1
Q
Can the engines be manually started?
A
- No, only automatically.
2
Q
What parameters are monitored by the EEC during Autostart?
A
- EGT
- N2 RPM
- Oil pressure
- Other parameters
3
Q
How many attempts does the Autostart system make for the GE engines?
A
- 3 attempts on the ground
- No start attempts limit in flight
4
Q
What conditions will AUTO START correct for during ground start?
A
- Compressor stall
- High residual EGT
- Hot start
- Hung start
- Loss of one starter
- No EGT rise
- Start time exceed the starter duty cycle
5
Q
For what conditions will Autostart NOT attempt a second start?
A
- Loss of both starters
- No N1
- No Oil pressure rise
6
Q
What happens when the fuel control switch is moved to RUN?
A
- Opens the spar fuel valve
- Arms the engine fuel valve (EEC opens the valve when required)
- Arms the selected igniters (EEC turns the igniters on when required)
7
Q
What happens when the fuel control switch is moved to CUTOFF?
A
- Closes fuel valve
- Removes igniter power
- Unlocks the Engine Fire switch
8
Q
What two modes does the EEC provide?
A
- Normal
- Alternate
9
Q
How many Alternate modes are there?
A
- 2 Alternate modes: Soft and Hard
10
Q
What is the difference between Soft and Hard EEC alternates?
A
- Soft: When the EEC Automatically switch to alternate mode, thrust does not change and the EEC mode switch remains in NORM.
- Hard: When ALTN mode is manually selected on an EEC mode switch, that engine is switched to the hard alternate mode. Thrust may change.
11
Q
What types of protections do the EECs provide?
A
- Overspeed Protection
- Thrust Ramping
- Thrust Control Malfunction Accommodation
- Thrust Asymmetry Protection (TAP)
- Transient Bleed System
- Ice crystal anti-ice (ICA)
12
Q
What is Overspeed Protection?
A
- EEC Monitors N2 rotor speed and commands reduced fuel flow if approaching redline limit
- Displays EICAS advisory message ENG RPM LIMITED (L or R) is displayed when RPM limiting is in effect
- If the redline limit is exceeded the EICAS caution message ENG LIMIT EXCEED (L or R) is displayed
- Overspeed protection is provided on the N2 shaft (N1 is indirectly protected by the N2 protection)
- If RPM limiting fails and an overspeed condition persists, the EEC commands fuel shut off to shut down the engine. The EICAS caution message ENG FAIL (L, R) is displayed with an aural beeper once the engine falls below idle speed.
- If the EECs are in alternate mode, advancing the thrust levers full foward provides some over-boost protection and should be considered only during emergencies situations when all other available actions have been taken, and terrain contact is immient.
13
Q
What is Thrust Ramping?
A
- During takeoff, the EEC compesantes fo high stress loads on engine fan blades to crosswinds and low groundspeed by slowly increasing thrust until takeoff thrust is achieved, a process known as thrust ramping.
- Delayed engine responde due to thust ramping may be noticed by flight crews during conditions of high altitude and high ambient temperature that necessitate maximum thrust settings.
- Thrust rampoing is only active on the ground with the EECs in normal mode.
- Due to thrust ramping, maximum takeoff thrust may not be available until reaching 65 KIAS.
14
Q
What is Thrust Control Malfunction Accommodation?
A
- An EEC function that provides protection against idle thrust assymmetry conditions while on the ground.
- The EEC commands shutdown of the affected engine when the airplane is on the gound and thrust levers are at idle, and engine is above idle speed and not decelerating normally.
- The EICAS caution message ENG FAIL (L, R) is displayed with an aural beeper once the engine fails below idle speed
15
Q
What is Thrust Asymmetry Protection (TAP)?
A
- TAP is an automatic feeature that provides protection against asymetric thrust during takeoff or go-around by limiting thrust on the higher thrust engine.
- TAP enhances safety by allowing a decrease in approach speed at light gross weights and providing engine-out control capability for speeds above stick shaker and allowing full rated thrust to be available for all-engine operation at all weights and airspeeds.
- For an engine-out condition, TAP reduces thrust on the operatin engine to ensure there is sufficient rudder for directional control
- TAP reduces thrust when the airpseed decreases below approximately V2 on a takeoff or below approximately VREF on a go-around.
- Once speed is increased above V2/VREF, TAP increases thrust.
- The TAP function does not affect thrust for engine out operations flown at or above V2/VREF, with the exception of a light weight go-around at weights less than 152,273 KG where TAP reduces thrust slightly at VREF on the go-around.
- TAP does not affect certified takeoff performance
- For airspeeds where TAP does limit thrust, climb gradient is higher with TAP limiting thrust than it would be if TAP did not limit thrust.
