Hawaiian 787 > Engines > Flashcards

Engines Flashcards

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1
Q

What are the primary engine indications displayed full time on the EICAS display?

A
  • N1
  • EGT

EICAS stands for Engine Indication and Crew Alerting System.

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2
Q

What does the green display indicate in Thrust Reference Mode?

A

Selected FMS thrust reference mode

This includes various thrust settings for takeoff, climb, and cruise.

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3
Q

What is the meaning of TO in Thrust Reference Mode?

A

Maximum rated takeoff thrust

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4
Q

What does TO 1 represent in Thrust Reference Mode?

A

Derate one takeoff thrust

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5
Q

What does CLB represent in Thrust Reference Mode?

A

Maximum rated climb thrust

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6
Q

What is displayed in green for Assumed Temperature?

A

Selected assumed temperature (°C) for reduced thrust takeoff

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7
Q

What does the amber display for Thrust Reverser Indication mean?

A

Reverser in transit

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8
Q

What does a green display for Thrust Reverser Indication indicate?

A

Reverser fully deployed

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9
Q

What does the RUN position of the FUEL CONTROL switch do?

A

• opens the spar fuel valve
• arms the engine fuel valve
• arms the selected igniters

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10
Q

What happens when the FUEL CONTROL switch is in the CUTOFF position?

A

• closes the engine fuel valve
• removes igniter power
• unlocks the engine fire switch

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11
Q

What does the EEC do when the FUEL CONTROL switch is in RUN?

A

opens the engine fuel valve and turns the igniters on

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12
Q

What is the function of the spar fuel valve in the FUEL CONTROL switch?

A

opens when the switch is in RUN position

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13
Q

True or False: The FUEL CONTROL switch allows for unlocking the engine fire switch in the RUN position.

A

False

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14
Q

What does the FUEL CONTROL switch do when it is switched to START?

A

closes the engine fuel valve and the spar fuel valve if applicable

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15
Q

What does the NORM position of the Electronic Engine Control (EEC) Mode Switch select?

A

The normal engine control mode for engine control

The EEC sets thrust using N1 as the controlling parameter.

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16
Q

What happens when the Off position is selected on the EEC Mode Switch?

A

The alternate engine control mode for engine control is selected

Thrust is set using N1 RPM as the controlling parameter.

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17
Q

What does an illuminated amber light on the EEC Alternate (ALTN) indicate?

A

The alternate engine control mode is either automatically or manually selected.

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18
Q

What does the NORM position of the Electronic Engine Control (EEC) Mode Switch select?

A

The normal engine control mode for engine control

The EEC sets thrust using N1 as the controlling parameter.

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19
Q

What happens when the Off position is selected on the EEC Mode Switch?

A

The alternate engine control mode for engine control is selected

Thrust is set using N1 RPM as the controlling parameter.

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20
Q

What does an illuminated amber light on the EEC Alternate (ALTN) indicate?

A

The alternate engine control mode is either automatically or manually selected.

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21
Q

What type of engines power the airplane?

A

Two General Electric GEnx-1B74/75 engines

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22
Q

What is the rated takeoff thrust for each engine?

A

74,100 pounds

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23
Q

What type of engine is the GEnx-1B74/75?

A

Two rotor axial flow turbofan engine

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24
Q

What components are included in the N1 rotor?

