LET 410 UVP TTR (Technical Type Rating) EXAM

MAXIMUM TAKE-OFF WEIGHT (MTOW). 14,594 LB (6,620 KG). 14,550 KG ( 6,600 KG).

MAXIMUM RAMP WEIGHT (MRW). 14, 594 LB ( 6,620 KG). 14,550 LB (6,600 KG).

MAXIMUM LANDING WEIGHT (MLW). 14,594 LB (6,620 KG). 14,109 LB (6,400 KG).

MAXIMUM ZERO FUEL WEIGHT (MZFW) WITHOUT WING TIP TANK. 13,227 LB (6,000 KG). 13, 360 LB (6,060 KG).

MAXIMUM ZERO FUEL WEIGHT (MZFW) WITH WING TIP TANK. 13,227 LB (6,000 KG). 13,360 LB (6,060 KG).

MAXIMUM FLOOR LOADING OF PASSANGER. 74 LB/SQ FT. 82 LB/SQ FT.

MAXIMUM LOAD IN THE BAGGAGE COMPARTMENT. 330 LB. 550 LB.

MAXIMUM PERMISSIBLE OPERATING ALTITUDE. 13,000 FT. 14,000 FT.

MAXIMUM OPERATING SPEED. 191 KTS. 181 KTS.

MAXIMUM SPEED IN THE TURBULENCE. 135 KTS. 140 KTS.

MAXIMUM FLAPS EXTENDED SPEED, VFE WITH 18° FLAP POSITION. 135 KTS. 119 KTS.

MINIMUM CONTROL SPEED FOR TAKE-OFF RUN (VMCG). 70 KTS. 73 KTS.

MINIMUM CONTROL SPEED FOR TAKE-OFF RUN VMCA. 70 KTS. 73 KTS.

MINIMUM CONTROL SPEED FOR LANDING (VMCL). 70 KTS. 73 KTS.

BEST RATE OF CLIMB WITH ONE ENGINE INOPERATIVE. 100 KTS. 108 KTS.

APPROACH SPEED 42° ( VREF). 84 KTS. 89 KTS.

APPROACH SPEED 18° ( VREF). 84 KTS. 89 KTS.

MAXIMUM ALTITUDE FOR STARTING THE ENGINE. 13,000 FT. 14,000 FT.

ROTATION AIRSPEED VR (18°). 81 KTS. 84 KTS.

TAKE-OFF SAFETY AIRSPEED V2 (18°). 81 KTS. 84 KTS.

DESIGN MANEUVERING SPEED (VA). 140 KTS. 150 KTS.

MAXIMUM OPERATING LIMIT SPEED (VMO). 181 KTS. 191 KTS.

MAXIMUM LANDING GEAR OPERATING SPEED (VLO). 135 KTS. 145 KTS.

MAXIMUM LANDING GEAR EXTENDED SPEED (VLE). 135 KTS. 145 KTS.

MAXIMUM FLAPS EXTENDED (42°). 119 KTS. 129 KTS.

MAXIMUM PERMISSIBLE SPOILER EXTENSION (VSPOIL). 102 KTS. 105 KTS.

UNDER MAXIMUM CONTINUOUS POWER CONDITIONS THE MAXIMUM PERMISSIBLE ITT IS. 690°C. 790°C.

AT REVERSE THRUST POWER SETTINGS THE MAXIMUM GAS GENERATOR (NG) SPEED IS. 87%. 97%.

AT REVERSE POWER SETTINGS, THE MAXIMUM OBSERVED ITT ALLOWED IS. 710°C. 610°C.

DURING THE ENGINE ACCELERATION THE MAXIMUM PERMISSIBLE GAS GENERATOR SPEED IS. 101%. 107%.

THE BASIS RADIO NAVIGATIONAL EQUIPMENT FOR IFR OPERATION IS. VHF COMMUNICATION RADIO SETS. VHF, VOR-ILS, MKR 75 MHZ.

THE FORWARD CENTER OF GRAVITY POSITION LIMIT FOR 5700 KG IS. 22% MEAN AERODYNAMIC CHORD. 30% MEAN AERODYNAMIC CHORD.

THE AFT CENTER OF GRAVITY POSITION LIMIT AT 5700KG IS. 22% MEAN AERODYNAMIC CHORD. 30% MEAN AERODYNAMIC CHORD.

THE MAXIMUM POSITIVE LIMIT LOAD FACTOR WITH THE WING FLAP EXTENDED IS. 2.0. 3.1.