- This occurs because additiona thrust asymmetry creats more airplane drag than the thrust that was addded. Therefore, if TAP becomes active due to a speed reduction below V2, any reduction in climb gradient fomr that scheduled takeof is due to misnanaged speed and not due to TAP.
- TAP is only available when the flight controls are operating in normal mode and the EEC is in normal or alternate modes.
16
Q
What is the purpose of the Transient Bleed System?
A
- The purpose of the transient bleed system is to unload the compressor during engine acceleration for increased engine stall margin.
- The system is composed of one fuel operate transient bleed valve (TBV) per engine controlled by the EEC and based on N2 rotor speed.
- The EEC commands the TBV to open during an above idle acceleration
- If the valve fails to open, the ENG TBV CLOSED (L, R) status message is set.
- If the TBV remains open when commanded to close by the EEC, the EICAS advisory message ENG TBV OPEN (L, R) is displayed when the airplane is on the ground and below 80 KCAS. Additionally, the ENG TBV OPEN (L, R) status message is set.
- To protect the stuctural integrity of the reversers from hot gases, the associated Thrust reverser is inhibited if the TBV fails open prior to thrust reverser deployment or is limited to idle if the failure occurs while the trhust reverser is deployed. In either case, the EICAS advisory ENG REV LIMITED (L, R) is displayed.
- Failure of the TBV in the open position may lead to an EGT redline exceedence and associated flight deck alerts.
17
Q
When do the EECs set Approach Idle in flight?
A
- When Flaps are commanded to 25 or greater, or
- When Landing Gear is selected down
18
Q
When the thrust protection is lost?
A
In EEC ALTN mode.
19
Q
What happens to the engine idle setting when engine anti-ice is turned on?
A
- It switches to Icing idle.
20
Q
What is ICA and when does it occur?
A
- Ice Crystal Anti-Ice (ICA) is an automatic feature that provides engine protection against ice crystal icing (ICI)
- The ICA Activates above 30,000 feet and terminates below 28,500 feet.
- The ICA activates for 30 minutes and may continue in additional 15 minutes increments, for as long as ICI conditions are encountered.
- Engine parameters N1, N2, and EGT may fluctuate independently without any flight crew inputs.
- When ICA is active ICA is shown on either one of both N1 engine display.
- Each engine’s ICA indication may appear, independently or not at all.
- An ICA indication does not mean that the engine is currently encounreing ICI conditions.
- After engine maintenance activities, the ICA indication can show in cruise flight, in any weather conditions, for 75 minutes.
21
Q
How long is the ‘RUNNING’ indication displayed?
A
- 30 sec. after the engine reaches idle.
22
Q
What condition creates the AUTORELIGHT starting mode?
A
- Any time the engine is at idle or bleow idle with fuel control switch in run.
- It provides protection against an engine rollback or flame out by turning both ignitors ON.
23
Q
During an in-flight engine start, with speed below that for a windmilling start, describe the indication that is displayed if starter assist is required
A
- A magenta X-START is displayed under the N2.
24
Q
What alert is displayed if actual thrust is less than commanded thrust during takeoff?
A
- ENG FAIL is displayed RED on the PFD and GREEN on the HUD.
- It is available between 65 kts and 6 kts prior to V1.
25
If the engine **overspeed protection** fails, what do the EECs command?
- They command the fuel shut off to shut down the engine.
26
If Thrust Ramping is fitted, it will occur due to what environmental factor?
- It occurs t compensate for high stress loads on the fan blades due to crosswinds and low ground speed. Usually during high ambient temperature and high altitude.
27
If the EECs are compensating for Thrust Ramping, if fitted, maximum takeoff thrust may not be set until as late as what airspeed?
- 65 kts
28
What protecting does **Thrust Control Malfunction Accommodation** provide?
It commands an engine shutdown on the affected engine when the Thrust levers are at IDLE, and the Thrust is above idle and not decelerating normally.
29
What system provides **Thrust control malfunction accomodation**?
- EEC.
30
Is **Thrust Asymmetry Protection (TAP)** available in both EEC modes?
Yes, it operates in both Normal and Alternate modes.
31
What indication is displayed on the **EICAS** when TAP is in effect? What if the system fails, what indication will it show?
- If TAP is in effect an yellow line on the inside part of N1 functioning as a limit. (FCOM 7.20.7)
If inoperative:
- An EICAS advisory **THRUST ASYM PROT** is displayed.
32
What does amber **REV** indicate?
The reversers are unlocked.
33
What does green **REV** indicate?
The reversers are deployed.
34
Where and how is the thrust reference displayed?
It is digitaly display in green above the N1.
35
What powers the **Thrust Reversers**?