A
  • Fan
  • Low pressure compressor section
  • Low pressure turbine section
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25
What components are included in the N2 rotor?
* High pressure compressor section * High pressure turbine section
26
Are the N1 and N2 rotors mechanically dependent or independent?
Mechanically independent
27
What drives the engine accessory gearbox?
The high speed N2 engine shaft
28
What system controls each engine?
EEC (Electronic Engine Control)
29
What inputs does the EEC monitor?
* Autothrottle * Flight crew inputs through the thrust levers
30
Where are engine indications displayed?
On the EICAS display
31
What happens to engine indications if engine data is not available?
The associated engine indication blanks
32
What type of display unit normally shows the EICAS?
Inboard MFD window of the left or right inboard display unit
33
What are the primary engine indications displayed on the EICAS?
N1 and EGT ## Footnote EICAS stands for Engine Indication and Crew Alerting System.
34
List the secondary engine indications.
* N2 * oil temperature * fuel flow * oil quantity * oil pressure * engine vibration ## Footnote Secondary engine indications are displayed below primary indications on EICAS.
35
When are secondary engine indications automatically displayed on EICAS?
* displays initially receive electrical power * FUEL CONTROL switch is moved to CUTOFF in flight * engine fire switch is pulled in flight * a secondary engine parameter is exceeded * engine N2 RPM is below idle in flight * start selector is in the START position * FUEL FLOW ENG L/R Advisory is shown ## Footnote These conditions trigger automatic display of secondary indications.
36
How can secondary engine parameters be cleared from EICAS?
By pushing the engine (ENG) display switch ## Footnote Secondary parameters cannot be cleared until the triggering condition is resolved.
37
What is displayed in white on the dial or vertical indication?
Normal operating range ## Footnote This indicates the acceptable limits for engine performance.
38
What color indicates caution ranges for oil temperature and oil pressure?
Amber ## Footnote If oil temperature reaches the caution range, indicators change to amber.
39
What happens when oil temperature returns to the normal operating range?
The indication changes color back to white ## Footnote This visual change signals that the system is back within safe limits.
40
What do the red lines indicate for N1, N2, EGT, oil pressure, and oil temperature?
Operating limits ## Footnote If one of these indications reaches the red line, the digital readout, dial, box, and pointer change color to red.
41
What happens to oil temperature and oil pressure indications when they return to the normal operating range?
Change color back to white ## Footnote The indications revert to white when back in the normal operating range.
42
What occurs if an N1, N2, or EGT red line is exceeded?
The red box color remains after returning to normal range ## Footnote The red box can be canceled to white or recalled to red by pushing the cancel/recall switch.
43
What color does the EGT indication change to when it reaches the maximum continuous limit?
Amber ## Footnote The maximum continuous limit does not apply during takeoff or go-around.
44
During takeoff or go-around, how long are EGT indications inhibited from changing to amber?
Five minutes ## Footnote The inhibit is extended to ten minutes for single-engine operation.
45
What is the maximum takeoff limit for EGT indicated by?
Red line ## Footnote If EGT reaches the maximum takeoff limit, the digital indication, box, pointer, and dial change color to red.
46
What does the oil quantity digital readout display when the oil quantity is low?
Black text on a white background with LO displayed ## Footnote This indicates low oil quantity clearly.
47
What does the vibration digital readout indicate for high engine vibration?
Changes to black text on a white background ## Footnote This visual cue alerts the crew to high engine vibration.
48
What is the primary function of the EEC?
To have full authority over engine operation ## Footnote It controls both forward and reverse thrust.
49
What are the two control modes of the EEC?
* Normal * Alternate ## Footnote Both modes use N1 RPM as the controlling parameter.
50
What parameter does the EEC use for control in both modes?
N1 RPM ## Footnote N1 RPM is essential for thrust control.
51
What types of sensor inputs does the EEC utilize?
* Static pressure inputs from the Air Data Reference System (ADRS) * Static ports located on the fan cowls ## Footnote The static ports are positioned at the 4 o'clock and 8 o'clock locations.
52
Where are the static ports located?
On the lower portion of the fan cowls, at the 4 o'clock and 8 o'clock positions ## Footnote These ports serve as an alternate source for static pressure inputs.
53
What supplies initial EEC power during engine start?
