibits and fire missile. Safety inhibits can-

not be overridden.

16. Pilot - Establish aircraft in constraints for alter-

nate channel.

14. Weapons trigger switch - Press and release.

15. Target - Lase or call for terminal guidance.

17. HAD messages - Observe.

16. Pilot - Establish aircraft in constraints for alter-

nate channel.

18. Weapons trigger switch - Press and release.

17. HAD messages - Observe.

19. Target - Lase or call for terminal guidance.

18. Weapons trigger switch - Press and release.

19. Target - Lase or call for terminal guidance.

NOTE

Execute steps 12 through 19 until desired

number of missiles has been fired.

Execute steps 12 through 19 until desired

number of missiles has been fired.

20. WAS - Deselect as desired.

21. A/S button - As desired.

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

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4.80.5 RF Missile Engagement (Sight FCR

12. HAD messages - Observe.

1. WPN page - Select.WAS

NOTE

2. MSL button - Select.

If performance constraint criteria are not

met, the 2nd detent of the weapons trigger

3. TYPE button - RF.

switch may be used to override constraint

4. MSL PWR button - As desired.

inhibits and fire missile. Safety inhibits can-

not be overridden.

2nd TARGET INHIBIT button - As desired.

13. Weapons trigger switch - Press and release.

6. LOBL INHIBIT button - As desired.

14. WAS - Deselect as desired.

7. Sight Select switch - Select LINK if visual identi-

fication desired.

15. A/S button - As desired.

8. WAS - MSL.

4.80.7 RFHO Send.

9. A/S button - ARM.

1. NTS - Desired target.

10. WPN page or AND - Observe for missile selec-

tion, coding, and ready status.

2. RFHO button - Select.

11. Aircraft - Establish in constraints.

3. Zone Member Callsign button - Select.

12. HAD messages - Observe.

4. SEND button - Select.

NOTE

4.80.8 RF Missile Engagement (RFHO).

If performance constraint criteria are not

1. UFD - Observe RFHO advisory.

met, the 2nd detent of the weapons trigger

2. TSD page - Select.

switch may be used to override constraint

inhibits and fire missile. Safety inhibits can-

3. REC button - Select.

not be overridden.

4. TSD page - Observe target and NTS symbol.

13. Weapons trigger switch - Press and release.

5. Pilot - Establish aircraft in position for launch.

14. WAS - Deselect as desired.

6. Sight Select switch - FCR.

15. A/S button - As desired.

7. WPN page - Select.

4.80.6 RF Missile Engagement (Sight - TADS).

8. TYPE button - Verify default to RF.

1. Sight Select switch - TADS.

9. WAS - MSL.

2. WPN page - Select.

10. A/S button - ARM.

3. MSL button - Select.

11. WPN page or AND - Observe for missile selec-

tion, coding, and ready status.

4. TYPE button - RF.

12. Pilot - Establish aircraft in constraints.

5. MSL PWR button - As desired.

NOTE

2nd TARGET INHIBIT button - As desired.

If performance constraint criteria are not

7. LOBL INHIBIT button - As desired.

met, the 2nd detent of the weapons trigger

8. WAS - MSL.

switch may be used to override constraint

inhibits and fire missile. Safety inhibits can-

9. A/S button - ARM.

not be overridden.

10. Target - Track and lase target for at least 3 se-

13. Weapon trigger switch - Press and release.

conds or until HAD message TARGET DATA?

blanks.

14. WAS - Deselect as desired.

11. Aircraft - Establish in constraints.

15. A/S button - As desired.

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

4-106

Change 2

TM 1-1520-251-10

4.80.9 RFI Only Operation - Pinned MMA.

12.

IDM auto transmit capability - Set as required.

1. Manually rotate MMA until forward alignment

a. SET page IDM INHBT - Deselect as re-

mark is aligned with pedestal alignment mark.

quired: IDM INHIBIT advisory is not dis-

played and IDM INHIBIT button is non OIP.

NOTE

BLK 1

perform b,c, and d.

MMA movement may be required to engage

locking pin.

b. AUTO REPLY - Set as required.

Press locking pin detent and push locking pin

c. AUTO ACK - Set as required.

until spring is compressed. Hold locking and re-

lease detent. Verify MMA will not move and lock-

d. TACFIRE Net - Set as required.

ing pin remains engaged.

13.

HF RADIO - Set as required.

FCR UTIL page - Verify PINNED.

a. HF RADIO GND OVRD - On or Off.

RFI button - ON.

and/or

4.80.10

Rapid Rearming.

b. HF RADIO SILENT - On or Off.

WPN UTIL page - MSL, RKT, GUN - OFF.

4.80.11

Armament Safing and Postflight Procedures.

A/S button - SAFE.

GND ORIDE button - OFF.

WARNING

TAIL WHEEL button - LOCK.

• Do not preflight or postflight until ar-

PARK BRAKE - Set.

mament systems are safe.

Armament and pylon safety pins - Installed.

• During preflight and after all live fires,

when the AWS has been used, the bar-

Launcher A/S switch(es) - SAFE.

rel will be inspected by the crew for

IDM auto transmit - Disable

cracks.

a. SET page IDM INHBT - Select, IDM IN-

If armament system has been used, check as follows:

HIBIT advisory is displayed.

1. Right EFAB - Open. Check feed system for

rounds.

BLK 1

perform b,c, and d.

2. Gun chute assembly - Check for rounds.

b. AUTO REPLY - Off.

3. Bolt status indicator - FEED (green range).

c. AUTO ACK - Off.

4. Transfer door - Open. Check bolt is to rear, no

d. TACFIRE Net - Not tuned.

rounds in transfer assembly, and chamber clear.

HF RADIO - Disable auto radio transmission

5. Transfer door - Secure.

capability.

6. AWS - General condition and security. Check

a. HF RADIO GND OVRD - Off.

for leaks and proper piston index groove indica-

tion.

7. Launcher ARM/SAFE switches - SAFE.

b. HF RADIO SILENT - On.

8. Wing stores pylon - Check for unexpended ord-

10.

Rearming - Monitor.

nance.

11.

Launcher A/S switch(es) - ARM.

9. Armament and pylon safety pins - Install.

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

Change 3

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Section III. ACTIVE AND PASSIVE DEFENSE EQUIPMENT

4.81 INTRODUCTION

Defense Subsystems consists of the following compo-

nents:

INTRODUCTION. Active and Passive Defense Equip-

• AN/APR-39A(V)4 Radar Signal Detecting Set

ment (fig 4-98) consists of active countermeasures and

• AN/AVR-2A Laser Signal Detecting Set

electronic passive threat detection as well as airframe fea-

• AN/APR-48A Radar Frequency Interferometer

tures such as armor, IR paint, and the Wire Strike Protec-

(RFI)

tion System (WSPS). This section describes the Active

4.81.2 Active Defense Subsystems. The Active De-

and Passive Defense Subsystems that are operated from

fense Subsystems consists of the following components:

dedicated controls and the MPD. There is no power up

• AN/ALQ-136(V)5 Radar Jammer

BIT for the ASE equipment.

• AN/ALQ-144A(V)3 Infrared Jammer (IRJAM)

4.81.1 Passive Defense Subsystems. The Passive

• M-141 Chaff Dispenser (CHAFF)

LASER DETECTION SYSTEM

RADAR DETECTION

SENSORS (AVR−2A)

SYSTEM (RDS)

SENSOR (APR−39A(V)4)

RADAR DETECTION SYSTEM (RDS)

SENSOR (APR−39A(V)4)

CHAFF DISPENSER (M141)

RADAR DETECTION

LASER DETECTION SYSTEM

SYSTEM (RDS)

SENSORS (AVR−2A)

RADAR DETECTION SYSTEM (RDS)

SENSOR (APR−39A(V)4)

RADAR JAMMER

RECEIVE ANTENNA

RADAR DETECTION SYSTEM (RDS)

(ALQ136(V)5)

SENSOR (APR−39A(V)4) (2 PLACES)

RADAR JAMMER

TRANSMIT ANTENNA

RADAR FREQUENCY INTERFEROMETER (RFI)

(ALQ136(V)5)

(APR−48A)

IR JAMMER TRANSMITTER

(ALQ−144A)

RADAR DETECTION

SYSTEM (RDS)

SENSOR (APR−39A(V)4)

(2 PLACES)

CHAFF DISPENSER (M141)

LASER DETECTION SYSTEM

SENSORS (AVR−2A)

RDS BLADE ANTENNA

(4 PLACES)

(APR−39A(V)4)

LBA1969

Figure 4-98. ASE Equipment Locations

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

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TM 1-1520-251-10

4.82 AN/APR-39A(V)4 RADAR SIGNAL DETECTING

• Threat Count

SET

• Threat Priority

• Threat Type

CAUTION

• New Threat Signal - Bold for 3 Seconds

• Threat Signal No Longer Detected - Ghosted for

To prevent damage to the receiver detec-

10 Seconds

tor crystals, assure that the radar warn-

• Threat Mode (Search, Acquisition, Track, or Lock -

ing set antennas are at least 60 meters

On/Launch)

from active ground radar antennas or 6

meters from active airborne radar anten-

• Correlated C/D bank Threat

nas. Allow an extra margin for new, un-

• Threat Azimuth

usual, or high power emitters.

In addition, the digital processor also generates a corre-

4.82.1

System Description. The AN/APR-39A(V)4

sponding computer-synthesized voice threat message

Radar Signal Detecting Set (RSDS) is a passive electron-

which is sent to the communication interface unit for dis-

ic warfare system that provides visual and aural indica-

semination to the pilot and CPG headsets. Selection and

tions of the presence of and bearing to active radar trans-

volume control of this audio is provided by the commu-

mitters. The system is omnidirectional and provides for

nication control panel in each crewstation. If the received

signal parameters do not match a threat in the EID files,

the detection, identification, classification, and prioritiza-

the digital processor generates the threat data for a “U” to

tion of pulse and pulse doppler radar emitters and also

indicate an unknown threat. The digital processor also

supplies moding and bearing information about these

processes threat data inputs from the laser detecting set

emitters. The RSDS detects those pulse radar signals

AN/AVR-2A for display on the MPDs and annunciation

usually associated with hostile fire control radars operat-

over the ICS. When dense signal environments cause the

ing in the C/D and E-M frequency bands. These pulse ra-

system to operate in a degraded (reduced sensitivity)

dar signals are seen as potential threats to the helicopter

mode, the system informs the operator with the voice

and are displayed as symbols on the MPDs. The system

message “Threat Detection Degraded,” heard over the

also generates computer-synthesized voice threat mes-

ICS. When the system sensitivity returns to normal, the

sages for audible indications of potential threats. These

voice message “Threat Detection Restored” will be enun-

voice threat messages, heard over the Intercommunica-

ciated over the ICS.

tions System (ICS), and the display symbols, seen on the

MPDs, occur simultaneously to indicate the type of threat,

4.83 AN/AVR-2A LASER SIGNAL DETECTING SET

threat mode, and its relative bearing to the helicopter. The

system consists of a digital processor, two radar receivers

4.83.1 AN/AVR-2A Laser Detecting Set (LDS) System

(one forward and one aft), four hi-band spiral antenna-de-

Description. The AN/AVR-2A Laser Detecting Set

tectors (two forward and two aft), and a lo-band blade an-

(LDS) is a passive electronic warfare system that detects,

tenna. The RSDS employs a removable User Data Mod-

locates, and identifies hostile laser-aided weapon threats

ule (UDM) which is mounted in the top of the digital

fired from both airborne and ground-based platforms. The

processor. The UDM contains the classified portion of the

LDS is a frequency extension of the RSDS and interfaces

system Operational Flight Program (OFP) and the classi-

with the RSDS to function as an integrated Radar Laser

fied Emitter Identification Data (EID) files. The EID files

Warning Receiver (RLWR). The system detects optical

contain the threat library which includes threat signal

radiation illuminating the helicopter, processes this laser

parametric data.

