TECHNICAL MANUAL MAINTENANCE MANUAL FOR ARMY CH-47D HELICOPTER (1992)

TM 55-1520-240-10

Table 3-6. AN/ASN-149V) GPS Start-Up Procedure-(Continued).

Step

Procedure

Display

Enter 13 on display line 1.

Check L2 path delay on display line 2. If displayed L2

path delay and actual 12 path delay differ, enter actual

L2 path delay in nanoseconds on display line 2.

NOTE

After NAV is selected, initialization inputs

cannot be changed. If a cold start is required,

COLD will alternate with FM on display line 1

while cold start is in progress. Cold start

progress may be checked by setting the data

switch to STAT and pressing the slew key three times.

After NAV is selected, FM will be replaced with

MEM or DOP until FM 2 or less is displayed.

Set mode switch to NAV.

aa.

Set data switch to STAT.

ab.

Check number of satellite measurements (SAT) being used

in the navigation solution and estimated position error

(EPE) on display line 3. The AN/ASN-149(V) is ready

for operation when four satellite measurements are

being used and EPE is less than 25 meters,

approximately 2 minutes. If only three satellites are

available, the AN/ASN-149(V) may be prepared for use

by entering an altitude estimate. Altitude can be entered

by setting the data switch to POS and entering the

altitude estimate. M will be displayed to left of altitude

display indicating that an altitude may be entered. If an

altitude has been entered AHLD (altitude hold) will

alternate with FM while the entered altitude is being

used. M and AHLD will be automatically dropped when

four satellites are acquired. Manual altitude hold

may be dropped by pressing line select key 4 twice.

Change 6 3-45

TM 55-1520-240-10

Table 3-7. Units of Measurement, Coordinate Systems. North Reference, Altitude Reference,

and Lever Arm Selection Procedure.

Step

Procedure

Display

Set mode switch to INIT or NAV.

Set data switch to OPT.

Check display line 1. If WP is displayed, press WP key.

Press line select key 2 to select a desired north reference

TRUE, GRID, or MAG (magnetic).

NOTE

Convergence factor (CG) is meaningless unless

GRID is selected.

NOTE

Leading zeros must be entered (example:

0.00098, 0.00100) in step e, if required. Leading

zeros will not be erased when entry is complete.

Check convergence factor (CF) displayed on display line 3.

If the displayed convergence factor is different than the

convergence factor of the map in use, enter new

convergence factor on display line 3.

Press line select key 4 until the desired coordinate system

is displayed on display line 4:

L/L SECONDS - Latitude/longitude in degrees,

minutes, seconds, and tenths of seconds.

L/L MINUTES - Latitude/longitude in degrees,

minutes, and thousandths of minutes.

MGRS - Military grid reference system.

Press slew key.

Press line select key 1 to select FT (feet) or M (meters)

for altitude (ALT) and estimated position error (EPE)

displays.

3-46 Change 6

TM 55-1520-240-10

Table 3-7. Units of Measurement, Coordinate Systems. North Reference, Altitude Reference,

and Lever Arm Selection Procedure - (Continued).

Step

Procedure

Display

Press line select key 2 to select NM (nautical miles) or KM

(kilometers) for distance (DIS) displays.

Press line select key 3 to select KTS (knots) or KPH

(kilometers per hour) for speed (VEL) displays.

Press line select key 4 to select mean sea level (MSL) or

map datum (DTM) for altitude reference.

Press and release slew key until LA SRC: is displayed on

display line 2.

Check lever arm source (LA SRC) on display line 2:

ANT - antenna

CDU - C-11702/UR

DL - data loader

HV - aircraft external navigation equipment

NOTE

The status will change automatically depending

on the selection on display line 2.

Change 6 3-47

TM 55-1520-240-10

Table 3-7. Units of Measurement, Coordinate Systems. North Reference, Altitude Reference,

and Lever Ann Selection Procedure - (Continued).

Step

Procedure

Display

Check status of LA SRC on display line 3:

AVAILABLE - Indicates data is available for the LA SRC

displayed on display line 2, but is not

being currently used.

NO DATA - Indicates no data is available for LA SRC

displayed on display line 2.

USING - Indicates LA SRC displayed on display line 2 is

being used for lever arm input data.

DEFAULT - Indicates the AN/ASN-149(V) has no LA

SRC in memory. The default lever arm data

source is the antenna. To select the antenna,

press line select key 3. Display line 3 will

automatically change from DEFAULT TO

USING. If line select key 3 is not pressed,

the AN/ASN-149(V) will automatically select

the antenna as the LA SRC.

NOTE

An LA SRC may be selected only when display

line 3 displays AVAILABLE or DEFAULT.

Select desired LA SRC on display line 2 by pressing line

select key 3.

NOTE

To check actual lever arm data being used by the

AN/ASN-149(V), complete steps p thru v. To

enter lever arm enter data using the C-11702/UR,

complete steps w thru ab.

Press and release slew key until CW is displayed on

display line 1.

Enter 08 on display line 1.

3-48 Change 6

TM 55-1520-240-10

Table 3-7. Units of Measurement, Coordinate Systems. North Reference, Altitude Reference,

and Lever Arm Selection Procedure - (Continued).

Step

Procedure

Display

Check current up/down (+ - up, - = down) lever arm

displayed in meters (M) on display line 2.

Enter 09 on display line 1.

Check current fore/aft (+ = fore, - = aft) lever arm

displayed in meters (M) an display line 2.

Enter 10 on display line 1.

Check current left/right (+ = left, - = right) lever arm in

meters (M) displayed on display line 2.

NOTE

To enter new or correct lever arm source data,

complete steps w. thru ab.

Enter 05 on display line 1.

NOTE

Leading zeros must be entered (example: 005.0 =

5, 010.0 = 10.0) in steps x, z, and ab if required.

