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767 Systems (ASM 9) Flashcards

1
Q

Overhead Panel Organization (gen)

A

H: Hydraulics
E: Electrics
F: Fuel
A: Air

Flight Controls
Landing Gear & Breaks

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2
Q

ACFT Electrical System Components (elec)

A
  1. Main AC Power (main source of ACFT power)
  2. Main DC Power
  3. Battery / STBY Power
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3
Q

AC Electrical Power Sources (elec)

A
  1. LT & RT Engine IDG’s
  2. APU Gen
  3. External Power
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4
Q

AC Busses (elec)

A
  1. LT/RT Main AC Busses
  2. LT/RT AC Transfer Busses
  3. CA/FO Flight Instrument Transfer Busses
  4. LT/RT Utility Busses
  5. Galley Bus
  6. Ground Service Bus
  7. Ground Handling Bus
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5
Q

Autoland Power Source (elec)

A
  1. Left AP and CA Flight Instrument Transfer Bus: LT Main AC System
  2. Right AP and FO Flight Instrument Transfer Bus: RT Main AC System
  3. Center AP: Batt/STBY System

Autoland: 3 independent power sources via 3 isolated busses to 3 different autopilots

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6
Q

Autoland Loss of Generator Above 200’ (elec)

A

NO LAND 3

Both Tie breakers close, remaining GEN powers both LT and RT AC bussed
LT Main System power the Center Autopilot

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7
Q

Autoland Loss of Generator Below 200’ (elec)

A

Autoland continues using remaining 2 autopilots

Both Bus Tie breakers remain open
Autopilot who’s Gen failed, remains unpowered
Flight instruments powered through the FLT Inst Transfer Busses

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8
Q

DC Electrical Power Source (elec)

A
  1. LT/RT Main AC Busses (through TRU’s to produce DC)

* No flight deck controls for Main AC System*

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9
Q

DC Busses (elec)

A
  1. LT/RT Main DC Busses
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10
Q

Batt/STBY Power Sources (elec)

A

No Power to ACFT: Source is Battery

Power to ACFT: Source is Batt Charger or LT Main DC (through Main AC)

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11
Q

Batt/STBY Busses (elec)

A
  1. Hot Batt Bus
  2. Batt Bus
  3. STBY AC Bus
  4. STBY DC Bus
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12
Q

HDG (elec)

A

Hydraulic Driven Generator

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13
Q

HDG (elec)

When Activated:
Power Source:
Provides Power To:

A

When Activated: Automatically when loss of both LT and RT Main AC Busses

Power Source: Center Hydraulic System

Provides Power To: 
AC
1. LT AC Transfer Bus
2. RT AC Transfer Bus
3. STBY AC Bus
4. CA Flight Inst Transfer Bus

DC

  1. Hot Batt Bus
  2. Batt Bus
  3. STBY DC Bus
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14
Q

Number of Fuel Tanks and Qty (fuel)

A

3 tanks

  1. LT Main / 6,000 gal / 40,000 lbs
  2. RT Main / 6,000 gal / 40,000 lbs
  3. Center / 12,000 gal / 80,000 lbs

Total 24,000 gal / 160,000 lbs

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15
Q

Fuel Low Level Warning (fuel)

A

LT or RT Main Tank below 2,200 lbs

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16
Q

Where is fuel temp taken (fuel)

A

RT Main Tank

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17
Q

of Fuel Pumps (fuel)

A

2 in each tank

A single pump can supply one engine

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18
Q

Fuel Pumps Power Source (fuel)

A

All 6: AC Power

DC fuel pump for APU if no AC Power (1 located in the left main)

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19
Q

What tanks drain first (fuel)

A

Center - center pumps have greater output

Center pumps automatically power off when tank is dry

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20
Q

How does the APU get its fuel (fuel)

A

Any AC fuel pump - supply’s to left fuel manifold

DC - fuel pump in the LT Main Tank

  * no controls or indications
  * Auto Ops when no AC power*
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21
Q

FUEL CONFIG light (fuel)

A
  1. Imbalance, 2000 between LT and RT Main tanks
  2. Center fuel pump switched off with more than 1200 lbs in tank
  3. LOW FUEL displayed on EICAS, LT or RT Main tank < 2200 lbs
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22
Q

How to fix a fuel imbalance (fuel)

A
  1. Open X-Feed

2. Turn OFF fuel pumps in tank with the lowest qty

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23
Q

Fuel Jettison (fuel)

Tank:
Pump:
Rate:

A

Tank: Center Fuel Tank
Pump: 2 fuel pumps
Rate: 2600 lbs/min

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24
Q

How to turn on Fuel Jettison (fuel)