THE MAXIMUM NEGATIVE LIMIT LOAD FACTOR IS. - 1.24. - 1.34.

THE MAXIMUM NUMBER OF PERSONS INCLUDING THE CREW CARRIED ON THE AIRCRAFT SHALL BE. 21. 17.

THE MAXIMUM NUMBER OF PERSONS INCLUDING THE CREW CARRIED ON THE AIRCRAFT SHALL BE. 19. 17.

THE LIMITATIONS ON THE STARTER OPERATING TIME ARE. COOL DOWN THE START FOR ONE HOUR AFTER FIVE ATTEMPTS. COOL DOWN THE STARTER FOR 30 SEC BETWEEN EACH START AND MONITORING RUN.

THE ENGINE FITTED ON THE AIRCRAFT IS. ONE SHAFT, REVERSE FLOW WITH FREE TURBINE. TWO SHAFT, REVERSE FLOW WITH FREE TURBINE.

THE MAXIMUM CONTINUOUS SHAFT POWER IS. 657 SHP. 567 SHP.

THE SPEED FOR GAS GENERATOR IS. 31,023 R.P.M. 36,660 R.P.M.

THE PROPELLER SPEED CONTROL RANGE IS. 1700 - 2080 R.P.M. 1800 - 2000 R.P.M.

MAXIMUM INTER TURBINE TEMPERATURE ALLOWED AT THE TIME OF STARTING WITH AIRCRAFT BATTERIES IS. 730°C. 750°C.

MAXIMUM NUMBER OF SUBSEQUENT STARTING IN INTERVALS OF TWO MINUTES EACH IS. 3. 5.

MINIMUM AMBIENT AIR TEMPERATURE ALLOWED FOR THE USE OF WATER INJECTION AT SEA LEVEL IS. 23°C. 25°C.

THE TORQUE AT MAXIMUM CONTINGENCY IS. 101.2%. 106.5%.

MAXIMUM PROPELLER SPEED AT TAKE-OFF WITH WATER INJECTION IS. 1900 R.P.M. 2080 R.P.M.

MAXIMUM OVERSHOOT OF THE PROPELLER SPEED AFTER ACCELERATION IN CASE OF MISSED APPROACH IS. 1900 R.P.M. 2000 R.P.M.

FUEL CONSUMPTION IN TAXING PER MINUTE IS. 3.4 LB. 4.4 LB.

AFTER USING MAXIMUM CONTINGENCY POWER. THE ENGINE SHOULD NOT BE OPERATED UNTIL SERVICED. THE ENGINE MANUFACTURER MUST DECIDE ABOUT THE FURTHER OPERATION OF THE ENGINE.

HOW IS THE WATER INJECTION STOPPED WHEN THE ENGINE IS THROTTLED BACK FROM MAXIMUM TAKE-OFF TO POWER SETTING?. MANUALLY. AUTOMATICALLY.

DIFFERENCE BETWEEN SPEED OF LEFT AND RIGHT PROPELLER MUST NOT EXCEED. 30. 40.

WHEN THE ENGINE OPERATES AT THE MAXIMUM TAKE-OFF POWER THE AIR BLEED FOR AIRCRAFT PORPOSES. MUST BE CLOSED. MUST BE REDUCED.

PULLING THE TCL BACK BEHIND THE IDLE STOP SETS THE PROPELLER BLADES TO NEGATIVE ANGLES WHILE. INCREASING THE ENGINE OUTPUT. DECREASING THE ENGINE OUTPUT.

IF ONE OR BOTH OF THE ENGINE FAILS TO PRODUCE POWER AFTER WATER INJECTION IS COMMENCE, THIS INDICATES A FLAME OUT CAUSED BY. TOO HIGH RUNNING SPEED OF THE GAS GENERATOR. TOO LOW RUNNING SPEED OF THE GAS GENERATOR.

FUEL SYSTEM CONSIST OF INDIVIDUAL SUBSYSTEM DIVIDED INTO. OUTER, MIDDLE AND COLLECTOR TANKS IN EACH WING. OUTER AND MIDDLE TANKS IN EACH WING.

FUEL SUPPLY TO THE ENGINE IS PROVIDED BY. BOOSTER PUMPS AND ENGINE PUMPS. BOOSTER PUMPS.

FUEL TANKS ARE FILLED THROUGH. FILLER ON THE UPPER PART WINGS SURFACE. FULLER ON UPPER STARBOARD WING SURFACE.

