workbook - 87th · this workbook is designed to introduce you to features of the flight...

F-16

PILOT TRAINING COURSE

WORKBOOK

FLIGHT INSTRUMENTS

WL-075-6X

JUL 02

SME: MIKE ELLYSON – BOEING AEROSPACE, TUCSON

SECURITY AGREEMENT This information is furnished upon the condition that it will not be released to another nation without specific authority of the Department of the Air Force of the United States, that it will be used for military purposes only, that individual or corporate rights originating in the information, whether patented or not, will be respected, that the information will be provided substantially the same degree of security afforded it by the Department of Defense of the United States, and that recipients will report promptly and fully to the US authorities any known or suspected compromise of United States military information released to them.

FLIGHT INSTRUMENTS WL-075-6X CHANGE SHEET JUL 02

i

CHANGE INSTRUCTIONS

DOCUMENT REMOVE INSERT ALL, JUL 02 New workbook replaces IL-075-XX (FEB 99).

ii

INTENTIONALLY BLANK

FLIGHT INSTRUMENTS WL-075-6X JUL 02

A-1

Administrative Information Instructions This workbook is designed to introduce you to features of the flight instruments. You should review the objectives and read through the workbook text. Any questions you have after completion of the workbook should be referred to an instructor. Purpose The purpose of this lesson is to introduce features of the F-16 flight instruments. This is a stand-alone workbook; there is no lecture. Workbook Objectives 1. Identify the features of the primary flight instrument displays, including ADI, HSI,

altimeter, and airspeed Mach indicator. 2. Interpret the angle of attack indicator, indexer, and HUD AOA bracket. 3. Select the proper ILS/navigation instrument options, and interpret HUD, HSI, and

ADI displays. Administrative Information.......................................................................................................A-1 Text .........................................................................................................................................B-1 Main Topics

1. Overview

2. Flight Instrument Features

3. Angle of Attack System

4. Instrument Landing System

Reading Assignment 1. T.O. 1F-16C-1 a. Instrument Landing System b. INSTR MODE Select Panel c. Flight Instruments 2. 1F-16C-34-1-1, HUD Symbology

FLIGHT INSTRUMENTS WL-075-6X JUL 02

A-2

References 1. T.O. 1F-16C-1 2. T.O. 1F-16C-34-1-1

FLIGHT INSTRUMENTS WL-075-6X FEATURES JUL 02

B-1

FLIGHT INSTRUMENT FEATURES Altimeter The altimeter is a dual-mode indicator with a range of -1000' to +80,000'. The operating mode is manually selected by a mode lever located on the lower right corner of the indicator. The primary mode is the electric (ELECT) mode in which the altimeter is driven by the central air data computer (CADC). The secondary operating mode is pneumatic (PNEU) in which the altimeter is pneumatically operated by static pressure supplied by the pitot-static system. If you have CADC or altimeter servo failure in the electric mode, the altimeter automatically reverts to the pneumatic mode. This is indicated by the PNEU flag appearing on the face of the altimeter. This flag may also appear when in the transonic region or while performing high-G maneuvers. The barometer pressure setting knob is located at the lower left corner of the instrument. The knob is used to set the current barometric setting. This setting is electrically transmitted to the CADC as a correction for the pressure altitude displayed on the HUD.

WL-075-6X 001

0 123

45678

9ALT

IN HG

PNEU

ELECT

29780011

0

01000 FT100 FT

MODELEVER

PNEU INDICATOR(Failures)

BAROMETRICPRESSURE SET

Figure 1. Altimeter.