The airplane until a Permanent Magnet Alternator (PMA) provides sufficient power ## Footnote The airplane can also act as an alternate power source if the PMA is unavailable.
54
What is the role of the PMA in EEC operations?
To provide sufficient power for the EEC during engine operation ## Footnote The PMA becomes the primary power source after initial EEC power from the airplane.
55
How does the EEC set thrust in normal mode?
By controlling N1 based on thrust lever position ## Footnote Thrust can be commanded automatically with autothrottles or manually by the flight crew.
56
How can maximum rated thrust be achieved during any phase of flight?
By moving the thrust levers to the full forward positions ## Footnote This action allows access to maximum thrust.
57
What happens when the required signals are not available for normal EEC operation?
The EEC automatically uses the alternate mode ## Footnote This mode allows scheduling of N1 based on thrust lever position.
58
What are the two levels of control in the EEC alternate mode?
Soft and Hard ## Footnote These levels provide different methods of thrust control.
59
What indicates the EEC is in soft alternate mode?
EEC mode switch in NORM, thrust does not change at fixed thrust lever position ## Footnote The switch remains in NORM while the EEC operates in alternate mode.
60
What occurs in hard alternate mode?
Engine switched to hard alternate mode when ALTN is manually selected ## Footnote Reference and target N1 values are displayed on the NI indication.
61
What information is displayed during normal, soft alternate, and hard alternate modes?
Actual, command, reference/target, maximum, and red line N information ## Footnote This ensures pilots have all necessary thrust data.
62
How is automatic reversion or manual selection to alternate mode indicated?
EICAS advisory message ENG EEC MODE (L, R) and illumination of the EEC ALTN light ## Footnote This alerts the crew to mode changes.
63
What effect does selecting the alternate mode on both engines have?
Eliminates thrust lever stagger and asymmetric thrust ## Footnote Useful for maintaining balanced thrust settings.
64
What happens to autothrottles during the alternate mode?
They remain connected ## Footnote This applies in both soft and hard alternate modes.
65
What does the alternate mode N1 schedule provide?
Equal or greater thrust than the normal mode for the same thrust lever position ## Footnote Ensures performance is at least as good as normal operation.
66
What risk is associated with thrust protection in the alternate mode?
Thrust protection is not provided, leading to possible thrust overboost ## Footnote Maximum rated thrust can be reached at a thrust lever position less than full forward.
67
What caution message is displayed if thrust lever position commands an N1 greater than the maximum rated thrust?
ENG LIMIT PROT (L, R) ## Footnote This warns the crew of potential thrust overboost.
68
What protections are still available in the alternate control mode?
N1 and N2 red line protection ## Footnote These protections help prevent engine damage.
69
What does the EEC monitor to provide overspeed protection?
N2 rotor speed ## Footnote The EEC commands reduced fuel flow if the rotor speed approaches its redline limit.
70
What advisory message is displayed when RPM limiting is in effect?
ENG RPM LIMITED (L or R) ## Footnote This message indicates that the engine RPM is being limited due to overspeed protection.
71
What happens if the redline limit is exceeded?
EICAS caution message ENG LIMIT EXCEED (L or R) is displayed ## Footnote This indicates that the engine has exceeded its operational limits.
72
How does the EEC respond if RPM limiting fails and an overspeed condition persists?
Commands fuel shut off to shutdown the engine ## Footnote The EICAS caution message ENG FAIL (L or R) is displayed once the engine falls below idle speed.
73
What is the purpose of thrust ramping during takeoff?
To compensate for high stress loads on engine fan blades due to crosswinds and low groundspeed ## Footnote Thrust ramping involves slowly increasing thrust until takeoff thrust is achieved.
74
When is thrust ramping only active?
On the ground with the EEC in normal mode ## Footnote Delayed engine response due to thrust ramping may be noticed under certain conditions.
75
What might flight crews notice due to thrust ramping?
Delayed engine response ## Footnote This may occur during high altitude and high ambient temperature conditions when maximum takeoff thrust is needed.
76
At what speed may maximum takeoff thrust not be available due to thrust ramping?
Until reaching 65 KIAS ## Footnote KIAS stands for Knots Indicated Airspeed.
77
What does Thrust Control Malfunction Accommodation protect against?
Idle thrust asymmetry conditions while on the ground ## Footnote This function ensures engine shutdown under specific conditions to maintain safety.
78
What conditions must be met for the EEC to command shutdown of the affected engine?
