Power plant

Question 1

Aircraft fitted with:

Answer 1

– two Pratt &Whitney, PW 127 F (72-212A), E (42-500) or M (42-500/72-212A)
– two, six blades propellers (Hamilton)

Question 2

LOW PRESSURE and HIGH PRESSURE COMPRESSORS are the … type

Answer 2

Centrifugal

Question 3

LOW PRESSURE and HIGH PRESSURE TURBINES are the … type

Answer 3

Axial

Question 4

REDUCTION GEAR BOX

These equipments are fitted on the RGB:

Answer 4

– the ACW generator
– the Propeller Valve Module (PVM)
– the propeller pump (HP) and overspeed
governor
– the auxiliary feathering pump
– the propeller brake (on RH engine only)

Question 5

ACCESSORY GEAR BOX driven by the HP spool, drives the:

Answer 5

– the DC starter/generator
– the HP fuel pump
–the engine oil pumps

Question 6

The COMBUSTION CHAMBER is the … type

Answer 6

ANNULAR

Question 7

RTO (Reserve Take Off) (maximum power), used in case of an engine flame out during take off (up trim) or in case of go-around (ramp)

Answer 7

• ATR 72-500: 2750 SHP

- ATR 42-500: 2400 SHP

Question 8

MCT (Maximum continuous)

Answer 8

• ATR 72-500: 2500 SHP

- ATR 42-500: 2400 SHP

Question 9

TO (Take Off 0,9 RTO)

Answer 9

• ATR 72-500: 2475 SHP

- ATR 42-500: 2160 SHP

Question 10

Climb

Answer 10

• ATR 72-500: 2192 SHP

- ATR 42-500: 2160 SHP

Question 11

Cruise

Answer 11

• ATR 72-500: 2132 SHP

- ATR 42-500: 2132 SHP

Question 12

Power (PWR) =

Answer 12

Torque (TQ) x NP

Question 13

Power setting is characterized by constant …

Answer 13

Power lever (PL) and condition lever (CL) positions.

Question 14

The EEC (Engine Electronic Control) controls the …

Answer 14

Fuel flow to the engine, with input coming from the PWR MGT and the position of the PL.

Question 15

PL’s to the WALL, TQ up to …

Answer 15

115%

Question 16

PL’s to the RAMP, TQ up to …

Answer 16

100%

Question 17

The PEC (Propeller Engine Control) controls the … using input from …

Answer 17

NP (propeller speed) by changing the blades angle / the PWR MGT and the position of the CL

Question 18

CL on 100% OVRD the NP is at …

Answer 18

100%, regardless of the PWR MGT position

Question 19

With the CL’s in the AUTO position …

Answer 19

• Blade angle governing mode. The NP is regulated by the PEC (Blade angle change).
• PWR MGT in:
  TO → NP = 100%
  MCT → NP = 100%
  CLB → NP = 82%
  CRZ → NP = 82%

Question 20

On FTR (Feather position) the fuel governing mode is …

Answer 20

cancelled (No ACW generator)

Question 21

TQ values:

• RTO
• TO
• MCT

Answer 21

• TQ = 100% (ATR 72-500) / TQ = 100% (ATR 42-500)
• TQ = 90% (ATR 72-500) / TQ = 90% (ATR 42-500)
• TQ = 90.9% (ATR 72-500) / TQ = 100% (ATR 42-500)

Question 22

TORQUE ind. white bug is …

Answer 22

manually selected

Question 23

TORQUE ind. INTERNAL BUG …

Answer 23

computed by FDAU; shows RTO MGT on T/O, otherwise max TQ depending on PWR MGT selection

Question 24

TORQUE ind. (DC EMER)

Answer 24

2 probes located on the reduction gear box shafts
sends signal to the AFU (Auto Feathering Unit) and to
the EEC (Engine Electronic Control) which supply the
torque indicator.
The AFU controls the pointer and the EEC controls the
digital display.

Question 25

NP ind.

Answer 25

DC ESS from 0 to 120%

Question 26

ITT ind.

Answer 26

``` (DC ESS) from 0 to 1200°C Red point: 20’’ max Red point + S: 5’’max on start H: limite for hotel mode operation ```

Question 27

ITT ind. ALERT

Answer 27

ALERT When ITT > 800°C or 715°C in hotel mode Lt CAP

Question 28

ITT ind. TEST

Answer 28

TEST | 1150°C (blue dot)

Question 29

NH /NL ind (DC ESS) NH actual display from

Answer 29

0 to 120%

Question 30

NH /NL ind - TEST

Answer 30

TEST | 115 % (blue dot)

Question 31

OIL LOW PRESS Lt

Answer 31

40 PSI

Question 32

OIL TEMP (Main DC BUS) from

Answer 32

0 to 130°C

Question 33

CRANK means ...

Answer 33

dry motoring (no ignition)

Question 34

STARTER - ON

Answer 34

Starter engaged. At 45% NH, light goes off and the starter is disconnected

Question 35

STARTER - FAULT

Answer 35

``` Illuminates when: – remains ON with NH >45% or – GCU failure during start or – starter failure or – ENG 2 only: ENG START selector on start position + PROP BRK ON + GUST lock not engaged ```

Question 36

MAN IGN ON

Answer 36

``` Continuous ignition (both A and B exciters). Memo panel light. ```

Question 37

PROP BREAK READY

Answer 37

engagement or disengagement conditions are met: – A/C on ground – gust lock engaged – CL on FTR or FUEL S/O – blue hyd press available on the prop brake input >2100psi – Fire handle not pulled

Question 38

PROP BRAKE UNLOCK

Answer 38

``` PROP BRAKE not fully locked or not fully released. After 15 sec: CAP alarm. Also used to check lock/unlock time: – 5 sec. to unlock – 10 sec. to lock ```

Question 39

START A OR B

Answer 39

- On ground, only exciter A or B is supllied (except for the position A and B) - In flight regardless of start selection (A, B or A+B) both exciters are energized

Question 40

ATPCS

Answer 40

– ARM on ground = uptrim + auto FTR (2.15’’ delay) | – ARM in flight (In case of go around) = auto FTR only

Question 41

LO PITCH

Answer 41

blade angle

Question 42

UP TRIM

Answer 42

signal sent to respective eng during ATPCS sequence. | Eng power = RTO

Question 43

ATPCS TRIGGER

Answer 43

- one TQ below 18% | Cancel: PWR MGT out of TO or ATPCS pb OFF or at least one PL retarded below 49° or both TQ

Question 44

EEC FAULT flashing

Answer 44

EEC failure. The fuel flow is frozen to maintain the power - FAULT steady: EEC failure, HMU base law = reversion - FAULT flashing, never deselect the EEC. Retard first, the PL in the green sector (FAULT become steady: PL

Question 45

PEC SGL CH illuminates when ...

Answer 45

one channel is lost (2’’ for self test when advancing CL from FTR to AUTO)

Question 46

PEC FAULT illuminates when ...

Answer 46

both PEC channels are lost. CAP

Question 47

PEC OFF

Answer 47

PEC is deactivated and NP is limited at 102,5% if power is sufficient

Question 48

IDLE GATE FAIL light illuminates amber and the CCAS | is activated when the gate

Answer 48

does not engage automatically in flight or does not retract at landing