B-2

Airspeed/Mach Indicator The airspeed/Mach indicator displays indicated airspeed (IAS), Mach number, and maximum allowable airspeed. The indicator is pneumatically operated by both total and static pressure supplied by the pitot-static system. IAS is displayed by a moving pointer against a fixed airspeed dial graduated in knots. The range of the indicator is from 80 to 850 kts. Mach number is read against the airspeed pointer on a rotating disk in numbers ranging from 0.5 to 2.2 Mach. The maximum allowable airspeed pointer indicates 800 kts at sea level. Higher airspeeds are indicated as altitude is increased. This indication is not a valid maximum allowable airspeed cue; it should be disregarded. Refer to the maximum airspeed operating limitations in Section V of the Dash 1. There is also a airspeed reference index that can be adjusted using the set index knob.

WL-075-6X 002

SETINDEX

1

1.5

23

4

5

6

7

8KNOTSX 100

MAXIMUMALLOWABLEAIRSPEEDPOINTER

MACH SCALE

AIRSPEEDREFERENCE

INDEX

SET INDEXKNOB

AIRSPEED/MACHPOINTER

Figure 2. Airspeed/Mach Indicator.


B-3

Standby Attitude Indicator The standby attitude indicator (SAI) is a self-contained, electrically powered, vertical gyroscope that mechanically positions the attitude sphere of the indicator to display roll and pitch attitudes. Pulling the PULL TO CAGE knob and holding it until the barrel is caged manually erects the gyro. The aircraft reference symbol can be positioned vertically by rotating the PULL TO CAGE knob. The standby attitude indicator operates for approximately 9 minutes after loss of battery bus electrical power. It indicates 4° less than the ADI when both indicators are set at the pitch index since the SAI is mounted at an angle. When caging the indicator on the ground, allow 2 minutes of gyro spin time prior to taxi. When airborne, ensure the wings are level while caging the indicator. The SAI gyroscope is unrestricted in roll but limited to approximately ±85° in pitch. The OFF warning flag is in view during loss of electrical power to the indicator and whenever the PULL TO CAGE knob is pulled. The indicator can develop errors during aerobatic maneuvering, especially when pitch is near 90°. If the errors exceed 7°, automatic erection will be cut off after returning to level flight. In this case, you must manually cage the instrument to eliminate the error.

WL-075-6X 003

OFF FLAG(Loss of electric

and caging indicator)

MANUAL CAGING/ADJUSTMENT KNOB

Figure 3. Standby Altitude Indicator.


B-4

Vertical Velocity Indicator The vertical velocity indicator (VVI) displays a rate of climb or descent within a range of 6000 fpm and receives its information from the CADC. The indicator is powered by the emergency ac bus No. 1. The VVI is a sliding scale as opposed to a moving needle. Because you are only viewing a small part of the scale in the window at any given moment, it is very difficult to determine trends or read the instrument quickly. The VVI must be read and interpreted by taking into consideration the indications of other performance instruments.

WL-075-6X 004

1.50.51

VVI

1000FPM

Figure 4. Vertical Velocity Indicator.


B-5

Magnetic Compass The magnetic compass is a self-contained indicator showing the heading of the aircraft with respect to magnetic north. Magnetic disturbances caused by the aircraft are automatically compensated for with built-in magnets. A deviation correction card for the compass is located immediately below and aft of the compass on the right bulkhead. There is no magnetic compass in the rear cockpit of the F-16D.

WL-075-6X 005 Figure 5. Magnetic Compass.


B-6

Altitude Director Indicator The attitude director indicator (ADI) displays aircraft attitude supplied by the inertial navigation set (INS). The ADI is not limited in roll or pitch and accurately displays any aircraft attitude. The pitch trim knob is used to adjust the attitude sphere to the desired pitch attitude. The ADI is not AOA compensated. This means that the degrees shown on the ADI in figure 6 are degrees attitude. The picture in this example could be a climb or it could be level flight with 9° of AOA. It would indicate a 2° dive if the aircraft had 11° AOA. Other flight instruments must be cross-checked, especially when recovering from an unusual attitude. During an ILS the indicator displays glideslope and localizer information. The turn needle senses aircraft turn rate and displays one needle width in response to a 1.5° per second turn rate. The slip indicator is self-contained.