• Airplane is on the ground • Thrust lever is at idle • Engine is above idle speed and not decelerating normally ## Footnote The EICAS caution message ENG FAIL (L or R) is displayed once the engine falls below idle speed.
79
What does TAP stand for?
Thrust Asymmetry Protection ## Footnote TAP is an automatic feature designed to enhance safety during flight operations.
80
What is the primary function of Thrust Asymmetry Protection?
Provides protection against asymmetric thrust during takeoff or go-around by limiting thrust on the higher thrust engine.
81
How does TAP enhance safety during light gross weights?
By allowing a decrease in approach speed.
82
What capability does TAP provide for engine-out conditions?
Engine-out control capability for speeds above stick shaker.
83
What does TAP allow for all-engine operation at all weights and airspeeds?
Full rated thrust.
84
When does TAP reduce thrust on the operating engine?
When airspeed decreases below approximately V2 on takeoff or VREF on a go-around.
85
What happens to thrust once speed is increased above V2/VREF?
TAP increases thrust.
86
Does TAP affect certified takeoff performance?
No, TAP does not affect certified takeoff performance.
87
What occurs to climb gradient when TAP limits thrust?
Climb gradient is higher with TAP limiting thrust than without it.
88
When is TAP available?
When flight controls are in normal mode and the EEC is in normal or alternate modes.
89
In the example of a right engine failure, what does TAP do to the left engine's thrust?
Reduces thrust on the left engine.
90
What happens to the maximum and commanded N1 ties when TAP reduces thrust?
They move down to the reduced TAP thrust value.
91
What do the reference/target N1 indication and thrust levers do during TAP operation?
They do not move.
92
What is the purpose of the transient bleed system?
To unload the compressor during engine acceleration for increased engine stall margin. ## Footnote The transient bleed system enhances engine performance during acceleration.
93
What components make up the transient bleed system?
One fuel operated transient bleed valve (TBV) per engine controlled by the EEC. ## Footnote The transient bleed valve is crucial for managing compressor unloading.
94
What is the transient bleed valve (TBV) controlled by?
The EEC based on N2 rotor speed. ## Footnote EEC stands for Engine Electronic Controller, which optimizes engine performance.
95
Fill in the blank: The transient bleed system is composed of one fuel operated _______ per engine.
[transient bleed valve (TBV)]
96
True or False: The transient bleed system is designed to increase engine stall margin during deceleration.
False ## Footnote The system's main function is during engine acceleration.
97
What system is used to start the engines?
The autostart system. ## Footnote This system is designed to automate engine start procedures.
98
What powers the starter motors during engine starts?
The airplane's electrical system. ## Footnote Power is drawn from either the APU or forward external power.
99
What is the normal power source for engine starters?
APU power. ## Footnote APU stands for Auxiliary Power Unit.
100
When is simultaneous engine start allowed?
When the APU is running and both APU starter/generators are operational.
101
What happens if both engines are commanded to start with an inadequate power configuration?
The second start command is ignored.
102
What does the EEC monitor during engine start?
The start and commands starter cutout when the engine reaches idle speed.
103
What indicates a failure of both starters on the respective engine?
STARTERS displays across the respective starter symbols on the electrical synoptic.
104
What is displayed on the EGT indication when the FUEL CONTROL switch is moved to CUTOFF?
A maximum start limit line (red).
105
What happens to the EGT indication when the EGT start limit is reached?
The EGT indication changes color to red.
106
What initiates the autostart sequence?
Rotating the START selector to START and moving the FUEL CONTROL switch to RUN.
107
How is the autostart sequence initiated for in-flight windmill starts?
By moving the FUEL CONTROL switch to RUN.
108
What does the EEC command the TBV to do during an above idle acceleration?
The EEC commands the TBV to open ## Footnote TBV stands for Thrust Bypass Valve
109
What status message is set if the TBV fails to open?
ENG TBV CLOSED (L or R) ## Footnote L or R indicates the left or right engine
110
What happens if the TBV remains open when commanded to close by the EEC?
EICAS advisory message ENG TBV OPEN (L or R) is displayed ## Footnote This occurs when the airplane is on the ground and below 80 KCAS
111
What is inhibited if the TBV fails open prior to thrust reverser deployment?
The associated thrust reverser is inhibited ## Footnote If it fails while deployed, it is limited to idle
112
What EICAS advisory message is displayed if the thrust reverser is limited due to TBV failure?
ENG REV LIMITED (L or R) ## Footnote This indicates a limitation on thrust reverser operation
113
What may failure of the TBV in the open position lead to?
