Overhead

Cargo Fire Panel

1. FWD or AFT HEAT/SMOKE light

Illuminates when heat or smoke is detected in lower FWD or AFT (respective) cargo compartment

HEAT OR SMOKE (illuminated)

Illuminates (steady red) to indicate where heat or smoke has been detected
Automatically shuts off the respective lower cargo vent fans

2. FWD or AFT FLOW Light & Switch

DISAG (illuminated)

Disagreement between switch and operation of the fans
indicates vent fans in respective compartment have automatically stopped to prevent the fire agent from escaping

Pressing the Switch

Extinguishes the DISAG light
Illuminates the OFF light

OFF

Flow (via vent fans) has been command off by pressing the switch
Prevents vent fans from automatically starting when heat or smoke is no longer detected

3. AGENT DISCH FWD 1 / AFT 1 / LOW Switch

FWD 1 or AFT 1 (Illuminated)

Light flashes, indicating where fire/smoke has been detected

Pressing the switch

Discharges fire bottle #1 into the respective compartment
Light extinguishes when smoke/heat is no longer detected

LOW (illuminated)

Illuminates steady after agent is discharged (appx 28 seconds)

4. AGENT DISCH FWD 2 / AFT 2 / LOW Switch

FWD 2 or AFT 2 (illuminated)

Light flashes appx 90 minutes after discharge of FWD 1 or AFT 1 fire bottle (if bottle 2 has not already been manually discharged)

Pressing the switch

Discharges fire bottle #2 into the respective compartment
Light extinguishes and LOW light illuminates

LOW (illuminated)

Illuminates steady after agent is discharged (appx 15 seconds)

The Cargo Fire Test will automatically start when the first IRS selector is moved from OFF to NAV. This test is rearmed to start automatically after each landing, or when electrical power is removed from the aircraft. If an IRS selector is subsequently cycled OFF, then back to NAV (without the accomplishment of a landing or without removing power from the aircraft), the automatic Cargo Fire Test will not start. If, for any reason, the automatic Cargo Fire Test does not after the IRS selector from OFF to NAV, the Cargo Fire Test can be initiated manually by pressing the MANUAL TEST switch.

Initiating the cargo fire test:

Illuminates the TEST button light
Illuminates the HEAT / SMOKE lights
Illuminates all 4 LOW lights
Illuminates both DISAG lights
Illuminates the Master Warning light
Illuminates the Cabin Air System "Smoke" warning light on the Air Panel
Generates the Alert sound
Displays CARGO FIRE TEST on EAD
Displays CARGO SMOKE TEST on SD

During the Cargo Fire Test, the Air Synoptic Display will show the status of smoke and heat detectors. Smoke detectors are normally displayed as solid amber triangles in their respective compartment locations. Heat detectors are normally displayed as solid amber circles in their respective compartment locations.

IRS Panel

1. IRS OFF / NAV Select Switch

Moving the IRS selectors from OFF to NAV begins a 10 minute alignment period. During this alignment period, the IRS determines the approximate current latitude based on calculations using the motion measured from the rotation of the Earth. The calculated latitude is then compared to the present position latitude from the FMS INIT page when the "INITIALIZE IRS" prompt is selected. A significant mismatch between the calculated latitude and the latitude entered from the INIT page will result in a failed alignment. Longitude cannot be calculated during initialization in the same manner. However, the longitude from the last shutdown is stored and used as a reasonableness check during the next alignment. Pressing the "INITIALIZE IRS" prompt when a significant (assumed) longitude position error exists will also result in a failed alignment. Any failed alignment will be indicated by flashing NAV OFF lights, level I "IRU I NO ALIGN, IRU 2 NO ALIGN and IRU AUX NO ALIGN" alerts, and a Master Caution alert. Be very careful when verifying the INIT page LAT/LONG. The FMS/IRS can, in certain cases, be forced to accept an incorrect position Although the FMS receives position updates from several sources, the IRS does not receive any enroute updates. If you enter an incorrect present position during initialization, the IRS will operate with this error for the entire flight. Since the FMS receives updates, this won't be a serious problem until you lose both FMSs in Class 11 airspace, and you are left with only IRS navigation. If this occurs, you will have an immediate position error approximately equal to the position error entered during alignment. For this reason, it is very important to ensure that the INIT page present position coordinates are correct prior to selecting the "INITIALIZE IRS" prompt. A rapid alignment (appx 3 mins) may be accomplished by moving the IRS switches from NAV to OFF, then back to NAV within 5 seconds. Realignment will then be initialized with the existing attitude and heading. Velocities will be zeroed.

Movement of the first IRS switch from OFF to NAV (after a landing has occured) will initiate the Cargo Fire Test

2. NAV OFF (light)

Extinguished

Alignment is complete, operating in NAV mode

Steady On

IRS system is either off, in align mode, or has failed

Flashing

Position not entered within ten minutes, present latitude does not agree with calculated position in the IRU, or the IRU has sensed motion during the alignment phase.

