24 Electrical

Dornier 328 DORNIER LUFTFAHRT

TRAINING MANUAL

LINE /BASE MAINTENANCE

ATA CHAPTER 24 ELECTRICAL POWER 24-00 GENERAL

5

24-20 AC GENERATION

7

GENERAL ............................................. .................................................................... .............................................. .............................................. .............................................. .............................. ....... 7 FUNCTIONAL DESCRIPTION .............................................. ..................................................................... .............................................. ......................................... .................. 8 AC Alternator System ........................................... .................................................................. .............................................. .............................................. .................................. ........... 8 AC Inverter System ........................................... .................................................................. .............................................. ............................................... ...................................... .............. 8

24-21 AC ALTERNATOR SYSTEM

9

GENERAL ............................................. .................................................................... .............................................. .............................................. .............................................. .............................. ....... 9 INTERFACE TO OTHER SYSTEMS ............................................ ................................................................... .............................................. ................................ ......... 10 Indicating................................................ Indicating......................... .............................................. .............................................. .............................................. .............................................. ......................... 10 Emergency DC Power System .............................................. ..................................................................... .............................................. ....................................... ................ 10 AC External Power........................................ Power............................................................... .............................................. .............................................. ........................................ ................. 11 Control and Dimming (Chapter 33-LIGHTS)..................................................... 33-LIGHTS)............................................................................ ................................ ......... 11 FUNCTIONAL DESCRIPTION 12

Dornier 328 TRAINING MANUAL LINE /BASE MAINTENANCE

DORNIER LUFTFAHR

24-31 DC STARTER/ GENERATOR SYSTEM

26

GENERAL...................................................................................... GENERAL............................................................... .............................................. .............................................. ..................................26 ...........26 INTERFACE TO OTHER SYSTEMS....................................... SYSTEMS.............................................................. .............................................. ......................................27 ...............27 Indicating (Chapter 31 - INDICATING/RECORDING SYSTEMS)........................ SYSTEMS)............................................... ..........................27 ...27 Starting (Chapter 80 - STARTING SYSTEM)............................................................. SYSTEM).................................................................................... .......................27 27 Engine Fire Extinguishing (Chapter 26 - FIRE PROTECTION) ............................................. ........................................................28 ...........28 Landing Gear (Chapter 32 - LANDING GEAR).............................................................. GEAR).................................................................................28 ...................28 DC Electrical Load Distribution ............................................. .................................................................... .............................................. ......................................28 ...............28 Control and dimming (Chapter 33 - LIGHTS) .............................................. ..................................................................... ......................................28 ...............28 FUNCTIONAL DESCRIPTION ............................................ ................................................................... .............................................. ..........................................28 ...................28 General................................................................. General.......................................... .............................................. .............................................. .............................................. ..................................28 ...........28 Starter/Generator 1PC-1 (1PC-2)............................. (1PC-2).................................................... .............................................. .............................................. ..............................29 .......29 Generator Control Unit 2PC (12PC)................................... (12PC).......................................................... .............................................. ..........................................30 ...................30 Bus Power Control Unit (BPCU) 20PC .............................................. ..................................................................... .............................................. ..........................30 ...30 Hall Effect Sensors 3PC (13PC), 4PC-1 (4PC-2) .............................................. ..................................................................... ..................................30 ...........30 OPERATION............................................................... OPERATION........................................ .............................................. .............................................. .............................................. ..............................31 .......31 Power Supply ........................................... .................................................................. .............................................. .............................................. .............................................. .......................31 31 Starter/Generator 1PC-1 (1PC-2)............................. (1PC-2).................................................... .............................................. .............................................. ..............................31 .......31 Hall Effect Sensors 3PC (13PC), 4PC-1 (4PC-2) .............................................. ..................................................................... ..................................35 ...........35 DC Relay Box (1VE) ........................................... .................................................................. .............................................. .............................................. ..................................37 ...........37 SYSTEM INDICATIONS ............................................... ...................................................................... .............................................. .............................................. ..........................38 ...38

24-32 BATTERY SYSTEM

39

INTERFACE TO OTHER SYSTEMS....................................... SYSTEMS.............................................................. .............................................. ......................................40 ...............40 Indicating (Chapter 31 - INDICATING/RECORDING SYSTEMS)........................ SYSTEMS)............................................... ..........................40 ...40 Emergency DC Power System................................. .......40