EGT redline exceedance and associated flight deck alerts ## Footnote EGT stands for Exhaust Gas Temperature
114
What types of idle does the EEC automatically select?
Minimum idle, approach idle, icing idle ## Footnote Each type of idle has specific operational conditions
115
When is minimum idle selected?
For ground operation and most phases of flight ## Footnote Minimum idle is lower than approach idle
116
When is approach idle selected in flight?
When flaps are commanded to 25 or greater or landing gear is selected DOWN ## Footnote Approach idle decreases engine acceleration time for go-around
117
When does icing idle get selected?
When engine anti-ice is on ## Footnote Icing idle helps prevent ice accumulation on the engine
118
What does the Ice Crystal Anti-Ice (ICA) function provide?
Engine protection against ice crystal icing (ICI) ## Footnote ICA activates only above 30,000 feet
119
How long does the ICA function activate for?
At least 30 minutes, may continue in additional 15-minute increments ## Footnote It continues as long as ICI conditions are encountered
120
What happens to the ICA function when the airplane descends below 28,500 feet?
The ICA function terminates ## Footnote This is a safety measure to avoid unnecessary engine operation
121
What indication shows when ICA is active?
'ICA' shows on one or both N1 engine displays ## Footnote N1 refers to the speed of the first stage of the engine
122
What can happen to engine parameters N1, N2, and EGT while ICA is active?
They may fluctuate independently without any flight crew inputs ## Footnote This is considered normal behavior during ICA operation
123
Are the ice crystal icing functions of each engine independent?
Yes, each engine's ICA function is independent ## Footnote This means each engine can have different parameters and indications
124
What does the START selector do?
Applies electrical power to the starter motors to begin dry motoring the engine ## Footnote The START selector is crucial for initiating the engine starting process.
125
What happens when the FUEL CONTROL switch is moved to RUN?
Opens the spar fuel valve ## Footnote This is part of the engine start sequence.
126
Who controls the proper sequencing of fuel and ignition during engine start?
The autostart system ## Footnote The autostart system automates the engine starting process.
127
What does the EEC do during autostart?
Monitors EGT, N2 RPM, and other engine parameters until the engine reaches idle speed ## Footnote EEC stands for Engine Electronic Control.
128
What should be done if the ENG OIL PRESS (L or R) caution message is displayed after engine start?
Accomplish the ENG OIL PRESS checklist ## Footnote This indicates a potential issue with oil pressure.
129
What conditions can cause the autostart system to abort the start during ground starts?
• Loss of both starters • No N1 rotation • No oil pressure rise ## Footnote These conditions indicate a failure in the starting process.
130
What happens if the autostart sequence is aborted?
The starters are de-energized and the START selector returns to the NORM position ## Footnote An EICAS caution message ENG AUTOSTART (L or R) is displayed.
131
What conditions can the autostart system attempt to correct during ground starts?
• Compressor stall • Loss of one starter • High residual EGT • No EGT rise • Hot start • Start time exceeds the starter duty cycle timer • Hung start ## Footnote These conditions may indicate issues that can be resolved during the start.
132
What does the EEC do if it cannot correct for a hung start or compressor stall?
Cancels the autostart, shuts off fuel and ignition, and motors the engine to clear residual fuel ## Footnote This ensures that unburnt fuel does not remain in the engine.
133
What is the limit on start attempts per start sequence while on the ground?
3 start attempts ## Footnote This limit is set to prevent damage to the starters.
134
Does the EEC limit start attempts in the air?
No ## Footnote In-flight starts can exceed the attempt limit.
135
Under what conditions does the autostart system discontinue the start temporarily during in-flight starts?
If a preset EGT between the start and takeoff EGT is reached or a hung start is detected ## Footnote This protects the engine from potential damage during abnormal conditions.
136
True or False: The autostart system aborts the start if problems are detected during in-flight starts.
False ## Footnote The system takes corrective action but does not abort the start.
137
What is displayed on the EICAS display during an in-flight start?
In-flight start envelope information ## Footnote Indicates the airspeed range necessary for an in-flight start at the current flight level.
138
What happens if the current flight level is above the maximum start altitude?
Maximum start altitude and respective airspeed range are displayed ## Footnote This ensures pilots have the necessary information for engine starts.
139
When are secondary engine indications displayed in flight?