Leading zeros will be erased when entry is

complete.

Enter desired up/down (+ = up, - = down) lever arm in

meters (M) on display line 2.

Enter 06 on display line 1.

Enter desired fore/aft (+ = fore, - = aft) lever arm in

meters (M) on display line 2.

aa.

Enter 07 on display line 1.

ab.

Enter desired left/right (+ = left, - = right) lever arm in

meters (M) on display line 2.

Change 6 3-49

TM 55-1520-240-10

d. GPS Self-Test. Testing is divided into three

The keyboard/display test is done by pressing each of

parts: automatic built-in test (BIT), command self-test

the keys on the indicator controller and checking that

and keyboard/display test. The automatic BIT is done

each character is displayed correctly. Perform the

each time the indicator controller is set to INIT, NAV or

keyboard/display test only when the keyboard or the data

TEST from OFF. The command self-test is done when

display appears to work incorrectly.

the indicator controller mode switch is set to TEST.

Preliminary Procedures. None

Table 3-8. Command Self-Test Procedure.

Step

Procedure

Display

NOTE

Be sure aircraft power is applied to AN/ASN-149(V)

before starting procedure.

Adjust indicator controller BRT control full clockwise.

Set mode switch to TEST. Mode switch must be pulled out

to set to TEST.

NOTE

The indicator controller requires a 30-second warm-up

before the data display will display data.

NOTE

If failure data is displayed instead of TEST IN PROG,

notify organizational maintenance.

After 30 seconds, check TEST IN PROG is displayed on

display line 1.

NOTE

Test may take up to 5 minutes Test progress

reports will flash briefly during testing.

Adjust indicator controller BRT control counterclockwise for a

comfortable viewing level.

NOTE

Indicator controller panel lighting glows green. Light

level is very low; shield C-1 1702/UR from any

light while checking.

3-50 Change 6

TM 55-1520-240-10

Table 3-8. Command Self-Test Procedure - (Continued).

Step

Procedure

Display

Adjust aircraft dimmer control clockwise and

Panel light level varies with

counterclockwise while checking indicator controller panel

changing setting of aircraft

lighting.

dimmer control.

Adjust aircraft dimmer control for a comfortable viewing

level.

Check data display. If no failures were detected, display

line 1 will display TEST COMPLETE. Display line 2 will

display TEST OK- Display line 4 will display CLEAR N/V

MENU; this is for maintenance use only. If a failure

is detected, H/W FAILURE or a fault code will be

displayed on display line 1. Display lines 2 and 3 will

display failure codes. Display line 4 may display

additional information. Report all failures to

organizational maintenance.

Set mode switch to any position except TEST to end

commanded self-test.

Change 6 3-51

TM 55-1520-240-10

Table 3-9. Keyboard/Display Test Procedure.

Step

Procedure

Display

Set mode switch to NAV.

Set data switch to OPT.

Check display line 1. If WP is displayed, press WP key.

Press slew key until CDU TEST is displayed on display

line 1.

e. Press line select key 1.

Check symbols +-°O, ‘ “ , :

> / = are displayed on display line 4.

Press line select key 1. Check display line 1 is cleared.

Press USE/LTR key. Check (*) is displayed on display

line 1.

NOTE

Letters will blink after entering. This is normal.

Enter letters A thru Z while checking that letters are

displayed on display line 1, in the first character

position.

Press line select key 1.

Press line select key 2. Check display line 2 is cleared.

Enter numbers 1 thru 0 while checking 1234567890 are

displayed on display line 2.

Press CLR key and check last number is erased.

Press line select key 2.

3-52 Change 6

TM 55-1520-240-10

Entering and Checking Waypoints.

Waypoints can also be defined by a bearing (BRG),

range (RNG), and elevation angle (EL ANG) from some

A waypoint is the location of a point on the desired

reference point.

Present positionor a previously

course. The AN/ASN-149(V) provides information to

defined

waypoint

are

theusual references.

perform area navigation (RNAV) operations.

The

Alphanumeric identifier can be stored for all

209

AN/ASN-149 (V) displays data that allows the aircraft to

waypoints. If the waypoint identifies a NAVAID, the

fly from the present position to the next programmed

frequency or channel can be stored. An alphanumeric

waypoint. The next waypoint is referred to as the

identifier is required if more than one waypoint will be

current steer-to destination. A normal mission consists

stored using the same frequency or channel information.

of a series of waypoints. During normal operation the

Desired track (DTK) vertical angle (VA), and map datum

aircraft is navigated from the departure point to waypoint

(DTM) to the waypoint may also be stored.

1 (WP1). After arriving at WP1, WP2 is entered as the

steerto destination and the aircraft is navigated to WP2

Waypoints can be automatically entered with a data

The aircraft is navigated to consecutive waypoints until

loader using a data transfer module containing the

reaching the final destination. The location of targets,

required data.

When a data loader capability is

prominent landmarks, or navigational aids (NAVAID) are

available, entering waypoints is accomplished during the

usually used to define waypoints. NAVAID include very

start-up procedure (Table

3-6).

If the data loader

high frequency omnidirectional radio range (VOR),

capability is not available, waypoints may be entered

tactical air navigation (TACAN), and nondirectional

using the indicator controller, Table 3-6.

beacon (NDB) stations. Another aircraft can also be

defined as a moving waypoint. Moving waypoints are

NOTE

normally used in rendezvous (*REND) operation. The

Keeping a written record of the waypoint

AN/ASN-149(V) can store 209 waypoints in memory.

memory

numbers, alphanumeric

These waypoints are numbered WP1 thru WP209. WP1

identifiers, and frequency or channel

thru WP9 may be used as stationary or moving

numbers may save time later.

destinations. WP100 thru WP209 may be used with

stationary destinations only. Data for moving waypoints

may be stored in W10 thru WP209; however, the data

must be moved to a WP1 thru WP9 location to be

selected as a destination. All waypoints are defined by

position (latitude/longitude (L/L) or military grid reference

system (MGRS) coordinates) altitude, and map datum

(DTM). A ground track (TRK), ground speed (GS), and

time of fix (TOF) are also required for moving waypoints.