CVR/GEN BUS

1. GEN BUS FAULT RESET

Maintenance use only

Not to be used by Flight Crew

2. BUS FAULT (illuminated)

Switch is used to reset the associated Generator Control Unit

3. CVR TEST (pressed)

Minimum of level 8 during test

4. ERASE (Pressed)

Can only be accomplished on ground with parking brake set

Misc

1. ANNUN BRT/DIM

Used to control annunciator light intensity

2. ANNUN TEST

Used to test all annunciator lights in the cockpit. Pressing button will illuminate all lights. Holding button (approximately 5s) will initiate the CAWS test.

FADEC

The FADEC controls:

Engine acceleration to idle speed during start
Acceleration and deceleration limiting
Automatic control of available thrust
Minimum / Approach Idle speeds during descent
Compressor airflow control
Thrust control as a function of throttle position and thrust reverser lever
Protection from exceeding N1, N2, internal pressures, and max thrust lmts

The FADEC system utilizes dual channel ECU (GE) or EEC (P&W) units, each having two CADC inputs. Cross-talk between channels allows for normal operation with the failure of one ECU or EEC channel. Each ECU or EEC is selfpowered by an N2 driven PMA (Permanent Magnet Alternator). The PMA has dual windings, each powering an individual ECU or EEC channel. 28vDC power is also available on all GE, and some P&W powered MD-11s, from its respective DC bus in the event of a failure of both PMA windings. The failure of both EEC/ECU channels, or the failure of both windings of the PMA (if not equipped with 28v backup power), will cause an automatically controlled engine shutdown to occur.

1. ALTN

FADEC uses two CADC inputs to each EEC or ECU channel. The loss of one CADC input to an ECU or EEC channel has no affect on normal operation. When both CADC inputs to an EEC or ECU channel have been lost, FADEC automatically switches to the other EEC or ECU channel. If both CADC channels have been lost to both EEC or ECU channels, SELECT and ALTN will illuminate. When this condition exists, the FADEC uses the last CADC input it sensed to calculate thrust. When ALTN is pressed, SELECT will extinguish and ALTN will remain illuminated. Alternate mode of the FADEC utilizes an internal, fixed schedule to determine thrust level for the selected throttle position. This internal schedule may cause thrust to increase, but will never cause thrust to decrease. With P&W engines, autothrottles are not available when operating in the ALTN mode. Pushing throttles through overboost bar will also cause FADEC to revert to ALTN mode.

2. Ignition Pwr Sources

Ign A is powered by L emergency bus, and is required for dispatch. Ign B is powered by R emergency bus. (“A” Odd flt # / “B” even flt #)

3. ENG IGN OFF (Illum).

-No ignition source is selected and no power is being supplied to the ignitors.

4. ENGINE IGNITION SWITCH (A & B)

A (or B) - Switch selects ignition in the Auto mode. A (or B) Illuminates when ignition A (or B) is selected. Selecting Ign A or B will:

Extinguish the ENG IGN OFF light
Supply 28v DC power to each engine start switch
Arm ingitor A or B
Command APU to 100%
Prepares EAD for display of start indications
Configures fuel system for engine start
Arms the engine driven hydraulic pump test
Packs shut off (packs turn back on if engine not started within 2 mins after selecting). Packs turn back on after engine is started.

MANUAL (illuminated) Auto ignition control has failed, and the engine ignition that is selected (either A or B) is commanded on continuously until the pilot chooses to assume on / off control manually.

Continuous Ignition (Auto mode) Automatically on for start, takeoff (On when > 70o throttle resolver angle; Off when slats retracted), landing (On when slats, flaps or gear extended; Off 1 minute after ground shift) and 60 seconds after engine A/I is turned on.

5. OVRD Switch

Pressing switch powers both ignitors on all engines and bypasses auto ignition control.

OVRD ON

Illuminated when on

Engine Fire

1. ENGINE FIRE HANDLES

Illuminates for an overheat or fire in the respective engine nacelle
Remains illuminated until the fire / overheat no longer exists

Simultaneously to fire handle illumination, the following occurs:

Fuel switch illuminates red for the respective engine
Master warning light illuminates
EAD annunciation
Fire bell sounds

Pulling the fire handle accomplishes the following:

Silences alarm (if not silenced by pressing the master wrng switch)
Disconnects the generator field
Closes the Hyd Fire Shutoff Valve
Closes the Fuel Fire Shutoff Valve
Shuts down the associated Air System (if Air Sys in Auto mode)

Rotating the Fire Handle (after pulling)

Discharges the respective agent bottle into the engine nacelle

2. AGT LOW (1 or 2) light

Illuminates when respective bottle is discharged (battery bus powered)

3. FUEL SWITCHES

Illuminates red when respective fire handle illuminates
Remains illuminated if the fire warning still exists
With the Fire Handle pulled and the fire warning terminated, this light stays illuminated until it is moved to OFF

Hydraulic

Min Hyd quantity for dispatch Sys 3 = 6 gals, sys 1 & 2 = 4.75 (5.25 desired) - Loss of fluid in system 3 down to 4.75 gals will close a oneway check valve, preventing total fluid loss from leak in the tail section. HYD QTY LOW alert

when qty reaches 4.74 on the ground, or 2.5 in flight

HYD SYS FAIL

alert when hyd qty reaches 1 gallon

Non-Reversible Motor Pumps 2-1 NRMP provides hyd power for the upper rudder and stab trim with a loss of Sys 1 hydraulics. 3-2 NRMP provides hyd power for the lower rudder with a loss of Sys 2 hydraulics. No fluid is exchanged through the NRMP’s. Fluid is provided from alternate reservoir systems referred to as compensators.

