LANDING GEAR Flashcards
THE LANDING GEAR POSITION INDICATIONS ARE CONTROLLED BY:
TWO ISOLATED SYSTEMS, SYSTEM 1 AND SYSTEM 2 AND TWO SEPARATED POSITION
INDICATORS
AIRCRAFT IS SUPPLIED BY BATTERIES ONLY:
SYSTEM 1 ONLY IS SUPPLIED (CENTRAL PANEL)
LANDING GEAR NOT DOWN, THE ALARM IS GENERATED:
A) BY MFC 2 ASSOCIATED TO THE OVERHEAD PANEL (SYSTEM 2)
B) BY MFC 1 ASSOCIATED TO THE CENTRAL PANEL (SYSTEM 1)
AN ANTI-RETRACTION LATCH PREVENTS SELECTION OF THE LANDING GEAR LEVER TO THE
“UP” POSITION AS LONG AS:
ONE OF THE MAIN GEAR SHOCK ABSORBERS SENSES WEIGHT ON WHEELS
THE PRIMARY DETECTION SYSTEM LANDING GEAR CONTROL INDICATIONS AND ALERTS ARE
CONTROLLED ELECTRICALLY FROM WHICH BUS:
DC STBY BUS
LANDING GEAR NORMAL OPERATIONS:
A) THE MAIN GEAR WHEELS ARE BRAKED AUTOMATICALLY AS SOON AS THE LEVER IS SELECTED UP
B) AS SOON AS THE GEAR IS LOCKED AT ITS SELECTED POSITION, HYDRAULIC PRESSURE IS
RELEASED
TO CONSIDER THE GEAR DOWN, 3 GREEN LIGHTS MUST BE ILLUMINATED ON:
EITHER, OVERHEAD OR CENTRAL INSTRUMENT PANELS
ON THE LANDING GEAR PANELS, “UNLK” LIGHT ILLUMINATES TO INDICATE
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 “FWS”
WILL BE ACTIVATED WHENEVER ANY GEAR IS NOT SEEN DOWN AND LOCKED:
A) FLAPS 30° AND ZRA BELOW 500FT
B) AT LEAST ONE POWER LEVER AT FI AND ZRA BELOW 500FT
LANDING GEAR NOT LOCKED DOWN ON OVERHEAD PANEL, ONE “PL” AT “FI”, THE OTHER
ONE BELOW TAKE-OFF POSITION AND ZRA BELOW 500FT, THE AURAL ALERT MAY BE
SILENCED BY:
A) THE RETRACTION OF AT LEAST ONE LANDING GEAR FOR 150 SECONDS OR DEPRESSING
MASTER WARNING LIGHT IF FLAPS ARE NOT IN 30° POSITION
B) USING EMERGENCY AUDIO CANCEL IF THE FLAPS ARE IN THE 30° POSITION
IF THE NORMAL GEAR EXTENSION FAILS, EMERGENCY EXTENSION HANDLE ALLOWS
MECHANICAL UNLOCKING THEN:
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
HOW MANY VALVES IN THE NOSE WHEEL STEERING SYSTEM MUST BE OPEN BEFORE NOSE
WHEEL STEERING IS AVAILABLE?
BOTH OF THE VALVES MUST BE OPEN TO OBTAIN A MAXIMUM LH OR RH DEFLECTION
OF 60°
THE NOSE WHEEL STEERING OPERATIONS:
A) BEFORE TAKE-OFF, IT WILL BE MAINTAINED AS SOON AS ONE GEAR STAYS ON THE
GROUND
B) AT LANDING, IT WILL WORK WITH NOSE GEAR LOCKED DOWN, NOSE AND MAIN SHOCK
ABSORBERS COMPRESSED
HOW LONG SHOULD THE ANTI-SKID “F” LIGHTS ILLUMINATE DURING A TEST OF A NORMAL
SYSTEM
6 SECONDS ON THE GROUND, 3 SECONDS IN FLIGHT
THE ANTI-SKID TEST IS INHIBITED AT WHEEL SPEEDS ABOVE:
17 KTS
THE ANTI-SKID PROTECTION IS OPERATIVE AT SPEEDS OVER:
10 KTS
IF AN ANTI-SKID CHANNEL FAILS, THE ANTI-SKID TEST SHOWS:
RELATED “F” LIGHT DOES NOT EXTINGUISH AFTER THE TEST
WHEN “F” LIGHT ILLUMINATES ON THE ANTI-SKID DISPLAY:
ANTI-SKID IS LOST ON ASSOCIATED WHEEL
THE ANTI-SKID SYSTEM USES WHICH ELECTRICAL BUSSES:
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 PARKING/EMERGENCY BRAKE:
AT LEAST 6 APPLICATIONS OF BRAKING FORCE AT FULL EMERGENCY BRAKING PRESSURE
WITHOUT ANTI-SKID PROTECTION
THE BRAKE AND TYRE HIGH TEMPERATURE PROTECTIONS CONSIST OF:
A) THE HOT LIGHT ON THE EWD INDICATING A BRAKES TEMPERATURE OF 160° OR MORE
B) FUSE PLUGS DESIGNED TO RELEASE INTERNAL TYRE PRESSURE AT HIGH TEMPERATURE
(177° OR MORE) ON THE MAIN WHEELS
THE GEAR WHEELS ARE BRAKED AFTER TAKE-OFF:
AUTOMATICALLY MAIN GEAR ONLY, AS SOON AS THE PILOT SELECTS UP LANDING GEAR
CONTROL LEVER
THE ANTI-SKID SYSTEM IS PROVIDED FOR:
A) LOCKED WHEEL PROTECTION, TO PRECLUDE TYRE SCUFFING FOR WHEELS SPEED MORE
THAN 23KTS
B) TOUCH DOWN PROTECTION, TO PRECLUDE INADVERTENT BRAKE APPLICATION WHEN
SPIN UP IS BELOW 35KTS OR FOR 5 SECONDS WHICHEVER OCCURS FIRST
