mcdonnell douglas dc 10 40 flight instruments

C H A P T E R 10

FLIGHT INSTRUMENTS

Page

TABLE OF CONTENTS 10-00-01/02

DESCRIPTION

General 10-10-01

Description 10-10-01

Controls and Indicators 10-10-02

COMPONENTS (Not Used)

CONTROLS AND INDICATORS 10-30-01

FUNCTIONAL SCHEMATICS

Pitot/Static System 10-40-01/02

Central Air Data Computer/Pitot Static Interface 10-40-03/04

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FLIGHT INSTRUMENTS

GENERAL

The flight instruments chapter includesthe pitot static system, the air data sys-tem, and those basic flight instruments,standby instruments, and related com-ponents which provide altitude, airspeed,Mach, vertical speed, true airspeed,over speed warning, attitude, and airtemperature data to the flight crew.Sensors provide inputs to three centralair data computers where temperatureand instrument position corrective fac-tors are applied as appropriate. Theflight recorder maintains a history oftime-related flight parameters.

DESCRIPTION

PITOT/STATIC SYSTEM

During normal operation, the pitot/staticsystem inputs variable pressure valuesto the central air data computers whichprovide computed outputs for readout ofairspeed, vertical speed, and altitude.Two parallel static systems (the Cap-tain' s and First Officer's) provide inputsto the central air data computers, whilea third system provides raw inputs(uncorrected barometric) to the standbyaltimeter, the standby airspeed indicator,and provides input to the third central airdata computer. A fourth (alternate static)system provides raw inputs to the cabinpressure controller and the cabin dif-ferential pressure indicator.

PRIMARY FLIGHT INSTRUMENTS

The primary Mach/AS indicators, trueairspeed indicators, vertical speed indi-cators, altimeters, and the over speedwarning system derive their inputs fromthe central air data computers whichreceive and process (correct for

temperature and position error) raw datafrom the pitot static system. The over-speed warning sensor will activate anaural warning device when limiting air-speeds are reached.

DIRECTIONAL INDICATING SYSTEMS

There are two independent compass sys-tems. Each compass system is stabi-lized by the associated directional gyroor inertial navigation system (INS) plat-form (if installed). The compass systemcan operate in the slaved (normal) modeor DG (unslaved) mode. The mode isselected by the COMPASS switch on theoverhead panel. In the slaved mode thecompass is synchronized with a fluxvalve and provides magnetic heading.The synchronization indicator is on theoverhead panel. In the DG mode thecompass heading is controlled by theSET HDG knob on the overhead panel.The compass heading is displayed on theradio magnetic indicators (RMI) at alltimes, and on the horizontal situationindicator (HSI) compass card when theHSI switch is in the RAD position. Thenumber 1 compass system normallydrives the Captain's HSI and the FirstOfficer's RMI. The number two compasssystem normally drives the First Officer'sHSI and the Captain's RMI. When theCOMP Selector on the overhead panel isplaced in the BOTH ON 2 (or BOTH ON 1)position, the number two (or one) com-pass system drives all compass cards.The adjacent annunciator light will be on.On aircraft with INS installed, when theHSI switch is in INS, the HSI compasscard will display true heading derivedfrom the associated INS. A standbymagnetic compass provides a headingreference in relation to magnetic north.

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ATTITUDE DIRECTOR INDICATOR

For the purpose of this chapter, theAttitude Director Indicator (ADI) is con-sidered as a basic attitude display andnot for the broader role it performs asthe command focal point in the flightdirector and flight guidance subsystems.These diverse aspects are described inthe navigation and flight guidancechapters.

Two remote vertical gyros or inertialplatforms (if installed) provide basicattitude information to the Captain's andFirst Officer's ADI's. The ATT COMPSTAB selector permits selection of thethird vertical gyro or the third inertialplatform (if installed) for input to eitherthe Captain's or First Officer's indicators.An ATT warning flag on the ADI indicatesattitude data are unusable. The ADI has

a test button which, when pushed, teststhe attitude, flight director, and risingrunway functions.

DIGITAL FLIGHT DATA RECORDER

A digital flight data recorder (DFDR)records data from aircraft subsystems,sensors and flight data entry panel inputs.