3-54 Change 6

TM 55-1520-240-10

Table 3-10. Entering Stationary Waypoints via the Indicator Controller

Step

Procedure

Display

NOTE

This procedure can be used for waypoint

numbers 1 thru 209. The waypoint must be

stationary

Ensure mode switch set to NAV or INIT.

Set data switch to VAR-DTM

Check display line 1. If > is displayed, press WP key.

NOTE

If WP entered in step d has been previously

defined with an alphanumeric identifier, the

alphanumeric identifier will be displayed when

the waypoint number is entered.

Enter waypoint (WP) number (1 thru 209) for waypoint to

be defined on line 1

NOTE

Step e is optional.

NOTE

Leading zeros must be entered (example: 1=

00.0, 10- 010.0) in step e, if required. Leading

zeros will not be erased when entry is complete.

Enter waypoint magnetic variation (VAR) on display line

2. First character must be E (east) or W (west).

Enter waypoint map datum (DTM) code on display line 3

Map datum codes are listed in Table 3-12

Change 6 3-55

TM 55-1520-240-10

Table 3-10. Entering Stationary Waypoints via the Indicator Controller - (Continued).

Step

Procedure

Display

Set data switch to POS.

NOTE

When entering MGRS coordinates, do not press

line select key 2 after entering zone, and line

select key 3 before entering coordinates. MGRS

zone and coordinates are entered like a one

display line entry.

NOTE

Leading zeros must be entered (example:

91 02’28.3" = 091 02’28.3", 800 =00800) in steps

h thru j, if required.

Enter waypoint latitude or MGRS grid zone on display

line 2.

Enter waypoint longitude or MGRS coordinates on display

line 3.

Enter waypoint altitude on display line 4.

NOTE

Steps k thru m are optional. A waypoint may

be identified by entering an alphanumeric

identifier (step 1) and/or a NAVAID frequency

(step m) in addition to the waypoint number

(step d).

NOTE

If an alphanumeric identifier is selected and the

data switch is set to another position, the WP

display will indicate the alphanumeric identifier

and the waypoint number will not be displayed.

If an alphanumeric identifier is not selected, the

waypoint number will be displayed.

3-56 Change 6

TM 55-1520-240-10

Table 3-10. Entering Stationary Waypoints via the Indicator Controller - (Continued)

Step

Procedure

Display

Press slew key

Enter waypoint alphanumeric identifier on display line 2.

Alphanumeric identifier can be a maximum of six

characters.

Enter NAVAID frequency or channel on display line 3.

Allowable NAVAID frequencies are:

VOR - 108.00 to 117.99

TACAN - IX to 126X and IY to 126Y.

NDB - 1 to 9999

Decimal point must be entered for VOR or NDB

frequencies.

NOTE

To transfer waypoint description into WP 1

thru 9, enter applicable waypoint (WP) number

on display line 4.

NOTE

Steps n thru q are optional.

Set data switch to DTK-VA

NOTE

Leading zeros must be entered (example: 5 =

000.5, 50 = 050.0) in step o, if required. leading

zeros will not be erased when entry is complete.

Enter desired track (DTK) to waypoint as referenced to

true (1), grid (G), or magnetic (M) north on display

line 2.

NOTE

Display line 3 displays STORED WP DTK to

remind operator that DTK displayed is entered

for waypoint number displayed on display

line 1.

Change 6 3-57

TM 55-1520-240-10

Table 3-10. Entering Stationary Waypoints via the Indicator Controller - (Continued)

Step

Procedure

Display

Press slew key.

NOTE

Leading zeros must be entered (example: .5 =

00.5, 2 = 02.0) in step q, if required. Leading

zeros will not be erased when entry is complete.

Enter vertical angle (VA) from present position to

waypoint on display line 2.

NOTE

Display line 3 displays STORED WP VA to

remind operator that VA displayed is entered

for waypoint number displayed on display

line 1.

Table 3-11. Entering Moving Waypoints via the Indicator Controller.

Step

Procedure

Display

NOTE

The displayed position coordinates of a moving

waypoint will not change unless it is selected as

the destination in rendezvous (*REND)

operation.

Ensure mode switch set to NAV or INIT.

Set data switch to VAR-DTM.

Check display line 1. If > is displayed, press WP key

3-58 Change 6

TM 55-1520-240-10

Table 3-11. Entering Moving Waypoints via the Indicator Controller (Continued).

Step

Procedure

Display

Enter waypoint (WP) number for waypoint to be defined

on display line 1

NOTE

Step e. is optional

NOTE

Leading zeros must be entered (example: 1 =

001.0, 10 = 010.0) in step e, if required. Leading

zeros will not be erased when entry is complete

Enter waypoint magnetic variation (VAR) on display line

First character must be E (east) or W (west)

Enter waypoint map datum (DTM) code on display line 3.

Map datum codes are listed in Appendix E. If datum

code is 20, complete paragraph 2-27 before going to

step g

Set data switch to POS

NOTE

When entering MGRS coordinates, do not press

line select key 2 after entering zone and line

select key 3 before entering coordinates. MGRS

zone, and coordinates are entered like a one

display line entry

NOTE

Leading zeros must be entered(example:

91 02"28.3" = 091 °02"28.3",800 in steps

h. thru j. if required

Enter waypoint initial latitude or MGRS grid zone on

display line 2

Change 6 3-59

TM 55-1520-240-10

Table 3-11. Entering Moving Waypoints via the Indicator Controller (Continued)

Step

Procedure

Display

Enter waypoint initial longitude or MGRS coordinates on

display line 3

Enter waypoint initial altitude on display line 4

NOTE

Steps k. thru m. are optional. A waypoint may

be identified by entering an alphanumeric

identifier (step 1) and/or a NAVAID frequency

(step m.) in addition to the waypoint number

(step d.)

