Original Flight Hardware: Air Data Sensor Heat

The Air Data Sensor Heat panel is located in the overhead panel of the Lockheed L-1011. The switches on the panel control the heaters in the mast or the tip of the various air data sensors. The sensors are heated to prevent ice from forming in flight. Is on air data sensors has been a problem with many aircraft such as the Boeing 757 and the Airbus A340, so it's a pretty important feature.



The switches on the panel are:

PITOT CAPT .... Status light for the pitot tube and the pitot tube mast heater operating the captain's air data computer.
PITOT F/O ... Status light for the pitot tube and the pitot tube mast heater operating the first officer air data computer.
MAST LIGHT INHIBIT ... turns off the mast heater light.
TEMP PROBES ... Status light for the temperature probe heaters.
ALPHA ... Status light for the alpha vane heater.



Panel Location

Original Flight Hardware: Flight Recorder and Waste Water

The Flight Recorder and Waste Water panel is a combination panel that is located on the lower Flight Engineer panel on the Lockheed L-1011. It's functions are pretty basic. The Flight Recorder switched actives and de-activates the Flight Recorder on the ground and the Waste Water panel has an indicator to show waste water pump status and two switches to activate the mid-ship and aft-ship drain mast heaters.



The flight recorder switch will illuminate OFF when the recorded is turned off. The recorder can not be turned off in flight.



The drain mast heater indicator lights wil illuminate if the internal temperature in the masts goes below a set temperature. If light remains illuminated longer than a few seconds, select the other heater element.



Panel Location

Original Flight Hardware: Nacelle/Pylon Overheat Detection Test

The Nacelle/Pylon Ovht Det Test panel is part of the Fire Warning and Suppression system on the Lockheed L-1011. The panel has a test system for each engine nacelle/pylon combination. Each system is monitored by two fire detection loops; labeled "A" and "B".



Below the dual loop light, there is a loop selector switch for each engine. Pressing the test button illuminates lights to indicate system integrity.



Panel Location

Original Flight Hardware: Oxygen Regulator Deman

Crew oxygen on the Lockheed L-1011 is provided form an central source and controlled by a diluter demand regulator mounted at each crew position. Actually, there are a total of 5 oxygen masks in the Lockheed L-1011 cockpit; 3 for the crew and two for the observer seats.

The Oxygen Regulator has the following components:

FLOW ... an window that indicates the flow of oxygen.
REGULATOR OXYGEN PRESSURE ... The line pressure of the oxygen supply.
SUPPLY ... opens the valve from the supply line to the oxygen regulator.
100% OXYGEN and NORMAL OXYGEN ... switches the dilution of the oxygen supply from pure to mixed.
EMERGENCY, NORMAL and TEST MASK ... Sets the oxygen regulator mode.



Panel Location

The 3 panels for the crew are obstructed by the two forward facing crew seats an by the work desk below the flight engineer panel.

Original Flight Hardware: Engine Anti Ice

The Wing Anti Ice panel on the Lockheed L-1011 is part of the Ice and Rain Protection system of the aircraft. The engine inlet cowl and the P1 probe on each engine receive intermediate pressure bleed air to prevent icing. Air flow is controlled by a pressure regulating shutoff valve. The three individual engine inlet cowl anti-ice systems are controled and monitored from the engine anti-ice control panel on the pilot's overhead panel.



Operating conditions of each system are sensed by an overpressure switch and on underpressure switch.

HEAT LIGHT ... should illuminate shortly after control switch is pushed in; it indicates pressure is adequate for anti-icing. At idle power the light may not illuminate.
CONTROL SWITCH ... ON illuminates to show the switch position.
HI PR LIGHT ... indicates an overpressure in system, which will continue to function nusing overpressure relief valve.



Panel Location

Original Flight Hardware: Exterior Lights and Emergency Lighting

The Exterior Light and Emergency Lighting panel is located directly in front of the captain on the overhead panel of the Lockheed L-1011. The panel controls the exterior lighting of the L-1011 as well as the interior emergency lighting. It is directly adjacent to the Standby Power and Interior Lighting panel as can be seen below.