CONTROLS AND INDICATORS

The controls, indicators, and annunciatorlights are on the Captains and FirstOfficers instrument panels, Centerinstrument panel, Overhead panel, andFlight Engineers Upper No. 2 and 3panels. Illustrations of the panels arein Chapter 1. Individual controls andindicators are illustrated and describedin this chapter.

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Feb 1/79

FLIGHT INSTRUMENTS - Controls and Indicators

Altitude Advisory LightWorks in conjunction with altitude ad-visory system. Provides steady onsignal (in conjunction with aural tone)when aircraft is at the altitude ad-visory threshold (minimum of 750feet from selected altitude) and goesoff when within 250 feet of selectedaltitude. Advisory light flashes (in con-junction with aural tone) when air-craft deviates 250 feet or more frompreviously selected and acquiredaltitude. Pushing the altitude advisoryRESET button will turn off theflashing advisory light.The steady light can be turned off anytime in flight by rotating the ALT pre-select knob to set in new altitude.

100 Foot PointerThe pointer will make a full circle foreach 1000 ft. of altitude gained orlost. Negative altitudes are read onthe dial as 900 feet for a - 100foot altitude, et cetera. Pointer willremain in last position with powerfailure.

BARO Set KnobPush-to-turn BARO knob is rotatedto change barometric pressurevalues as read in the MB/IN HGreadouts.

OFF FlagAppears to indicate mach data areunusable.

Vmo PointerReads maximum permissible air-speed as related to altitude. Failureof the Vmo advisory system willdrive the Vmo pointer to 257.5 kts.Normal static sea level indication is350 knots.

Airspeed PointerReads indicated airspeed. Failure ofairspeed indicating system will causepointer to remain in the last position.

Airspeed Command BugThis bug reflects airspeed set in flightguidance SPD readout.

(OVERHEAD PANEL)

Altitude WarningsThe digital readout also displays anOFF failure flag which is associatedwith either a loss of input power, in-valid computer input, no input for2 +- 0.5 seconds or more, internalpower supply failure or other inter-nal failures.

FAILURE FLAG

ALTIMETERAltitudeReferenceIndex

MACH/AS INDICATOR

CAPTAIN'S AND COPILOT'SINSTRUMENT PANELS

MAX SPD WARN TEST Selector1 —Rotat ing and holding switch

momentarily will test Max SpeedWarning System 1. An auralwarning will sound.

2—Rotat ing and holding switchmomentarily will test Max SpeedWarning System 2. An auralwarning will sound.

Digital ReadoutIndicates altitude from 0 to 50,000feet. The right-hand two-digit drum isnumbered in 20-foot increments. The"0" position of the left-hand ten-thousands drum is green for alert in-dication of altitudes of less than 10,000feet.

Altitude Reference Bugs (2)Movable pointer used to alert pilotto specified altitudes.

NEG FlagA negative altitude shutter ob-scures the digital readout to annun-ciate altitudes below sea level.

Reference Index KnobUsed to set the altitude referenceindex as desired.

MB/IN HG ReadoutIndicates the selected barometricpressure as expressed in millibarsand inches of mercury.

MACH ReadoutIndicates mach number. The mini-mum mach readout is .150.

A/S FlagAppears when airspeed data areunusable.

Airspeed Reference Bugs (4)Movable pointers normally usedto alert the pilot to specified air-speeds.

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McDonnell Douglas Corporation Proprietary Information - Use or disclosure of THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.10-30-01

Pilot

Highlight


OFF FlagAppears when TAS data are un-usuable In conjunction with flag,failure warning codes are dis-played in the TAS readout. 111indicates instrument failure, 999indicates loss of CADC digitalbus data.