NOTE

If an alphanumeric identifier is selected and the

data switch is set to another position, the WP

display will indicate the alphanumeric identifier

and the waypoint number will not be displayed

If an alphanumeric identifier is not selected, the

waypoint number will remain displayed

Press slew key

Enter moving waypoint alphanumeric identifier on display

line 2. Alphanumeric identifier can be a maximum of six

characters

3-60 Change 6

TM 55-1520-240-10

Table 3-11. Entering Moving Waypoints via the Indicator Controller (Continued)

Step

Procedure

Display

Enter NAVAID frequency or channel on display line 3.

Allowable NAVAID frequencies are:

VOR- 108.00 to 117.99

TACAN -IX to 126X and 1Y to 126Y

NDB - 1. to 9999Decimal point must be entered for VOR or NDB

frequencies

Set data switch to TRK-GS

NOTE

Leading zeros must be entered (example: 0.1 =

000.1, 1=001.0) in step o, if required. Leading

zeros will not be erased when entry is complete

Enter moving waypoint track (TRK) referenced to true

(T), grid (G), or magnetic (M) north on display line 2

NOTE

Leading zeros must be entered (example: 10 =

0010, 100 = 0100) in step p, if required. Leading

zeros will be erased when entry is complete

Enter moving waypoint ground speed (GS) in knots (KTS)

or kilometers per hour (KPH) on display line 3

NOTE

Time of fix (TOF) is the time at which the

waypoint was at the position coordinates,

altitude, TRK, and GS just entered;

The starting time for the waypoint to begin

moving

Change 6 3-61

TM 55-1520-240-10

Table 3-11. Entering Moving Waypoints via the Indicator Controller - (Continued)

Step

Procedure

Display

Press slew key

NOTE

Leading zeros must be entered (example: 1:09:08

= 01:09:08) in step r, if required. Leading zeros

will not be erased when entry is complete

Enter time of fix (TOF) of moving waypoint on display

line 2

NOTE

Leading zeros must be entered (example: 3 =

003, 33=033) in step s if required. Leading

zeros will not be erased when entry is complete

Enter year (YR) and Julienne date (day of year) (DOY) on

display line 4

NOTE

Complete steps t thru w to move data to

waypoints 1 thru 9 if necessary

Set data switch to POS

Check display line 1. If I> is displayed, press WP key

Press slew key

Enter waypoint number on display line 4 where waypoint

data is to be moved

3-62 Change 6

TM 55-1520-240-10

Table 3-12. Entering Waypoints by Bearing, Range and Elevation Angle Procedure

Step

Procedure

Display

Ensure mode switch set to NAV or INIT

Set data switch to POS

Check display line 1 If > is selected, press WP key

Enter waypoint (WP) number (1 thru 209) for waypoint to

be defined on display line 1

Set data switch to DIS-TG

NOTE

After BRG has been entered, data display will

automatically change to enter range (RNG). Do

not press slew key

NOTE

Leading zeros must be entered (Example: .5 =

000.5, 10 = 0010) in step f and g, if required.

Leading zeros will not be erased when entry is

complete

Enter bearing (BRG) to waypoint referenced to true (T),

grid (G), or magnetic (M) north on display line 4

NOTE

If no range is entered, AN/ASN-149(V) will

assume range of zero

Change 6 3-63

TM 55-1520-240-10

Table 3-12. Entering Waypoints by Bearing, Range and Elevation Angle Procedure - (Continued)

Step

Procedure

Display

Enter range (RNG) in kilometers (KM) or nautical miles

(NM) on display line 2

NOTE

A negative elevation angle means the waypoint

is lower than reference point. If no elevation

angle is entered, the range in step g is a great

circle distance and the AN/ASN-149(V) will

assume waypoint is at same altitude as

reference point

NOTE

Leading zeros must be entered (Example: I =

00.1, 1 = 01) in step h, if required. Leading zeros

will not be erased when entry is complete

Enter elevation angle (EL ANG) on display line 3

NOTE

If no reference waypoint number or identifier is

entered, AN/ASN-149(V) will assume reference

is present position and will display dashes (-)

Enter reference waypoint number or alphanumeric

identifier on display line 4

NOTE

Waypoint position will not be computed until

step j. is performed. If present position is being

used as reference and aircraft has moved since

bearing, range, and elevation angle were

determined, waypoint position will be incorrect

3-64 Change 6

TM 55-1520-240-10

Table 3-12.

Entering Waypoints by Bearing, Range and Elevation Angle Procedure - (Continued)

Step

Procedure

Display

Press slew key to return to normal DIS-TG display

NOTE

Steps k. thru n. are optional. A waypoint may be

identified by entering an alphanumeric

identifier (step m.) and/or a NAVAID frequency

(step n.) in addition to the waypoint number

(step d.)

NOTE

If an alphanumeric identifier is selected and the

data switch is set to another position, the WP

display will indicate the alphanumeric identifier

and the waypoint number will be erased. If an

alphanumeric identifier is not selected, the

waypoint number will be displayed

Set data switch to POS

Press slew key

Enter waypoint alphanumeric identifier on display line 2.

Alphanumeric identifier can be a maximum of six

characters

Enter NAVAID frequency or channel on display line 3.