data into laser threat messages, and sends these mes-

sages to the RSDS digital processor. The digital proces-

4.82.2 System Operation. The RSDS uses the four hi-

sor processes these inputs to provide for both visual and

band antenna-detectors and the lo-band (C/D) blade an-

aural threat indications for the system. The LDS can also

tenna to receive RF energy from pulse radars. Each of the

be used with both the RSDS and the Air-to-Ground En-

three spiral elements within an antenna-detector receive

gagement System (AGES) to provide an engagement

RF signals in their respective band and supply it to the de-

simulation system, in the operational training mode. The

tector circuits. A radar warning receiver track file that is

system is composed of five components: four laser sensor

transferred from the digital processor to the display pro-

units and an Interface Unit Comparator (IUC). The four

cessors contains threat information from up to 10 RLWR

sensor units are strategically located around the helicop-

detected emitters and includes the following data:

ter with two mounted forward, facing forward and two

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

4-109

TM 1-1520-251-10

mounted aft, facing aft. Each sensor unit provides a 100°

a. Training. During training operation, the LDS op-

Field-Of-View (FOV) and ±45° of coverage in elevation.

erates as a detecting system in a MILES environment and

This configuration provides for 360° coverage in azimuth

the operating software within the LDS does not recognize

and ±45° in elevation about the helicopter with substantial

.904 micron gallium arsenide (GaAs) MILES laser hits as

overlap. Each sensor unit contains four separate laser de-

actual laser threats.

tectors. They are located under a special optical window

and supply coverage of three different spectral regions:

b. Tactical. During tactical operation, the LDS de-

Electro-Optical (EO) bands I, II, and III. Two detectors are

tects, identifies, and characterizes three different types of

employed in the band III region, the band IIIA and band

optical signals. Each sensor unit provides laser threat

IIIB detectors, to provide the required band III detection

detection in three different spectral bands; band I, band II,

coverage.

and band III. When a sensor unit detects optical, coherent

radiation within its FOV, it provides band and pulse char-

acteristics as laser threat data to the IUC. The IUC further

processes this threat data, thus comparing received sig-

4.83.2 System Operation. The sensor units perform

nal characteristics with stored parameters. It then deter-

the actual laser detection function for the system and con-

mines the existence of a laser threat, threat type, and

tain the necessary electronics to process detected laser

Angle-Of-Arrival (AOA) (quadrant resolution only).

signals. If a validated laser signal is detected, a threat

message containing the laser type (band I, II, or III) is sent

This threat data is sent as laser threat messages to the

to the IUC for processing. Each sensor unit contains opti-

RSDS digital processor for manipulation to provide visual

cal and electrical Built-In Test (BIT) electronics to perform

threat indications on the MPD ASE and TSD pages and

a self-test upon command from the IUC. When a self-test

aural voice threat messages over the helicopter ICS. Both

command is received, the sensor unit disables detection

the visual and aural threat indications provide threat type

of all externally generated signals and performs a self-

and relative position information to the crewmembers.

test. When the self-test is completed, the appropriate

pass or fail message is sent to the IUC for processing and

4.84 AN/APR-48A RADAR FREQUENCY

normal operation is resumed. The IUC is located in the LH

INTERFEROMETER (RFI)

aft avionics bay. It is mounted just forward of the RSDS

digital processor with which it directly interfaces. The IUC

4.84.1 System Description. The AN/APR-48A Radar

provides the control and timing necessary for the interface

Frequency Interferometer (RFI) is a passive Electronic

with the sensor units. It also provides the interface with the

Support Measure (ESM) system that provides for the

RSDS. The LDS was designed to operate in conjunction

detection, acquisition, identification, classification, loca-

with the RSDS, therefore, being an integral part of the

tion, and prioritization of radar emitters. The system de-

RSDS. The IUC provides the majority of the wiring inter-

tects and processes pulse, pulse doppler, and Continuous

face between the RSDS and the associated helicopter

Wave (CW) radar signals operating in a currently classi-

systems. If the IUC is removed from the helicopter, a

fied frequency range. The RFI is primarily an offensive

jumper box must be installed in the system or an alternate

system providing narrow FOV target cueing for onboard

connector configuration employed to permit the RSDS to

and offboard sights/sensors for the accurate and timely

operate. The LDS employs a removable User Data Mod-

employment of weapons. It also supplies highly effective

ule (UDM) which is mounted in the face of the IUC. The

defensive threat warning capability for the ASE suite. The

UDM contains the classified operational software required

high sensitivity of the system provides for not only main

for tactical operation of the system. This software gets

beam signal detection, but also sidelobe and/or backlobe

downloaded into volatile memory within the sensor units

signal detection as well. The system is designed to detect

during system power-up and initialization, and the sensor

Low Probability of Intercept (LPI) signals and to detect the

units then become classified. When system power is re-

threat long before it detects the helicopter. It is capable of

moved, the sensor units zeroize the classified software

threat acquisition well beyond threat lethal range and pro-

and become unclassified components. The removal of

vides for masked detection of threats based on its mount-

system power and the UDM for the IUC effectively declas-

ing location above the rotor mast. The RFI provides for

sifies the system. The LDS has the capability to operate in

360° coverage about the helicopter for coarse DF and

two modes, training and tactical. In the training mode, the

instantaneous 90° coverage for precision fine DF. The

system operates with AGES in the Multiple Integrated La-

coarse DF routing employs amplitude DF techniques and

ser Engagement System (MILES) to provide the crew-

utilizes four coarse DF antenna elements, comparing the

members with a realistic combat tactical training system

amplitude of adjacent antenna channels to determine sig-

that closely simulates the effect of weapon engagements.

nal AOA. The system utilizes a five antenna baseline for

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

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TM 1-1520-251-10

the phase interferometry to perform the accurate fine DF

• RF, PRI, Sigma PRI, PW Limits

(8 Specific

routine Pulse Spacing (PS).

Parameters)

• Scan Type

• Parametric Volume (Ambiguity Resolver)

• Scan Rate

• Priority

• Time In Main Beam (TIMB)

• Identification Code

• Flags ( Hostile/Friendly, Airborne, CW, etc.)

4.84.2 System Operation. The identification proces-

sing allows for the handling of multi-beam emitters that

4.85 AN/ALQ-136(V)5 RADAR JAMMER

output more than one type of RF signal either simulta-

COUNTERMEASURES SET (RJAM)

neously or on a time scheduled basis. The RFI correlates

these signals so that only one threat ID is displayed with

4.85.1 System Description. The AN/ALQ-136(V)5 Ra-

its corresponding moding information (search, acquisition,

dar Jammer Countermeasures Set (RJAM) is an active

track, lock-on/launch, etc.) on the MPD. The sophisticated

Electronic Counter Measure (ECM) system designed to

signal processing allows for the detection and identifica-

protest the helicopter against certain Anti-Aircraft Artillery

tion of frequency and Pulse Repetition Interval (PRI) agile

(AAA) and Surface-to-Air Missile (SAM) threats. It is a

emitters. The RFI processor controls the RFI receiver and

self-contained system that receives, detects, analyzes,

the RFI antenna to detect and classify threats. It develops

and processes those pulse radar signals usually

both coarse and fine azimuth locations of emitters, based

associated with hostile fire control radars, and initiates the

on aspect angle and threat frequency. The RFI antenna

appropriate jamming in an attempt to effectively counter

consists of two array sets; a coarse array set and a fine

the detected threats. The RJAM system consists of a Re-

array set. The coarse array provides 360° coverage in azi-

ceiver/Transmitter (R/T) and two antennas; one antenna

muth about the helicopter, while the fine array phase an-

used for reception and one antenna used for transmis-

tennas are switched to forward, left, or right channels for

sion. The system performs effectively as both a detection

Intermediate Frequency (IF) processing. The RFI receiver

system and a jamming system for pulse radar threats. The

measures pulse parameters from four inputs received

receive antenna receives pulse radar signals and supplies

from the RFI antenna providing 360° coverage. The sys-

them to the R/T receiver circuits via a special low-loss

tem performs accurate parametric data measurement for

coaxial cable. The receiver processes this Radio Fre-

precise, unambiguous identification and classification of

quency (RF) energy and extracts the video (pulses) from

detected emitters. The threat parametric data scrutinized

it. This video is filtered, limited, amplified, and detected,

by the processor for detected signals includes:

and provided to the processor section of the R/T for analy-

• Frequency

sis. The processor compares the resultant video with the

stored threat signal parameters to determine whether the

• Bandwidth

received signal originated from a threat. These signal pa-

rameters include:

• Pulse Width (PW)

• Pulse Width

The emitter acquisition process involves the evaluation of

• Pulse Spacing

received pulse parameters and the sorting of these pulse

parameters into emitters. Once emitter parameter mea-

• Pulse Repetition Interval

surement is complete, the emitters are identified utilizing a

• Signal Strength

threat library stored on the UDM. The system must then

resolve multiple matches and perform the correlation of

• Modulation Type

multiple signals emanating from one emitter. The UDM is

mounted in the face of the RFI processor. It contains the

• Center Frequency

classified portion of the operational software, a Dwell Se-

quence Monitor Table (DSMT), and an Emitter ID table

If it is determined that a threat exists, the processor quer-

(EIDT). The DSMT controls the sequence of RF band

ies the stored jamming parameters table for the appropri-

monitoring, with each entry in the table containing a fre-

ate jamming profile. If one exists, the jamming parameters

quency band at which to dwell, a length of time in which to

are extracted, to include center frequency, modulation

dwell, and the number of sort windows. The EIDT accom-

type, and jamming technique, and sent to the transmitter

modates 100 threat entries with each entry containing the

section. The transmitter section generates the appropriate

following information:

jamming signals and applies them to the transmit antenna

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

4-111

TM 1-1520-251-10

for radiation via another low-loss coaxial cable. The Sys-

4.86 AN/ALQ-144A(V)3 INFRARED JAMMER

tem can detect, process, and jam multiple threats in a mul-

COUNTERMEASURES SET (IRJAM)

tiplex fashion using one set of antennas; however, the cur-

rent system configuration only provides for forward sector

WARNING

coverage for pulse radar threats.

Do not continuously look at the infrared

countermeasures transmitter during op-

eration, or for a period of 1 minute from a

distance of less than 3 feet. Skin expo-

WARNING

sure to countermeasure radiation for

longer than 10 seconds at a distance

less than 4 inches shall be avoided.

The AN/ALQ-136(V)5 system poses a po-

tential RF radiation hazard to personnel

CAUTION

due to its operating frequency range and

• The infrared countermeasures set (IR

transmitter output power. When the sys-

Jammer) should be operated for a

tem is powered up, personnel should re-

minimum of 15 minutes after energiz-

main clear of the transmit antenna by a

ing the system, otherwise life of the

minimum of 10 feet to prevent overexpo-

source may be drastically shortened.

sure to high frequency RF radiation and

• The IR jammer can be damaged if the

its corresponding effects.

IR jammer is not turned off for one

minute via the MPD prior to removing

power from the aircraft.

4.85.2 System Operation. The system radiates during

4.86.1 System Description. The AN/ALQ-144A(V)3

self-test (at a reduced power setting) and when stimulated

Infrared Jammer (IRJAM) is an active infrared counter-

by a threat signal while in the operate mode. The RJAM

measure set that operates as an omnidirectional IR trans-

receiver/transmitter contains a WAR/TNG switch which is

mitter to jam heat-seeking IR missiles. The system con-

located on the face of the unit. The switch is a lever-

sists of an IR transmitter located on the fairing

locked, two position switch which is safety wired in the de-

immediately aft of the rotor mast. The transmitter consists

sired position.

of an IR source, low and high speed modulators, covert

window, and housing. The transmitter generates IR ener-

gy, modulates it, and then passes it through the covert

window in the form of invisible IR energy. The transmis-

a. Training. In a training environment, the switch is

sion of unwanted wavelengths of electromagnetic energy,

safety wired in the TNG position. With TNG selected, the

such as visible light, is blocked by the covert windows.

system provides very limited frequency band coverage,

The radiation is modulated mechanically at low and high

frequencies. This IR energy is used to confuse IR seeking

utilizes non-operational test programs, and generates un-

missiles.

classified, non-operational jamming signals. The primary

purpose of the training mode is to exercise the system in

4.86.2 System Operation. The transmitter requires

a peacetime environment without compromising its actual

approximately a 1 minute warm-up period. The IR jammer

operational capability, which is classified.

is equipped with the following switches and indicators

which can be accessed and observed when the BIT indi-

cator panel is removed from the transmitter. RST/FXD/

SWP Switch - allows the operator to reset the BIT indica-

b. Tactical. In a wartime environment, the switch is

tors (RST), select fixed (FXD) frequency mode of

safety wired in the WAR position. With WAR selected, the

operation, and select sweep (SWP) frequency mode of

system provides full-up operational capability to include

operation. After using this switch to reset the BIT indica-

complete frequency band coverage, operational ECM

tors, ensure that the switch is set to the required jam pro-

programs, and actual jamming signals.

gram mode (FXD or SWP).