Autopilot use with hydraulic system loss: Lose 1 - Use A/P 1 Lose 2 - Use A/P 2 Lose 3 - Use A/P 2 *

Autopilot 1 uses hyd sys 2 & 3
Autopilot 2 uses hyd sys 1

If using A/P 1 with a loss of Sys 3, A/P will not be able to control stab trim.

Enhancement “Sioux City” Valve Valve located near pressure bulkhead in HYD System 3 protects hyd fluid forward of the valve. Closes at 4.75 gals Enough Sys 3 fluid will be retained to allow pitch & roll control through use of horizontal stab trim and lateral controls powered by Hyd system 3. Controls Avail.:

Ailerons
Spoilers
Stab Trim

1.1-3 & 2-3 RMP (Reversible Motor Pump) switch

Switch Controls the RMP shutoff valves when hydraulic system is in Manual mode RMP(s) On (ON illuminated) RMP(s) OFF (ON Extinguished) If in Manual Mode -Hyd reservoir quantity < 1 gal on either side of RMP -Switch pressed and Respective RMP has been commanded on -ADG deployed with ADG electric switch off If in Auto Mode -Cruise flight with two hyd systems pressurized -Any N2 falls below 45% during taxi, takeoff or landing -Engine start in flight -Eng driven pumps unable to maintain pressure during taxi, T/O or landing -Auto slat extend DISAG -Loss of second engine or second hyd system during cruise phase of flight -Disagreement between valves and commanded position -When selecting Manual during Auto operation -RMP commanded OFF & pressure still exists in system

2. SYS (1,2,3) PRESS

Illuminates if hyd pressure is too high or too low (<2400 or >3500). Extinguishes when press is normal

3. L PUMP / R PUMP Switches (Systems 1,2,3)

The L PUMP switch commands the respective engine hyd pump On/Off when operating in Manual mode. The R PUMP switch commands the respective engine hyd pump Armed/Off when operating in manual mode. Both switches for the respective engine are disabled in Auto mode. With the engine running and hydraulic systems operating normally, the respective engine driven L PUMP is ON, and the R PUMP is armed (ready to operate in the event of a L PUMP malfunction). Right pumps are tested at engine start. FAULT (illuminated) When low pressure (<2400) or high temperature (>245o in pump case drain) is detected. In auto mode, a failure of the primary (left) pump will cause the secondary (right) pump to start.

OFF

Extinguished when pump is operating normally, and respective system is pressurized. Pumps are off (and OFF is illuminated) when pump or system pressure is too low or too high, when pump or system temperature is too high, when fluid qty is low (<2.5 gals), during engine start and when fire handle is pulled. When electrical power is lost, engine pumps fail to ON.
OFF also illuminates when pump is manually commanded off (which only possible when operating in manual mode).

4. AUX PUMP (1 & 2)

Switches command AUX PUMP(S) on or off when operating in Auto or Manual mode.

Illuminates when respective aux pump is on for the purpose of pressurizing hydraulic system 3. The Aux pumps can be commanded on automatically by the HSC, or commanded on manually by the pilot. The #1 aux pump is also commanded on prior to engine start when the AUX HYD PUMP 1 switch on the Brake Control Panel is pressed - then automatically shuts down when the first fuel switch is turned on.

5. HYD PRESS TEST

Initiates hyd pressure test. Switch operates only in Auto mode. TEST (Illum.)

Indicates hyd test is in progress. Tests RMP's and Aux pumps If Aux Pump pressed while test is in progress, the test stops.

6. SYSTEM SELECT / MANUAL switch

Two channels - pressing once selects manual. Pressing a second time selects second auto channel. SELECT (illuminated)

System has automatically switched to manual. Pressing switch locks system in manual mode (SELECT no longer illuminated). MANUAL (illuminated)
System operating in manual mode
MANUAL flashes if switch has been pressed that has no effect in auto mode.

Electrical

Electrical Priority for the AC gen bus is:

Associated IDG
APU Gen
AC Tie Bus (Ext or IDG)

Electrical Priority for the AC Tie bus is:

Ext Pwr
Any IDG

1. BUS OFF lights (13 total)

OFF

Illuminates if associated bus is not powered

2. BAT Switch

Connects/Disconnects Batt from Bat bus and charger
Switch operates in Auto or Manual

ON (Off light extinguished)

Batt powers Batt Bus (if AC pwr is not available)
Batt charger allowed to charge, except when:
-EMER pwr is in use
-Inverter powered refueling is being used
-AC power is not present at charger input

OFF (Off light illuminated)

Batt disconnects from Bat Bus
Charger is inhibited
Auto transfer of EMER pwr is inhibited

3. AC TIE Switch (1, 2, 3)

In Manual mode, Switch controls the Bus Tie Relay. ARM illuminates in Auto mode.

ARM

Illuminates when bus tie relay is open and switch is in ARM position

OFF

Bus tie relay is open and switch s in the OFF position. Busses are solated from Tie Bus.