Allowable NAVAID frequencies are:

VOR- 108.00to 117.99

TACAN - 1X to 126X and 1Y to 126Y

NDB - 1. to 9999Decimal point must be entered for

VOR or NDB frequencies

NOTE

To transfer waypoint description into WP 1

thru 9, enter applicable waypoint (WP) number

on display line 4

Change 6 3-65

TM 55-1520-240-10

Table 3-13. Checking Waypoints Procedure

Step

Procedure

Display

Ensure mode switch set to NAV or INIT

Set data switch to POS

Check display line 1. If is displayed, press WP key

NOTE

More than one waypoint may be defined

using the same NAVAID frequency or channel. The

first waypoint displayed is the closest to present

position. The next waypoint or waypoints are

displayed in the order entered. Verify

alphanumeric identifier is the correct choice

before selecting waypoint for checking

Enter waypoint (WP) number, alphanumeric identifier, or

NAVAID frequency or channel on display line 1

NOTE

Allowable NAVAID frequencies are:

VOR- 10800 to 117.99

TACAN - IX to 126X and 1Y to 126Y

NDB - 1. to 9999.

Decimal point must be entered for VOR or

NDB frequencies

If multiple waypoints were entered that

have the same NAVAID frequency or channel

go to step e; if not, go to step F

Check waypoint (WP) identifier displayed on display

line 1

If incorrect, press line select key 3 (NEXT) for next

waypoint with the same frequency or channel

If correct, press line select key 4 (USE) to return to

normal display

3-66 Change 6

TM 55-1520-240-10

Table 3-13. Checking Waypoints Procedure (Continued)

Step

Procedure

Display

Check waypoint position coordinates and altitude on

display lines 2, 3, and 4

Press slew key

Check waypoint number on display line 1, alphanumeric

identifier on display line 2, and NAVAID frequency or

channel on display line 3

NOTE

Entering a number (1-9) on display line 4

causes the waypoint being checked to be

transferred into the WP number selected

Set data switch to VAR-DTM

Check magnetic variation (VAR) on display line 2 and map

datum (DTM) code on display line 3. If no magnetic

variation is stored display line 2 will display dashes

Set data switch to DIS-TG

Check great circle distance (DIS) to waypoint on display

line 2, time to go (TG) to waypoint in days; hours,

minutes, and seconds on display line 3; and bearing

(BRG) to waypoint on display line 4

Press slew key

Check slant range (RNG) to waypoint on display line 2

Set data switch to TRK-GS

Check ground track (TRK) on display line 2 and ground

speed (GS) for the moving waypoint (*REND operation

only) on display line 3

Change 6 3-67

TM 55-1520-240-10

Table 3-13. Checking Waypoints Procedure - (Continued)

Step

Procedure

Display

Press slew key

Check starting time of fix (TOF) for moving waypoint

(*REND operation only) on display line 2 and year (YR)

and day of year (DOY) for the starting time on display

line 4. Line 3 always displays YR and DOY as label

references for line 4

Set data switch to DTK-VA

Check desired track (DTK) to rendezvous with moving

waypoint (*REND operation only) or desired track

(DTK) stored with stationary waypoint on display line 2.

If no (DTK) is stored, display line 2 will display dashes

Press slew key

Check vertical angle (VA) to moving waypoint (*REND

operation only) or vertical angle stored with stationary

waypoint on display line 2.

If no VA is stored, display

line 2 will display dashes (-)

Displaying Present Position.

be displayed at any time after start-up is completed This

data is available while the aircraft is moving or stationary.

Present position latitude, longitude or military grid

To display present position perform the procedure in

reference system (MGRS) coordinates, and altitude may

Table 3-14

3-68 Change 6

TM 55-1520-240-10

Table 3-14. Displaying Present Position

Step

Procedure

Display

Set mode switch to NAV

Set data switch to POS

Check display line 1. If WP is displayed, press WP key

Read present position:

Display line 2 - Latitude or MGRS zone

Display line 3 - Longitude or MGRS coordinates

Display line 4 - Altitude in feet (FT) or meters (M),

referenced to mean sea level (MSL)

or datum (DTM)

NOTE

Present position is calculated from the antenna

position, or at the point designated by the lever

arm. This position may differ from expected

present position

NOTE

If the figure of merit is high and AN/ASN-

149(V) is tracking fewer than four satellites,

accuracy may be improved by entering a

manual altitude hold. Manual altitude hold can

be entered any time M is displayed on display

line 4

If manual altitude hold is desired, enter present altitude

estimate on display line 4. M will continue to be

displayed and AHLD will alternate with FM

NOTE

AN/ASN-149(V) will automatically drop manual

altitude hold if four satellites are received

NOTE

The position display is more accurate when

*STATIONARY operation is selected. The

aircraft must be stationary when

*STATIONARY operation is selected. Complete

steps f thru h for *STATIONARY operation

Change 6 3-69

TM 55-1520-240-10

Table 3-14. Displaying Present Position - (Continued)

Step

Procedure

Display

Set data switch to OPT

Press and release slew key until STATIONARY is

displayed on display 1

Check display line 1, if-STATIONARY displayed press

line select key 1.

Set data switch to POS

Repeat steps d thru e

NOTE

To return to moving operation

(-STATIONARY) complete steps k. thru m.

Set data switch to OPT

Press and release slew key until *STATIONARY is

displayed on display line 1

Press line select key 1.