SAT ReadoutIndicates static air temperaturein degrees centigradeIf no computed data is receivedfor 2 seconds, last temperaturedisplayed will be maintained inthe SAT readout

TAT ButtonPush t o r e a d t o t a l a i rtemperature in the SAT readoutReading is independent of TATon EPR/TAT readout

Vertical Speed PointerIndicates vertical speed in feetper minute

TAS/SAT INDICATOR(CENTER INSTRUMENT PANEL)

(For description refer toAutomatic Flight Chapter)

ATTITUDE DIRECTOR INDICATOR (ADI)

VERTICAL SPEED INDICATORCAPTAIN'S AND COPILOT'S INSTRUMENT PANELS

TAS ReadoutIndicates true airspeed, i.e., air-speed which is computer cor-rected for posi t ion er ror ,temperature, and compressibility.If no computed data is receivedfor 2 seconds, instrument will dis-play it's lowest value, 130 knots.

OFF FlagAppears when SAT/TAT data areunusable. In conjunction withflag, failure warning codes ared i s p l a y e d in the SATreadout: +11 indicates instru-ment failure, +99 indicates lossof CADC digital bus data.

OFF FlagAppears when vertical speeddata are unusable.

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Feb 1/79


(For description, refer to Navigation System Chapter)

HORIZONTAL SITUATION INDICATOR (HSI)

CAPTAIN'S AND COPILOT'S INSTRUMENT PANELS

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Airplane SymbolIndicates position of the airplanein relation to the horizon index.

Standby Airspeed PointerPoints to the airplane's airspeed asdetermined from the uncorrectedpitot/static inputs

MILLIBARS/IN HG ReadoutsIndicates the selected barometricpressure as expressed in millibarsand inches of mercury.

Baro Set KnobRotate to change barometric pres-sure values as read in the MB/INHG readouts

STANDBY ATTITUDE INDICATOR

STANDBY IAS INDICATOR

STBY ALT

CENTER INSTRUMENT PANEL

Power Off FlagAppears when power is lost to the in-dicator or gyro failure

Caging/Pitch Trim ControlTurning the knob to C (climb) or D(dive) adjusts the airplane symbolup or down for pitch attitude ref-erence.Pulling the knob out will erect thegyro in pitch and roll.

1000 Foot DrumA digital presentation of airplanealtitude. Each reading must bemultiplied by 1000

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May 1/76

100 Foot PointerThe pointer will make a full circlefor each 1000 feet of altitudegained or lost. Indicates uncor-rected barometric pressure alti-tude.


COMPASS SwitchDG —Permits respective com

pass system to be operated as an azimuth stabilized reference withheading reference selectable by the pilot andindependent of the fluxvalve

SLAVED—Normal position in whichthe compass card isslaved to the flux valveand compass couplerAutomatic slaving occurswithin a few momentsafter electrical power isappl ied Cyc l ing theswitch once and returning to SLAVED energizesa fast sync rate

Synchronization IndicatorDeviation from center line indicatesthe compass card is not synchronized with the flux valve

Lubber LinePoints to the airplane's heading onthe adjacent rotating compasscard

Compass CardA rotating compass card which indicates the airplane's heading asread under the lubber line

COMPASS PANEL (2)

(OVERHEAD PANEL)

RADIO MAGNETIC INDICATOR (RMI)

CAPTAIN'S AND COPILOT'SINSTRUMENT PANELS

COMPASS SET HDG KnobPermits manual re synchronizationof the compass coupler outputswith the flux valve when in theSLAVED mode, or selection of compass heading when in the DG modeFirst mark on either side will provide slow heading correction, second mark provides acceleratedheading correction Knob is springloaded to neutral position

OFF FlagAppears when heading data are un-usable

Reciprocal ArrowPoints to the airplane's reciprocalheading

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COMP SelectorNORM — Compass system 1 (2)

provides magnetic headingfor Capt's (F/0's) HSI(with HSI switch in RAD)and the F/0's (Capt's) RMI.No annunciator light

BOTH — C o m p a s s system 1ON 1 provides magnetic heading

for both the Capt's andF/0's HSI's (with HSIswitch in RAD) and RMI'sCOMP annunciator lighton

BOTH — Compass system 2ON 2 provides magnetic heading

for both the Capt's andF/0's HSI's (with HSIswitch in RAD) and RMI'sCOMP annunciator lighton

Annunciator LightsLight on indicates selector not inNORM position and switching unithas switched to correct position