24-41 AC EXTERNAL POWER

TRAINING MANUAL


48

GENERAL ............................................. .................................................................... .............................................. .............................................. .............................................. ............................ ..... 48 INTERFACE TO OTHER SYSTEMS ............................................ ................................................................... .............................................. ................................ ......... 49 Indicating................................................ Indicating......................... .............................................. .............................................. .............................................. .............................................. ......................... 49 AC Alternator System ........................................... .................................................................. .............................................. .............................................. ................................ ......... 49 Control and Dimming (Chapter 33 - LIGHTS)..................... LIGHTS) ............................................ .............................................. ....................................... ................ 49 FUNCTIONAL DESCRIPTION .............................................. ..................................................................... .............................................. ....................................... ................ 49 General ........................................... .................................................................. .............................................. .............................................. .............................................. ................................ ......... 49 Ground Power Protection Unit 6XD ............................................ ................................................................... .............................................. ................................ ......... 49 OPERATION ............................................. .................................................................... .............................................. .............................................. .............................................. ......................... 50 SYSTEM INDICATIONS ............................................ ................................................................... .............................................. .............................................. ............................ ..... 51

24-42 DC EXTERNAL POWER

52

GENERAL ............................................. .................................................................... .............................................. .............................................. .............................................. ............................ ..... 52 INTERFACE TO OTHER SYSTEMS ............................................ ................................................................... .............................................. ................................ ......... 53 Indicating................................................ Indicating......................... .............................................. .............................................. .............................................. .............................................. ......................... 53 DC Electrical Load Distribution System............................................................. System.................................................................................... ................................ ......... 53 Control and Dimming (Chapter 33 - LIGHTS)..................... LIGHTS) ............................................ .............................................. ....................................... ................ 53 FUNCTIONAL DESCRIPTION .............................................. ..................................................................... .............................................. ....................................... ................ 54 General ........................................... .................................................................. .............................................. .............................................. .............................................. ................................ ......... 54 Bus Power Control Unit 20PC .............................................. ..................................................................... .............................................. ....................................... ................ 54 OPERATION ............................................. .................................................................... .............................................. .............................................. .............................................. ......................... 55 SYSTEM INDICATIONS ............................................ ................................................................... .............................................. .............................................. ............................ ..... 56

24 50 AC ELECTR LOAD DISTRIBUTION

57


DORNIER LUFTFAHR

DC HYD SUB BUS.............................................................................................................................67 Bus TIE Relay 9PP ..............................................................................................................................67 DC Voltmeter 20PX, 21PX..................................................................................................................67 SYSTEM INDICATIONS .......................................................................................................................68

INDEX

69

LIST OF ILLUSTRATIONS

69


TRAINING MANUAL


24-00 GENERAL ELECTRIC

DC NON-ESS1

BUS 1

O F F

BUS 2

NON-ESS2

O F F

ESSENTIAL

AC BUS 1

BUS 2

FAIL

FAIL

OFF

OFF

ALT LH

TRU

ALT RH

V AVAIL

TIE

ON EXT 115V

TIE

26V

26V

115V

FAIL

FAIL

AVAIL

FAIL

FAIL

FAIL

FAIL

FAIL

OFF

OFF

ON

ON

OFF

OFF

OFF

OFF

GEN-LH

BAT 1

EXT

APU

BAT 2

GEN-RH

INV 1

INV 2

Fig. 1 Electric Panel

This chapter contains a description of the systems which supply and distribute voltage to the AC and DC

D o r n i e r

L T I N R E A / B I A N S I E N M G A 3 I N M T A 2 E 8 N N A U N C A E L

I P s a s u g e : e : 0 2 1 4 / 9 6 6 E T M / E T X DC TRU AC

T M -E l e c t r i c a l P o w e r

F O R T R A I N I N G P U R P O S E S O N L Y -

F i g . 2 E l e c t r i c B u s S y s t e m

NON/BUS

ESS-BUS

NON/BUS

TIE BUS I

GCU

ALT 3ø

GCU

LH

Hot 1

Hot 2

BATT 1

BATT 2

ALT 3ø RH

GCU

GEN I

GCU Ext.115V 3ø

BUS II

Ext.28V DC

GEN II

GCU

GCU APU

GCU

Option

3 2 8 -1 E 0 0 f f M e c t o i v d i .1 t y 0 :

D O R N I E R L U F T F A H R

3 2 E f f 8 -1 e c t 0 0 vi i M t y : o d .1 0



I s s u e : 0 1 / 9 6 P E a T g M e : / E 2 T 4 X -7

TIE

GEN1-BUS

F i g . 1PP 2PP 3 A NON-ESS-BUS 1 BUS I C G e n er a EXT-PWR ALT.1 ALT.2 t i o DC n AC B a TRU s i c C o n f i g ur a t i o n