When an engine is not running with N2 RPM below idle or when the FUEL CONTROL switch is moved to CUTOFF ## Footnote Helps pilots monitor engine status effectively.
140
What does the starter assist indication (X-START) indicate?
Airspeed is below that recommended for a windmilling start ## Footnote Provides critical feedback for the pilot during the start process.
141
What is the role of autostart during in-flight starts?
Makes continuous start attempts until the engine starts or the pilot aborts the attempt ## Footnote Ensures a higher chance of successful engine ignition.
142
How does the EEC assist during a windmilling in-flight start?
Monitors engine parameters to provide the best fuel schedule for the shortest possible start time ## Footnote Helps optimize the engine start process.
143
What is a key characteristic of EGT during engine start?
EGT may fluctuate and rise rapidly ## Footnote This behavior is acceptable as the EEC controls the start.
144
What is the standard power source for engine ignition?
Aircraft supplied DC power ## Footnote Standby power serves as a backup.
145
What is the function of auto-relight in engines?
Provides protection for flameout and sub-idle stall recovery ## Footnote It automatically activates under certain conditions to attempt engine recovery.
146
When is the auto-relight function activated?
On the ground and in-flight whenever an engine is at or below idle with the FUEL CONTROL switch in RUN ## Footnote Ensures engine recovery attempts are made in critical situations.
147
What triggers the EEC to switch on both igniters during a flameout?
A rapid decrease in N2 or an engine rollback ## Footnote This action attempts to recover the engine to idle.
148
When are the igniters switched off during the auto-relight process?
When the engine again reaches idle ## Footnote This indicates successful recovery of engine operation.
149
What are the two types of igniters used for engine starts?
Two igniters per engine ## Footnote Dual igniters are always used for in-flight starts.
150
Fill in the blank: The FUEL CONTROL switch must be in _______ for auto-relight to function.
RUN
151
True or False: There is a manual continuous ignition selection available for the engines.
False ## Footnote The system does not include a manual continuous ignition function.
152
What happens when a sub-idle stall is detected?
Fuel is shut off for one second to attempt to clear the stall, then the fuel schedule is reduced to help return the engine to idle.
153
What occurs when the engine reaches idle after a sub-idle stall?
The fuel schedule returns to normal.
154
What protection does the EEC provide against flameout?
It energizes both igniters during periods of excessive rain/hail ingestion.
155
What is the first action taken by the EEC when a sub-idle stall is detected?
Fuel is shut off for one second.
156
What component allows fuel to flow from the main tank?
Spar valve ## Footnote This valve is crucial for directing fuel towards the engine.
157
What happens to fuel after it flows through the first stage engine fuel pump?
It passes through a fuel/oil heat exchanger for preheating ## Footnote This step is essential for optimizing fuel temperature before entering the engine.
158
What activates the engine fuel valve?
When the engine fire switch is IN and the FUEL CONTROL switch is in RUN ## Footnote Similar to the spar valve, this condition is necessary for engine operation.
159
What causes both the spar and engine fuel valves to close?
When the engine fire switch is OUT or the FUEL CONTROL switch is in CUTOFF and the START selector is in NORM ## Footnote This safety mechanism prevents fuel flow during shutdown.
160
How is fuel flow information displayed?
On the secondary engine display ## Footnote Additionally, this information is provided to the Flight Management System (FMS).
161
How does the oil system contribute to fuel system protection?
It provides automatic fuel heating for fuel system icing protection.
162
What happens if the oil filter becomes clogged?
An EICAS advisory message ENG OIL FILTER (L or R) is displayed and oil bypasses the filter.
163
How is the engine oil primarily cooled?
By a fuel/oil heat exchanger.
164
What secondary component assists in oil cooling under specific conditions?
A secondary air/oil heat exchanger.
165
Under what conditions does the secondary air/oil heat exchanger provide oil cooling?
Under conditions of low fuel flow or high fuel temperatures.
166
How does the oil system contribute to fuel system protection?
It provides automatic fuel heating for fuel system icing protection.
167
What happens if the oil filter becomes clogged?
An EICAS advisory message ENG OIL FILTER (L or R) is displayed and oil bypasses the filter.
168
How is the engine oil primarily cooled?
By a fuel/oil heat exchanger.
169
What secondary component assists in oil cooling under specific conditions?
A secondary air/oil heat exchanger.
170
Under what conditions does the secondary air/oil heat exchanger provide oil cooling?