WL-075-6X 006

PITCH TRIM KNOBSLIP INDICATOR

TURN NEEDLE

Figure 6. Altitude Director Indicator.


B-7

There are four warning flags on the ADI. The OFF flag indicates either INS or ADI failure. The GS flag indicates the glideslope deviation bar is unreliable. The LOC flag indicates the localizer signal is unreliable. The AUX flag signals that the INS has failed or is operating in a less precise attitude condition. It also indicates an INS heading malfunction, requiring the HSI heading to be set manually on the instrument mode select panel.

WL-075-6X 007

AUX WARNING FLAG

LOCALIZER WARNING FLAGGLIDESLOPE WARNING FLAG

OFF WARNING FLAG

Figure 7. ADI Warning Flags.


B-8

Horizontal Situation Indicator The horizontal situation indicator (HSI) provides a horizontal view of the navigation situation. The aircraft symbol in the center of the indicator is fixed and is similar to an aircraft on a compass rose. The face of the HSI is a compass card driven by the INS. The aircraft magnetic heading is always read at the upper index line. The heading reference marker or "captains bars," once set with the HDG set knob, rotates with the compass rose. This marker provides the reference when the AUTOPILOT ROLL switch is positioned to heading select (HDG SEL). Rotating the CRS set knob moves the head of the course arrow to the desired course on the compass card. The course selector window should be checked for the precise reading. Once set, the course arrow rotates with the compass card. The bearing pointer provides bearing information to a TACAN station or an INS destination. The range indicator is distance in nautical miles to a TACAN station, DME navigational aid, or INS steerpoint. A red warning flag covers the range window when an unreliable signal is received. Also, loss of electrical power causes the HSI warning flag to appear. The to/from indicators are two small triangles to the right of the aircraft symbol. The course deviation indicator displays aircraft position in relation to the selected course.

WL-075-6X 008

AIRCRAFT MAGNETICHEADING

MILES COURSE000 100

BEARINGPOINTER

RANGEINDICATOR

MILES000

WARNING FLAG

COURSE ARROW

TO-FROM INDICATORS

COURSEDEVIATIONINDICATOR

HEADING SET KNOB COURSE SET KNOB

COURSEDEVIATIONWARNING

FLAG

COURSESELECTORWINDOW

HSI WARNING FLAG

UPPER LUBBER LINE

HEADINGREFERENCE

MARKER

BEARING POINTER TAIL

Figure 8. Horizontal Situation Indicator.


B-9

Clock The flight instruments include an 8-day, manually wound clock. The button at the top right corner starts, stops, and resets the elapsed time pointer.

12 12

3

4

567

8

9

10

11

605

10

15

20

2530

45

50

55

35

40

PUSH HARD

WL-075-6X 009 Figure 9. Clock.

FLIGHT INSTRUMENTS WL-075-6X INSTRUMENT LANDING SYSTEM JUL 02

B-10

ANGLE OF ATTACK INDICATORS AOA System The angle of attack (AOA) system consists of two AOA transmitters located on each side of the nose radome, AOA ports on the fuselage-mounted air data probe, a pneumatic sensor assembly (PSA), an AOA correction device in the CADC, an AOA indexer, and a vertical scale AOA indicator. AOA Indicator The AOA indicator, located on the instrument panel, displays actual AOA in degrees. The indicator has a vertically moving tape with a scale from -5° to +32°. The tape is color-coded from 9 to 17° which coincides with the color-coded symbols on the AOA indexer.

WL-075-6X 010

15

10

APPROACH

AOA

DEG

RED(14–17°)

GREEN(12–14°)

AMBER(9–12°)

Figure 10. AOA Indicator.


B-11

AOA Indexer The AOA indexer located on the top left side of the glareshield, consists of three color-coded symbols arranged vertically. The indexer provides a head-up indication of aircraft AOA by illuminating the symbols individually or in combinations. The indexer lights display AOA corrections based on approximately 13° AOA. The indexer operates continuously with the landing gear handle up or down. A dimming lever, located on the side of the indexer, controls the intensity of the lighted symbols.