A

FUEL JETTISON selector ON
jettison transfer valves open
jettison Pumps operate

FUEL JETTISON NOZZLE switches ON
nozzle valves open

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25
How is fuel calculated during dump (fuel)
Durning Dump FMC discontinues calculations Totalizer valve is used After Dump Calculated value will reset using totalizer value
26
Totalizer vs Calculated Fuel (Fuel)
Totalizer: Measurement of each tank Calculated: Measurement of START fuel - FUEL USED
27
Nitrogen Generator System NGS (fuel)
Converts bleed air to nitrogen enriched air to prevent a dry center fuel tank from having explosive gasses *No flight crew action*
28
Suction Fuel Feed (fuel)
Each engine can get fuel from its corresponding Main Tank GND: Ok Climb: dissolved air in the tank could cause a flame-out Cruise: may be able to (after dissolved air depletes)
29
How many Hydraulic Systems (HYD)
3 systems 1. Left 2. Center 3. Right
30
What does hydraulics power (HYD)
1. Flight Controls 2. Flaps/Slats 3. Gear 4. Brakes 5. Nose Wheel Steering 6. Tail Skid 7. Autopilot Servos 8. Yaw Damper
31
Left Hydraulic System (HYD) Powers Source
Powers 1. Flight Controls 2. Right Yaw Damper 3. Stab Trim module 4. Trapped fluid used by PES Source 1. Engine-Driven Primary Pump 2. Electrical-Driven Primary Pump
32
Right Hydraulic System (HYD) Powers Source
Powers 1. Flight Controls 2. Normal Brakes 3. Pitch Enhancement System (PES) Source 1. Engine-Driven Primary Pumps 2. Electrical-Drive Primary Pumps
33
Center Hydraulic System (HYD) Powers
1. Flight Controls 2. Flaps/Slats 3. Gear 4. Alternate Brakes 5. Nose Wheel Steering 6. Tail Skid 7. Left Yaw Damper 8. HDG - Hydraulic Driven Generator 9. Stab Trim module 10. Reserve fluid used by C1 for reserve brakes and steering.
34
Center Hydraulic System (HYD) Source
Reservoir 1. 2 Electrical-Driven Primary Pumps 2. Air-Driven Demand Pump 3. RAT (for flight controls)
35
Center System Hydraulic Leak, What Remains (HYD)
Reservoir maintains reserve fluid for 1. Brakes 2. Steering ***Reserve Brakes and Steering isolation*** Center #1 electric-driven primary pump is auto isolated if low qty
36
HDG (HYD)
Hydraulic Driven Generator - Provides AC Power HDG is automatically powered by “C” Hyd System when both Main AC busses are lost
37
RAT (HYD)
Ram Air Turbine - Provides HYD Power RAT provides hyd power to flight controls portion of the Center Hyd System Adequate HYD power at speed above 130 kts In flight, auto deploys when both engines fail Manually deploys by pressing button
38
Hydraulic Fluid Symbols (HYD) RF OF QTY
``` RF = Re-Fill OF = Over Filled QTY = Quantity is Low ```
39
Speed Brake Lever (flt cont) Positions and Ops
Down: All spoilers retract ARMED: After landing, lever moves up and spoiler panels extend UP: Spoiler panels expanded max (flight or ground) On the ground: Trust Lever advanced to T/O position - Lever moves DOWN Either Thrust Reverser raised to reverse idle - Lever moves UP ***lever does not need to be armed***
40
SPEED BRAKE light (flt cont)
If the speed brakes are extended and, 1. RA is 800' or below 2. Flaps in the landing position
41
Flap Lever (flt cont) Position and Ops
UP: Slats and Flaps are retracted 1: Slats - Extend (midrange) Flaps - Retracted 5, 15, 20: Slats - Extended (remain midrange) Flaps - Commanded Position 25, 30: Slats - Fully Extended Flaps- Commanded Position
42
T/O and Landing Flaps setting (flt cont)
T/O: 5, 15, 20 Landing: 25, 30 ***Flaps 1 = Slats Extend***
43
Flaps gate (flt cont)
1 - Prevents inadvertent retraction of the Slats 20- Prevents inadvertent retractions of the flaps past Go-Around position
44
Primary and Secondary Flight Controls (flt cont)
Primary: 1. Elevator 2. Ailerons 3. Rudder Secondary: 1. Horizontal Stab 2. Spoilers 3. Slats 4. Flaps
45
Flight Controls Powered by (flt cont)
Elevator - HYD L/C/R Rudder - HYD L/C/R Spoilers - HYD L/C/R Ailerons - HYD L/R Stab - HYD L/C (it is a mixed combination) Flaps/Slats - HYD C (Alternate is through electric motors)
46