OFF & ARM Extinguished

Bus Tie elay is closed

4. DC Tie Switch (1 & 3)

Switch controls RCCBs in Man mode Switch inop in Auto mode OFF

DC Tie Bus is

open due to:

Switch pushed (Man) or
RCCB protective trip

5. EXT PWR Switch

AVAIL

Illuminates when EXT pwr is available.

When AVAIL is illuminated, pressing switch provides external pwr to the AC Tie Bus.
When AC Tie Bus is powered, ON illuminates.
Pressing switch again disconnects external pwr.

6. ADG ELEC Switch

Extinguished (default mode after ADG is deployed)

ADG will power L EMER AC bus and AUX hyd pump 1.

ADG pwrs L & R EMER AC & DC busses, batt chrgr and batt bus. (Aux hyd pump no longer pwrd)

7. System Select Switch

Allows selection between Auto and Man

SELECT

will illuminate if system reverts to Man.
Pressing the switch extinguishes SELECT, and locks the system in Manual.
MANUAL - System operating in Man mode

8. SMOKE ELEC/AIR Switch

Isolates Elec & Air (for smoke) in Auto or Manual modes

NORM

Elec/Air ops normal

3/1 OFF

Gen 3 sys & Pack 1Air sys OFF
ECON mode OFF
EIS CRTs to full bright

2/3 OFF

Gen 2 sys & Pack 3 Air sys OFF

1/2 OFF

Gen 1 sys & Pack 2 air sys OFF
EMER pwr transfer inhibited

9. CAB BUS

OFF (Illuminated)

Pwr is removed from Cargo Loading bus and Cabin AC Grnd Service Bus

10. APU PWR Switch

Switch starts APU (if not already started from APU panel) and powers GEN busses. AVAIL

Flashes until APU reaches 95% & power is OK. Steady when OK for power transfer.

Illuminates when APU is powering a bus (any bus).

11. GEN Switch (1,2,3)

Switch resets generator in manual mode. Auto mode will perform this function automatically, if req'd.

OFF

Illuminates when GCR is tripped open (no pwr being supplied).

ARM

Illuminated when GCR is closed and generator relay is open. System is ready for pwr transfer.

12. DRIVE Switch (1,2,3)

Switch disconnects IDG in Auto or Man modes Fault: illuminates when:

IDG oil temp high
IDG oil press low
IDG oil temp diff. out of limits

IDG disconnect req'd

DISC

Press to disconnect IDG.
Successful disconnect is indicated by illuminated DISC

13. EMER PWR OFF/ARM/ON Selector

Controls Batt transfer to L EMER AC/DC bus Selector operates in Auto or Manual mode

OFF (also illuminates OFF light)

Batt / Inverter inhibited from supplying pwr to L EMER AC & DC Busses

ARM: If normal pwr is lost, batt will automatically supply pwr to:

L EMER DC bus
L EMER AC bus (through static inverter)
ON light illuminates if auto transferred to EMER pwr.

For auto transfer to occur:

Batt switch must be ON
SMOKE/ELEC/AIR selector not in 1/2 OFF

ON (also illuminates ON light)

L EMER AC & DC being powered by Batt / Inverter

Air

1. COCKPIT / COURIER / CARGO Temp

65^o^ to 85^o^ range - Center position is 75^o^

OFF

Respective trim air valve is closed (cold)
Zone TEMP OFF alert appears

COLD (full)

All 3 packs driven to full cold

HOT

Trim air is added

2. PACK Switch (1,2,3)

Controls respective pack flow valve in manual mode - Switch inhibited in Auto

FLOW

Amber if packs are on, but flow is insufficient, or flow is present with packs commanded off.

OFF

Illuminated when pack is commanded off manually (Ram Air Door is commanded closed)

3. TRIM AIR Switch

Opens/closes Trim Air Press Regulator Valves in manual mode

OFF (pushed in Manual Mode)

Trim Air PRVs manually turned off
Prevents hot air from entering Trim Air Manifold

AVNCS OVHT

Amber when overheat is sensed in avionics compartment.
Assumes trim air duct rupture
Auto closes trim air PRVs Must be reset by maintenance

Pushing a 2nd time (while illum.) reopens the AC shutoff valve.

4. Air SYSTEM Select Switch

Allows selection between (2) Auto channels and (1) Manual channel. When functioning properly, the Air System defaults to an Auto Channel. Pressing the switch then selects the Manual mode. Pressing the switch again selects the other Auto channel.

SELECT

Illuminates if system detects a malfunction, and reverts from Auto to Manual mode.

MANUAL

Illuminates if Manual mode has been selected by pressing the switch.
Flashes if system is in auto and any switch on Air Panel is pressed that has no effect in auto mode.

5. BLEED AIR (1,2,3) PRESS / OFF Switch

Controls the Eng bleed valve in the manual mode Operates in parallel with, & identical to the MAN TEMP HI switch PRESS (illuminated)

Air press low (< 11psi)

OFF (Pressed in Man)

Bleed valve is manually commanded off

6. ECON Switch

Works in Auto or Manual mode Starts/Stops Econ op's of packs ESC automatically turns ECON mode on/off as req'd for flt conditions. Unless otherwise needed, Air system normally operates in ECON mode with packs operating on low volume.

OFF

ECON manually selected off
Will not illuminate if ESC automatically selects ECON off.