WL-075-6X 011

RED(14–17°)

GREEN(12–14°)

AMBER(9–12°)

Figure 11. AOA Indexer.


B-12

Indexer Test Lights The indexer lights are tested by the MAL & IND LTS switch on the test panel. The test should be performed with the dimming lever in the BRT position.

WL-075-6X 012

TEST

EPU/GEN

NORM

OFF

OFF

OXY QTY

MAL &IND LTS

FLCSPWR

L R

TEST

MAINT

TEST

PROBE HEAT

OFF

C H A N _ 2 1

OHEAT DETECTFIRE &

B C D

A

Figure 12. AOA Indexer Light Test.


B-13

INSTRUMENT LANDING SYSTEM (ILS) INSTR MODE Select Panel

The INSTR MODE select panel provides for the selection of displays on the HSI and ADI. When an ILS mode is selected by the INSTR MODE knob, localizer and glide slope deviation bars are also displayed on the HUD.

The INSTR HDG knob is (pushed to turn) used to manually set the INS heading to a known magnetic heading in the event of an INS failure (indicated by the AUX warning flag on the ADI). Turning the knob will rotate the HSI compass card.

The instrument modes are ILS/TCN, TCN, NAV, and ILS/NAV.

WL-075-6X 013

MODE

INSTR

PUSH

HDG

ILS/TCN

ILS/NAV

NAVTCN

Figure 13. AOA Indications.

ILS Displays

The ILS provides precision approaches to runways equipped with localizer, glide slope, and marker beacon equipment. The glide slope and localizer receivers supply glide slope and localizer deviation to the deviation bars on the ADI and HUD; the HSI also displays course or localizer deviation data.

HUD symbology consists of localizer and glide slope deviation bars. Dashed deviation bars indicate invalid data. Deviation bars are roll stabilized with tic marcs positioned at the one-dot and two-dot deflections. Also displayed is a caret depicting the selected course on the heading scale.


B-14

ILS/TCN Selected When ILS/TCN is selected, the data displayed on the ADI includes glide slope deviation bar and the localizer deviation bar. If the glide slope or localizer signals become unreliable, the GS and/or LOC warning flags will appear and the deviation bar(s) will center. Data displayed on the HSI with ILS/TCN selected includes INS magnetic heading, manually set localizer course, localizer deviation, magnetic bearing, and range to the selected TACAN station. If the localizer signal becomes unreliable, the warning flag will appear.

MILES COURSE010 123

MODE

INSTR

PUSH

HDG

ILS/TCN

ILS/NAV

NAVTCN

WL-075-6X 014

INS MAGNETICHEADING

MAUALLY SETLOCALIZERCOURSE

LOCALIZERCOURSEDEVIATIONBAR

LOCALIZERCOURSEDEVIATIONBAR

GLIDESLOPEDEVIATIONBAR

RANGETO TACAN

BEARING TO TACAN

BEARING POINTER TAIL

COURSE DEVIATIONWARNING FLAGWINDOW

Figure 14. ILS/TCN Selected.


B-15

With the INSTR MODE knob in ILS/TCN, the data displayed on the HUD includes glide slope and localizer deviation bars, and ILS command steering symbol. When the nose landing gear is down (and locked) the AOA bracket also displays on the HUD.

The ILS command steering consists of a circle, a tick mark positioned at the top of the circle, and a course caret on the heading scale.

Note that although the deviation bars indicate the direction and magnitude of the glide slope and localizer course deviation from aircraft present position, the bars do not necessarily provide steering information; therefore, they should not be used as steering bars.

An X appears over the command steering symbol tick mark if pitch steering becomes invalid. In this instance, the command steering symbol will return to the horizon line but will continue to provide localizer steering information as long as there is a valid localizer signal.

