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47 Cards in this Set
- Front
- Back
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The maximum speed with the MACH TRIM system inoperative is?
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280/0.82M
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The recommended turbulent penetration airspeed is
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280Kts/0.76M
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The maximum landing weight of the B737-700 is
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58,059 Kg
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The maximum differential pressure is
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9.1 psi
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The Allied Signal 131 APU maximum EGT is
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No limit
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The maximum aircraft altitude for electrical use of the Allied Signal 131 APU is
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41,000ft.
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The Maximum N1 RPM is
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Indicated by a red line on the DU.
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The minimum start pressure at 2000 feet above sea level (prior to starter engagement) is
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No limit
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The typical maximum fuel tank quantities are
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3,900 kgs in each wing tank, 12,800 kgs in the centre tank
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What is the approximate minimum engine oil quantity (per engine) for despatch.
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12 US Quarts ie 69% Full
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For an automatic landing the head and crosswind limits are
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Headwind limit is 25 kts and the crosswind limit is 20 kts.
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The maximum demonstrated crosswind component for take-off and landing is
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36 kts.
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The Allied Signal APU is rated at
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90KVA up to FL310 and 66KVA above FL310.
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If a malfunction exists causing an automatic shutdown of the APU and the APU switch is placed to OFF
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The FAULT light extinguishes after 5 minutes.
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Electrical power to start the APU comes from
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The main battery only if no AC power is available.
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Which of these statements is true?
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The start lever controls the spar fuel shut off valve and is powered from the hot battery bus.
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The fuel LOW indication
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Is amber and illuminates when the related main tank contains less than 907Kgs
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The fuel IMBAL indication
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Illuminates if the main tanks differ by more than 453kgs and will continue to display until imbalance is reduced to 91Kgs.
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The fuel CONFIG indication illuminates if the center tank contains more than 726kgs, both centre tank pumps are producing low or no pressure and either engine is running...
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And will continue to display until centre tank is less than 363Kgs, one centre tank pump is producing high pressure or both engines are not running.
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Centre tank fuel
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Is pressure fed
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The centre tank fuel scavenge jet pump
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Is activated by a float switch
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Pulling an engine fire switch
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Closes both fuel valves.
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The DISPLAYS CONTROL PANEL annunciation is accompanied by
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An ALT flag against the altitude tape.
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The hydraulic quantity RF annunciation displays when the hydraulic quantity is less than
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76%
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The overboard exhaust valve
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Is driven open if either pack switch is in HIGH and the recirc fan is OFF.
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The antiskid switch
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Is not fitted to the NG.
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How many tyre damage impact fittings are there?
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Two. (One each side of the wheel well).
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Landing autobrake settings may be selected
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After touchdown prior to 60Kts.
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EEC gives redline protection for
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N1 and N2.
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The EEC will close the engine fuel shut off valve and de-energise the igniters during an engine start if:
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No increase in EGT within 15 seconds after the start lever is raised to IDLE.
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The START VALVE OPEN, LOW OIL PRESSURE and OIL FILTER BYPASS lights
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Will blink for 10 seconds if condition occurs, except during take-off and landing.
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With flap 15 selected and landing gear UP, the landing gear warning horn cannot be silenced with the HORN CUTOUT switch if
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Either thrust lever is below 20 degrees or an engine not running and the other thrust lever is less than 34 degrees.
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The Proximity Switch Electronic Unit (PSEU) light illuminates
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Is inhibited from thrust lever advance for take-off until 30 seconds after landing.
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EGPWS terrain display changes from dotted to solid yellow
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40 - 60 seconds from impact.
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The weather radar automatically begins scanning for windshear when:
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In flight below 2300ft RA.
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With FMC U10, after TOGA is pressed for a go-around, the CRZ page will show.
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The highest of: 1500ft or MCP altitude or the LEGS missed approach level.
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The flap limit speed for FLAP 30 is
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165K
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The flap limit speed for FLAP 1 is
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250K
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The standby yaw damper is powered
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From the standby hydraulic system, only when both FLT CONTROL switches are positioned to STBY RUD.
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The Flaps/Slat Electronics Unit (FSEU)
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Monitors flap load, assymetry, skew and overrun on all T/E flaps and L/E slats 2 to 7.
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A leak in the system B hydraulic will also reduce the quantity in the B system
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To approx zero and is sufficient for PTU operation
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A leak in the standby hydraulic system will also reduce the quantity in the B system to
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72%
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An IDG will auto disconnect due to
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High oil temperature
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TR UNIT light in-flight indicates
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TR1 or TR2 and TR3 failed.
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ELEC light means
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A fault exists in DC power system or standby power system and only operates on the ground.
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The SOURCE OFF lights indicate that
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No source has been manually selected to power the related transfer bus, or the manually selected source has been disconnected.
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The STANDBY POWER OFF light illuminates if there is no power to either
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AC standby bus, DC standby bus or battery bus.
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