Flight Controls for Pitch (flt cont)
2 Elevators | Horizontal Stab
47
Flight Controls for Roll (flt cont)
4 Ailerons | 12 Spoilers
48
Flight Controls for Yaw (flt cont)
Single Rudder
49
Stab Trim Control source (flt cont)
1. Electric (yoke) 2. Alternate (pedestal) 3. Automatic (autopilot)
50
Pitch backup (flt cont)
Pitch Enhancement System - PES Hydraulic motor in the RIGHT system drives a pump that uses fluid from the LEFT trim system to operate the Stab * **Auto activation if both L/C Hyd System lost in flight*** * **Only electric trim is available***
51
Control Jam (flt cont)
Pitch: Significant force fwd/aft causes columns to OVRD STAB Roll: Significant force L/R causes columns to OVRD
52
Flaps Load Relief (flt cont)
Flaps 25 or 30 speed exceeded, flaps automatically revert to 20 ***as you slow down, they re-extend***
53
Alternate Flaps (flt cont)
Manually operates through electric motors * **max flaps 20 (due to FDX Ops because no asym protection)*** * ** No Flaps asymmetry protection / time increases***
54
Degrees of Steering (gear)
Tiller: 65° Pedals: 7° ***Tiller overrides pedals***
55
Air / Ground Sensing (gear)
Tilt sensor on Main Gear | Strut compression sensor on Nose Gear
56
How is the gear held up (gear)
Main: Door structure Nose: Up locks
57
Power source for gear retraction (gear)
Center HYD System
58
Power source for gear extension (gear)
Primary: Center HYD System Alternate: Electric motor trim locking mechanism Free-fall to the down and locked position
59
Power source for Nose Wheel Steering (gear)
Primary: Center HYD System Alternate: Reserve Brakes and Steering System Provides hyd fluid to the Center #1 electric primary hyd pump, this pump pressure is exclusive to the alternate Brakes and NWS system
60
Brake System Components (gear)
1. Normal Brakes - HYD System “R” 2. Alternate Brake - HYD System “C” (automatic if “R” system lost / if fluid lost to “C” system, trapped fluid and #1 elec pump provides Reserve Brakes and Sterling) 3. Brake Accumulator 4. Anti-Skid Protection 5. Auto Brake System 6. Parking Brake
61
Power Source for Brakes (gear)
1. Normal Brakes: Right HYD System 2. Alternate Brakes: Automatic - Center HYD System (automatic) 3. Reserve Brakes and Steering: Push switch - Provides HYD fluid to center #1 Electric Primary HYD Pump 4. Brake Accumulator: If Normal and Alt brakes lost, Accumulators provide several brake applications or parking brake
62
Power source for Anti-Skid Protection (gear)
1. Normal Brakes HYD System | 2. Alternate Brakes HYD System
63
Power source for Auto Brakes System (gear)
1. Normal Brake HYD System - ONLY
64
Auto Brakes RTO (gear)
Max Brake pressure if, 1. ACFT is on the ground 2. Ground speed is above 85 knots 3. Both Thrust Levers are retarded to idle
65
Auto Brakes on Landing (gear)
1. Both Thrust Levers idle 2. The wheels have spun up * 5 levels of deceleration - rotary selector * On dry RWY, manual brakes are stronger * Provides braking to full stop or disarmed
66
Auto Brakes Disarm (gear)
1. Pedal brakes applied 2. Either Thrust Reverser advanced after landing 3. Speed Brake Lever move from full UP position 4. DISARM or OFF selected on Auto Brake selector 5. Auto Brake fault 6. Normal anti-skid fault
67
Power source Parking Brake (gear)
1. Normal Brakes HYD System 2. Alternate Brake HYD System 3. Brake Accumulators - Right HYD System (brake press indicator left side)
68
Power source Tail Skid (gear)
Uses Main Landing Gear Actuation System
70
LDS
Large Display System 15” LCD's
71
IRS
Inertial Reference System
72
ISSP
Instrument Source Select Panel
73
MCP
Mode Control Panel
74
PFD/ND
Primary Flight Display Nav Display
75
ISFD
Integrated Standby Flight Display
76
SEI
Standby Engine Indictor
77
EICAS
Engine Indication and Crew Alert System
78
TMSP
Thrust Mode Select Panel
79
ASA
Autoland Status Annunciator
80
MCDU
Multi-Function Control Display Unit
81
EFIS-DCP
Electronic Flight Instrument - Display Control Panel
82
ACP
Audio Control Panel

FedEx (20 decks)

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