OVERHEAD PANEL

ATT COMP STAB SelectorNORM - INS 1 (2) (if installed) or

VG/DG 1 (2) (if INS not in-stalled) provide attitudereference signals to theCapt's (F/0's) ADI, FGS 1(2), ATS 1 (2), andweather radar 1 (2), andalso provides azimuthstabilization signals to theCapt's (F/0's) compasssystem No annunciatorlight

CAPT — A l l instruments andON 3 systems that normally

(switch in NORM) receivesignals from INS 1 (if in-stalled) or VG/DG 1 (if INSnot installed) now receivesignals from INS 3 (if in-stalled) or VG/DG 3 (if INSnot installed). ATT COMPSTAB annunciator light on.

F/0 — All instruments andON 3 systems that normally

(switch in NORM) receivesignals from INS 2 (if in-stalled) or VG/DG 2 (If INSnot installed) now receivesignals from INS 3 (if in-stalled) or VG/DG 3 (if INSnot installed) ATT COMPSTAB annunciator light on

CADC SelectorNORM - CADC 1 (2) provides data

for the Capt's (F/0's)pitot/static instrumentsand FGS 1 (2) No annun-ciator light

CAPT - CADC 3 provides data forON 3 Capt's pitot/static in-

struments and FGS 1CADC 2 provides data forF/0's pi tot /stat ic in-struments and FGS 2CADC annunciator light on

F/0 — CADC 3 provides data forON 3 F/0 p i t o t / s t a t i c in-

struments and FGS 2CADC 1 provides data forCapt s pitot/static in-struments and FGS 1CADC annunciator light on

NOTEIf a CADC fails verify that the ATCTransponder in use is matched withthe operating CADC

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Aug 1/86Printed in U S A


BRT ControlRotating the brightness controlclockwise increases the brightnessof the IDENT and VALUE annunciators

EVENT ButtonPushing the EVENT button transmits a discrete entry to the flightrecorder

TEST ButtonPushing the TEST button, momentarily causes the flight recorder toturn on thereby causing the FLTRECORDER OFF light to go off andall six IDENT and VALUE annunciators to display the number 8

ENTER ButtonPushing the ENTER button causesthe displayed data to be transmitted to the digital flight data recorder via the flight data acquisition unit When both the IDENT andVALUE annunciators go off the recorder is ready to receive the nextsegment of information Up to fourseconds may be required for theIDENT and VALUE annunciators toclear

FLT RECORDER OFF LightComes on to indicate the flightrecorder is not recording information properly

FLIGHT DATA ENTRY PANEL (FDEP)

(F/E UPPER PANEL NO 2)

(PEDESTAL)

IDENT and VALUE AnnunciatorThe first two blank IDENT annunciators on the left are reserved forfuture monitoring of AIDS informationThe third IDENT annunciator on theleft displays the identification codenumber of the parameter being entered in the flight recorder Thenumber pushed first will appear inthis IDENT annunciatorThe right group of five VALUE annunciators display the value of theparameter being entered in theflight recorder As the numericalvalues are being inserted, thenumbers will transfer from right toleft in the VALUE annunciator

Pushbutton KeyboardThe pushbutton keyboard consistsof ten illuminated pushbuttonswhich are used to insert the IDENTcode number of the parameter(trip, date, leg) and the numericalVALUE of the parameter

CLEAR ButtonPushing the CLEAR button willerase the IDENT and VALUE annunciators This results in no datatransmission to the flight recorderand allows new data to be selectedand displayed

FLT RCDR SwitchOVRD -Applies power to the flight

recorder systemNORM - Appl ies power to the

flight recorder systemwhen parking brakes arereleased with any engineoperating or the groundsensing relay is in flightmode

PILOT IN CMD Switch (Provisionsonly)Provides for future monitoring andrecording of switch position by theAIDS

Effective for airplanes with BFDAS FLIGHT DATAENTRY PANEL (FDEP) installed.

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DC-1O

FLIGHT CREW OPERATING MANUAL


Pushbutton Keyboard

The pushbutton keyboard consists of ten illuminatedpushbuttons which are used to enter the parameteridentifier code and/or the value of the parameter to betransmitted to the Data Management Unit.