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

4-112

Change 4

TM 1-1520-251-10

Jam Program Selector Switch - this thumb wheel switch

screws. The retainer plate contains slots to permit the im-

selects the jam program for transmitter operation. Jam

pulse cartridges to mate with the breech plate contact pins

Program Indicator - this indicator displays the selected

and grounding clips to enable electrical contact to fire the

jam program through an opening in the wall of the card

cartridges.

cage. Elapsed Time Indicator - this indictor monitors the

operation time of the unit and provides a digital readout in

c. Chaff Safety Switch. The chaff safety switch is

hours.

located on the tailboom about 3 inches forward of the

chaff dispenser and provides another means of safing the

4.87 M141 GENERAL PURPOSE AIRCRAFT

system to prevent inadvertent expenditure of impulse/

DISPENSER (CHAFF)

chaff cartridges. When the safety pin is installed in the

switch, chaff arm power is disconnected from the chaff

dispenser and the chaff test connector. When the safety

WARNING

pin is removed from the switch, arm power is distributed to

both the dispenser and the test connector. The SP serves

Avoid exposure to high concentrations

as the primary processing center for the chaff dispenser

of chaff; high concentrations of chaff can

system management control. The SP monitors direct sta-

cause temporary irritation to eyes and

tus inputs from the cyclic chaff dispense switches and

throat.

controls the firing of chaff based on these inputs. The SP

receives chaff control selections made on the MPDs from

4.87.1 System Description. The M141 General Pur-

the DP via MUX bus channel 1. It controls arm power to

pose Aircraft Dispenser (CHAFF) is an active ECM sys-

the chaff dispenser and monitors arm power status

tem designed to protect the helicopter from AAA, SAM,

through ELC #1.

and Airborne Intercept (AI) radar threats. The system can

dispense up to 30 chaff cartridges (MI) as a countermea-

4.87.2 System Operation. The M141 system can dis-

sure against radar guided weapons systems. The chaff

pense chaff in 1 of 2 modes of operation: manual or pro-

system is basically composed of three components, the

gram. In the MANUAL mode, the system dispenses one

dispenser assembly, the payload module, and the chaff

chaff cartridge when either of the chaff dispense switches

safety switch.

is actioned. The programming of the chaff burst/salvo set-

tings can be accomplished on the MPD ASE UTIL page or

a. Dispenser Assembly. The dispenser assembly

can be uploaded into the system via the DTC. Regardless

consists of a breech plate, sequencer switch module, and

of the selected mode, the dispensing of chaff cartridges

a chaff/flare select switch. The breech plate contains 30

must be manually initiated by one of the crewmembers,

contact pins and 15 spring grounding clips, which mate

thus requiring crewmember interaction and the latency

with the impulse cartridges when a payload module is

associated with that interaction.

installed. The contact pins are wired to the sequencer

switch electrical connector. The breech plate also con-

4.88 DEDICATED CONTROLS

tains 2 guide pins and 2 fastener receptacles to align and

secure the payload module to the dispenser assembly.

The passive defense subsystem interfaces with 2 dedi-

The sequencer switch module converts dispense signals

cated controls that augment the MPD format controls. The

to 1 dispenser breech plate contact pin to electrically fire

RLWR volume control on the COMM panel and the chaff

the impulse cartridge. The sequencer switch contains 2

dispense position on the cyclic.

rotary stepping switches, 2 circuit cards, and 2 electrical

connectors. The rotary stepping switch resets to its initial

starting sequence when a payload module is installed, the

4.88.1 COMM Panel - RLWR Volume Control. The

safety pin is removed, and electrical power is applied to

RLWR volume control (fig 3-5) provides independent vol-

the dispenser assembly.

ume control of the RLWR voice messages, allowing the

crew the capability to set the audio output to a comfortable

b. Payload Module. The payload module consists

level. This volume control knob cannot be pulled to dis-

of a molded fiberglass block with compartments for 30

able audio.

cartridges and a metal retainer plate. The block also con-

tains 2 quick disconnect bolts to secure the payload mod-

4.88.2 CHAFF (C) Button. The CHAFF (C) button (fig

ule to the dispenser assembly. The retainer plate is to be

4-99) is located on both the pilot and CPG cyclic grips. If

installed after the cartridges are loaded. The retainer plate

the CHAFF is armed, chaff can be dispensed by depress-

fits onto the front of the block and is secured by 2 retaining

ing the CHAFF (C) button.

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

4-113

TM 1-1520-251-10

CHAFF

LBA−1971

LBA5172

Figure 4-99. Cyclic Grip-Chaff Dispense Button

Figure 4-100A.

[

BLK 2

ASE Page]

4.89 AIRCRAFT SURVIVABILITY EQUIPMENT (ASE)

PAGE

The ASE page contains the following unique buttons:

The ASE page (figs [

BLK 1

4-100] and [

BLK 2

• T1

CHAFF button

4-100A ] ) can be accessed from the MENU page, TSD

• T2

ASE button

UTIL page, or the WPN page.

•

ASE UTIL button

• L1

CHAFF MODE button

• L2

[

BLK 1

RFI button]

• L3

[

BLK 1

AUTOPAGE SRH button]

• L4

[

BLK 1

AUTOPAGE ACQ button]

• L5

[

BLK 1

AUTOPAGE TRK button]

• L6

[

BLK 1

AUTOPAGE OFF button]

• R1

[

BLK 1

IRJAM button]

• R4

[

BLK 1

CAQ button]

• R6

[

BLK 1

RLWR button]

• R1

[

BLK 2

AUTOPAGE button]

• R5

[

BLK 2

CAQ button]

• B4

RJAM OFF button

• B5

RJAM STBY button

• B6

RJAM OPER button

4.89.1 CHAFF Button. The CHAFF button modes the

LBA0418

chaff dispense system between SAFE and ARM. Chaff

SAFE/ARM status is also displayed on the WPN and ASE

Figure

4-100.

[

BLK 1

ASE Page]

UTIL pages.

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

4-114

Change 3

TM 1-1520-251-10

4.89.2 ASE Button. The ASE button displays the ASE

4.89.11 CAQ Select Button. It is barriered when the

page. The ASE page presents RFI and RLWR threat in-

RFI is powered OFF or sight selected is FCR.

dications, as well as subsystem controls.

4.89.11A [

BLK 2

AUTOPAGE Button. The AUTO-

PAGE button is used to select the state or condition of an

4.89.3 ASE UTIL Button. The ASE UTIL button dis-

acquiring threat system which causes autopaging of

plays the ASE UTIL page and presents chaff program

threat warning information.] The available selections are:

controls and other utility controls.

• SEARCH

4.89.4 CHAFF MODE Button. The CHAFF MODE but-

• ACQUISITION

ton modes the chaff dispense system between PRO-

• TRACK

GRAM and MANUAL. The PROGRAM mode provides

the ability to dispense chaff cartridges according to a pre-

• OFF

determined program when the chaff dispense switch is ac-

4.89.12 [

BLK 1

RLWR Button. The RLWR button

tioned. The MANUAL mode will dispense one chaff car-

powers the RLWR ON or OFF. Powering the RLWR ON

tridge each time the chaff dispense switch is actioned.

enables up to seven detected RLWR threats to be dis-

played on the inside of the ASE footprint and in the status

4.89.5 [

BLK 1

RFI Button. The RFI button is only

window.]

presented when the FCR is powered ON. The RFI button

powers the RFI ON or OFF. Powering the RFI ON enables

4.89.13 RJAM OFF Button. The RJAM OFF button

up to ten detected RFI threats to be displayed on the out-

powers the Radar Jammer OFF.

side of the ASE footprint and in the status window. RFI

ON/OFF is also presented on the FCR UTIL page and

NOTE

WPN UTIL page.]

RJAM STBY and OPER are not present

when RJAM is OFF on the TSD and VIDEO

4.89.6 [

BLK 1

AUTOPAGE SRH Button. The AU-

pages.

TOPAGE SRH button sets the ASE Autopaging threshold

to search. ASE Autopage triggering occurs when a new

4.89.14 RJAM STBY Button. The RJAM STBY button

RLWR is detected in the search mode or a threat transi-

sets the Radar Jammer in the standby mode for warm-up

tions to a higher mode.]

period of 3 minutes. A deselected JAM button is pres-

ented on the TSD and VIDEO pages which can be used to

mode the RJAM between standby and operate. Selecting

4.89.7 [

BLK 1

AUTOPAGE ACQ Button. The AU-

the OFF button will interrupt the standby mode warm up

TOPAGE ACQ button sets the ASE Autopaging threshold

period.

to acquisition. ASE Autopage triggering occurs when a

new RLWR is detected in the acquisition mode or a threat

4.89.15 RJAM OPER Button. The RJAM OPER but-

transitions to a higher mode.]

ton sets the Radar Jammer in the operate mode. A se-

lected JAM button is presented on the TSD and VIDEO

pages which can be used to mode the RJAM between op-

4.89.8 [

BLK 1

AUTOPAGE TRK Button. The AU-

erate and standby. The system processor reverts the

TOPAGE TRK button sets the ASE Autopaging threshold

RJAM back to standby if operate is selected before the

to track. ASE Autopage triggering occurs when a new

warm up period.

RLWR threat is detected in the track mode or a threat tran-

sitions to a higher mode.]

4.89.15A [

BLK 2

Combined Emitter Status Win-

dow. The Combined Emitter status window displays

4.89.9 [

BLK 1

AUTOPAGE OFF Button. The AU-

the number of emitters reported from the RFI (up to 10)

TOPAGE OFF button sets the ASE Autopaging to OFF.]

and the number of emitters reported from the RWR or

RLWR (up to 7). The RFI, RWR or RLWR line is not dis-

played if the equipment is not installed or power on. If

4.89.10 [

BLK 1

IRJAM Button. The IRJAM button

none of these boxes are power on, then the status window

powers the IR Jammer ON or OFF. When powered on, the

is not displayed.]

IR Jammer will begin to function after a one minute warm-

up period. While in the warm up mode, the status window

4.89.16 CHAFF Status Window. The CHAFF status

will reflect WARM, then change to OPER when complete.

window displays the remaining number of chaff cartridges

If the IRJAM is not installed, the IRJAM button is not dis-

decremented by the system processor. It is also displayed

played.]

on the WPN page.

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

Change 2

4-115

TM 1-1520-251-10

4.89.16A [

BLK 2

IRJAM Status Window. The IR-

JAM status window displays the state of the IR Jammer

(OPER or WARM). This status window is not displayed if

the IR Jammer is not installed or off.]

4.89.17 ASE Footprint. The ASE footprint is the circu-

lar area in the center of the ASE page. It is used to segre-

gate the RLWR and RFI threat indications. RLWR threat

indications appear on the inside of the ASE footprint and

RFI threat indications appear on the outside of the ASE

footprint. A rectangular threat footprint is also displayed

on the TSD page to segregate RLWR and RFI threat in-

dications.

4.89.18 RLWR or RFI Threat Indications. The RLWR/

RFI threat indications are displayed on the ASE footprint.

