Installation Guide

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.

Sensor Alignment: Rotate sensor 5 to 10 Deg. downward from level or cowling hinge line.