TOTAL CAPACITY OF FUEL SYSTEM WITH 8 TANKS AND 2 WING TANKS (EXPANSION VOLUME EXCLUDE) IS. 1695 LITRES. 1678 LITRES.

TOTAL USABLE FUEL CAPACITY IN FUEL SYSTEM WITH 8 TANKS AND 2 WING TANKS IS. 1695 LITERS. 1678 LITERS.

UNDER NORMAL OPERATING CONDITION IN FLIGHT FUEL FOR THE ENGINES IS DELIVERED FROM. EACH FUEL SUBSYSTEM FEEDS THE CORRESPONDING ENGINE. BOTH FUEL SUBSYSTEMS FEED ALL ENGINES.

STEADY YELLOW LIGHT ON CENTRAL WARNING DISPLAY PORT FUEL INDICATOR SIGNALS. 108 +- 15 IN CERTAIN GROUPS OF FUEL TANKS. CROSS-FEED VALVE IS OPEN TRANSFERRING FUEL TO THE OPPOSITE TANK.

YELLOW CELL FUEL PRESSURE LIGHT ON CWD ILLUMINATING IN FLIGHT WITH FUEL PRESSURE DROP ON FUEL PRESSURE INDICATOR SIGNALS. FUEL PUMP OF REPRESENTATIVE ENGINE HAS FAILED. FILTER IS CLOGGED ON RESPECTIVE FUEL SYSTEM.

FUEL TRANSFER IS ONLY USED. DURING LONGER FLIGHTS WITH ONE ENGINE ONLY. DURING LONGER FLIGHTS WITH ONE ENGINE OR DURING BOTH PUMPS FAILURE ON ONE SIDE.

DURING FLIGHT IN CASE OF COMPLETE LOSS OF ELECTRICAL POWER. THE BOOSTER PUMPS WILL AUTOMATICALLY CHANGE TO BATTERY POWER AND FLIGHT CAN BE ENDED. FLIGHT CAN BE ENDED BY USING ENGINE DRIVEN FUEL PUMP.

THE OIL CAPACITY OF EACH OIL TANK IS. 7 LITERS. 8 LITERS.

MIXING OILS OF VARIOUS TYPES AND MARKING IS. PERMITTED PROVIDED MANUFACTURE HAS GIVEN AN APPROVAL. NOT PERMITTED UNDER ANY CIRCUMSTANCES.

THE MINIMUM CONSTANT OIL PRESSURE VALUE IS. 1.2 KP/SQ CM. 2.7 KP/SQ CM.

WHEN INTERMEDIATE CONTINGENCY POWER IS USED, THE MAXIMUM OIL TEMPERATURE MAY BE INCREASED TO. 85°C. 95°C.

THE RUDDER TRIM TAB IS CONTROLLED BY. ELECTRO MECHANISM. HYDRAULIC MECHANISM.

THE ELEVATOR ARE FITTED WITH. A TRIM TAB ON THE LEFT ELEVATOR. A TRIM TAB ON BOTH THE LEFT AND RIGHT ELEVATORS.

THE AILERONS ARE FITTED WITH. A GEARED TAB ON THE LEFT AND RIGHT AILERONS AND A TRIM TAB ON LEFT AILERON ONLY. ELECTRO-MECHANICAL CONTROLLED TRIM TAB.

THE GROUND SPOILERS ARE CONTROLLED BY. HYDRAULIC ACTUATOR SITUATED AFT OF THE WING REAR SPAR. ELECTRICAL ACTUATOR SITUATED IN FRONT OF THE WING SPAR.

THE ELEVATOR TRIM TAB IS OPERATED BY. AN ELECTRIC ACTUATOR. A TRIM TAB CONTROL WHEELS SITUATED ON THE FRONT CONTROL PANEL.

THE AILERON TRIM TAB IS OPERATED BY. HAND OPERATED WHEEL ON THE FRONT CONTROL PANEL. THE LEFT-BANK RIGHT CHANGE OVER SWITCH ON THE FRONT CONTROL PANEL.

THE WING FLAP ARE ACTUATED BY. HYDRAULIC ACTUATOR ATTACHED TO THE WING FRONT SPAR. ELECTRIC MOTOR ATTACHED TO THE WING FRONT SPAR.

ALL WING FLAP DEFLECTIONS DATA AND WING FLAP CONTROL LEVER POSITIONS RELATE TO. OUTER FLAPS. INNER FLAPS.