1 XP

2 XP

BUS 1

BUS 2

AC/VARIABLE 115/200V~

G E N E R A L

GEN2-BUS

3PP

4PP

ESSENTIAL-BUS

BUS II

5PP NON-ESS-BUS 2

2 4 -2 0 A C G E N E R A T I O N

D O R N I E R L U F T F A H R T

DC/28V

INV I

INV II

3 XP 4 XP 115V 26V

6 XP 26V

AC/400 Hz 115/26V~

5 XP 115V

D o r n i e r



DORNIER LUFTFAHR

This section provides information on the AC Generation subsystem. The actual AC generation is provided by two AC alternators and two static AC inverters. The section is divided into the following sub-subsystems: - AC Alternator System - AC Inverter System

FUNCTIONAL DESCRIPTION AC Alternator System

The AC alternator system supplies two separate three-phase AC bus-bars with 115/200 VAC via each of its two AC alternators (ALT's). The frequency of the alternators is regulated to within 290 to 440 Hz at an engine performance of 65 to 100%. AC Inverter System

The AC inverter system (INV) is a single-phase system and supplies a frequency-regulated voltage of 26/115 VAC, 400 Hz via each of its two static inverters. The two inverters each supply two AC bus-bars via two separate voltage outlets.


TRAINING MANUAL


24-21 AC ALTERNATOR SYSTEM GENERAL DC POWER CONTROL UNIT 1VE – CIRCUIT BREAKER 1XR (5XR) – 28 VDC MAIN BUS 1 (2)

ALTERNATOR 1XA-2

C/B AND RELAY PANEL 35VE – AC PWR CTL CIRCUIT BREAKER 11XX TO 16XX AC POWER CONTROL UNIT 2VE – CIRCUIT BREAKER 5XA (15XA) – 115 / 200 VAC BUS 1 (2) – CURRENT TRANSFORMER 4XA (14XA) – ALTERNATOR RELAY 3XA (13XA)

ALTERNATOR 1XA-1

ALT LH SWITCH / LIGHT 6XR ALT RH SWITCH / LIGHT 3XR ELECTRIC

DC NON-ESS 1

O F F

BUS 1

B US 2

ESSENTIAL

N ON -E SS 2

O F F

AC BUS 1

BUS 2

FAIL

FAIL

OFF

OFF

ELECTRIC PANEL

Dornier 328 TRAINING MANUAL

DORNIER LUFTFAHR


The AC alternator system has the following main components: - Switch/light ALT LH 6XR (ALT RH 3XR) - Alternator 1XA-1 (1XA-2) - Alternator control unit 2XA (12XA) - Current transformer 4XA (14XA) - Alternator line relay 3XA (13XA) FIN

Component

Panel

Zone

Access Door

6XR 3XR 1XA-1 1XA-2 2XA 12XA 4XA 14XA

Switch light ALT LH Switch light ALT RH Alternator (LH) Alternator (RH) Alternator control unit (LH) Alternator control unit (RH) Current transformer (LH) Current transformer (RH)

30 PP 30 PP

2VE 2VE

210 210 410 420 210 210 221 221

412-BL 422-CL 214-EZW 214-EZW 221-LZF 221-LZF

3XA 13XA 1XR 5XR 5XA 15XA 2XP-A

Alternator line relay (LH) Alternator line relay (RH) Circuit breaker 5A Circuit breaker 5A Circuit breaker 60A Circuit breaker 60A AC Power Control Circuit breaker 1A

2VE 2VE 1VE 1VE 2VE 2VE 35VE

221 221 221 221 221 221 221

221-LZF 221-LZF 221-LZF 221-LZF 221-LZF 221-LZF 221-PZF


TRAINING MANUAL


AC External Power

If the 115/200 VAC GPU is connected and switched on, the relay 7XD interrupts the switch-in control circuit of the two alternators. At the same time the ALR 3XA (coil B) is supplied with voltage via the EPR 2XD, which energizes and makes the bus-bar contact between AC BUS 1 1XP and AC BUS 2 2XP via it s main contacts. Control and Dimming (Chapter 33-LIGHTS)

The brightness or dimming regulation of the lights FAIL and OFF, inside the switch lights, is controlled with the switch DAY-NIGHT (in field INT-LIGHT) on the overhead panel. The lights are connected to the dimmer 2LF. A check of the lights is made with the pushbutton TEST which is also in the field INT-LIGHT.