The Exterior Lighting switches have the following functions:

LANDING LIGHT SWITCH - Controls left and right landing lights mounted in wing fillet leading edges.
NOSE WHEEL LANDING LIGHT - Controls nosewheel light.
NOSEWHEEL TAXI LIGHT SWITCH - Provides low intensity control of lights mounted on nosewheel strut.
RUNWAY TURNOFF - controls lights in fuselage wing fillet leading edge
LOGO - controls the lights illuminating the company logo.

POSITION LIGHTS SWITCH - controls forward and rear position lights mounted on wing tips.
STROBE LIGHTS SWITCH - controls forward and aft strobe lights mounted on each wing tip.
ANTI-COLLISION LIGHTS SWITCH - controls rotating lights on top and bottom of fuselage.
WING FLOOD LIGHTS SWITCH - controls fuselage mounted lights to illuminate wing leading edges and engine inlets
WHEEL WELL LIGHTS SWITCH - controls wheel well lights.



The EMERGENCY LIGHTING SWITCH and UNARM LIGHT control the emergency lighting for flight station escape hatch, cabin exit signs, cabin aisle lights, galley, emergency evacuation slide areas and lavatories.



Panel Location

Original Flight Hardware: Second Officer's Annunciator Panel

The Second Officer's Annunciator Panel is located on the upper Flight Engineers panel on the Lockheed L-1011. There are 32 indicators on the panel. All of them are amber and illuminate if a fault or unsafe condition has been encountered:

LH FWD ENTRY ... Left Forward Entry door not closed.
FWD CARGO ... Forward Cargo door not closed.
RH FWD ENTRY ... Right Forward Entry door not closed.
GALLEY ... Galley Elevator Fault.
LH CTR ENTRY ... Left Center Entry door not closed.
CENTER CARGO ... Center Cargo door not closed.
RH CTR CARGO ... Right Center Entry door not closed.
AVIONICS ... External Avionics door not closed.
LH AFT ENTRY ... Left Aft Entry door not closed.
AFT CARGO ... Aft Cargo door not closed.
RH AFT ENTRY ... Right Aft Entry door not closed.
FWD S DUCT ... Forward engine 2 S-duct obstructed.
LH EMERGENCY ... Left Emergency escape not closed.
ESCAPE HATCH ... Cockpit overhead escape hatch not closed.
RH EMERGENCY ... Right Emergency escape not closed.
AFT S DUCT ... Aft engine 2 S-duct obstructed.
LH GEAR DOOR ... Left gear door in motion or fault.
NOSE GEAR DOOR ... Nose gear door in motion or fault.
RH GEAR DOOR ... Right gear door in motion or fault.
MAIN ELEC ... Main Electrical bay access door open.
SLAT ASYM DET FAULT ... Slat asymmetry detection failed.
TAIL SKID ... Tail skit compressed ... tail strike.
BLEED DUCT OVPRESS ... Bleed duct overpressure warning.
FLAT/SLAT LOCK ... Flap and Slat lock engaged.
WATER CPRSR 1 ... Water compressor 1 failed.
WATER LINE HTR ... Water line heater failed.
ELEVATOR ... Elevator asymmetry detected.
FLAP ASYM DET FAULT ... Flap asymmetry detection failed.
WATER CPRSR 2 ... Water compressor 2 failed.





Panel Location

Original Flight Hardware: Flight Control Electronics System (FCES)

The Flight Control Electronics System (FCES) panel is located right above the panel that we discussed in the previous post. The Lockheed L-1011 has a number of computer systems that control YAW SAS, DLC/AUTO SPLR, STALL WARN, ATS, PITCH TRIM and MACH TRIM. There are two computer systems for each. The FCES panel gives a way of turning the individual computers on or indicate FAULT.



The standard switch position is latched, which will extinguish the OFF light and will arm the FAULT light. When the switch is unlatched, a white OFF sign is displayed for the respective computer system and the FAULT light is disarmed.

