Engine

Question 1

What engines are on the Phenom 300?

Answer 1

Pratt and Whitney PW535E

3360 lbs of thrust

Question 2

How are the engines controlled?

Answer 2

By a dual channel Full Authority Digital Electronic Control, (FADEC) system.

Question 3

Each engine is controlled and monitored by _____ FADEC channels.

Answer 3

Two FADEC channels per engine.

Question 4

What supplies power to the FADEC?

Answer 4

A 28VDC airframe power is required to enable operation of the control system and
to start the engine.

Once the engine is running, the FADEC takes its primary power from either the engine driven PMA or the 28VDC airframe power, whichever provides more power.

The 28VDC airframe power bus is available for
back-up supply purposes.

Question 5

What are some of the functions of the FADEC? (7)

Answer 5

• During START, it accelerates the operating engine’s N2 to 72% to protect the gear box from damage.
• Ensures no LIMITS are exceeded on hot, hung or no start.
• Controls Automatic Thrust, (ATR).
• Provides WHSAIS envelope information to the AMS controller.
• Schedules FUEL FLOW during starting based on N2 speed and ambient conditions.
• Controls the IGNITERS.
• Calculates an N1 SPEED SETTING corresponding to the TLA (Thrust Lever Angle)

Question 6

During start, when are both igniters automatically energized?

Answer 6

One igniter for ground engine starting when TT0 is above 0°C.

Both igniters when TT0 is below 0°C.

Both igniters for in-flight engine starting.

Question 7

How many lbs of thrust?

Answer 7

3360 lbs. thrust

Question 8

During START, FADEC accelerates the operating engine’s N2 to ____ % to protect the gear box from damage.

Answer 8

72%

Question 9

How does the FADEC assist an In-Flight Start?

Answer 9

1. Automatically actuates both igniters during starting
2. Disables the abort starting logic.

(In this case, the decision on whether to abort an unsuccessful start is at the pilot’s discretion.)

Question 10

How does the FADEC assist for an Auto Relight?

Answer 10

Automatically turns on both igniters and schedules the relight fuel flow in case an engine flameout is detected.

(assuming the ENG START/STOP knob is out of the STOP position.)

Question 11

How is dry motoring performed?

Answer 11

1. ENG IGNITION switch to OFF

2. setting the ENG START/STOP knob to START

Question 12

What is the purpose of the Permanent Magnetic Alternator, (PMA)?

Answer 12

The PMA is the primary source of AC power to both channels of the FADEC when the engine is running above idle.

Below this speed, the primary source of AC power to the FADEC is the airframe 28VDC power, which is used during engine starting and as a backup source for
the PMA.

Question 13

What is the purpose of the ATR?

Answer 13

The ATR, controlled by the FADEC, automatically provides maximum engine thrust (TO RSV or GA RSV).

Question 14

What will happen if the START/STOP knob is moved to STOP and the TLA is not at idle?

Answer 14

The FADEC will disregard the STOP selection and not shut down the engine.

Question 15

Under normal operating conditions what color are the engine instruments pointers and digits?

Answer 15

Green

Question 16

What does an “E1/2 OIL IMP BYP” CAS message indicate?

Answer 16

There is an impending blockage of an oil filter.

Question 17

How does the FADEC assist an In-Flight Start?

Answer 17

1. Automatically actuates both igniters during starting
2. Disables the abort starting logic.

(In this case, the decision on whether to abort an unsuccessful start is at the pilot’s discretion.)

Question 18

How does the FADEC assist for an Auto Relight?

Answer 18

Automatically turns on both igniters and schedules the relight fuel flow in case an engine flameout is detected.

(assuming the ENG START/STOP knob is out of the STOP position.)

Question 19

How is dry motoring performed?

Answer 19

1. ENG IGNITION switch to OFF

2. setting the ENG START/STOP knob to START

Question 20

What is the purpose of the Permanent Magnetic Alternator, (PMA)?

Answer 20

The PMA is the primary source of AC power to both channels of the FADEC when the engine is running above idle.

Below this speed, the primary source of AC power to the FADEC is the airframe 28VDC power, which is used during engine starting and as a backup source for
the PMA.

Question 21

What is the purpose of the ATR? When is it activated? (3)

Answer 21

The ATR, controlled by the FADEC, automatically provides maximum engine thrust (TO RSV or GA RSV) whenever:

1. ATR armed
2. Thrust levers are at least at the TO/GA position

and one of following conditions occurs

A. ‣ Difference of N1 values is greater than 20% between both engines (one engine fails);
B. ‣ Loss of communication between both engines.

Question 22

When is ATR activated?

Answer 22

1. ATR armed
2. Thrust levers are at least at the TO/GA position

and one of following conditions occurs

‣ Difference of N1 values is greater than 20% between both engines (one engine fails);
‣ Loss of communication between both engines.

Question 23

Oil pressure range for normal operations ground, flight idle, to Max?

Answer 23

25-160

Question 24

Minimum oil temperature for starting and idle only?

Answer 24

-40C

Question 25

Minimum oil temperature for power above idle?

Answer 25

10C

Question 26

Maximum oil temperature?

Answer 26

132.2C

Question 27

Maximum transient oil temperature?

Answer 27

140.5C

Question 28

Whats inside the AGB? (5)

Answer 28

Starter Gen
Fuel Pump
Oil Pump
Hydraulic Pump 
The AGB itself is the oil tank.

Question 29

Must idle engines for ______ after touchdown.

Answer 29

Two minutes minimum.

Question 30

FADEC protects against

3

Answer 30

1. No light off, No ITT rise within 10 seconds
2. Hung Start, engine does not reach ground idle parameters in 60 seconds.
3. Hot Start, temp just before red line

Question 31

FADEC does not protect against:

2 big ones

Answer 31

No oil pressure.

No fan speed.

Question 32

Each ignition system has how many igniters?

Answer 32

two

Question 33

When are both igniters energized?

Answer 33

Start below 0C and engine failure in flight.