The symbology presented will identify the threats, show

the threat bearings relative to the ownship, and indicate

the mode of the threats (i.e. search, acquisition, track, or

launch). Friendly emitters are displayed in CYAN and en-

emy/gray emitters are displayed in YELLOW. Threat in-

LBA2486A

dications are also displayed on the TSD page.

Figure 4-101. ASE Symbology

4.89.19 Radar Jammer Icon. The Radar Jammer Icon

is displayed as a flashing lightening bolt in the center of

the Ownship Icon whenever the Radar Jammer is trans-

RWR and Other Than No.1 Emitter RFI Mode Icons.

mitting.

1. Search Mode. The search mode is identified by

4.89.20 Display Freeze Cue. The line through the A/C

the target symbol being unboxed.

Heading Status Window and the Next WPT Heading Sta-

tus Window indicates the ASE Symbology is not updating

2. Acquisition Mode. The acquisition mode is identi-

with respect to the aircraft. Reference Chapter 3, Section

fied by the target symbol being boxed.

III.

3. Tracking Mode. The tracking mode is identified

4.89.21 A/C Heading Map Freeze Cue. Reference

by the symbol being boxed and a dashed line between

Chapter 3, Section III.

Ownship and target symbol.

4.89.22 Ownship Icon. Reference Chapter 3, Section

4. Launch Mode. The launch mode is identified by

III.

the flashing box around the target symbol.

4.89.23 Deleted.

5. Uncorrelated RWR Detect. Identified by icon be-

ing oriented directly in front of ownship. Displays same as

4.89.24 Next WPT Heading Map Freeze Cue. Refer-

others (may or may not be boxed) but bearing unknown.

ence Chapter 3, Section III.

Laser Warning Receiver Mode Icons.

4.89.25 ASE Symbology. The symbology presented

(fig 4-101) will identify the threats, show the threat bear-

6. Ranging. Identified by icon being boxed.

ings relative to the ownship, and indicate the mode of the

threats (i.e. search, acquisition, track, or launch). Threat

mode icons are displayed in YELLOW. These icons will be

7. Designating. Identified by the icon being boxed

displayed on the ASE footprint of the ASE page and TSD

with dashed line between Ownship and target symbol.

page. RFI icons are displayed on the outside of the foot-

print and RLWR icons are displayed inside the footprint.

8. Beaming. Identified by the flashing box around

The FCR page only displays RFI icons (para.4.45.1).

the icon.

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

4-116

Change 2

TM 1-1520-251-10

4.89.26 Load Maintenance Panel. Chaff inventory is

performed by the system processor and can be manually

updated by the ground crew via the load maintenance

panel or the air crew via the MPD. The ground crew enters

the CHAFF option from the display main menu via the

load maintenance panel key pad. After the ground crew

enters the number of loaded chaff cartridges (0-30) and

enter via the key pad, the load maintenance panel trans-

mits the new chaff count to the system processor repre-

senting the cartridge count via the load maintenance pan-

el serial link. The system processor monitors and updates

the display processor and load maintenance panel with

cartridge count status.

4.90 ASE UTIL PAGE

The ASE UTIL Page (figs [

BLK 1

4-102] and [

BLK 2

4-102A ] ) is as depicted below and is used to configure

LBA5173

the ASE Subsystem:

Figure 4-102A.

[

BLK 2

ASE UTIL Page]

The ASE UTIL page contains the following unique but-

tons:

• L2

BURST COUNT button

• L3

BURST INTERVAL button

• L4

SALVO COUNT button

• L5

SALVO INTERVAL button

• L6

CARTRIDGES button

• R1

RFI TRAIN button

• R2

RFI MODE button

• R3

[

BLK 2

IRJAM button]

• R4

[

BLK 2

RLWR button]

• R5

RLWR VOICE button

NOTE

BURST COUNT, BURST INTERVAL, SAL-

VO COUNT, and SALVO INTERVAL but-

tons are present if CHAFF MODE is set to

PROGRAM.

LBA0417

4.90.2 BURST COUNT Button. The BURST COUNT

button enables programming of 1, 2, 3, 4, 6, or 8 chaff car-

tridges to be fired per salvo.

4.90.3

BURST INTERVAL Button. The BURST IN-

TERVAL button enables programming of 0.1, 0.2, 0.3, or

Figure

4-102.

[

BLK 1

ASE UTIL Page]

0.4 tenths of seconds between chaff bursts.

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

Change 2

4-117

TM 1-1520-251-10

4.90.4 SALVO COUNT Button. The SALVO COUNT

4.90.10 RLWR VOICE Button. The RLWR VOICE but-

button enables programming of 1, 2, 4, 8, or CONTINU-

ton modes the RLWR system between NORM or TERSE

OUS salvos per activation of the Chaff Dispense switch.

voice messages.

4.90.5

SALVO INTERVAL Button. The SALVO IN-

4.91

DISPENSER KIT OPERATION

TERVAL button enables programming of 1, 2, 3, 4, 5, 8, or

RANDOM time intervals in seconds, between salvos.

RANDOM is actually a pseudo random sequence set at 3,

CAUTION

5, 2, and 4 seconds.

Operation is totally independent of air-

4.90.6

CARTRIDGES Button. The Chaff CAR-

craft ARM/SAFE power.

TRIDGES button provides a means to enter a number

from 0 to 30, indicating the number of cartridges loaded

1. CARTRIDGES - Set for number of chaff car-

into the M-141 Chaff Dispenser through the KU. This is an

tridges in payload module.

alternative to entering the data via the Load Maintenance

Panel (LMP).

2. CHAFF MODE - Program - Select BURST

4.90.7 RFI TRAIN Button. The RFI TRAIN button is

COUNT, BURST INTERVAL, SALVO COUNT,

only presented when the RFI is powered on. RFI TRAIN

and SALVO INTERVAL - As desired.

modes the RFI system to the training mode. RFI TRAIN is

also presented on the FCR UTIL page.

3. CHAFF - ARM.

4.90.8 RFI MODE Button. The RFI MODE button is

4. Chaff Dispense button - Press and release.

only presented when the RFI is powered on. RFI MODE

modes the RFI system to display ALL or HOSTILE

5. CHAFF - SAFE.

threats. RFI MODE is also presented on the FCR UTIL

page.

4.92

ASE OPERATIONAL CHECK

4.90.8 [

BLK 2

IRJAM Button. The IRJAM button

powers the IR Jammer ON or OFF. When powered on, the

1. WPN ASE page - Power ON ASE systems as

IR Jammer will begin to function after a one minute warm-

desired.

up period. While in the warm up mode, the status window

will reflect WARM, then change to OPER when complete.

2. DMS IBIT page - Perform IBITs and verify “NO

If the IRJAM is not installed, the IRJAM button is not dis-

FAULTS FOUND” for:

played.]

a. RJAM.

4.90.9

[

BLK 2

RLWR Button. The RLWR button

powers the RLWR ON or OFF. Powering the RLWR ON

b. RLWR.

enables up to seven detected RLWR threats to be dis-

played on the inside of the ASE footprint and in the status

window.]

3. UFD - Check WCA for advisories.

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

4-118

Change 3

TM 1-1520-251-10

CHAPTER 5

OPERATING LIMITS AND RESTRICTIONS

Section I. GENERAL

5.1 PURPOSE

See current Interim Statement of Airworthiness Qualifica-

tion (ISAQ) for additional limitations/restrictions.

This chapter identifies operating limits and restrictions

5.2.1 Exceeding Operational Limits. Any time an op-

that will be observed during ground and flight operations.

erational limit is exceeded, an appropriate entry shall be

made on DA Form 2408-13-1. Entry will state what limit or

limits were exceeded, range, time beyond limit and any

5.2 GENERAL

additional data that would aid maintenance personnel in

the maintenance action that may be required. The DMS

The operating limitations set forth in this chapter are the

provides engine performance evaluation and fault detec-

direct results of design analysis, test and operational ex-

tion.

periences. Normal, transient and maximum limits are dis-

played via the MPDs to the crew with corresponding digi-

5.2.2 Minimum Crew Requirements. The minimum

tal readouts, vertical scales, timers and color coding.

crew required to fly the helicopter is a pilot and a copilot. A

Compliance with restrictions and limits outlined in this

technical observer may be authorized to occupy the CPG

chapter will allow the pilot to safely perform the assigned

station during ground maintenance at the discretion of the

missions and to derive maximum utility from the aircraft.

commander.

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

5-1

TM 1-1520-251-10

Section II. SYSTEM LIMITS

5.3 INSTRUMENT MARKINGS

• Wide: entire tape is RED; indicates the limit above

or below which continued operation is likely to

5.3.1 Instrument Marking Code. Operating limitations

cause damage or shorten component life.

and ranges are illustrated by graphic symbols and color

coding of systems instruments on the ENG page (fig 5-1).

Graphic symbols are displayed (fig 5-2) in conjunction

with each vertical tape to provide instrument limit mark-

ings:

• RED horizontal bar and diamond symbols indicate

the maximum operating limit.

• YELLOW horizontal bar indicates the beginning of

a sub - range cautionary operating range.

MAXIMUM LIMIT MARKING

SUBRANGE LIMIT MARKING

MAXIMUM LIMIT

MARKING (NR)

LBA3037

LBA−3036

Figure 5-2. Instrument Limit Marking Symbols

Figure 5-1. ENG Page Ground Format

5.3.2 Rotor Speed (N_R) Limitations. Main rotor speed

Digital readouts are color coded according to normal

(N_R %) (fig 5-3 ) is displayed as a vertical tape and a digi-

(GREEN), cautionary (YELLOW), maximum (RED) oper-

tal readout (within the tape) on the ENG page. The N_R in-

ating ranges of the system. Readouts are displayed in

strument graphic is displayed in conjunction with the N_P

WHITE when data is not in a valid range. Systems indica-

instrument of both engines. The following limits and their

tions displayed with a vertical tape incorporate color cod-

associated symbols apply to N_R.

ing and shape coding (width of the tape) to delineate the

normal, cautionary, maximum operating ranges of the

LIMIT - NR (%) Digital Readout

system. Tapes are displayed in three different widths and

colors based on the current operating range:

110

Maximum (>110 RED)

• Narrow: entire tape is GREEN; indicates safe or

106 - 110

Transient operation (YELLOW)

normal range of operation.

106

High rotor warning annunciated

• Medium: entire tape is YELLOW; indicates range

95 - 105

Normal operation (GREEN)

when special attention should be given to opera-

0-94

Transient operation (RED)

tion.

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

5-2

TM 1-1520-251-10

NOTE

120%

It is normal for oil pressure to be high during

first start when oil is cold. Oil pressure

110% MAXIMUM LIMIT

should return to normal after 5 minutes op-

106%110% TRANSIENT

eration at idle speed. During these 5 min-

105% MAXIMUM OF

utes, do not accelerate above ground idle

speed until oil pressure can be held at or be-

NORMAL OPERATING RANGE

low maximum limit throughout acceleration.

94% MINIMUM OF

LIMITS - ENGINE1 OR 2 OIL PRESSURE (PSI)

NORMAL OPERATING RANGE

120

Maximum (>120 RED w/box)

23 - 120

Normal operation (GREEN)

Minimum, PWR LVR at IDLE <23 RED

5.3.4 Hydraulic Systems. Primary (PRI) utility (UTIL),

LBA3038

and accumulator (ACC) hydraulic (HYD) pressure (PSI)

are displayed as digital readouts on the ENG and aircraft

SYS pages. The limits for all hydraulic systems digital

readouts are as follows:

LIMITS - HYDRAULIC PRESSURE

Figure

5-3. NR Vertical Tapes

>3400

Transient operation permitted for 5 se-

conds (YELLOW). ( ≥ 5 seconds RED

w/box)

3310 - 3400

Transient - operation permitted for 5

5.3.3

Engine Lubrication System. Engine oil (EN-

minutes (YELLOW) ( ≥ 5 minutes RED

GINE OIL) pressure (PSI) is displayed as digital readouts

w/box)

on the ENG and aircraft SYS pages. Engine lubrication oil

2750 - 3300

Normal operation (GREEN)

pressure digital readout limitations during stabilized pow-

1260

Minimum (<1260 RED w/box)

er settings are as follows:

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

5-3

TM 1-1520-251-10

Section III. POWER LIMITS

5.4 ENGINE POWER LIMITATIONS

701

Engine.