The L and R Hydraulic system.
36
Why are the thrust levers moved to a mid position before selecting Alternate Mode on the EEC? What indication is there on EICAS?
- This prevent exceeding the thrust limits when switching to ALTN mode.
- When in alternate mode the EICAS displays **ENG EEC MODE L,R**
37
How can an EGT exceedance be recalled?
- By pushing the cancel/recall button
38
Are both batteries required for APU start? If so, what does the Main battery power?
Yes, the main battery powers the DC fuel pump, the fuel shut off valve, the fire detection, and the CCS.
39
What does the APU battery powers?
- APU controler, the air inlet dorr and the R APU starter.
40
When starting the APU from an unpowered airplane, what must the APU controller wait for before proceeding with the APU start?
The CCS start up (CCR L).
41
When starting the APU, why does it have to wait for the Left CCR? How long?
- The CCS provides fire detection and fuel managment.
- Until the CDU page is available on the lower display, approximately 2 mins. (CCR L)
42
If and APU start fails, what EICAS message will be displayed?
- APU SHUTDOWN
43
if AC power is not availble for APU start what is the source for the APU fuel?
- The DC fuel pump.
44
Once AC power is available, which pump supplies fuel pressure to the APU?
The AFT L fuel pump is commanded ON regardless of the pump switch.
45
What is the ceiling for operation of the APU? What is the altitude that the APU is designed to start with no fuel pumps operating?
- There is no ceeling limit to operate the APU.
- It can be started in flight with no fuel pumps up to 14,000 ft.
46
How many start attempts are the APU battery designed for?
- APU start is designed to support 2 consecutive attempts.
- if the APU fails to start after the second attempt, a 5 minute cooling period must be observed.
47
In the **Attended mode**, what faults will cause automatic shutdown of the APU?
- APU fire or overtemperature
- APU inlet failed to open
- Speed droop
- APU start failure
- Overspeed or loss of overspeed protection
- APU controller failure
48
What faults cause the APU to shutdown in the Unattended Mode?
- APU Controller failure
- - APU inlet door failed closed
- - APU starter failure
- APU FIRE / overtemperature
- High EGT / loss of EGT information
- Overspeed or loss of Overspeed protection
- High Oil Temperature
- Low Oil pressure
- APU starte/generator oil filter approaching bypass
- Speed Droop
49
Is there a cool-down period for automatic APU shutdowns?
- There is no coll-down period.
50
In flight with an APU fire, will the APU fire bottle automatically discharge?
- Yes
51
What indication is given when the APU is running?
- The EICAS memo APU RUNNING
52
When does the APU cool-down timming begin?
- When the APU selector is rotated to OFF.
53
How long is the **cool-down period** for the APU?
2 min.
54
What happens at the end of the **cool-down period**?
An APU overspeed is simulated to test the overspeed and fuel shutoff protection.
55
For which faults will the APU continue to run while an EICAS caution message is displayed. What message is displayed on EICAS?
- High EGT
- High oil temperature
- Low oil pressure
## Footnote
FCOM SYS 7.30.3
56
In flight when will the APU start automatically? And how can we shut it down?
The APU automatically starts, regardless of APU selector position if:
- If **three or more engine generators** go offline
The APU can only be shutdown if:
- The start condition is no longer valid (The APU can be shut down by positioning the selector to ON, then OFF.
- If the start condition is still valid, the APU can only be shut down by pulling the APU fire switch.
57
How can the **APU** be shut down when the automatic start condition is no longer valid?
By positioning the selector to ON, then OFF
58
When can the **APU** only be shut down by pulling the APU fire switch?
When the automatic start condition is valid
59
What are the circumstances under which **Secondary Engine Instrument** information automatically displays? List them.
* Fuel switch moved to cutoff
* Engine start selector in the START position
* Engine Fire switch pulled
* Initial display power up
* Secondary Parameter is exceeded
* N2 below idle inflight
- **FUEL FLOW ENG L,R** displayed
RX Boeing 787 GACA Preparation
flashcards
Decks in class (17)
# Cards
-
Limitations18
-
Memory Items and Checklist Legend27
-
Systems - Airplane General, Emergency Equipaments, Doors, Windows23
-
System - Air Systems34
-
Systems - Anti-Ice, Rain14
-
Systems - Automatic Flight31
-
Systems - Communication6
-
Systems - Eletrical37
-
Systems - Engines, APU59
-
Systems - Fire Protection27
-
Systems - Flight Control58
-
Systems - Flight Instruments and Display64
-
Systems - Flight Management, Navigation14
-
Systems - Fuel22
-
Systems - Hydraulics8
-
Systems - Landing Gear10
-
Systems - Warning Systems20