CAB ALT

Illuminates when cabin altitude is greater than 9500 ft.

7. BLEED AIR (1,2,3) MANF / TEMP HI Switch

Controls the Eng Bleed valve in Manual mode Operates in parallel with, and identical to the BLEED AIR PRESS Switch

MANF (Auto or Manual)

Illuminates when excessive temperature is detected in any compartment in which a pneumatic manifold is routed. Indicates a failed or leaking manifold.

TEMP HI (Auto or Manual)

Illuminates when excessive bleed air temperature is detected downstream of the precooler

In Auto, the respective Eng Bleed valve closes to remove bleed air from a damaged system.

8. 1-2 ISOL / 1-3 ISOL Switches

Open/close respective ISOL valve when sys is in Manual. Inhibited in Auto mode

ON (Switch pressed in Manual)

ISOL valve is commanded open

DISAG

Illuminated when ISOL valve is not in commanded position.
Light inhibited for 10 secs in Auto mode. In Manual, illuminates when valves are in transit.

9. APU Switch

Opens & closes APU bleed air load valve

APU valve is selected open (if Air in Auto. ISOL valves 1-2 & 1-3 are auto controlled).

USE ENG AIR

APU air is ON and diff press is > 1.3 PSI (acft is beginning to pressurize)

10. AVNCS FAN Switch

Starts/Stops override of the avionics exhaust fan and venturi shutoff valve in the manual mode.

FLOW Illuminates if:

Cooling airflow through the avionics is below normal
Cabin inflow is insufficient for pressurization
Cabin altitude greater than 10,000' Auto closes venturi & fan turns on

OVRD (pressed in Manual mode)

Starts avionics exhaust fan
Closes avionics cooling outflow venturi

11. NO MASKS

Illuminates if cabin approaches 15,000 ft, and masks in crew rest module have not (auto) deployed. Pressed & held for 3 seconds deploys the masks

Fuel

Fuel Capacity Tank 2 = 64,000 lbs Tank 1 / 3 = 40,500 lbs U/L Aux = 98,100 lbs Tail = 13,100 lbs Total = 256,800 lbs

1. Tank 1,2,3 FILL Switches

Switch opens the respective Fill valve in Manual mode

1st Press:

In Manual mode, Arms the Fill valve for as long as it is held
Remains armed after release under these conditions
-Tank 2 Fill valve remains armed if any Upper Aux tank pump is on
-Tanks 1/3 valves remain armed if tank 2 > 40,000 lbs

2nd Press

Disarms the Fill valve

ARM (illuminated)

Fill valve armed to accept transferred fuel

FILL (illuminated)

Fill valve open and accepting transferred fuel

APU

APU In-Flight Parameters: Start Up to 25,000 ft. Run Up to 30,000 ft (electrical only)

APU Auto Shutdown: -Overspeed or loss of N1or N2 signal -High EGT or loss of EGT signal -Low oil pressure or high oil temp -No light-off during start, or slow start -Reverse flow in bleed air system -Inlet door not open, or power failure -Fire warning -Loss of DC power

1. AGENT DISCH Fire Handle

Illuminates when an APU fire is detected, and automatically commands:

Master Warning lights on
EAD alert
APU FIRE illuminates (red) on APU Fire Handle
Fire Horn sounds near external APU Panel (nose gear area)
APU shuts down
Aural Warning sounds
If equipped with 3rd, dedicated fire bottle, it will automatically discharge

Pulling the APU Fire Handle:

Emergency APU shutdown
Fire extinguishing agent is armed to discharge
APU Generator disconnects / de-energized
APU Fuel Valve closes
#2 Engine bleed valve closes

Rotating the handle (after pulling):

(Clockwise) Discharges fire bottle #1 (shared with engine 2)
(Counterclockwise) Discharges fire bottle #2 (shared with engine 2)

2. APU START/STOP Switch

Starts and stops the APU manually If this switch is used to start the APU, it must also be used to shut it down

ON (Switch pressed and ON illuminated)

Flashes when APU is starting. Steady when started and ready for use
If APU shuts down due to fire, light flashes until the switch is selected to OFF

OFF (When pressed)

Illuminates steady when APU shutdown is initiated
APU bleed valve automatically closes
APU shuts down 90 seconds after no longer supplying air
Remains illuminated until shutdown is complete

3. APU FUEL/FAIL/DOOR Status lights

FUEL (illuminated)

Fuel pressure is too low

DOOR (illuminated)

APU inlet door not fully open during start
APU inlet door not fully closed after shutdown (The door begins to close appx 60 seconds after shutdown. Shutdown occurs appx 90 seconds after APU is no longer supplying air. The door takes appx 12 seconds to close)

FAIL

APU has failed, and start is not possible

4. APU FIRE AGENT (1,2) (Low Light)

Associated with APU fire
bottles 1 & 2 that are shared with engine 2. These lights are not installed on all MD-11s

LOW (illuminated)

Associated fire bottle has been manually discharged

5. ENG/APU FIRE TEST Button

When pressed:

ENG and APU Fire Handles illuminate
Fuel Switches illuminate
Both Master Warning lights flash
Fire Bell and aural warning tone sounds
ENG 1,2,3 and APU FIRE alerts display
ENG FIRE voice warning sounds
(6) Eng FIRE AGT LOW lights and (2) APU FIRE AGENT LOW (if installed) illuminate

When on battery power only, the Master Warning lights, Fire Bell and FIRE alerts will not activate

6. APU GEN Switch

Pressed

Resets APU Gen if Elec in manual mode

OFF (illuminated)

Gen on speed, but malfunction has occurred

7. APU FIRE AGENT 3 DISC/LOW Switch

This switch is only installed on aircraft that have the third, dedicated APU fire bottle installed.