Area Navigation (RNAV). The GPS can

Features.A desired track may be defined

display information needed to navigate from present

and stored with each waypoint entry. When a waypoint

position to any mark or waypoint whether stationary or

is selected as the destination, the desired course is

moving, that is selected as the destination. Horizontal

computed by the GPS based on the desired track

information (bearing, great circle distance time to go to

information. The operator may enter a desired track

destination and slant range distance) can be displayed

when an approach to the destination is required from a

for all waypoints as well as the selected NAVAID

specific direction. When the destination waypoint is

frequency or channel and alphanumeric station identifier.

passed, the desired course will be maintained on the

To use the GPS efficiently, it is necessary to understand

outboard radial. The GPS does not automatically

the basic definitions of area navigation (RNAV).

advance to the next waypoint when the selected one has

been reached: the operator must manually select the

next waypoint

3-70 Change 6

TM 55-1520-240-10

Table 3-15. Area Navigation (RNAV)

Step

Procedure

Display

Set mode switch to NAV

Set data switch to POS

Check display line 1. If > is displayed, press the WP key

NOTE

Steer-to destination is the next waypoint you

want to steer to. It may not be the final

destination of the mission

Check display line 1. If waypoint (WP) number,

alphanumeric identifier, NAVAID frequency or channel

displayed is the next steer-to destination, go to step g. If

waypoint (WP) number alphanumeric identifier,

NAVAID frequency or channel displayed is not the next

steer-to destination, go to step e

NOTE

Multiple waypoints may be defined using the

same NAVAID frequency or channel The first

waypoint displayed is the closest to present

position. The next waypoint or waypoints are

displayed in the order entered. Verify

alphanumeric identifier is the correct choice

before selecting waypoint for use

Enter waypoint (WP) number, alphanumeric identifier,

NAVAID frequency or channel of steer-to destination on

display line 1. If multiple waypoints were entered that

have the same NAVAID frequency or channel go to step

f. if not, go to step g

Change 6 3-71

TM 55-1520-240-10

Table 3-15. Area Navigation (RNAV) - Continued)

Step

Procedure

Display

Check alphanumeric identifier displayed on display line 1

If incorrect press line select key 3 (NEXT) for waypoint

with the same frequency or channel

If correct, press line select key 4 (USE) to return to

normal display

Check waypoint position coordinates and altitude to be

sure that the correct waypoint is displayed

Press WP key. The > will be displayed on display line 1;

present position coordinates and altitude will be

displayed on display lines 2, 3, and 4

NOTE

GPS will continue to compute RNAV data to

the previously selected waypoint until

the next waypoint number entry is completed

by pressing line select key 1

Check steer-to destination number on display line 1. If not

correct, enter correct steer-to destination number on

display line 1

Set data switch to MSN

Check mission profile. If waypoint is not moving, RNAV

mission profile should be selected (- REND displayed).

If waypoint is moving, rendezvous mission profile

should be selected (- REND displayed). Press line select key 2

until correct profile is displayed on display line 2

NOTE

If NO REND DATA is displayed, some data for

a moving waypoint is missing. See paragraph 2-

Set data switch to DIS-TG

3-72 Change 6

TM 55-1520-240-10

Table 3-15. Area Navigation (RNAV)- Continued)

Step

Procedure

Display

Read great circle distance (DIS) in nautical miles (NM) or

kilometers (KM) to destination on display line 2

NOTE

Time to go (TG) is invalid unless your aircraft

is moving

Read time to go (TG) on display line 3

Read bearing (BRG) to destination referenced to true (T),

grid (G), or magnetic (M) north on display line 4

Press slew key

Read slant range (RNG) in nautical miles (NM) or

kilometers (KM) to destination on display line 2

Set data switch to DTK-VA

NOTE

If NO DEST or DEST MOVING is displayed

on display line 2, the GPS will not

accept a source of DTK or DTK entry

NOTE

Each time a new waypoint is selected as the

new destination, verify that the correct DTK

is being used

Change 6 3-73

TM 55-1520-240-10

Table 3-15. Area Navigation (RNAV) - Continued)

Step

Procedure

Display

Select source of desired track (DTK) by pressing line

select key 3. Sources are:

USING OE DTK - Using operator-entered DTK.

If selected and there is no operator-entered DTK,

display line 2 will display dashes (- -). A DTK may

be entered by completing step u on display line 2. A

DTK may be cleared by pressing line select key 2

twice. Display line 3 will automatically display

USING OE DTK if an entry has been made on

display line 2

USING WP DTK - Using the DTK entered during

waypoint entering (Table 3-10). If DTK was not

entered, display line 2 will display dashes (- -)

TO-TO NAV - Using FROM waypoint entered on

display line 4 as the destination to define a great

circle path as the desired course. If no valid FROM

waypoint is entered (by completing step t), display

lines 2 and 4 will display dashes (- -). Display line 3

will automatically display TO-TO NAV if a valid

FROM waypoint has been entered on display line 4

DIRECT-TO - Using present position to destination

great circle desired track. Gives desired track (DTK)

defined by the great circle path from the present

position to the destination

NOTE

Complete step t. if TO-TO NAV was selected on

display line 3

Enter waypoint (WP) number or alphanumeric identifier

(that was entered with the desired waypoint) on display

line 4

NOTE

Complete step u if USING OE DTK was

selected on display line 3

3-74 Change 6

TM 55-1520-240-10

Table 3-15. Area Navigation (RNAV) - Continued)

Step

Procedure

Display

Enter desired track (DTK) on display line 2

Read desired track (DTK) on display line 2

Press slew key

NOTE

If NO DEST is displayed on display line 3, the

GPS will not accept a VA entry

Select source of vertical angle (VA) by pressing line select

key 3. Sources of VA are:

USING OE VA - Using operator entered VA. If

selected and there is no operator entered VA, display

line 2 will display dashes (- -). A VA may be entered

by completing step y on display line 2. A VA may be

cleared by pressing line select key 2 twice. Display

line 3 will automatically display USING OE VA if an

entry has been made on display line 2

USING WP VA - Using the VA entered during

waypoint entering (Table 3-10). If VA was not

entered, display line 2 will display dashes (- -)

NO VA USED - No VA computation made or desired.

If VA is not desired go to step aa

NOTE

Complete step y if USING OE VA was selected

on display line 3. If not go to step aa

Enter vertical angle (VA) on display line 2

Read vertical angle (VA) on display line 2

aa.