WL-075-6X 015

ILSGLIDESLOPE

INTERCEPTED

NORMALFLIGHT

DIRECTOR

ILS PITCHSTEERING

DATA INVALID

ON GLIDESLOPEON COURSE

PITCH STEERINGDATA INVALID

AOA BRACKET

DEVIATIONBARS

(W/VALID DATA)

COMMANDSTEERINGSYMBOL

017>01

150

20

10

C

R 1,120AL 100

02,2

02,0

2,100

1.0

11 13123

5 5

5 5

017>01

150

20

10

C

R 1,120AL 100

02,2

02,0

2,100

1.0

11 13123

5 5

5 5

5 55 5

Figure 15. ILS/TCN HUD Symbology.


B-16

AOA Bracket

The HUD AOA bracket symbol and flightpath marker (FPM) provide a head-up display of aircraft AOA. The FPM, when aligned with the top of the bracket, indicates 11° AOA. The FPM centered on the bracket indicates 13° AOA, and when aligned with the bottom of the bracket, AOA is 15°. The HUD AOA display is only available with the landing gear handle down. This graphic depicts AOA indications for different flight conditions.

WL-075-6X 016

15

10

APPROACH

AOA

DEG

15

10

APPROACH

AOA

DEG

20

15

APPROACH10

AOA

DEG

11° AOA(Fast)

13° AOA(On speed)

15° AOA(Slow)

Figure 16. AOA Indications.


B-17

ILS/NAV Selected All data displayed in ILS/NAV is identical to the display of ILS/TCN with the following exceptions noted on Figure 17. Additionally, HUD displays are identical between ILS/TCN and ILS/NAV.

WL-075-6X 017

BEARINGTO INSDESTINATION

MODE

INSTR

PUSH

HDG

ILS/TCN

ILS/NAV

NAVTCN

MILES COURSE010 123

RANGE TO INSDESTINATION

Figure 17. ILS/NAV HUD Symbology.


B-18

MRK BCN Light The MRK BCN light is located on the lower instrument panel, to the lower right of the ADI. When the aircraft is over a marker beacon facility, the light blinks according to its code.

WL-075-6X 018

MILES COURSE003 103

1.50.51

VVI

1000FPM

TEST NORM

RSVR

NORM

INTWING

EXTWING

EXTFUEL TRANS

FUEL

QTY

SEL

EXTCTR

09

MRKBCN

Figure 18. MRK BCN Light.


B-19

TCN Selected When TCN is selected with the INSTR MODE knob, the data displayed on the HSI includes INS magnetic heading, magnetic bearing and range to the selected TACAN station, manually set course, deviations from the set course, and TO-FROM indication. The TCN mode has no effect on HUD symbology. The deviation bars are out of view on the ADI.

WL-075-6X 019

MODE

INSTR

PUSH

HDG

ILS/TCN

ILS/NAV

NAVTCN

MILES COURSE125 100

BEARING TO TACAN STATION

INS MAGNETICHEADING

MILES TO TACAN STATION OR DME NAV AID

DEVIATIONFROM

COURSE

HEADING 100

125 nm

R-280

ACTUALPOSITION

DESIREDPOSITION

IF TACAN SIGNALBECOMES UNRELIABLE,TURNS RED, FLAG APPEARS OVER MILES AND TO-FROM INDICATORS BLANK

MANUALLYSET COURSE

TO-FROMINDICATORS

BEARINGPOINTER TAIL

VORTAC

R-256

Figure 19. TCN Selected.


B-20

NAV Selected When NAV is selected, the data displayed on the HSI is the same as the TCN mode with a few exceptions. First, bearing and range are to the INS destination. Second, TO-FROM windows are blanked. Finally, the warning flags appear when the INS fails.

WL-075-6X 020

MODE

INSTR

PUSH

HDG

ILS/TCN

ILS/NAV

NAVTCN

Figure 20. NAV Selected.

workbook - 87th · this workbook is designed to introduce you to features of the flight...

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