LOW (illuminated)

Respective fire bottle has been automatically or manually discharged

DISC (illuminated)

APU Fire Handle has been pulled

DISC Switch Pressed

Manually discharges fire bottle 3 (if auto discharge fails - APU fire handle must be pulled before switch is pressed)

LSAS

LSAS provides:

Pitch Attitude Hold and Automatic Pitch Trim - With no force on the control column, and bank angle less than 30 degrees, LSAS holds the current pitch attitude. LSAS holds this attitude by deflecting the elevators as much as 5 degrees. The horizontal stabilizer is automatically adjusted to relieve the sustained elevator deflection and maintain a full 5 degree elevator authority.
Pitch Attitude Limiting - LSAS maintains pitch attitude to less than 10 degrees of dive, or less than 30 degrees of climb.
Pitch Rate Damping - Increases the apparent static stability to reduce the chance of over-control in pitch. It is active throughout the flight envelope. 100% of max damping is available above 20,000ft, decreasing linearly to 30% below 16,500 ft.
Speed Protection - If the autopilot is not engaged and the autothrottle is not available (or able to maintain a safe speed), LSAS Speed Limiting will engage to provide overspeed or stall protection. LSAS overspeed protection is accomplished by changing pitch. LSAS does not provide flap, slat or gear overspeed protection.
Stall Protection - At 75-85 pct of the angle of attack required to activate the stick shaker, the LSAS stall protection engages. LSAS reduces pitch until the AOA is sufficiently reduced.
Pitch Attitude Protection and Positive Nose Lowering - During takeoff rotation, LSAS provides Pitch Attitude Protection (PAP) to reduce the possibility of a tail strike. During landing, after spoiler deployment is commanded, LSAS initiates Positive Nose Lowering (PNL) to assist in transitioning the nose wheel to the runway after main gear touchdown. LSAS is off when:
The autopilot is engaged
Below 100 ft RA, except active for pitch attitude protection during takeoff and positive nose lowering during landing.
Bank angle exceeds 30 degrees
During manual trim operation
Pilot can override LSAS if, when below 1500 ft., more than appx 2 lbs. of pressure is applied to the control column; or, when 10-15 lbs of force is applied while PAP or PNL is active. The pilot may counteract the LSAS overspeed or stall protection by using enough manual force on the control column (appx 50 lbs) to defeat the LSAS inputs.

1. FLAP LIMIT AUTO / OVRD

The Flap Limiting System automatically retracts flaps if the airspeed exceeds speed limits for flap settings between 22 and 50 degrees. This automatic flap limiting is only active at speeds greater than 175 kts. The system provides automatic retraction and prevents further extension. If flap position airspeeds are exceeded (causing auto retraction), flaps will return to the selected position when speed is reduced.

MANUAL (illuminated) The Auto Flap Limiting System has two channels. Failure of the first channel will cause the Flap Limiting System to automatically switch to the remaining channel. In the event of a failure of both channels, MANUAL will illuminate and a SEL FLAP LIM OVRD level 2 alert will display. In this case, manual override is required through the use of the AUTO / OVRD selector. MANUAL will also illuminate if the AUTO / OVRD selector is moved out of the AUTO position (regardless of whether or not the Auto Flap Limiting System has failed).

AUTO/OVRD Selector:

Normally selected to AUTO. Selecting OVRD (1 or 2)
overrides normal flap limit system.

2. YAW DAMPER SYSTEM

Provides turn coordination and dutch roll damping. The Yaw damper operates continuously when power is applied to the acft, except during autoland localizer track and flare, and during engine out flight. There are 2 Yaw Damper channels (A & B) for each of the two FCC's (1 & 2). FCC 1 operates the lower rudder, and FCC 2 operates the upper rudder. If dual Y/D channels (A and B) fail on the same rudder surface, dual control is automatically maintained by the other FCC.

FAIL (illuminated)

The associated channel has failed

OFF (illuminated)

The associated channel has been selected off by manually by pressing the respective Yaw Damper switch.

3. ELEV FEEL System

The Elevator Feel System provides a simulated feel of elevator aerodynamic loads (as a function of airspeed). The system has two Auto channels, and a (pilot selectable) manual override system. ELF functions are performed by the Flight Control Computer.

ELEV FEEL (Selector) AUTO

With the selector in AUTO, the dual channel system automatically adjusts elevator feel to correspond with the current airspeed.
HI (1or 2) or LO (1 or 2) - Slews the elevator load feel to correspond to a higher or lower airspeed as indicated on the speed scale. The speed scale will appear on the SD Config page, when the selector is pulled.