Set data switch to ERR

ab.

Read crosstrack error (XTK) left (L) or right (R) of

desired course in nautical miles (NM) or kilometers

(KM) on display line 2

Change 6 3-75

TM 55-1520-240-10

3-66. GPS Data Loader Receptacle. (fig. 3-18)

rotate Data Select switch to position desired. Then

compare data displayed with the known programmed

The GPS data loader receptacle allows the operator to

data.

load pre-programmed navigation information into the

GPS receiver. This navigational information, such as

(5)

Repeat steps (1) thru (5) as desired

way point position, DTM or almanac data is pre-loaded

for any or all remaining way points.

on a data loader module, part number 164191-01-02 or

164191-03-01, if Unit Operations and mission dictates.

(6)

GPS should now be ready for use

during flight operations.

3-67. Controls and Function

- GPS Data Loader

Receptacle.

3-69. GPS KYK-13 Remote Fill Panel. (fig. 3-18)

Controls of the GPS Data Loader Receptacle are as

The GPS KYK-13 Remote Fill Panel allows encryption

follows:

data to be loaded from a KYK-13 or KOI-18 fill device.

Reference will only be made to the KYK-13.

CONTROLS/

INDICATOR

FUNCTION

3-70. Controls and Function - GPS KYK-13 Remote

Fill Panel. (fig. 3-18)

RELEASE

When pressed, releases

Pushbutton

Data Loader Module from

Controls of the GPS KYK-13 Remote Fill Panel are as

Data Loader Receptacle.

follows:

3-68. Normal Operation - GPS Data Loader

CONTROLS/

Receptacle.

INDICATOR

FUNCTION

Perform the following steps in sequence to operate the

LOADProvides positive indication that

data loader system:

STATUS

GPS receiver has successfully

LED

received crypto key fill.

Turn on the GPS System. Allow system to

INIT

When pressed, causes the trans-

warm up and time in for approximately one minute.

LOADfer of crypto key from fill de-

switch

vice (KYK-13 or KOI-18) to GPS

Note

receiver.

Loading data loader must be done in INIT

Mode.

3-71. Normal Operation - GPS KYK-13 Remote Fill

Panel.

Insert data loader module into data loader

receptacle. Wait at least 30 seconds before switching to

To load keys from KYK-13 into the GPS receiver:

another mode. Display momentarily flashes when

information has been successfully transferred.

Note

The GPS receiver does not need to be

Locate module release button on left side of

on to load keys with the KYK-13 Fill

data loader receptacle. Release and remove data loader

Device.

module from data loader receptacle.

Connect KYK-13. either directly or using a

Verify operation of data loader system by:

fill cable, to KYK/GPS FILL JI receptacle located on the

Remote Fill Panel (Figure 3-18).

(1)

Turn GPS Data Select switch to POS.

Turn KYK-13 Fill switch to desired position.

(2)

Select a way point that is known to be

pre-programmed.

Turn KYK-13 Mode switch to ON.

(3)

Compare data displayed with known

Press LOAD IN!T switch on the Remote Fill

programmed data.

Panel (Figure 3-18). Wait approximately 5 seconds. If

key was successfully loaded, Load Indicator light on the

(4)

If other selections are to be checked,

Remote Fill Panel will flash.

Repeat steps b. thru d. to load additional

keys.

Change 6 3-79

TM 55-1520-240-10

Turn KYK-13 Mode switch to OFF.

Lift protective guard from zeroize toggle

switch and activate switch.

Disconnect KYK-13 from aircraft receptacle.

If GPS receiver is on, turn Data Switch to

Stat. Observe message on Page 1, Line 2.

3-72. GPS Zeroize Switch. (fig. 2-9)

The message ZEROED indicates a successful attempt to

The GPS Zeroize switch is located on center instrument

erase information stored in the GPS receiver.

panel, right side of AN/APR-39AV(1) Indicator, and is

used to erase any crypto data and all navigational

The message ZERO FAIL indicates an unsuccessful

information stored in the GPS Receiver.

attempt to erase the information. The GPS receiver

remains classified.

This zeorize switch consists of a guarded toggle switch.

An alternate method to zeroize the GPS

3-73. Normal Operation - GPS Zeroize Switch.

receiver is to use the C-11702/UR and GPS Control Unit

keyboard as follows:

Note

Aircraft battery must be connected, or power applied to

(1)

Select STAT page 1.

aircraft.

(2)

Enter ZZ on line 4, and push Line

Select Key 4.

(3)

If ZEROIZED message is displayed on

Stat Page 1, Line 2, the GPS receiver is declassified.

(4)

If ZERO FAIL message is displayed,

zeroization was not successful and the GPS receiver

remains classified.

3-80 Change 6

55-1520-240-10

CHAPTER

MISSION EQUIPMENT

SECTION I MISSION AVIONICS

4-1.

Radar Signal Detecting Set, AN/

interval (PRI), pulse width (PW).

