b) – Reduction gear for Rotax engine
Design model : Rotax 912 (S)
Reduction ratio : 2.43 : 1
4.3. Maintenance and repair of engine 
For complete data on the engine, operating and maintenance instructions, identification and removal of damages, repairing instructions for the engine and engine equipment, see the Rotax engine documentation.
5. FUEL SYSTEM 
Main components of fuel system: -wing fuel tanks; -fuel supply and return circuit; -control devices; 
5.1. Description and operation (see Schematic diagram of fuel system on page 38)
Two wing fuel tanks are fitted on the airplane, one in each wing, between ribs no. 1 and 3, the main and rear spars, each of 40l (10.5 USA gallons) capacity. Each wing tank is riveted on primer PR-1431 type 1, sealed with primers PR 1422-2 and PR 1005L (applied by splashing). Inside each tank are mounted: a ventilation pipe (up to the top of the tank) a coarse filter (finger filter), a fuel lever transducer and a fuel inlet flange. The tank drainage is ensured by a drain valve mounted on the lower side of the settling tank. Each tank is provided with an inlet for connecting the engine return pipe. The tank ventilation is ensured by a ventilation loop located in the wing-to-fuselage joint area, and exiting into the atmosphere; this loop is connected to the ventilation pipe inside the tank.
The engine fuel supply circuit comprises the following elements: a rigid pipe exiting the tank in the wing-to-fuselage joint area (LH-RH), a rigid pipe in the fuselage (LH-RH),a by-pass valve (LH-RH), a rigid pipe entering the shut-off valve (LH-RH), a shut-off valve, a rigid pipe exiting the
S.C. AEROSTAR  S.A.
FESTIVAL R40S
BACAU - ROMANIA
   AIRPLANE MAINTENANCE MANUAL
valve, a hose entering the settling filter, a hose entering the fine filter, a hose entering the electrical (boost) pump, a hose exiting the electrical pump and entering the distributor, a hose entering the engine pump, a hose exiting the engine pump and entering the distributor, carburetor supply hoses (LH-RH), a return hose from distributor to the firewall inlet, rigid pipes inside the fuselage for fuel return to the tanks (LH-RH, 6 pcs.), flexible tubes for purging of settling filter, flexible tubes for draining the carburetors and the suction dashpot, fittings, collars, rubber pistons.
The engine fuelling route is turned on/off by means of the shut off valve control handle, installed on the RH control desk at the lower side of the control panel. A control rod is located between the shut-off valve and the control handle (on the panel), joint to both parts. The position of the valve control handle is defined by the red tag, riveted to the panel in the control handle area. The LH/RH by-pass valves are mounted along the circuit of the corresponding fueling pipes, at floor level, in the LH/RH side of the cockpit, being controlled directly by pilots in case of unequal fuel use from the tanks. Purging of the fueling circuit is ensured by the drain valve mounted at the settling filter on the firewall panel. This valve is actuated by pressing its lower disk, while drainage is ensured by a flexible tube, exiting in the atmosphere, under the  fuselage. (The same type of valve ensures the purging of tanks). In case of engine pump failure, the engine fueling can be ensured by the boost electrical pump installed on the firewall and controlled by a switch located on the control panel. The auxiliary pump operation is signaled by a yellow lamp on the control panel.
　
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