NOTE

The following limitations present absolute limitations for

the pneumatic engine starter and engine(s) power regard-

Each engine incorporates a steady state

less of the atmospheric conditions. For variation in power

TGT limiter control which limits engine op-

available with temperature and pressure altitude, refer to

eration according to the following indicated

the charts in the Performance Data Chapter (Chapter 7 for

TGT values:

and Chapter 7A for

engines).

Dual Engine: 860 +/ - 12 (848 - 872)° C

Single Engine: 917 +/ - 12 (905 - 929)° C

The limit value within these ranges can

5.4.1

Engine Starter Limitations. The pneumatic

change over a period time.

starter is capable of making the number of consecutive

start cycles listed below, when exposed to the environ-

LIMITS - 701 TGT (°C) DIGITAL READOUT

mental conditions specified, with an interval of at least 60

965

Maximum (> 965 RED)

seconds between the completion of one cycle and the be-

ginning of the next cycle. A starting cycle is the interval

920 - 965

Single engine transient, 12 second limit

(YELLOW)

from start initiation and acceleration of the output drive

shaft, from zero rpm, to starter dropout. The 60 second

865 - 919

Single engine contingency, 2.5 minute

delay between start attempts applies when the first at-

limit (YELLOW)

tempt is aborted for any reason and it applies regardless

869

Maximum during start

of the duration of the first attempt. If motoring is required

808 - 864

Intermediate rated power, 30 minute

for an emergency, the 60 second delay does not apply.

limit (YELLOW)

807

Maximum continuous power

a. Engine Starts At Ambient Temperatures of 61

0-807

Normal operation (GREEN)

°F (16 °C) and Below. Two consecutive start cycles

may be made, followed by a 3 minute rest period, followed

by two additional consecutive start cycles. A 30 minute

rest period is then required before any additional

starts.

999 °C

965 °C MAXIMUM LIMIT

b. Engine Starts At Ambient Temperatures Above

61 °F (16 °C). Two consecutive start cycles may be

808 °C 864 °C TRANSIENT

made. A 30 minute rest period is then required before any

RANGE (30 MINUTE)

additional starts.

807 °C MAXIMUM LIMIT

c. Dual Engine Starts. Dual engine starts are pro-

NORMAL OPERATING RANGE

hibited.

5.4.2 Engine Temperature Limitations (

and

engines). Engine Turbine Gas Temperature (TGT °C) is

displayed (figs 5-4, 5-5, 5-6, 5-7) as a vertical tape and a

0 °C

digital readout (within the tape) for each engine on the

ENG page. The configuration of the instrument graphic is

LBA3039

based upon the type engines installed and current mode

of operation, dual engine (DE) or single engine (SE). The

following limits and their associated symbols apply to TGT

limitations.

Figure

5-4. DE, 701 TGT Vertical Tapes

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

5-4

TM 1-1520-251-10

999° C

965° C MAXIMUM LIMIT

949° C MAXIMUM LIMIT

920 965 ° C TRANSIENT

RANGE (12 SECOND LIMIT)

871 878° C TRANSIENT

RANGE (10 MINUTE LIMIT)

865 919° C TRANSIENT

RANGE (2.5 MINUTE LIMIT)

811 870° C TRANSIENT

808 864° C TRANSIENT

RANGE (30 MINUTE LIMIT)

807° C MAXIMUM OF

810° C MAXIMUM OF

NORMAL OPERATING RANGE

0° C

LBA3040

LBA3041

Figure 5-5. SE, 701 TGT Vertical Tapes

Figure

5-6.

DE, 701C TGT Vertical Tapes

701C

Engine.

NOTE

999° C

Each engine incorporates a steady state

949° C MAXIMUM LIMIT

TGT limiter control which limits engine op-

eration according to the following indicated

897 949° C TRANSIENT

RANGE (12 SECOND LIMIT)

TGT values:

Dual Engine: 867 +/ - 12 (855 - 879)° C

879 896° C TRANSIENT

RANGE (2.5 MINUTE LIMIT)

Single Engine: 896 +/ - 12 (884 - 908)° C

The limit value within these ranges can

871 878° C TRANSIENT

RANGE (10 MINUTE LIMIT)

change over a period time.

811 870° C TRANSIENT

RANGE (30 MINUTE LIMIT)

LIMITS - 701C TGT (°C) DIGITAL READOUT

810° C MAXIMUM OF

NORMAL OPERATING RANGE

949

Maximum (>949 RED)

0° C

897 - 949

Single engine transient, 12 second limit

(YELLOW)

LBA3042

879 - 896

Single engine contingency, 2.5 minute

limit (YELLOW)

Figure

5-7.

SE, 701C TGT Vertical Tapes

871 - 878

Intermediate rated power, 10 minute

limit (YELLOW)

851

Maximum during start

5.4.3

Engine Power Turbine Speed, (N_P). Engine

811 - 870

Intermediate rated power, 30 minute

power turbine speed (N_P %) is displayed (fig 5-8 ) as a

limit (YELLOW)

vertical tape and a digital readout for each engine on the

ENG page. The N_P digital readouts are displayed sepa-

810

Maximum continuous power

rately from the vertical tapes. The following limits and their

0-810

Normal operation (GREEN)

associated symbols apply to engine N_P:

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

5-5

TM 1-1520-251-10

NOTE

LIMITS - ENGINE1 OR 2 N_G (%) DIGITAL

READOUT

• It is not abnormal to observe a N_P1 and

105.1

Maximum (>105.1 RED)

N_P2 speed split during autorotation de-

scent when the engines are fully de-

102.3 -

Transient 12 second limit (YELLOW)

coupled from the transmission. A speed

105.1

increase from 101% reference to 103% is

63.1 -

Normal operation (GREEN)

possible for

only.

102.2

Minimum engine out warning annun-

• Maximum N_P vertical tape indication is

ciated (<63.0 RED w/box).

120 %.

5.4.5 Engine Torque. Engine torque (TORQUE %) is

displayed (figs 5-9 thru 5-12) as a vertical tape and a digi-

LIMITS - ENGINE1 OR 2 NP (%) Digital Readouts

tal readout for each engine on the ENG page. The config-

uration of the instrument graphic is based upon main rotor

121

Maximum (>121 RED w/box).

speed (N_R) and the current mode of operation, dual en-

115

Engine overspeed annunciated

gine (DE) or single engine (SE). The following limits and

their associated symbols apply to engine torque limita-

106 - 121

Transient operation, 12 seconds

tions:

(YELLOW, w/box at 107).

0-105

Normal operation (GREEN)

LIMITS - TORQUE (%) DIGITAL READOUT

WITH N_R LESS THAN 50%

Maximum (>30 RED)

0-30

Normal operation (GREEN).

120%

106%120% TRANSIENT

130%

105% MAXIMUM OF

NORMAL OPERATING RANGE

30% MAXIMUM,

DO NOT EXCEED WITH LESS

THAN 50% NR

LBA3043A

LBA2618

Figure 5-8. NP Vertical Tapes

Figure 5-9. Torque Vertical Tapes, NR below 50%

LIMITS - TORQUE (%) DIGITAL READOUT

5.4.4

Engine Gas Generator (N_G) Limitations. En-

WITH N_R LESS THAN 90%

gine gas generator speed (N_G %) is displayed as a digital

Maximum (>70 RED)

readout for each engine on the ENG page. The following

0-70

Normal operation (GREEN).

limits apply to engine N_G:

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

5-6

TM 1-1520-251-10

5.5 AUXILIARY POWER UNIT (APU) OPERATING

CAUTION

LIMITS

Do not operate the APU for more than 5

minutes at a main transmission oil tem-

CAUTION

perature of 120 - 130° C. Shut down APU

to prevent damaging accessory gearbox

components.

Avoid prolonged operation at 94% - 96%

N_R with the APU running. The APU clutch

5.5.2 Extended APU Ground Operations. During pro-

will oscillate from engaged to disen-

longed ground operations greater than 30 minutes, ob-

gaged. This creates high loads on the

serve XMSN TEMP 1 and XMSN TEMP 2 on the SYS

clutch and shall be avoided.

page. If the temperatures exceed 130° C (266° F) the

APU shall be shutdown and the transmission fluid allowed

to cool for 30 minutes prior to resuming APU ground op-

5.5.1

APU Operating Limitations. APU operation is

erations; or transmission fluid may be cooled by operating

prohibited during normal flight. After a fault or aborted

an engine with rotor turning. There is no requirement to

start, wait 30 seconds after compressor has stopped be-

remove transmission side panels during extended APU

fore attempting another start. After 2 consecutive start at-

ground operations. However, the transmission fluid will

tempts, wait 20 minutes before third start attempt. No

not get as hot under high ambient temperature conditions

more than 3 start attempts are permitted in one hour.

if the side panels are removed.

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

5-8

TM 1-1520-251-10

Section IV. LOADING LIMITS

5.6 CENTER OF GRAVITY LIMITS

5.7 WEIGHT LIMITATIONS

Center of gravity limits for the helicopter to which this

The aircraft maximum gross weight is 20,260 pounds, ex-

manual applies and instructions for computation of center

cept for non - tactical ferry flights, which may not exceed

of the gravity are contained in Chapter 6.

23,000 pounds.

Section V. AIRSPEED LIMITS

5.8 AIRSPEED OPERATING LIMITS

5.8.6 Maximum Airspeed with Symmetrically Loaded

External Fuel Tanks (2 or 4) Installed. Maximum air-

See figure 5-13 to determine the Never Exceed Velocity

speed with symmetrically loaded external fuel tanks (2 or

(V_NE) as a function of weight, altitude and temperature.

4) installed is 130 KTAS.

Additional airspeed limits listed below.

5.8.7 Maximum Airspeed for Stores Jettison. Jetti-

5.8.1

Airspeed Limits For Autorotation. Maximum

son of external armament stores is not authorized except

airspeed for autorotation is 145 KTAS.

for emergency conditions and then only from unacceler-

ated flight during:

5.8.2

Airspeed Limits With One Engine Inoperati-

ve. Maximum airspeed with one engine inoperative is

a. Maximum airspeed for stores jettison is 130 KTAS.

the greater of:

b. Hover to 45 KTAS (minimize side slip, if possible).

67% of VNE determined from figure 5-13 using the

GROSS WEIGHT line.

45 to 130 KTAS (ball centered, if possible).

b. The speed for minimum power determined from

the Chapter 7

or Chapter 7A

cruise charts using

5.8.8

Maximum Airspeed for External Tanks Jetti-

the MAX END/MAX R/C lines.

son. Jettison of external fuel tanks is not authorized ex-

cept for emergency conditions and then only from air-

5.8.3 Maximum Airspeeds During Manual Stabilator

speeds less than 100 KTAS. Jettison from level flight if

Operations. Maximum airspeeds are based on stabila-

possible, and if not, jettison at an airspeed which mini-

tor position. The stabilator position and nominal airspeed

mizes the rate of descent at the time of jettison.

restrictions are displayed on the FLT page, FLT SET

page, as well as the SYS page, as described in paragraph

5.8.9 Airspeed Operating Limits Chart. Referring to

2.68.

figure 5-13, sheet 1, note that a FAT scale and pressure

altitude scale are provided in the upper grid and a weight

5.8.4

Maximum Rearward/Sideward Flight

scale and true airspeed scale on the lower grid. Using the

Speed. Maximum rearward/sideward flight speed is 45

observed FAT and altitude obtained from the aircraft in-

KTAS for all gross weights.

struments and the calculated aircraft weight, enter the

chart as directed in the chart example. Determine maxi-

5.8.5

Maximum Airspeed for Searchlight Exten-

mum true airspeed at the left side of the lower grid. To de-

sion. The searchlight is designed for operation (extend/

termine the maximum indicated airspeed, refer to figure

retract/rotate) at speeds up to 90 knots. However, as long

5-13, sheet 2 and enter as directed in the chart example

as operation is not attempted, the lighthead can be left in

with the KTAS and density altitude determined from figure

any extended position at speeds up to 200 knots.