DISPLAY Button

After entering the parameter identifier code into theFlight Data Entry Panel (FDEP), pushing the DISPLAYbutton will transmit the code to the Data ManagementUnit (DMU). The DMU will convert the code into alpha-numeric values, establish its value, and transmit bothback to the FDEP for IDENT and VALUE display. TheVALUE display will be updated by the DMU at onesecond intervals.

INSERT Button

After entering the parameter identifier code into theFlight Data Entry Panel (FDEP), pushing the INSERTbutton will transmit the parameter identifier code tothe Data Management Unit (DMU) The DMU will con-vert the code into alpha-numeric values and transmitit back to the FDEP for IDENT display. After verifyingthe IDENT display is correct, enter the value (theVALUE will be displayed as it is entered) and push theINSERT button The VALUE will be transmitted to theDMU and both the IDENT and VALUE will be trans-mitted by the DMU to the Digital AIDS Recorder (whenthe data is recorded the VALUE display will erase)

MODE Select Knob

STBY -The Digital AIDS recorder (DAR) receives nodata from the Data Management Unit (DMU)

AUTO - The DAR receives all data determined by andtransmitted by the DMU

FAST —Turns on the DAR when on the ground, withoutengines running, and receives and records con-tinuously transmitted data.

VALUE Readout

Displays the value of the parameter identifier

IDENT Readout

Displays the parameter identifier value or the identifi-cation of a fault condition.

Pushing the CLEAR button will clear the IDENT andVALUE readouts and clear the Flight Data Entry Panelfor new data The CLEAR button must: be pushed priorto entering any new parameter identifier.

LIMIT Switch/Light

Comes on when a monitored parameter is out of limits.Pushing the switch/light turns the light off (light willremain on if there are additional LIMIT exceedance),and transmits a request signal to the Data Manage-ment Unit (DMU) to display the out of limits parameteridentifier and its value on the IDENT and VALUE read-outs. The VALUE will be updated at one second inter-vals until the CLEAR button is pushed. If the lightremained on, repeat the procedure for other out oflimit parameter(s).

NOTEWhenever a LIMIT exceedance occurs the DMUtransmit the data to the airborne printer.

will

FAULT Switch/Light

Comes on when one of the Airborne Integrated DataSystem units is indicating a fault. Pushing the switch/light will turn the light off (light will remain on if thereare additional FAULT indications) and transmits a re-quest signal to the Data Management Unit (DMU) todisplay the source of the FAULT condition. The displayis removed by pushing the CLEAR button. If the lightremained on, repeat the procedure for other FAULTindications.

EVENT Button

Pushing the EVENT button transmits a discrete entryto the Digital AIDS Recorder and the Digital Flight DataRecorder.

PRINT Button

After entering the parameter identifier code into theFlight Data Entry Panel (FDEP), pushing the PRINTbutton will transmit the code to the Data ManagementUnit (DMU). The DMU will convert the code into alpha-numeric values, establish its value, and transmit bothto the Airborne Printer, the parameter identifier valuewill also be transmitted to the FDEP IDENT readout.

BRT Control

Rotating the BRT control controls brightness of theIDENT and VALUE readouts.

Effective for airplanes with AIDS FLIGHT

DATA ENTRY PANEL (FDEP) installed.

FLIGHT DATA ENTRY PANEL (FDEP)

FLIGHT ENGINEER'S UPPER PANEL NO. 3 CA1-1130 A

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Nov 1/79 10-30-09/10Printed in U S A

PITOT/STATIC SYSTEM

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10-40-01/02

DC-1OFLIGHT CREW OPERATING MANUAL

CENTRAL AIR DATA COMPUTER/PITOT STATIC INTERFACE

CAPTAIN CENTER PANEL

PITOT

VERTICAL SPD BARO SET

CENTRALAIR DATA

COMPUTER 1

STATIC

CENTRALAIR DATA

COMPUTER 3(AUX)

STATIC

CENTRALAIR DATA

COMPUTER 2

STATIC CAl-41111

JLFeb 1/79 10-43-03/04

Pr i n ted in U.S.A.

mcdonnell douglas dc 10 40 flight instruments

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