Landing Gear

THE LANDING GEAR POSTION INDICATIONS ARE CONTROLLED BY: One system which controls two position indicators. Two isolated systems, SYSTEM 1 and SYSTEM 2 and two separated position indicators. Two isolated systems, SYSTEM 1 and SYSTEM 2 controlling one position indicator.

AIRCRAFT IS SUPPLIED BY BATTERIES ONLY: (LANDING GEAR). SYSTEM 1 only is supplied (central panel). SYSTEM 2 only is supplied (overhead panel). Both SYSTEM 1 and SYSTEM.2 are supplied.

LANDING GEAR NOT DOWN, THE ALARM IS GENERATED: By MFC 2 associated to the overhead panel (SYSTEM 2). By MFC 1 associated to the central panel (SYSTEM 1). A + B are correct.

AN ANTI RETRACTION LATCH PREVENTS SELECTION OF THE LANDING GEAR LEVER TO THE 'UP' POSITION AS LONG AS: Nose landing gear shock absorbers sense weight on wheels. The three landing gear shock absorbers are not extended. One of the main gear shock absorbers sense weight on wheels.

THE 'LANDING GEAR SELECTOR VALVE' IS LOCATED IN THE LH MAIN GEAR FAIRING, AND IS CONTROLLED ELECTRICALLY FROM WHICH BUS?. ACWBUS 1. DC STBY BUS. DC BUS 2.

LANDING GEAR NORMAL OPERATIONS: The main gear wheels are braked automatically as soon as the lever is selected up. As soon as the gear is locked at it selected position, hydraulic pressure is released. A and B are correct.

TO CONSIDER THE GEAR DOWN, 3 GREEN LIGHTS MUST BE ILLUMINATED ON: Both, overhead and central instrument panels. Either, overhead or central instrument panel. One panel only, the central instrument panel.

ON THE LANDING GEAR PANELS, 'UNLK' LIGHT ILLUMINATES TO INDICATE: Uplock device has failed. Downlock device has failed. Respective gear not seen locked in lever selected position, or on the ground, the uplock box not in the opened position.

A RED LIGHT INCORPORATED IN THE LANDING GEAR LEVER WILL ILLUMINATE AND 'CCAS' WILL BE ACTIVATED WHENEVER ANY GEAR IS NOT SEEN DOWN AND LOCKED: Flaps 30degrees and Zra below 500 ft. At least one POWER LEVER at FI, and Zra below 500 ft. A + B are correct.

LANDING GEAR NOT LOCKED DOWN ON OVERHEAD PANEL, ONE 'PL' AT 'FI', THE OTHER ONE BELOW TAKE OFF POSITION AND Zra BELOW 500 FT, THE AURAL ALERT MAYBE SILENCED BY: The retraction of at least one landing gear for 150 seconds or depressing MASTER WARNING light if flaps are not in 30degrees position. Using EMERGENCY AUDIO CANCEL if the flaps are in 30degrees position. A + B are correct.

IF THE NORMAL GEAR EXTENSION FAILS, EMERGENCY EXTENSION HANDLE ALLOWS MECHANICAL UNLOCKING, THEN: Landing gear extends because of a spring device. Landing gear extends because of gravity, aerodynamic forces and gas actuator. Main landing gear is assisted by gas actuators and integrated springs, nose landing gear by a mechanical device. Landing gear extends because of a pneumatic device.

HOW MANY VALVES IN THE NOSE WHEEL STEERING SYSTEM MUST BE OPEN BEFORE NOSE WHEEL STEERING IS AVAILABLE: Only the SOLENOID VALVE, which is controlled by a combination of shock absorber (MFC) and the NOSE WHEEL STEERING CONTROL SWITCH. Only the SWIVEL VALVE, which is controlled by nose gear extension and retraction. Both of the valves must be open to obtain a maximum LH or RH deflection of 60degrees.

THE NOSE WHEEL STEERING OPERATIONS: Before take off, it will be maintained as soon as one gear stays on ground. At landing, it will work with nose gear locked down, nose and main shock absorbers compressed. A + B are correct.

HOW LONG SHOULD THE ANTI-SKID 'F' LIGHTS ILLUMINATE DURING A TEST OF A NORMAL SYSTEM?. As long as the TEST push-button is depressed. 10 seconds. 6 seconds on the ground, 3 seconds in flight.

THE ANTI-SKID TEST IS INHIBITED AT WHEEL SPEEDS ABOVE: 10kt. 17kt. Never.

THE ANTI-SKID PROTECTION IS OPERATIVE AT SPEEDS OVER: 10kt. 23kt. 25kt.

IF AN ANTI-SKID CHANNEL FAILS, THE ANTI-SKID TEST SHOWS: Related F light does not illuminate. Related F light does not extinguish after the test. Related F light flashes.

WHEN 'F' LIGHT ILLUMINATES ON THE ANTI-SKID PANEL: ANTI-SKID is lost on associated wheel. ANTI-SKID system is not activated. ANTI-SKID electrical supply is lost.

THE ANTI-SKID SYSTEM USES WHICH ELECTRICAL BUSSES?. AC BUS 1. DC BUS 1 for inboard wheels, DC BUS 2 for outboard wheels. DC ESS BUS for inboard wheels, DC EMER BUS for outboard wheels.

IN CASE OF TOTAL HYDRAULIC SYSTEMS FAILURE, THE BRAKE ACCUMULATOR ALLOWS VIA THE PARKINGIEMERGENCY BRAKE 'HANDLE: One application of braking force at full braking pressure. At least 6 application of braking force at full emergency braking pressure without ANTISKID protection. At least 6 application of braking force at full emergency braking pressure with ANTI-SKID protection.

THE BRAKE AND TIRE HIGH TEMPERATURE PROTECTIONS CONSIST OF: The HOT light on the central panel indicating a brakes temperature of 160degreesC or more. Fuse plugs designed to release internal tire pressure at high temperature (177degreesC or more) on the main wheels. A + B are correct.

GEAR WHEELS ARE BRAKED AFTER TAKE OFF: All automatically, as soon as the pilot selects UP landing gear control lever. Automatically main gear only, as soon as the pilot selects UP landing gear control lever. By the pilot using brake pedals.

THE ANTI SKID SYSTEM IS PROVIDED FOR: Locked wheel protection, to preclude tire scuffing for wheels speed more then 23 Kt. Touch down protection, to preclude inadvertent brake application when spin up is below 35 Kt or for 5 sec., whichever occurs first. A + B are correct.

LANDING GEAR NOT DOWN, ALARM IS GENERATED (BELOW 500degrees): As soon as one system detected a landing gear not down. By system one associated to central panel. By system two associated to central panel.