5-13, sheet 1.

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

5-9

TM 1-1520-251-10

20000

AIRSPEED OPERATING LIMITS

101% ROTOR RPM

LEVEL FLIGHT

15000

EXAMPLE 1

10000

WANTED

MAXIMUM ALLOWED TRUE AIRSPEED

AND DENSITY ALTITUDE

KNOWN

PRESSURE ALTITUDE = 6000 FEET

5000

FAT = 10°C

GROSS WEIGHT = 21,000 POUNDS

METHOD

ENTER AT 6000 FEET

PRESSURE ALTITUDE

MOVE RIGHT TO FAT = 10°C

MOVE DOWN TO 21,000 POUND

GROSS WEIGHT OR MACH LIMIT

FAT, WHICHEVER IS ENCOUNTERED

FIRST. MOVE LEFT AT 21,000 LB LINE

AND READ TRUE

AIRSPEED = 150 KNOTS

MOVE DOWN, READ DENSITY

ALTITUDE = 6800 FEET

100

EXAMPLE 2

WANTED

110

MAXIMUM ALLOWED TRUE AIRSPEED

MACH NO. LIMITS

AND DENSITY ALTITUDE

KNOWN

120

FAT: 60°

PRESSURE ALTITUDE = 8000 FEET

FAT = 20°C

GROSS WEIGHT = 18,000 POUNDS

130

METHOD

ENTER AT 8000 FEET

140

PRESSURE ALTITUDE

MOVE RIGHT TO FAT = 20°C

MOVE DOWN TO 18,000 POUND

150

GROSS WEIGHT OR MACH LIMIT

FAT, IN THIS CASE, THE MACH

LIMIT FAT LINE IS ENCOUNTERED

FIRST. MOVE LEFT AT 20°C LINE

160

AND READ TRUE AIRSPEED = 172 KNOTS

MOVE DOWN, READ DENSITY

ALTITUDE = 5500 FEET

170

180

190

200

AIRSPEED

OPERATING LIMITS AH64D

210

220

5000

10000

15000

20000

DATA BASIS:

DERIVED FROM FLIGHT TEST

DENSITY ALTITUDE ~ FEET

LBA01891

Figure

5-13.

Airspeed Operating Limits Chart (Sheet 1 of 2)

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

5-10

TM 1-1520-251-10

Section VI. MANEUVERING LIMITS

5.9 MANEUVERING LIMITS

5.9.4 External Tanks. With external fuel tanks (2 or 4)

containing fuel, symmetrically installed, the following re-

For normal load factors, refer to figure 5-14. Intentional

strictions apply:

maneuvers beyond attitudes ± 30° in pitch or ± 60° in roll

are prohibited.

a. Normal load factor of 2 Gs shall not be exceeded.

5.9.1

Prevent Excessive Tail Rotor Loads. Avoid

b. Maneuvers are limited to those required to takeoff,

large pedal step inputs in arresting right hovering/low

climb to optimum altitude, heading/course corrections, ob-

speed yawing turns greater than 60°/second. This is to

stacle avoidance, descend and land.

prevent excessive tail rotor drive system loads.

230 gal external fuel tanks shall be in the flight stow

5.9.2

Flight with Canopy Enclosure Open. Flight,

position (4° nose-up) with respect to the waterline (WL).

hovering flight and air taxiing with the canopy enclosure

open are prohibited, except for smoke/fume elimination.

d. Rapid and step-shaped pedal inputs in excess of

1/2 in. shall be avoided.

5.9.3 Landing Limits. Do not complete a landing on

terrain which produces a pitch attitude change from a hov-

e. Operation of the aircraft with the 230 - gallon Ex-

er greater than 7° nose up or 12° nose down; or a roll atti-

tended Range Fuel System (ERFS) is prohibited during

tude greater than 10°.

operations where hostile fire is highly probable.

Section VII. ENVIRONMENTAL RESTRICTIONS

5.10 ENVIRONMENTAL RESTRICTIONS

5.10.3

Flight In Instrument Meteorological Condi-

tions. The aircraft is not qualified for IMC flight. The

5.10.1 Flight into Turbulence. Flight into known or

back - up flight instruments are required to be installed and

forecast extreme turbulence or into known severe turbu-

operational for all flights.

lence is prohibited.

5.10.2 Flight In Icing Conditions. Intentional flights

into moderate icing conditions are prohibited. Flight into

5.10.4

Rotor Limitations

- Start and Stop Lim-

known or forecast trace or light icing conditions is autho-

rized and not considered a hazard unless the condition is

its. Maximum wind velocity for rotor start or stop is 45

encountered for an extended period (over one hour).

knots.

Section VIII. OTHER LIMITS

5.11 WING STORES CONFIGURATION

5.12 USE OF FORCE TRIM.

For authorized wing stores configurations refer to Chapter

Force trim will not be selected OFF except in a failed or

or 7A

, figure 7-26

or 7A-28

partial failed mode.

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

5-12

Change 4

TM 1-1520-251-10

CHAPTER 6

WEIGHT/BALANCE AND LOADING

Section I.

GENERAL

6.1 INTRODUCTION

b. Pilot Crew Station. The pilot station extends

from fuselage station 115.0 to station 168.0. The pilot

This chapter provides information required for helicopter

nominal centroid is at fuselage station 143.3, but the seat

loading and computing weight and balance.

can be adjusted so the pilot centroid can vary from fuse-

lage station 142.8 to 143.8. This produces a small mo-

6.1.1 Extent Of Coverage. This chapter contains suffi-

ment variation and should be ignored.

cient instructions and data so that an aviator, knowing the

basic weight and moment of the helicopter, can compute

NOTE

any combination of weight and balance using the pre-

When loading these two bays, check for ex-

scribed Army charts and forms.

ceeding the aft CG limit.

6.1.2 Helicopter Class. Army AH-64D Apache helicop-

c. Left Aft Equipment Storage Bay. The aft stor-

ter is in Class 2. Additional directives governing weight

age bay is on the left side from fuselage station 280.0 to

and balance of Class 2 aircraft forms and records are con-

station 310.0 and can be loaded to 15 pounds per square

tained in AR

95-1, DA PAM

738-751 and TM

foot with a capacity of 60 pounds. The floor area is

55-1500-342-23.

approximately 4.2 square feet and the volume is approxi-

mately 12.1 cubic feet. Floor tiedown fittings are in place

6.1.3

Helicopter Bays and Stations. The helicopter

to accommodate the flyaway kit.

has many bays; most of them contain electronic or other

equipment. Figure 6-1 shows the general location of the

major bays and equipment. The boundaries of all bays

d. Survival Equipment Stowage Bay. The survival

and a listing of the equipment in each bay are provided in

equipment stowage bay is reached from either side. From

the helicopter records Chart A - Basic Weight Checklist,

fuselage station 310.0 to station 340.0, it can be loaded to

DD form 365-1. The bays of primary concern to pilot,

15 pounds per square foot with a capacity of 100 pounds.

when loading, are the crew stations, left aft storage bay,

A single concentrated load of 45 pounds with a load densi-

survival kit bay and left and right flyaway kit bays. These

ty of 45 pounds per square foot may be carried. The floor

bays may contain personal items or extra equipment not

area is approximately 7.8 square feet and the volume is

accounted for in the basic weight (para 6.2.1). Any addi-

approximately 21.4 cubic feet. Floor tiedown fittings are in

tional items must be entered on the Weight and Balance

place to accommodate the survival kit.

Form F (DD365-4).

e. Flyaway Storage Bays. The Flyaway Storage

a. CPG Crew Station. The CPG station extends

Bays are located on the left and right sides of the aircraft

from fuselage station 35.5 to station 115.0. The CPG nom-

from fuselage stations 155.0 to 189.0. The bays have a

inal centroid is at fuselage station 82.2, but the seat can

load capacity of 33.5 pounds per bay. The floor area is

be adjusted so the CPG centroid can vary from fuselage

approximately 2 square feet with a volume of 3.5 cubic

station 81.9 to 82.8. This produces a small moment varia-

feet per bay. There are no tie down fittings in the bays. The

tion and should be ignored.

bays are capable of removal from the aircraft.

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

6-1

TM 1-1520-251-10

Section II. WEIGHT AND BALANCE

6.2 WEIGHT AND BALANCE

b. Arm. For balance purposes, the term Arm is the

horizontal distance (in inches) from the reference datum

to the center of gravity of a given item. For special cases,

This section contains information needed to compute the

Arm can be determined from Figure 6-1. For the AH-64D

weight and balance for an individual helicopter by using

Apache helicopter, Arm and Fuselage Station (FS) are the

the prescribed standard charts and forms.

same.

6.2.1 Weight Definitions. The three major terms used

when defining helicopter weight: basic weight, operating

NOTE

weight and gross weight are described in the following

Throughout this chapter, moment/100 fig-

paragraphs.

ures have been rounded off to the nearest

whole number. When moments from other

NOTE

sources are being used, they must be di-

The basic weight of the helicopter will vary

vided by 100 and rounded off.

with mission requirements and structural

modifications such as addition or removal of

c. Moment. Moment is the weight of an item multi-

Longbow kit, wing pylons, peculiar kits,

plied by its Arm. For the AH-64D Apache helicopter, mo-

30mm gun, turret, ammo handling system,

ment divided by 100 (moment/100) is used to simplify cal-

etc. A continuing record of an individual heli-

culations by reducing the number of digits.

copter’s basic weight is maintained on Chart

C - Basic Weight and Balance Record, DD

d. Average Arm. Average Arm is the Arm obtained

Form 365-3.

by adding the weights and the moments of a number of

items and dividing the total moment by the total weight.

a. Basic Weight. The normal basic weight of this

helicopter includes wing pylons, all fixed operating equip-

e. Basic Moment. Basic moment is the sum of the

ment, 30mm gun, all oil and trapped fuel. It is only neces-

moments of all items making up the basic weight with re-

sary to add the variables or expendables to these items

spect to the helicopter reference datum.

for the missions. Basic weight can be entered into the

DTC via the AMPS and then loaded into the aircraft sys-

tem via the DTU.

f. Center of Gravity (CG). CG is the point about

which the helicopter would balance if suspended. Dis-

b. Operating Weight. The operating weight of the

tance from the reference datum is found by dividing the

helicopter is the basic weight plus those variables which

total moment by the gross weight of the helicopter.

remain substantially constant for a particular mission.

These items include crew, baggage, rocket launchers,

g. CG Limits. The CG limits are the extremes of

Hellfire launchers, any emergency or extra equipment that

movement to which the helicopter CG can travel without

may be required.

endangering controllability or structural integrity. The CG

of the loaded helicopter must remain within these limits at

c. Gross Weight. The gross weight is the total

takeoff, throughout flight and during landing. The forward

weight of the helicopter and its contents.

and aft CG limits are displayed on the PERF page (para

7.2.8

or 7A.2.8

. The actual CG will be displayed

6.2.2

Balance Definitions. The seven major terms

under CG and a vertical bar will move between the limits

used when defining helicopter balance: reference datum,

in direct proportion to the actual CG.

arm, moment, average arm, basic moment, center of

gravity (CG) and CG limits are described in the following

6.2.3 Chart C - Basic Weight and Balance Record, DD

paragraphs.

Form 365-3. Chart C is a continuous history of the basic

weight and moment resulting from structural and equip-

a. Reference Datum. The reference datum is an

ment changes in service. At all times, the last weight and

imaginary vertical plane from which all horizontal dis-

moment/100 entries are considered the current weight

tances are measured (in inches) for balance purposes.

and balance status of the basic helicopter.