NORMAL HYDRAULIC POWER IS USED FOR THE OPERATION OF. FLAPS, WHEELS BREAKS, NOSE WHEEL STEERING AND INTAKE DEFLECTOR. FLAPS, WHEEL BREAKS, NOSE WHEEL STEERING, WINDSHIELD WIPERS AND LANDING GEAR.

NORMAL WORKING PRESSURE IS REGULATED BETWEEN. 100 TO 137 ( KP/SQ CM). 137 TO 167 ( KP/ SQ CM).

THE HYDRAULIC EMERGENCY HAND PUMP. WILL ONLY OPERARATE THE NOSE WHEEL STEERING SYSTEM. WILL OPERATE LANDING GEAR AND WING FLAPS.

NOSE WHEEL STEERING IS ACHIEVED BY. OPERATION OF THE LEVER ON CAPTAIN'S CONTROL COLUMN. OPERATION OF THE LEVER ON CAPTAIN'S CONTROL COLUMN AND RUDDER PEDALS.

THE HYDRAULIC PRESSURE IN THE FEEDING CIRCUIT IS INDICATED BY. ELECTRIC PRESSURE GAUGE ON THE CENTRAL PANEL. PRESSURE GAUGE AND YELLOW WARNING LIGHT ON CENTRAL PANEL.

THE HYDRAULIC FLUID LEVEL OF THE EMERGENCY CIRCUIT TANK IS INDICATED BY. OIL LEVEL GAUGE LOCATED ON THE TANK. A GAUGE LOCATED ON THE CENTRAL INSTRUMENT PANEL.

THE PRESSURE GAUGE FOR GROUND PRESSURE CHECK OF THE PRESSURE IN THE HYDRAULIC TANK IS INSTALLED IN THE. RIGHT HAND ENGINE NACELLE. BOTH RIGHT AND LEFT HAND ENGINE NACELLES.

THE BLEED AIR SYSTEM PROVIDE BY. COMPRESSED AND HEATED AIR FROM THE ENGINE COMPRESSOR FOR AIRCRAFT HEATING PNEUMATIC AND DE-ICING SYSTEM. HEATED AIR FROM ENGINE COMPRESSOR FOR CABIN HEATING AND DE-ICING.

ENGINE DE-ICING IS PROVIDED BY. ELECTRICALLY HEATED BOOTS BONDED TO THE LEADING EDGE OF THE AIR INTAKE LOWER COWLING, THERMOSTATICALLY CONTROLLED TO GIVE, FAST AND SLOW CYCLING. HOT AIR WHICH IS BLED FROM THE ENGINES TO THE ENGINE AIR INTAKES.

WING AND TAIL DE-ICING IS PROVIDED BY. REGULATED AIR SUPPLY FROM CABIN HEATING MANUALLY OR AUTOMATICALLY. ELECTRICALLY HEATED BOOTS THERMOSTATICALLY CONTROLLED MANUAL OR AUTO, FAST OR SLOW CYCLE.

PROPELLERS BLADE DE-ICING IS PROVIDED BY. ELECTRICAL HEATING OF THE BLADES LEADING EDGE. SLINGER RINGS AT THE BLADE ROOTS EJECTING ISOPROPYL ALCOHOL.

INCREASE IN ICE LAYER ON THE AIRCRAFT SURFACE ISINDICATED TO THE PILOTS BY. THE TEMPERATURE GAUGE ON THE INSTRUMENT PANEL. THE LIGHT SIGNALING SYSTEM.

THE REAL ICE LAYER IS ESTIMATED ACCORDING. BY VISUALLY SEEING THE SIZE OF INFORMATION. TO THE STATIC DETECTOR LOCATED AT THE COCKPIT SIDE WINDOW.

DC POWER SUPPLY IS FROM. TWO ENGINES DRIVEN GENERATOR OF 2 X 2.6 KW AND TWO BATTERIES OF 2 X 25 Ah CAPACITY. TWO ENGINES DRIVEN GENERATOR AND TWO BATTERIES OF 24 VOLTS.

AC POWER SUPPLIES IS FROM. TWO ROTARY INVERTERS OF 2 X 28 VOLTS. FOUR ROTARY INVERTERS OF 4 X 28 VOLTS.

THE DC ELECTRIC NETWORK CONSISTS OF. TWO SYSTEMS WHICH ARE INTERDEPENDENT OF EACH OTHER. TWO SYSTEMS WHICH ARE INDEPENDENT OF EACH OTHER.

WITH LEFT ENGINE GENERATOR NOT ON LINE IT WILL BE INDICATED BY. STEADY YELLOW LIGHT SIGNAL ON THE CWD. FLASHING LIGHT SIGNAL ON CWD.