APR-39A(V)1.

signal strength. The system does not

signals. I

The radar signal detecting set (RSresolution for detected

ibrary s

a passive electronic warfare systeparameters to the threat l

match

aural indications of the presence cation data (EID) files. If ar

ymbol data

transmitters. The RSDS detects thsends the appropriate s

sized

usually associated with hostile ficorresponding computer-synthe

S. If the recei

and MMW (millimeter wave) frequencto the helicopter IC

, the

the heart of the helicopter threatmatch a threat in the EID files

unknown thre

with the laser detecting set AN/bol “U” to indicate an

of an IBIT routin

system AN/AAR-47, and radar warniates the resultsR

Also, it

44(V)3 to process, display, and anresults on the indicator.y

those systems. The system consistsfromtheiAN/AVR-2,oAN/APR-44(3),

icator

center instrument panel (fig. 4-0)systems for display on the ind

in the right aft avionics pod, tICS.ideo receivers (one at

station

50, another at station

605d. The blade antenna senses C/D

(hi-band) outside the helicopter it to the C/D band amplifier porti

station 623). and a blade antennaThe RF signal is filtered, limited

bottom of the fuselage at stationband amplifier with the resultant v

AN/APR-39A volume control labeledpresence of a threat in the C/D ba

canted console provides additionalconjunction with the hi-band signa

ties external(fig.h4-1). The RSDS threat type and current threat mod

the No. 2 DC bus through the ASE launch, etc.).cuit

breaker on No. 2 PDP.

e. The RSDS employs a removable

a. The antenna-detector charact(UDM) which is mountede

in the digi

frequency range of the system. Eaccontains the classified portion of

contain two spiral elements, one oprogram (OFP) and the classified e

and one operating in the MMW (mil(EID) files. The EID.files contain

Each of the spiral elements receiincludes threat signal parameters,

signals in their respective band aaudio data. The UDM can be removed

circuits. The detector portion reprogrammed to accomodate new and

employs an elaborate set of filterallows the RSDS to be tailored

to th

(pulses) from the RF received intion and/or current mission requi

video outputs are then summed andUDM from the digital processor dec

video signal to the appropriate video receiver.

NOTE

b.Each video receiver has two videoThreat symbols (except for U) sh

they serve the left and right anteillustrations are for

illustra

corresponding forward or aft sector.Actual threat symbols are class

plies power to the antenna-detectors and amplifies the

f. The indicator displays threat

detected video inputs from the antenna-detectors. Two video

to threat signals detected and iden

outputs are then sent to the digital processor for signal

relative position from the helicopte

analysis. The video receiver also performs initiated built-in

Symbol position relative to the ce

test on command from the digital processor.

the threats lethality. The highest

c The digital processor suppliare shown nearest12touter edge marki

power to the two video receivers athe indicator graticule represent

signal on the 15 VDC power line to helicopter heading. The

sys

seven

self-test. The digital processor rthreat symbols. If the number

of t

video receivers and processes thexceeds the number the

system can

parameters. These signal parameterhigh

st priority threats will be d

Change

4-1

55-1520-240-10

cannot be identified as a specifictem, radar beacon transponder

syste

as an unknown (symbol U). Search tem, pulse radar jammer

system, or t

radars operating in search mode artem is transmitting. This blanking i

edge of the indicator. The positiothe possible detection of false thr

represents the relative bearing oence induced by these systems. Becau

helicopter. New threats appear insystem, it does not provide any inpu

Threats that drop out of the envirtial blanking of other systems.

displa

10 seconds

before being dropped. A ghosted

symbol appears as though drawn with4-2. dControls and Function, Ra

dar Signal

g. Threats are announced by voice mDetecting Set Indicator. (fig. 4-0)

helicopter ICS. Either of two voice message formats can be

selected using page 2 of the CDU ASE control layer. RWR

AUDIO 1 or normal (full message foCONTROLS/cts full audio.

RWR AUDIO 2 or terse (shortened mesINDICATOR

FUNCTION

shorter audio messages and reduces the audio clutter in dense

Indicator Screen

Displays the appro

signal environments. Both modes provide specific threat type

(CRT)

symbol at the appr

and threat position voice messages.

ate position for e

h. When dense signal environments cause the systeprocessed signal r

operate in a degraded (less sensitive) mode, the eivedm

by the anten

informs the operator by flashing the plus (+) symbodetectors.

RSDS indicator and the voice message “Threat Detection

Plus (+) Symbol

Displayed in cente

Degraded” will be heard over the ICS. When system sensitiv-

indicator during o

ity returns to normal, the plus (+) symbol in the center of the

tion and self-test

RSDS indicator stops flashing and the voice message “Threat

(+) symbol flashes

Detection Restored” will be heard over the ICS.

operator know when

i. The RSDS, LDS, and MWS all execute periodicsystem is operatin

built-in test (PBIT) routines during normal operatiodense signal envir

operational status with the results of these tests bment and threat de

to the digital processor. Failures of PBIT for thestion is degraded.

tems are indicated by the presence Tick MarksreplaciThe 12 out

er edge

(+) symbol in the center of the RSDS indicator. Tings o

n the indica

informs the operator that one or more of the systemsgraticuled

represen

at least some portion of their respective PBIT routpositionss

relative

prompts the operator to perform initiated built-in copter head

ing.

to determine what system(s) has failed and the extent of the

Red MA Indicator

Not used.

failure(s).

Anvis Yellow MA

Not used.

j. IBIT may be selected by the operator. If the RSDS

interface circuitry within either Indicator the self-test. the

RWR TEST FAIL advisory is displayedMA Lamp SwitchFauNot

used.

receivers are shown on the indicator as blinking symbols and

the voice message “APR-39 Failure” will be heard over the

ICS. If the test is good, the voice message “APR-39 Opera-

tional” will be heard over the ICS.BRIL ControlL cauVariessthe brillia

displayed if the RSDS interface circuitry within bothe indicator disp

fails while in its normal operating state. Self-tesTurning knober

clock

detecting set (LDS) and the missile warning systemincreases brightne

are incorporated in the RSDS self-test.

k. The system interfaces with the interference blanker

unit (IBU) in an attempt to prevent other aircraft systems,

Indicates that a s

which operate in the same approxiStroberequency range,

a fire co

from interfering with it. The lo-band portion of thradar ors

radar operating in

blanked by the IBU when either the IFF transponder system

mode has been dete

or the TACAN system is transmitting. The hi-band portion of

nd identified.

Change

4-2.1

TECHNICAL MANUAL MAINTENANCE MANUAL FOR ARMY CH-47D HELICOPTER (1992) - page 7