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

6-3

TM 1-1520-251-10

6.2.4 Loading Data. The loading data in this chapter is

6.2.6 CG Management. This paragraph contains fuel

intended to provide information necessary to work loading

management methods that can be used to maintain CG

problems for the helicopter. From this data, weight and

limits in flight and during the expending of external stores

moment/100 are obtained for all variable load items and

for some helicopter configurations. Table 6-1 lists CG shift

are added to the current basic weight and moment/100

as stores are expended. When the storage bays are used

from Chart C (DD Form 365-3) to determine the gross

for miscellaneous equipment, it is possible to cause an aft

weight moment/100 using Form F (DD Form 365-4). The

CG condition.

effect on helicopter CG of expending the fuel and arma-

ment in logical sequence may be checked by subtracting

a. Fuel Loading. The helicopter takeoff CG can be

the weight and moment/100 of each item from the takeoff

moved by loading either tank with more fuel than the oth-

gross weight and moment/100; then, checking the new

er. Example: to move the CG forward, fill the forward tank

moment (or helicopter CG) with the CG limits chart. This

(1012 pounds of JP-4) and reduce fuel load in the aft tank

check should be made to determine if the CG will remain

depending on CG shift required. For some missions, it

within limits during the entire flight. Refer to paragraph

may be necessary to reduce the stowed weight.

6.2.1 for helicopter CG management.

b. Table of Expendables. The table of expend-

ables (table 6-1) provides a guide for quick definition of in-

termediate flight CG as stores/fuel are expended at vari-

6.2.5 Weight and Balance Clearance Form F, DD Form

ous gross weights and at forward and aft CG limits. Table

365-4. Form F is the summary of the actual disposition

6-1 eliminates calculation of intermediate CG when the

of the load in the helicopter. It records the balance status

helicopter is well within limits. When flight limits are doubt-

of the helicopter step-by-step. It serves as a work sheet on

ful or when operation is close to CG limits, a detailed cal-

which to record weight and balance calculations and any

culation must be made to determine any CG limit violation.

corrections that must be made to ensure that the helicop-

ter will be within weight and CG limits throughout the mis-

c. Fuel Management. The following example pres-

sion. There are two versions of this form: Transport and

ents normal CG/fuel management where each fuel tank

Tactical. Each was designed to provide for the respective

supplies an engine. This procedure prevents drastic heli-

loading arrangement of these two types of aircraft. The

copter CG shifts as fuel is expended. Refer to Chapter 2

general use and fulfillment of either version is the same.

for fuel system details.

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

6-4

TM 1-1520-251-10

Table 6-1. Helicopter CG Movement When Load Items are Expended

When Aircraft CG Near

Aircraft Gross Weight

Fwd CG Limit

Aft CG Limit

Expended Items

Qty

14000

15000

17650

14000

15000

17650

Ammo

100

+0.32

+0.30

+0.27

+0.34

+0.31

+0.28

Ammo

200

+0.30

+0.28

+0.26

+0.33

+0.30

+0.28

Ammo

320

+0.29

+0.27

+0.25

+0.33

+0.30

+0.28

Rockets 27.1 lb

+0.90

+0.79

+1.01

+0.99

H-F Missiles (4 SAL, 4 RF)

+0.66

+0.58

+0.78

+0.75

Chaff

- 0.21

- 0.20

- 0.16

- 0.21

- 0.20

- 0.17

* Fuel

500 lb per tank

- 1.80

+1.85

Fuel

1000 lb per tank

** - 1.60

+3.15

NOTE

• A plus (+) means aircraft CG moves aft and negative ( - ) means forward CG movement.

• *The above fuel values represent the total fuel on board such that the 500 lb (1000 lb or full) in each tank

is the starting point and the expended fuel is 500 lb (1000 lb or full), leaving zero fuel in each tank.

• ** Limited to minimum 500 lbs when 1000 lbs fuel in forward tank in order not to exceed forward CG limit.

EXAMPLE:

Using Table 6-1, refer to Expended Items column and look across the “Fuel 500 lb per tank” row. Note that fuel

expended at the aircraft gross weight of 15,000 at forward CG limit, produces an aircraft CG shift of a negative

1.80 in. (or movement in the forward direction); and at aft CG limit, produces an aircraft CG shift of a positive

1.85 in. (or movement in the aft direction). When the helicopter CG is at the combined fuel CG (202.8 in.),

expending fuel will produce a zero shift. This is true only when the forward fuel tank remains in the lower portion

of the L-shape tank.

When filling the forward tank into the upper portion of the L-shape, the combined fuel expended CG moves aft

to 212.4 in. which means that the helicopter will always shift forward during fuel burn-off in this area.

Refer to the 1000 lb fuel expended each tank line in Table 6-1. Note that fuel expended at 17,650 lbs gross

weight at aft CG limit is +3.15 in. This is correct when total 2,000 lbs of fuel is expended, but this includes a

helicopter CG shift forward during initial fuel burn-off due to the forward L-shaped tank.

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

6-5

TM 1-1520-251-10

Section III. FUEL AND OIL

6.3 OIL MOMENTS

WARNING

Oil is shown in basic weight, Chart F (DD 365-4). Entries

• An increase in the risk of post-crash

are not required.

fire exists if a mishap occurs after

tanks are pressurized. Crash worthi-

6.4 FUEL WEIGHT AND MOMENT

ness of the fuel system is reduced by

external fuel tanks, which are de-

When the actual or planned fuel loading (pounds or gal-

signed for FERRY MISSION ONLY. Ex-

lons) and type is known, the total fuel weight and mo-

ternal fuel tank installation is prohib-

ment/100 can be determined from the fuel moment Table

ited for use in tactical missions.

6-2. The data presents JP-4, JP-5, and JP-8 fuel quantity.

•

Extended Range Fuel System (ERFS)

6.4.1 Fuel Moments. The forward fuel moment calcu-

tanks do not have any ballistic protec-

lations are complicated by the L-shape of the tank. Con-

tion and are vulnerable to high - speed

sider the tank being filled from empty to 132.8 gal.; the fuel

projectiles. Projectiles passing

CG remains constant at 150.6 in. From 132.8 gal. to full

through a fueled ERFS tank can gen-

(156 gal.), the CG of the total fuel moves aft linearly to

erate a fuel driven fuselage fire and or

153.4 in. at capacity. The aft fuel CG is constant at 255 in.

cause the tank to detonate with the

potential for losing both thw aircrew

and aircraft.

CAUTION

With external tanks installed, it will be

necessary to carefully plan the wing

store configurations including fuel

transfer from external tanks, expending

weapons, and possible jettison of wing

stores, to ensure the lateral center-of-

gravity remains within limits throughout

the flight. When determining allowable

wing stores, zero lateral C.G. should be

assumed for aircraft operating weight

(basic weight plus crew weight).

6.4.2

Wing Auxiliary Fuel and Tanks. The auxiliary

fuel tanks are normally installed on the wing pylons in sets

of 2 or 4 and are for extending the helicopter ferry range.

Plumbing from the fuselage to the tank is provided with

each tank. Each tank has a capacity of approximately 230

gal.. Table 6-3 lists the weight and moment/100 of each

fuel tank, wing plumbing and fuel for JP-4, JP-5, and JP-8.

Note that the data is given for one tank, wing plumbing

and indicated fuel so that any combination can be deter-

mined. The table can be used for inboard and outboard

locations because the small moment/100 differences can

be ignored. Remember to add the tank and specific fuel

together for one location, then multiply by 2 or 4 depend-

ing on the number of tanks carried. Add wing plumbing for

2 or 4 tanks as appropriate.

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

6-6

Change 4

TM 1-1520-251-10

Table 6-2. Main Tanks - Fuel Loading (sheet 1 of 3)

JP-4 Density = 6.5 lb/gal (See sheet 1)

JP-5 Density = 6.8 lb/gal (See sheet 2)

JP-8 Density = 6.7 lb/gal (See sheet 3)

Fuel: JP - 4

Aft Tank

U.S.

Forward Tank

Weight

Moment

Gallons

U.S.

(lb)

100

JP-4

Weight

Moment

Gallons

127

7.7

(lb)

100

JP-4

100

255

15.4

7.7

150

382

23.1

100

151

15.4

200

510

30.8

150

226

23.1

250

637

38.5

200

301

30.8

300

765

46.2

250

377

38.5

350

892

53.8

300

452

46.2

400

1020

61.5

350

527

53.8

450

1147

69.2

400

602

61.5

500

1275

76.9

450

678

69.2

550

1402

84.6

500

753

76.9

600

1530

92.3

550

828

84.6

650

1657

100.0

600

904

92.3

700

1785

107.7

650

979

100.0

750

1912

115.4

700

1054

107.7

800

2040

123.1

750

1130

115.4

850

2167

130.8

800

1205

123.1

900

2295

138.5

850

1281

130.8

950

2422

146.2

900

1365

138.5

1000

2550

153.9

950

1450

146.2

1050

2677

161.5

1000

1535

153.8

1100

2805

169.2

1012

1555

155.7

1150

2932

176.9

1200

3060

184.6

1250

3187

192.3

1300

3315

200.0

1350

3442

207.7

1400

3570

215.4

1430

3646

220.0

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

6-7

TM 1-1520-251-10

Table 6-2. Main Tanks - Fuel Loading (sheet 2 of 3)

Fuel: JP - 5

Aft Tank

U.S.

Forward Tank

Weight

Moment

Gallons

U.S.

(lb)

100

JP-5

Weight

Moment

Gallons

127

7.4

(lb)

100

JP-5

100

255

14.7

7.4

150

382

22.1

100

151

14.7

200

510

29.4

150

226

22.1

250

637

36.8

200

301

29.4

300

765

44.1

250

377

36.8

350

892

51.5

300

452

44.1

400

1020

58.8

350

527

51.5

450

1147

66.2

400

602

58.8

500

1275

73.5

450

678

66.2

550

1402

80.9

500

753

73.5

600

1530

88.2

550

828

80.9

650

1657

95.6

600

904

88.2

700

1785

102.9

650

979

95.6

750

1912

110.3

700

1054

102.9

800

2040

117.6

750

1130

110.3

850

2167

125.0

800

1205

117.6

900

2295

132.4

850

1280

125.0

950

2422

139.7

900

1358

132.4

1000

2550

147.1

950

1443

139.7

1050

2677

154.4

1000

1528

147.1

1100

2805

161.8

1058

1623

155.7

1150

2932

169.1

1200

3060

176.5

1250

3187

183.8

1300

3315

191.2

1350

3442

198.5

1400

3570

205.9

1450

3697

213.2

1496

3815

220.0

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

6-8

TM 1-1520-251-10

Table 6-2. Main Tanks - Fuel Loading (sheet 3 of 3)

Fuel: JP - 8

Aft Tank

U.S.

Forward Tank

Weight

Moment

Gallons

U.S.

(lb)

100

JP-8

Weight

Moment

Gallons

127

7.4

(lb)

100

JP-8

100

255

14.9

7.5

150

382

22.4

100

151

14.9

200

510

29.9

150

226

22.4

250

637

37.3

200

301

29.9

300

765

44.8

250

377

37.3

350

892

52.2

300

452

44.8

400

1020

59.7

350

527

52.2

450

1147

67.2

400

602

59.7

500

1275

74.6

450

678

67.2

550

1402

82.1

500

753

74.6

600

1530

89.6

550

828

82.1

650

1657

97.0

600

904

89.6

700

1785

104.5

650

979

97.0

750

1912

111.9

700

1054

104.5

800

2040

119.4

750

1130

111.9

850

2167

126.9

800

1205

119.4

900

2295

134.3

850

1280

126.9

950

2422

141.8

900

1360

134.3

1000

2550

149.3

950

1455

141.8

1050

2677

156.7

1000

1530

149.3

1100

2805

164.2

1043

1603

155.7

1150

2932

171.6

1200

3060

179.1

1250

3187

186.6

1300

3315

194.0

1350

3442

201.5

1400

3570

209.0

1450

3697

216.4

1474

3758

220.0

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

6-9

TM 1-1520-251-10

Table 6-3. Wing Auxiliary Tanks and Fuel

JP-4 Density = 6.5 lb/gal

JP-5 Density = 6.8 lb/gal

JP-8 Density = 6.7 lb/gal

Auxiliary Fuel Tanks

Moment

Item

Weight Each (lb)

100

Auxiliary Fuel Tanks (each)

140.0

268

Wing Tank Plumbing

2 Tanks

16.0

4 Tanks

20.0

Fuel : JP - 4 (6.5 lb/gal)

Moment

U.S.