YAW SAS ... Yaw and Stability Augmentation System
DLC / AUTO SPLR ... Direct Lift Computer and Auto Spoiler
STALL WARN ... Stall Warning
ATS ... Automatic Throttle System
PITCH TRIM ... Pitch and Trim
MACH TRIM ... nose up trim when above Mach .55



Panel Location

Original Flight Hardware: Primary Flight Control System (PFCS)

The Primary Flight Control System (PFCS) is located in the overhead panel above the captains' seat of the Lockheed L-1011. The PFCS is a dual channel system for each axis. Inputs to the system are from the pitch override bungees, the aft coupler and the cable open sensors for the stabilizer control paths; and the torque limiters for the aileron control paths. The inputs are processed in the Flight Control Electronics System (FCES) computer and the monitoring output is provided to the PFCS panel.

The pitch 1 and 2 lights and the roll 1 and 2 lights at the top of the panel indicate failures within the monitor system.



A jam in the stabilizer system causes the pitch override bungees and the aft coupler to compress or extend, causing switches to actuate. A broken cable in the stabilizer system allows a mechanical sensor riding on the cable to close tripping the break switches. The results are displayed on the stabilizer section of the PFCS panel.

A jam in the aileron system, for exmaple, causes relative movement between two sections of either torque limiter, causing switches to actuate. The results are displayed on the aileron and spoiler sections of the PFCS panel.





Panel Location

Original Flight Hardware: Slat Monitor

The Slat Monitor panel can be found on the upper Flight Engineer panel of the Lockheed L-1011. The panel shows the status and degree extension of the leading edge lifting devices, aka. Slats. There are 3 1/2 indicators for each wing showing the status of Slat panels 1, 2, 3, 4, 5, 6 and 7. There is an ON switch for the Slat monitor and a guarded switch that will lock the slats in place.



The round gauge has a flag that indicates system state and an indicator for the right and the left wing that shows degree extension of the slats.



Panel Location

Original Flight Hardware: Cockpit Voice Recorder (CVR)

The Cockpit Voice Recorder (CVR) panel is actually a relatively simple panel. It is placed in the overhead between the captain and the first officer. The elements on the CVR panel are

a. Area Microphone
b. Test Meter
c. Test Switch
d. Erase Switch and
e. Headset Jack



The TEST METER provides avsiaul indication of system performance. It will show the recoding level when the TEST switch is pressed.

The ERASE switch will clear all recordings on the tape. The tape can only be erased when the aircraft is on the ground with AC power applied, the parking brakes on. I guess the point is "not" to erase the CVR at will.



Panel Location

Original Flight Hardware: Interior Lights and Standby Power

The Interior Lights and Standby Power panel is a combination panel found on the forward overhead panel on the First Officer side of the Lockheed L-1011. The left hand side of the panel has the Standby Power switch and the UNARM Indicator light. The right hand side has light switches for the Magnetic Compass and the Eyebrow Panel light switch. The for square switches in the Interior Light panel are use for: No Smoking Sign Switch, Fasten Seat Belt Sign Switch, Eye Locator Light Switch and the Thunderstorm Light Switch.



Here is a more detailed description of the four square switches which all illuminate with "ON" when active. The descriptions are taken from a Lockheed L-1011 Eastern Airlines flight manual from 1973:

NO SMOKING SIGN

IN - ON is illuminated, single chime sounds, cabin NO SMOKING signs and cabin door EXIT signs are illuminated.
OUT - ON is extinguished, single chime sounds, cabin NO SMOKING signs and door EXIT signs are extinguished.

FASTEN SEAT BELT SIGN

IN - ON is illuminated, single chime sounds and cabin FAST SEAT BELT and lavatory RETURN TO SEAT signs are illuminated.
OUT - ON is extinguished, single chime sounds and cabin and lavatory sign lights are extinguished.

THUNDERSTORM LIGHT

IN - ON is illuminated, and all dimmable flight station lights are energized to maximum brilliance regardless of dimming control position.
OUT - ON is extinguished and all flight station lights are controlled by respective dimming control.

EYE LOCATOR

IN - ON is illuminated and pilots' eye position locator is energized.
OUT - ON is extinguished and pilots' eye position locator is de-energized



The Standby Power switch has three positions:

ON .. Manually connects DC Standby bus to the Battery bus which then powers the AC buses via the inverter.
ARM .. Permits automatic transfer to the DC Standby bus if the Essential AC bus fails.
OFF .. Disarms the AC Standby bus system only ... not the DC system.

The UNARM indicator light illuminates when the Standby Power switch is in the OFF position.



Panel Location