F-16 PILOT TRAINING COURSE

Transcription

1 F-16 PILOT TRINING COURSE WORKBOOK FLIGHT INSTRUMENTS JUL 02 SME: MIKE ELLYSON BOEING EROSPCE, TUCSON

2 SECURITY GREEMENT This information is furnished upon the condition that it will not be released to another nation without specific authority of the Department of the ir 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.

3 CHNGE SHEET JUL 02 CHNGE INSTRUCTIONS DOCUMENT REMOVE INSERT LL, JUL 02 New workbook replaces IL-075-XX (FEB 99). i

4 INTENTIONLLY BLNK ii

5 JUL 02 dministrative 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. ny 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 DI, HSI, altimeter, and airspeed Mach indicator. 2. Interpret the angle of attack indicator, indexer, and HUD O bracket. 3. Select the proper ILS/navigation instrument options, and interpret HUD, HSI, and DI displays. dministrative Information...-1 Text...B-1 Main Topics 1. Overview 2. Flight Instrument Features 3. ngle of ttack System 4. Instrument Landing System Reading ssignment 1. T.O. 1F-16C-1 a. Instrument Landing System b. INSTR MODE Select Panel c. Flight Instruments 2. 1F-16C , HUD Symbology -1

6 JUL 02 References 1. T.O. 1F-16C-1 2. T.O. 1F-16C

7 FETURES JUL 02 FLIGHT INSTRUMENT FETURES ltimeter 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 (CDC). 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 CDC 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 CDC as a correction for the pressure altitude displayed on the HUD. PNEU INDICTOR (Failures) BROMETRIC PRESSURE SET LT IN HG FT 100 FT ELECT P N E U MODE LEVER Figure 1. ltimeter. 001 B-1

8 FETURES JUL 02 irspeed/mach Indicator The airspeed/mach indicator displays indicated airspeed (IS), Mach number, and maximum allowable airspeed. The indicator is pneumatically operated by both total and static pressure supplied by the pitot-static system. IS 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. IRSPEED/MCH POINTER MXIMUM LLOWBLE IRSPEED POINTER KNOTS X SET INDEX MCH SCLE IRSPEED REFERENCE INDEX SET INDEX KNOB 002 Figure 2. irspeed/mach Indicator. B-2

9 FETURES JUL 02 Standby ttitude Indicator The standby attitude indicator (SI) 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 CGE 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 CGE knob. The standby attitude indicator operates for approximately 9 minutes after loss of battery bus electrical power. It indicates 4 less than the DI when both indicators are set at the pitch index since the SI 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 SI 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 CGE 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. OFF FLG (Loss of electric and caging indicator) MNUL CGING/ DJUSTMENT KNOB Figure 3. Standby ltitude Indicator. B-3 003

10 FETURES JUL 02 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 CDC. 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. V V I F P M Figure 4. Vertical Velocity Indicator. 004 B-4

11 FETURES JUL 02 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. 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. Figure 5. Magnetic Compass. 005 B-5

12 FETURES JUL 02 ltitude Director Indicator The attitude director indicator (DI) displays aircraft attitude supplied by the inertial navigation set (INS). The DI 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 DI is not O compensated. This means that the degrees shown on the DI in figure 6 are degrees attitude. The picture in this example could be a climb or it could be level flight with 9 of O. It would indicate a 2 dive if the aircraft had 11 O. 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. SLIP INDICTOR PITCH TRIM KNOB TURN NEEDLE 006 Figure 6. ltitude Director Indicator. B-6

13 FETURES JUL 02 There are four warning flags on the DI. The OFF flag indicates either INS or DI failure. The GS flag indicates the glideslope deviation bar is unreliable. The LOC flag indicates the localizer signal is unreliable. The UX 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. GLIDESLOPE WRNING FLG LOCLIZER WRNING FLG OFF WRNING FLG UX WRNING FLG 007 Figure 7. DI Warning Flags. B-7

14 FETURES JUL 02 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 UTOPILOT 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 TCN station or an INS destination. The range indicator is distance in nautical miles to a TCN station, DME navigational aid, or INS steerpoint. red warning flag covers the range window when an unreliable signal is received. lso, 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. 000 MILES RNGE INDICTOR BERING POINTER COURSE DEVITION WRNING FLG WRNING FLG MILES UPPER LUBBER LINE COURSE IRCRFT MGNETIC HEDING COURSE SELECTOR WINDOW COURSE RROW HSI WRNING FLG COURSE DEVITION INDICTOR HEDING REFERENCE MRKER TO-FROM INDICTORS HEDING SET KNOB BERING POINTER TIL COURSE SET KNOB Figure 8. Horizontal Situation Indicator. 008 B-8

15 FETURES JUL 02 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. PUSH HRD Figure 9. Clock. 009 B-9

16 INSTRUMENT LNDING SYSTEM JUL 02 NGLE OF TTCK INDICTORS O System The angle of attack (O) system consists of two O transmitters located on each side of the nose radome, O ports on the fuselage-mounted air data probe, a pneumatic sensor assembly (PS), an O correction device in the CDC, an O indexer, and a vertical scale O indicator. O Indicator The O indicator, located on the instrument panel, displays actual O 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 O indexer. O D E G P P R O C H RED (14 17 ) GREEN (12 14 ) MBER (9 12 ) Figure 10. O Indicator. 010 B-10