MANUAL (illuminated)

The Elevator Feel System has two channels. Failure of the first channel will cause the system to automatically switch to the remaining channel.
In the event of a failure of both channels, MANUAL will illuminate and a SEL ELEV FEEL OVRD level 2 alert will display. In this case, manual override is required through the use of the AUTO/Manual selector. MANUAL will also illuminate if the AUTO/Manual selector is moved out of the AUTO position (regardless of whether or not the Elevator Feel System has failed).

5. LSAS Switches

FAIL (illuminated)

Control channel has failed, and has shut off

OFF (illuminated)

Respective LSAS switch has been pressed, and the corresponding control channel has been turned off

Presurization

When slats are extended for T/O, cabin is pressurized to 100 ft below departure airport field elevation. Cabin will return to departure airport field elevation if aircraft descends before reaching 5,000 ft.

1. Outflow valve indicator

Displays outflow valve position (in Auto or Manual mode)

2. MANUAL LDG ALT

Used to enter landing field elevation if not available from FMS database.
Inhibited with CABIN PRESS switch in MANUAL mode.
Knob must be turned 120^o^ to operate.
Value is shown on Air Synoptic (boxed).

3. DITCHING Switch

Controls the rate of depressurization, and seals any ports associated with the Air System that would allow entry of water after ditching

ON (Pressed and illuminated)

Maintains existing cabin altitude during descent
At 2500 ft or <.5 PSID (whichever 1st)
-Packs and bleeds shut off
-GPWS is inhibited
-Avionics venturi closes (in auto mode)
-Outflow valve opens (in auto mode)
-Ram Air Doors close
At 1000 ft
Outflow valve closes.

4. SYSTEM - SELECT / MANUAL Switch

Allows selection between MANUAL and AUTO Two alternating auto channels (1 primary, 1 stby)

SELECT (illuminated)

Both (auto) control channels failed. System has automatically switched to manual mode.

MANUAL (pressed and illuminated)

System locked in Manual mode.
Pressing a second time selects other auto channel.

5. CLIMB - DESC

Allows manual selection of outflow valve position in manual mode

6. CLOSED (illuminated)

Indicates that the outflow valve is fully closed

Anti Ice

The Anti-Ice “System” refers to ENG, WING, TAIL and WINDSHIELD Anti-Ice. When anti-ice is required, these should all be ON. The primary method of ice detection is the Ice Detection System. If an ICE DETECTED alert is displayed, Anti-Ice must be turned on. If the aircraft is equipped with an operational Automatic Anti-Ice system, anti-ice will automatically engage when required.

Icing Conditions Definition Icing conditions exist on the ground when:

OAT 6O or less (42^O^ F), and 1 of the following:
-Visible moisture
-OAT / Dew point within 3OC (5^O^ F) (gnd or Flt)
-Snow, slush, ice or standing water on taxiways

Icing conditions exist in flight when:

TAT 6O or less(42^O^ F), and 1 of the following:
-Visible moisture
-OAT / Dew point within 3OC (5^O^ F) (gnd or Flt)
-ICE DETECTED alert displayed (non auto A/I)
-Visible ice accumulates on the aircraft

Engine Run-up - GE When anti-ice is used during ground operations in icing condit ions, perform an engine run -up of 60% N1 for 30 seconds prior to takeoff. This run -up should also be performed if anti-ice is used during ground operation for any period greater than 30 minutes, and repeated at intervals of no greater than 30 minutes.

Engine Run-up - P&W When anti-ice is used during ground operations in icing conditions, perform a momentary engine run -up of (min) 50% N1 prior to takeoff. This run-up should also be performed at intervals of no greater than 15 minutes during ground operat ions with anti-ice on.

1. ENGINE ANTI-ICE Switch (1,2,3)

Switch Opens and closes respective engine anti-ice shutoff valves. ON -Illuminates when anti ice is on. DISAG -Shutoff valve in transit, or remains illuminated if: -Disagreement between switch and valve.

2. WING and TAIL ANTI-ICE Switches

Opens and closes the wing / tail anti-ice shutoff valves Wing A/I uses Air Sys 1 & 3 - Tail uses Air Sys 2

The respective switch is on

DISAG

On the Ground: Valve is open regardless of switch position
In Flight: Valve is in transit, or disagreement between valve and switch position.

3. ANTI-ICE SYSTEM Manual Swich (Auto A/I Acft Only)

Pressing switch (MANUAL illum.) deselects the auto function, and allows pilot control of Eng, Wing and Tail Anti-Ice.

Manual

System reverts from Auto to Manual due to a malfunction, or
System is pilot-selected to Manual.

Note – Auto anti-ice is optional on MD-11s. If equipped with auto antiice, the system MUST be selected to MANUAL if the pilot wishes to override the auto function, and control anti-ice functions manually.

4. WINDSHIELD DEFOG Switch

Turns Low heat to inner windshield pane on or off

OFF (light extinguished)

Defog is commanded on

Under normal conditions, Defog should always be on in flight. Defog automatically turns on when electric power is applied to the aircraft.

5. Windshield ANTI-ICE HIGH/NORM Switch

Provides High or Normal heat to the windshield. Anti-Ice system defaults to NORM when powered.

