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Installation
Guide
"LTDS" "Low Thrust Detector System"
The Average Installation time is 16 to 25 hours.
This is a basic guide to the
installation. Each system comes with all installation detail parts,
blueprints, Detail installation instructions, STC, 337 form, Log book entry form
and maintenance manual.
Description:
The systems primary function is to
instantly identify the left or right engine if an engine should fail during
takeoff or climb. The system also identifies the specific prop control to be
used to feather if you have a complete engine failure.
The system functions best at speeds associated with takeoff and landing.
The "LTDS" is a pneumatic/electrical
system that indicates to the pilot a condition of unsymmetrical power.
The engine with the low thrust condition is identified to the pilot by a
flashing amber indicator on the instrument panel.
Also a red and amber indicator on the prop control knob identifies the
effected engine. An Aural tone
accompanies the flashing indicator for a few pulses.
The system functions by measuring the differential thrust between the
left and right engine.
THE SYSTEM CONSISTS OF THE
FOLLOWING FIVE COMPONENTS:
1.
SENSOR: A
pressure sensor (pitot) is mounted on the nacelle in the
slipstream of each engine.
2. CONTROL UNIT: Pressure sending unit that translates the pressure into electrical pulses.
3.
VISUAL INDICATORS: On the instrument panel and on each prop control knob a
red and amber light.
4.
AURAL INDICATOR: The first few indicator flashes are accomplished by an aural
pulsed tone.
5.
SWITCH:
An “on/off” switch for (LTDS) System and sensor heat.
ACCESS:
1. Remove upper and side engine
cowlings only where required.
2. Remove access panel aft of
firewall. Some models you must
remove cowling fairings.
3.
Remove leading edge panel between engine and fuselage.
4. Remove portion of side
interior or just loosen interior panel for access to line routing from
engine.
5.
Remove cover on throttle quadrant.
SUGGESTED
TOOLS:
1. “Unibit”
for drilling clean burr free holes in sheet metal 1/8” thru ½” diameter.
2. 6/32 tap and 7/32 drill, if
panel indicator is to be mounted directly to the instrument panel.
RECOMMENDATIONS
1. Locate a
position for the black box “101-5100” and plan routing of the white nylon
pneumatic tubing. Route one side
completely before cutting to length.
2. Routing of the ¼” Nylon
pneumatic line from the firewall to the fuselage is through the leading edge in
the wing.
3. Sensor Location:
(Locate on down going prop side of cowling, inboard side of the cowling)
Mount sensor as shown in sketch. Route
lines upwards from sensor to avoid moisture from flowing back into tubing.
Follow ignition wiring if possible.
Ground one sensor wire to airframe or engine baffling.
Route second wire with pneumatic line to heat on/off switch in fuselage.
4. Locate the sound indicators
under the instrument panel near the pilot position
5.
(Under instrument Panel) Plan
the routing of all wires from indicators, horns, master switch, black box and
sensor heat to one central location. Trim
excess wires and make all eight (8) connections.
Allow a length of brown wire for a ground to the airframe. Connect all blue to blue, green to green, all black to black
etc. (Reference wiring schematic
101-1100) Connect the gray wire
from the master switch to a 5 amp circuit breaker.
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Sensor Alignment: Rotate sensor 5 to 10 Deg. downward from level or cowling hinge line.
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