17 INSTRUMENT LNDING SYSTEM JUL 02 O Indexer The O 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 O by illuminating the symbols individually or in combinations. The indexer lights display O corrections based on approximately 13 O. The indexer operates continuously with the landing gear handle up or down. dimming lever, located on the side of the indexer, controls the intensity of the lighted symbols. RED (14 17 ) GREEN (12 14 ) MBER (9 12 ) Figure 11. O Indexer. 011 B-11

18 INSTRUMENT LNDING SYSTEM JUL 02 Indexer Test Lights The indexer lights are tested by the ML & IND LTS switch on the test panel. The test should be performed with the dimming lever in the BRT position. FIRE & OHET DETECT T E S T PROBE HET OFF OXY QTY OFF EPU/GEN ML & IND LTS FLCS PWR L R C D B C H N _ 1 2 TEST OFF TEST NORM MINT Figure 12. O Indexer Light Test. 012 B-12

19 INSTRUMENT LNDING SYSTEM JUL 02 INSTRUMENT LNDING SYSTEM (ILS) INSTR MODE Select Panel The INSTR MODE select panel provides for the selection of displays on the HSI and DI. 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 UX warning flag on the DI). Turning the knob will rotate the HSI compass card. The instrument modes are ILS/TCN, TCN, NV, and ILS/NV. MODE TCN NV ILS/ TCN ILS/ NV I N S T R HDG PUSH ILS Displays Figure 13. O Indications. 013 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 DI 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. lso displayed is a caret depicting the selected course on the heading scale. B-13

20 INSTRUMENT LNDING SYSTEM JUL 02 ILS/TCN Selected When ILS/TCN is selected, the data displayed on the DI 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 TCN station. If the localizer signal becomes unreliable, the warning flag will appear. MODE TCN NV ILS/ TCN ILS/ NV I N S T R HDG PUSH RNGE TO TCN GLIDESLOPE DEVITION BR LOCLIZER COURSE DEVITION BR INS MGNETIC HEDING BERING TO TCN MILES COURSE MULLY SET LOCLIZER COURSE COURSE DEVITION WRNING FLG WINDOW BERING POINTER TIL LOCLIZER COURSE DEVITION BR 014 Figure 14. ILS/TCN Selected. B-14

21 INSTRUMENT LNDING SYSTEM JUL 02 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 O 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. n 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 C ,2 2, ,0 R 1,120 L >01 O BRCKET 5 5 DEVITION BRS (W/VLID DT) COMMND STEERING SYMBOL NORML FLIGHT DIRECTOR ILS GLIDESLOPE INTERCEPTED ILS PITCH STEERING DT INVLID ON GLIDESLOPE ON COURSE PITCH STEERING DT INVLID 015 Figure 15. ILS/TCN HUD Symbology. B-15

22 INSTRUMENT LNDING SYSTEM JUL 02 O Bracket The HUD O bracket symbol and flightpath marker (FPM) provide a head-up display of aircraft O. The FPM, when aligned with the top of the bracket, indicates 11 O. The FPM centered on the bracket indicates 13 O, and when aligned with the bottom of the bracket, O is 15. The HUD O display is only available with the landing gear handle down. This graphic depicts O indications for different flight conditions. O D E G P P R O C H O D E G P P R O C H O D E G P P R O C H 11 O (Fast) 13 O (On speed) 15 O (Slow) Figure 16. O Indications. 016 B-16

23 INSTRUMENT LNDING SYSTEM JUL 02 ILS/NV Selected ll data displayed in ILS/NV is identical to the display of ILS/TCN with the following exceptions noted on Figure 17. dditionally, HUD displays are identical between ILS/TCN and ILS/NV. MODE TCN NV ILS/ TCN ILS/ NV I N S T R HDG PUSH RNGE TO INS DESTINTION BERING TO INS DESTINTION MILES COURSE 017 Figure 17. ILS/NV HUD Symbology. B-17

24 INSTRUMENT LNDING SYSTEM JUL 02 MRK BCN Light The MRK BCN light is located on the lower instrument panel, to the lower right of the DI. When the aircraft is over a marker beacon facility, the light blinks according to its code. V V I F P M MILES COURSE MRK BCN F U E L Q T Y TEST EXT CTR 09 NORM RSVR INT WING EXT WING S E L EXT FUEL TRNS NORM Figure 18. MRK BCN Light. 018 B-18

25 INSTRUMENT LNDING SYSTEM JUL 02 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 TCN 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 DI. MILES TO TCN STTION OR DME NV ID BERING TO TCN STTION INS MGNETIC HEDING ILS/ TCN TCN MODE NV ILS/ NV MILES COURSE MNULLY SET COURSE I N S T R HDG IF TCN SIGNL BECOMES UNRELIBLE, TURNS RED, FLG PPERS OVER MILES ND TO-FROM INDICTORS BLNK PUSH TO-FROM INDICTORS DEVITION FROM COURSE R-280 BERING POINTER TIL DESIRED POSITION HEDING 100 R-256 CTUL POSITION 125 nm VORTC 019 Figure 19. TCN Selected. B-19

26 INSTRUMENT LNDING SYSTEM JUL 02 NV Selected When NV 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. MODE TCN NV ILS/ TCN ILS/ NV I N S T R HDG PUSH 020 Figure 20. NV Selected. B-20