HIGH

Only used to deice windshield when NORM is insufficient

6. L / R WINDSHIELD ANTI-ICE Switch

Switch turns power to the windshield anti-ice controller on / off ON

Anti-Ice is on (NORM or HIGH)

Windshield Anti-Ice is not controlled by the automatic anti-ice system (if applicable), and must be manually turned on when icing conditions are anticipated or encountered.

Forward Overhead

1. WINDSHLD WIPE Selector - (Captain and First Officer)

Each wiper has an OFF, SLOW, FAST speed. When selected OFF, the wiper and arm assembly move to the vertical parked position. Operation on a dry surface is not recommended.

2. FUEL DUMP EMER STOP Switch - amber

Alternate action switch that electrically overrides the fuel DUMP switch by reversing the signal and stopping the fuel dump sequence. Illuminates amber if dump valves have been commanded closed. The fuel dump sequence can be restarted by pushing the FUEL DUMP EMER STOP switch a second time.

3. DOME Switch

Turns dome lights on and off.

4. OVHD PNL FLOOD Rheostats

Outer rheostat regulates intensity of overhead panel switchplate lighting. Inner rheostat regulates intensity of overhead panel floodlights. All lights are off when rheostats are turned completely counterclockwise. Light intensity increases by turning rheostat in a clockwise direction.

5. INSTR & PED PNL FLOOD Rheostats

Outer rheostat regulates intensity of instrument panel and pedestal switchplate lighting. Inner rheostat regulates intensity of instrument panel and pedestal floodlights. All associated lighting is off when rheostats are turned completely counterclockwise.

6. EMER LT Switch

OFF

Normal for ground operations. Emergency lights will not illuminate. Batteries will charge when power is available. EMER LTS DISARM alert will be displayed on EAD.

ARM

Normal for flight. Allows emergency lights to illuminate automatically if normal electrical power is interrupted. Connects batteries to charging system if power is available.

For ground test. Illuminates emergency lights as long as power is available. EMER LTS DISARM alert is displayed on EAD.

7. STBY COMP Switch - blue

Turns on the standby compass light. ON illuminates blue.

8. EMER LT TEST Button

When this button is pushed:

Emergency lights illuminate.
Integral batteries are tested under load.
EMER LTS TEST PASS alert is displayed on EAD when all circuits and batteries are satisfactory.

If EMER LTS TST PASS does not appear, batteries with abnormal voltage can be identified on the SD STATUS page MAINT column by pushing the button again.

9. LDG LT Switch (L and R)

Activates respective primary landing lights mounted on the forward fuselage. RET

Lamp are off and the lights are retracted flush with the fuselage.

EXT OFF

Lights are extended but the lamps are off.

EXT ON

Lights are extended and the lamps are on.

10. NOSE LT Switch

Turns on nose gear landing lights for taxiing and landing. These lights will only come on if landing gear control handle is in DOWN position. OFF

Lights are off.

TAXI

Lights are on with less than full intensity for ground operation.

LAND

Lights are on at full intensity for landing.

11. NO SMOKE Sign Switch

Illuminates NO SMOKING signs and sounds a chime in cabin.

AUTO or OFF

NO SMOKING signs will illuminate and a chime will sound in cabin if a cabin decompression occurs (cabin altitude exceeds 10,000 feet).

AUTO

NO SMOKING - sign will illuminate and a chime will sound in cabin when landing gear handle is in DOWN position.

12. SEAT BELTS Sign Switch

Illuminates FASTEN SEAT BELT and RETURN TO CABIN signs and sounds a chime in cabin.

AUTO or OFF

FASTEN SEAT BELT signs will illuminate and a chime will sound in cabin if a cabin decompression occurs (cabin altitude exceeds 10,000 feet). RETURN TO CABIN signs will not illuminate.

AUTO

FASTEN SEAT BELT and RETURN TO CABIN signs will illuminate and a chime will sound in cabin when FLAP handle is out of the UP position and/or landing GEAR handle is in DOWN position.

13. LDG LT Switch (L)

Activates respective primary landing lights mounted on the forward fuselage. RET

Lamp are off and the lights are retracted flush with the fuselage.

EXT OFF

Lights are extended but the lamps are off.

EXT ON

Lights are extended and the lamps are on.

14. LDG LT Switch (R)

Activates respective primary landing lights mounted on the forward fuselage. RET

Lamp are off and the lights are retracted flush with the fuselage.

EXT OFF

Lights are extended but the lamps are off.

EXT ON

Lights are extended and the lamps are on.

15. NAV Switch - amber

Turns on position lights in each wing tip. The two left forward lights emit red lighting. The two right forward lights emit green lighting. The two aft lights in each wing tip emit white lighting.

OFF

illuminates amber when lights are off.

16. LOGO Switch - blue

Turns on logo light on horizontal stabilizer to illuminate vertical stabilizer. ON

illuminates blue when switch is selected on.

OFF

illuminates blue when switch is selected off.

17. BCN Switch - amber

Turns on beacon lights on top and bottom of aircraft.

OFF

illuminates amber when anti-collision lights are off.

18. HI-INT Switch - blue

Turns on supplemental high intensity recognition lights on each wing tip. Each wing tip has three lights (two forward and one aft). Lights flash in sequence with anticollision lights. Illuminates blue when high intensity lights are off.

19. CALL RESET Button

Pushing the button will turn off the blue CALL light.

Overhead

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