Under conditions of low fuel flow or high fuel temperatures.
171
Is there a minimum oil quantity limit for the engine?
No minimum oil quantity limit ## Footnote There are no amber or red line limits indicated for oil quantity.
172
What happens when there is low oil quantity?
Automatic display of the secondary engine display with black numbers on a white background ## Footnote This indicates that the oil quantity is low without explicitly setting a limit.
173
Are there any operating limitations for engine oil quantity?
No operating limitations ## Footnote Therefore, flight crew procedures are not based on low oil quantity.
174
What condition must be met for the reverse thrust levers to be raised?
The forward thrust levers must be in the idle position.
175
What does the EEC do when the reverse thrust levers are raised?
The EEC opens the reverser isolation valve.
176
Under what condition does the EEC inhibit reverser isolation valve actuation?
Unless the airplane is on the ground with the engine running.
177
What is the purpose of the physical interlock located in the aisle stand?
To prevent movement of the reverse thrust lever beyond the reverse idle position.
178
What happens when the reverse thrust levers are pulled aft to the interlock position?
• The autothrottle disengages • The auto speedbrakes deploy ## Footnote This is part of the reverse thrust sequence in the 787 Flight Crew Operations Manual.
179
What does it mean when the REV indication changes to green?
The reverser is fully deployed ## Footnote This occurs after the reverse thrust levers are raised to the maximum reverse thrust position.
180
What does the EICAS advisory message ENG REV LIMITED (L or R) indicate?
The reverser cannot deploy when commanded, or can deploy only with reverse thrust limited to idle ## Footnote Not all conditions limiting or preventing reverse thrust can be detected before reverse thrust selection.
181
What does the EICAS advisory message ENG REVERSER (L or R) indicate?
A reverser system fault ## Footnote This message is displayed on the ground.
182
What does the EICAS caution message ENG REV AIR/GND indicate?
The air/ground logic that prevents in-flight thrust reverser deployment has failed ## Footnote This is a critical alert for safety during flight.
183
What does the EICAS caution message ENG REV COMMANDED (L or R) indicate?
The left or right reverse thrust lever is not in the down position in flight ## Footnote This alert is crucial for ensuring proper thrust management.
184
What does the engine monitor unit track?
Engine vibration levels ## Footnote The vibration indications are displayed on the secondary engine display.
185
What does the vibration source indication display?
N1, N2, or BB ## Footnote BB stands for broadband, which indicates that the vibration monitoring system cannot determine the specific source.
186
What is the primary purpose of the airborne vibration monitoring feature?
To track rotor imbalance ## Footnote It is also useful for isolating and determining corrective action for engine anomalies.
187
What happens when a vibration value of 4 units is reached?
Secondary engine parameters are displayed and the digital vibration readout is shown in reverse ## Footnote This means black digits on a white background.
188
Are there certified vibration limits in this system?
No ## Footnote There are no specific flight crew actions based solely on vibration indication.
189
How can high N1 vibration be felt?
Accompanied by tactile vibration ## Footnote High N2 vibration may not be felt.
190
What does the engine failure alert system indicate?
When actual engine performance is less than commanded engine performance ## Footnote This occurs during takeoff and other phases of flight.
191
What is displayed on PFDs during an engine failure alert?
A red ENG FAIL ## Footnote This is displayed if actual thrust is less than commanded thrust during takeoff with airspeed between 65 knots and 6 knots prior to V1.
192
What accompanies the PFD and HUD displays during an engine failure alert?
Voice annunciation 'Engine Fail' and Master WARNING lights illuminating ## Footnote This alerts the crew of the engine failure.
193
What does the EICAS caution message ENG FAIL indicate?
An engine unexpectedly decelerates to less than idle speed ## Footnote The message remains until the engine recovers or the fuel control switch is moved to CUTOFF.
194
What conditions trigger the EICAS caution message ENG THRUST?
Either: * Engine producing less than commanded thrust with no satisfactory increase * Engine producing more than commanded thrust with no satisfactory decrease * Current airspeed greater than 6 knots prior to V1 ## Footnote This message is displayed for both left and right engines.
195
What visual indicators accompany the EICAS caution message ENG THRUST?
Thrust command area filled amber, Master CAUTION light, and beeper aural ## Footnote These indicators provide additional alerts to the crew.
Hawaiian 787
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