Condition*

Weight (lb)

(in-lb/100)

Gallons

Tank Full

1495.0

2906

230.0

Tank 3/4 Full

1121.3

2180

172.5

Tank 1/2 Full

747.5

1453

115.0

Tanks 1/4 Full

373.8

727

57.5

* Tank at 0° (level) attitude

Fuel : JP - 5 (6.8 lb/gal)

Moment

U.S.

Condition*

Weight (lb)

(in-lb/100)

Gallons

Tank Full

1564.0

3040

230.0

Tank 3/4 Full

1173.0

2280

172.5

Tank 1/2 Full

782.0

1520

115.0

Tanks 1/4 Full

391.0

760

57.5

* Tank at 0° (level) attitude

Fuel : JP - 8 (6.7 lb/gal)

Moment

U.S.

Condition*

Weight (lb)

(in-lb/100)

Gallons

Tank Full

1541.0

2996

230.0

Tank 3/4 Full

1155.8

2247

172.5

Tank 1/2 Full

770.5

1498

115.0

Tanks 1/4 Full

385.3

749

57.5

* Tank at 0° (level) attitude

NOTE

• Weight and moment are shown for one tank with fuel; and must be doubled for 2 inboard or

multiplied by 4 when inboard and outboard stations are used.

• Add wing tank plumbing for 2 tanks or 4 tanks as appropriate.

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

6-10

TM 1-1520-251-10

Table 6-3B. Internal Auxiliary Fuel and Ammo System Installation, Fuel, and Ammo

Combo Pack Assembly Installation

Moment

Item

Weight (lb)

100

Combo Pack Assembly, Fuel Hoses (2), and Nitrogen Hose

320.6

651

Fuel: JP - 4 (6.5 lb/gal)

Moment

U.S.

Tank at Level Attitude

Weight (lb)

(in-lb/100)

Gallons

Tank Full

643.5

1349

99.0

Tank 3/4 Full

482.6

999

74.3

Tank 1/2 Full

321.8

666

49.5

Tank 1/4 Full

160.9

333

24.8

Fuel: JP - 5 (6.8 lb/gal)

Moment

U.S.

Tank at Level Attitude

Weight (lb)

(in-lb/100)

Gallons

Tank Full

673.2

1411

99.0

Tank 3/4 Full

504.9

1045

74.3

Tank 1/2 Full

336.6

697

49.5

Tank 1/4 Full

168.3

348

24.8

Fuel: JP - 8 (6.7 lb/gal)

Moment

U.S.

Tank at Level Attitude

Weight (lb)

(in-lb/100)

Gallons

Tank Full

663.3

1390

99.0

Tank 3/4 Full

497.5

1030

74.3

Tank 1/2 Full

331.7

687

49.5

Tank 1/4 Full

165.8

343

24.8

Ammo (Aluminum)

Combo Ammo Container and Flex

Moment

Rounds

Weight (lb)

Chute

(in-lb/100)

Ammo

100

77.0

109

Ammo

200

154.0

254

Ammo

300

231.0

400

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

6-10.2

Change 2

TM 1-1520-251-10

Section IV. PERSONNEL

6.5 GENERAL

equipment, compute weight according to each individuals

estimate.

Personnel provisions consist of the pilot and CPG located

in the cockpit.

6.6 PERSONNEL WEIGHT

6.6.1

Personnel Moments. Correct weight of each

crew member, including all equipment and any personal

When aircraft are operated at critical gross weights, the

items stored in the crew station, should be used. If weigh-

exact weight of each individual occupant plus equipment

ing facilities are not available, then use the best estimate

should be used. If weighting facilities are not available, or

available. Table 6-4 presents the crew CG with the seat in

if the tactical situation dictates, a crewmember with no

its nominal location.

Table 6-4. Crew Weight

Crew Member

Copilot Station

Pilot Station

Weight Including Equipment

Nominal

(lb)

Arm

Moment

Arm

Moment

(in.)

(in.-lb/100)

(in.)

(in.-lb/100)

100

82.2

143.3

143

110

82.2

143.3

158

120

82.2

143.3

172

130

82.2

107

143.3

186

140

82.2

115

143.3

201

150

82.2

123

143.3

215

160

82.2

132

143.3

229

170

82.2

140

143.3

244

180

82.2

148

143.3

258

190

82.2

156

143.3

272

200

82.2

164

143.3

287

210

82.2

173

143.3

301

220

82.2

181

143.3

315

230

82.2

189

143.3

330

240

82.2

197

143.3

344

250

82.2

206

143.3

358

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

6-11

TM 1-1520-251-10

Section V. MISSION EQUIPMENT

6.7 MISSION EQUIPMENT

6-6 lists the RF weight and moment/100 of each RF mis-

sile accumulated to a capacity of 4 missiles per launcher.

When a pair of inboard launchers are filled to capacity,

Aircraft mission equipment includes pylons, Hellfire mis-

double the (missile no. 4) weight and moment/100. When

siles and launchers, 2.75-in. rockets and launchers,

4 launchers are used, multiply the numbers by 4.

30mm ammunition and chaff cartridges. External fuel

tanks are delineated in paragraph 6.4.2. All electronic

6.7.5

Rocket Launchers. Figure 6-2 presents the

mission equipment is part of basic weight and may be

M261 2.75-in. rocket launchers in pairs, weight and mo-

found in Chart A (Form DD 365-1).

ment/100. Double the weight and moment/100 when 4

launchers are used.

6.7.1 Pylons. The wing pylons should be included on

Chart A (Form DD 365-1) as part of the basic weight.

6.7.6 Rockets (2.75-in.). Table 6-7 lists all authorized

Check Charts A and C (Form DD 365-3) to ensure this has

2.75-in. rockets weight and moment/100. Select the cor-

been done. If pylons are installed and they are not listed

rect type of rocket and multiply the weight and mo-

on Chart A, they should be listed on Chart C and A and

ment/100 times total rockets loaded for each type. The

included in the basic weight from this date on.

table is presented so that any combination or mix can be

easily determined for a launcher.

6.7.2

Missile Launchers. Figure 6-2 presents the

M-299 Longbow Hellfire launchers in pairs, weight and

6.7.7

Ammunition. Table 6-8 presents the M788 or

moment/100. Double the weight and moment/100 when 4

M789 30mm linkless aluminum case ammunition accu-

launchers are used.

mulated weight and moment/100 to a capacity of 1200

rounds. Approximately 99 rounds are in the right chute

6.7.3 Longbow Hellfire Semi-Active Laser (SAL) Mis-

and the remainder is in the magazine. A note on the table

siles. The present SAL dummy missile (M34), tactical

allows conversion of the table numbers to ADEN or DEFA

laser seeker training missile (M36) and tactical missile

ammunition.

(AGM 114) weigh the same. Table 6-5 lists the SAL weight

and moment/100 of each SAL missile accumulated to a

6.7.8 Chaff Dispenser/Laser Warning Sensors. The

capacity of four missiles per launcher. When a pair of in-

helicopter survivability equipment is a kit. It is added to the

board launchers are filled to capacity, double the (missile

helicopter as dictated by mission requirements. The elec-

no. 4) weight and moment/100. When 4 launchers are

tronic equipment, controls and supports are part of the ba-

used, multiply the numbers by 4.

sic weight and are listed in Chart A (Form DD 365-1).

Tables 6-9 and 6-10 list the chaff dispenser empty and full

6.7.4

Longbow Hellfire Radar Frequency (RF) Mis-

with 30 chaff (M1) cartridges and the forward and aft laser

siles. The present RF dummy missile, tactical RF train-

warning sensors. These values are to be used on Form F

ing missile and tactical RF missile weigh the same. Table

(DD 365-4) when chaff is on board.

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

6-12

Change 4

TM 1-1520-251-10

Table 6-7.

2.75-Inch Rocket Loading

NOTE

When computing weight and balance, crewmember must remember to multiply each rocket type weight

(lb) and moment (in.-lb/100) by the quantity of that rocket type loaded onboard the aircraft. Failure to do so

will result in incorrect CG calculations. The SP calculates total rocket weight based upon rocket type (i.e:

6PD, 6RC) rather than warhead types (M151, M229 or M274). The weight calculation is based on LMP

settings, unless the load settings are altered in either crew station.

Inboard Station 2, 3 or

Outboard Station 1, 4

Rocket

Rocket Nomenclature

Weight (lb)

Moment

Type

per rocket

(in.-lb/100)

per rocket

Dummy

Dummy MK66 Rocket

23.0

44.80

6PD

MK66 Rocket Motor with Point Detonation, High

Explosive Warhead

23.0

44.80

6RC

MK66 Rocket Motor with Penetration, High Explosive

Warhead

24.0

46.44

6IL

MK66 Rocket Motor with Time, Illumination Warhead

24.3

46.18

6SK

MK66 Rocket Motor with Time, Smoke Warhead

22.5

43.42

6MP

MK66 Rocket Motor with Time, Multi-purpose

Submunition Warhead

27.4

51.96

6FL

MK66 Rocket Motor with Flechette Warhea

27.5

52.05

PD7

CRV7 Rocket Motor with Point Detonation, High

22.1

42.69

Explosive Warhead

RA7

CRV7 Rocket Motor with Armor Piercing, Point

25.8

49.26

Detonation, High Explosive Warhead

IL7

CRV7 Rocket Motor with Time, Illumination Warhead

23.5

44.08

SK7

CRV7 Rocket Motor with Time, Smoke Warhead

21.6

41.44

MP7

CRV7 Rocket Motor with Time, Multi - purpose

26.6

49.86

SubmunitionWarhead

FL7

CRV7 Rocket Motor with Flechette Warhead

20.0

38.68

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

6-14

TM 1-1520-251-10

Table 6-8. Ammunition Loading for M788 or M789 30mm Rounds (Aluminum Cartridges)

NOTE

When ADEN (brass cartridges) are used, multiply weight and moment by 1.354. When DEFA (steel car-

tridges) are used, multiply weight and moment by 1.343.

Weight

Moment

Weight

Moment

Number of Rounds

(lb)

(in.-lb/100)

Number of Rounds

(lb)

(in.-lb/100)

38.5

650

500.5

988

100

77.0

110

700

539.0

1063

150

115.5

189

750

577.5

1146

200

154.0

269

800

616.0

1221

250

192.5

346

850

654.5

1304

300

231.0

427

900

693.0

1379

350

269.5

504

950

731.5

1462

400

308.0

585

1000

770.0

1537

450

346.5

662

1050

808.5

1620

500

385.0

744

1100

847.0

1696

550

423.5

819

1150

885.5

1778

600

462.0

905

1200

924.0

1868

Table 6-9. Chaff Dispenser and Cartridges/Laser Warning Sensors ASE Equipment

Weight

Moment

Item

(lb)

(in.-lb/100)

IR Jammer

28.0

63.2

Radar Jammer

44.0

45.6

Radar Warning Receiver

14.3

44.6

Laser Warning Receiver with forward

19.2

58.3

and aft sensors

Forward Laser Warning Sensors (2 ea)

9.0

AFT Laser Warning Sensors (2 ea)

9.0

Chaff Dispenser M141 (Empty)

9.0

44.8

Table 6-10. Chaff Dispenser Cartridges

Weight

Moment

Number of Rounds

(lb)

(in.-lb/100)

30 Chaff Cartridges

10.0

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

6-15

HELICOPTER, ATTACK, AH-64D LONGBOW APACHE. TECHNICAL MANUAL (2002) - page 12