IF EXTERNAL POWER SUPPLY IS PLUGGED IN. DC GENERATORS WARNING LIGHT ON CWD WILL GO OFF. DC GENERATOR WARNING LIGHT ON CWD WILL COME ON.

IF EITHER OF THE TWO INVERTERS STOP SUPPLYING ALTERNATE VOLTAGE TO THE CIRCUIT. A FLASHING YELLOW LIGHT ON CWD INDICATES WHICH INVERTER HAS STOPPED SUPPLYING THE VOLTAGE. A STEADY YELLOW LIGHT WILL INDICATE ON CWD WHICH INVERTER HAS STOPPED SUPPLYING THE VOLTAGE.

VISUAL ENGINE FIRE WARNING IS GIVEN BY. ILLUMINATION OF RED FIRE LIGHT ON THE ENGINE WITH FIRE ON THE CWD. ILLUMINATION OF RED CAUTION LIGHTS IN THE CAUTION PANEL.

IF AN ENGINE HAS BEEN ON FIRE, AND THE FIRE HAS BEEN SUCCESSFULLY PUT OFF. THE ENGINE MAY BE RESTARTED AGAIN PROVIDED ALL THE FIRE EXTINGUISHERS ARE NOT DISCHARGED. THE ENGINE SHOULD NOT BE RESTARTED AGAIN.

WHEN BOTH LH DC GENERATOR AND RH DC GENERATOR SIGNAL OR DWD LIGHT UP. CHECK ON AND ATTEMPT TO RE-ENGAGE THE GENERATOR ONLY TWICE. CHECK ON AND ATTEMPT TO RE-ENGAGE THE GENERATOR ONLY ONCE.

IT IS RECOMMENDED THAT FOR ALL EMERGENCY LANDINGS ON LAND, THE WING SHOULD BE EXTENDED TO (EVEN SURFACE). 18° AND LANDING GEAR EXTENDED. 42° AND LANDING GEAR EXTENDED.

EMERGENCY EVACUATION OF THE AERO PLANE DURING EMERGENCY LANDING IS CARRIED OUT. THROUGH EMERGENCY EXIT WINDOW ON THE PORT SIDE. THROUGH THE PORT MAIN BOARDING DOOR OR PASSENGER FRONT STARBOARD DOOR.

THE OXYGEN BREATHING APPARATUS FRO CREW IS LOCATED. REAR SIDE OF PILOT'S SEAT. UNDER THE PILOT'S SEAT.

THE PORTABLE FIRE EXTINGUISHERS ARE LOCATED. BEHIND CO-PILOT SEAT AND FUSELAGE REAR NEAR THE MAIN DOOR. ABOVE THE MAIN DOOR.

IF FIRE FAILURE INDICATION OCCURS DURING THE TAKE-OFF AT AIRSPEED LESS OR EQUAL TO V1. CONTINUE THE TAKE; DON NOT RETRACT THE LANDING GEAR. INTERUPT THE TAKE-OFF.

DURING TAKE-OFF WITH THE USE OF WATER INJECTION, WHAT IS THE MINIMUM TORQUE TO BE SET?. 60%. 70%.

WHAT IS THE CAPACITY OF THE TIP TANK IN LITERS?. 196.5 LITERS (346 LB). 247.7 LITERS (436 LB).

WHICH IS THE CRITICAL ENGINE?. RIGHT. LEFT.

THE AILERON TRIM TAB IS FITTED ON. ON THE RIGHT AILERON. ON THE LEFT AILERON.

THE LET 410 IS EQUIPPED WITH TWO ENGINES OF WHICH MAKE. WALTER M601E. WALTER M701E.

THE BATTERIES ARE CONNECTED IN WHICH ARRANGEMENT. PARALLELS. SERIES.

THE AIRCRAFT CAN BE OPERATED AT AMBIENT TEMPERATURE RANGING FROM. -50°C TO +40°C. -50°C TO +30°C.

TAXING MANUALLY WITH THE TILLER, THE NOSE CAN DEFLECT EITHER SIDE. + - 50°. + - 30°.

WHEN TAXING WITH RUDDERS , THE NOSE CAN DEFLECT EITHER SIDE. + - 3.5°. + - 4.5°.

WHAT IS THE MAXIMUM CROSSWIND COMPONENT ON UNPAVED GROUND OR GRASS STRIPS. 17.4 KTS. 19.4 KTS.