Power plant

Question 1

Main components of the engine?

Answer 1

Question 2

What is the function of the FDGS?

Answer 2

Allows the Fan to rotate 3 times sloer than the LPC (n1) shaft

Question 3

Where is EEC located?

Answer 3

On each engine

Question 4

Where are REV indicated?

Answer 4

At N1 indicator

Question 5

How many fuel nozzles are in the combustion chamber?

Answer 5

16

Question 6

How many igniters in the fuel chamber?

Answer 6

2

Question 7

What is provided b the Main engine gearbox?

Answer 7

Accessories
- hydraulic engine driven pump
- oil lubrication and scavange pump
- IFPC (integrated fuel pump and control)
- permanent magnet alternator PMA
variable frequency generator VFG

Question 8

How many channels has each EEC?

Answer 8

2 channels - one has complete control, the other is a backup

Question 9

What powers the EEC?

Answer 9

PMAG. If PMAG is not available, then DC ESS BUS

Question 10

Meaning of EICAS

Answer 10

Engine indication and crew alerting system

Question 11

What part of the engine is the starter turbine attached to?

Answer 11

Main Gear Box

Question 12

What is the max speed for inflight engine e-start?

Answer 12

250 kt

Question 13

At what point during engine start the EEC turns off the Starter air Valve (SAV) and igniters?

Answer 13

51% N2

Question 14

How long the wait between ECU aborted start and the next try?

Answer 14

30 seconds and N2 below 20%

Question 15

The conditions that activate the continuous ignition system automatically
are as follows:

Answer 15

• A second start attempt is required by the automatic start,
• During takeoff and landing phase, based on the Flight Management
  System (FMS) information,
• Cowl Anti-Ice System (CAIS) is turned on by automatic mode or
  manual mode,
• With the L ENG or R ENG switch set to ON and airspeed greater
  than 60 kt, engine flameout is detected within 2 seconds by the
  FADEC engine flameout protection logic, or
• Surge is detected in-flight or during takeof

Question 16

Normally, the EEC alternates control channels after each subsequent
start. The EEC automatically commands both igniter plugs to fire for the
conditions that follow:

Answer 16

Cowl anti-ice is selected,
* An engine flameout is detected,
* An in-flight start is attempted, or
- During takeoff, or if an in-flight surge is detected.

The FADEC automatic relight system energizes both igniters within 2 seconds of an engine flameout detection when the respective L ENG or
R ENG switch is in the ON position and airspeed is greater than 60 kt.

Question 17

What is OCM

Answer 17

Oil Control Module.
The Oil Control Module (OCM) filters the oil, senses the oil pressure and temperature, monitors debris, and sends the oil to the engine bearings, Fan Drive Gear System (FDGS), Main Gearbox (MGB), Angle Gearbox (AGB), and to the heat exchangers

Question 18

How many liters does the oil tank hold?

Answer 18

24,4 l

Question 19

What is TLLS

Answer 19

Thrust limitation at low speed.

Thrust Limitation at Low Speed (TLLS) ensures that the nose landing gear is sufficiently loaded during the takeoff phase. The Full Authority
Digital Engine Control (FADEC) limits the thrust of the engines to approximately 60% of the takeoff power. As the aircraft accelerates in the takeoff run, thrust increases with airspeed and reaches full power at 80 kt.

The limits are indicated by a light gray sector on the N1 indications on the EICAS page. TLLS is disabled when the parking brake is set to allow
full power run-ups. Refer to Figure 18−09−5.

Question 20

When is FLEX takeoff prohibited?

Answer 20

On contaminated runways or whe Windchear on TS in vicinity or AT inop

Question 21

At waht point is Approach Idle selected by EEC?

Answer 21

When Flap 1 selected

Question 22

When is Steep approach mode activated by EEC?

Answer 22

Question 23

APR means?

Answer 23

Automatic Power Reserve

Question 24

When is APR activated?

Answer 24

Question 25

When does the EEC de-active APR mode?

Answer 25

Question 26

When is the N1 limit reached?

Answer 26