I P s a s u g e : e : 0 2 1 4 / 9 -1 6 2 E T M / E T X



CONTROL POWER

EXCITER CURRENT CONTROL

VR

3 Ø VOLTAGE SENSING

OUTPUT

A

F i g . 5 A l t er n a t or F u n c t i o n

B

C

+

-

N

T1

T2

PMG STATOR

T3

F U N C T I O N A L D E S C R I P T I O N

D o r n i e r


STATOR EXCITER FIELD

MAIN STATOR

EXCITER ROTOR

ROTOR MAIN FIELD

PM

PERMANENT MAGNET

3 2 8 -1 E 0 0 f f M e c t o i v d i .1 t y 0 :

A l t e r n a t o r 1 X A -1 ( 1 X A -2 )

ROTATING DIODE ASSY

ROTOR



TRAINING MANUAL


A parallel connection of the alternators (1XA-1 and 1XA-2), which are installed on the left and right engine, is not possible. The frequency is unregulated and is dependent on the variable speed of the engine. But as the cruising flight is made at an almost constant engine speed, the AC alternator system is designed so that at this speed range a frequency of approximately 400 Hz is supplied. This AC supply is provided to the AC BUS 1 and AC BUS 2. The alternator (ALT) is a brushless three-phase generator with 115/200 VAC and an output of 20 kVA. It has the following main components: - Main stator winding - Rotating rectifier winding - Main exciter - Permanent magnet generator. The alternator is installed on and driven by the reduction gearbox of the engine. A blower unit installed in the alternator makes sure the alternator is sufficiently cooled. Alternator control unit 2XA (12XA)

The alternator control unit (ACU) provides voltage regulation, current limitation and protection of the system. In addition the alternator also controls the switch-in and switch-over functions. The ACU 2XA and 12XA are installed in the Avionic Rack RH. Current transformer 4XA (14XA)

The current transformer (CT) monitors the current status in the AC alternator system. It registers the current which flows through the lines as a proportional value and triggers differential signals, overcurrent


AC - BUS 1XP

BUS 1

1 16XX

4VE A/B SHEET 2

1 15XX

1 14XX

AC POWER CONTROL

60 5XA

15XA

1 12XX

1 11XX

AC POWER CONTROL

4VE A/A SHEET 2

21 3XA/B

26 3XA/A

25 13XA/A INTERLOCK A B SHEET 3 C

F i g . 6 A l t er n a t or C i r c u i t

1 13XX

C B A

1 TU


30 3XA/B

BUS 2

C B A

60

2 0 R 9 E 0 W A 4 O 4 P 2 . T E X E E S

DATA AQUISITION UNIT 1


AC - BUS 2XP C B A

DATA AQUISITION UNIT 2

2 TU

INTERLOCK 3XB (TRU)

SHEET 3

CURRENT CURRENT 4XA TRANSFORMER TRANSFORMER UNIT 1 UNIT 2

A B C

14XA

D E F

12XAA C

B

A

N

N

A

B

C

4VE A/K SHEET 2

4VE A/J SHEET 2

A1 ALT. LH ON/ OFF

A1 3XR ALT. RH ON/ OFF A3

6XR A3 2XA

1XA-1

1XA-2 12XA

3 2 8 -1 E 0 0 f f M e c t o i v d i .1 t y 0 :

D o r n i e r


ALTERNATOR 1

GENERATOR CONTROL UNIT 1

1

2

3

4

ALTERNATOR 2

5

6

7


8

8

10



MAIN-BUS 2 28V

TRAINING MANUAL


ESS-BUS 3PP 28V

5XR 7,5

MAIN-BUS 1 28V

10XR AC TRU

1XR 5

7XB

6XB 42

43

DAY/NIGHT 2XAA/SHEET 1

2LF

SHEET 1 12XA

2XA

B018

B018

13XAB 30

3XAB 30 DAY/NIGHT

DAY/NIGHT

2LF

2LF EICAS

EICAS


DORNIER LUFTFAHR

The control of the AC alternator system is made with DC power from the DC MAIN BUS 1 and DC MAIN BUS 2. The operation of the left and right alternator is the same. The subsequent text describes the left alternator, and the figures in brackets refer to the system components of the right alternator. When the switch/light ALT LH 6XR (ALT RH 3XR) is pushed the white light OFF 6XX (OFF 5XX) goes off and the ALT 1 (2) is switched on. At the same time, if the ACU 2XA (12XA) releases the switch-in, the ALR 3XA (13XA) excitation-coil A are supplied and locked via the open contacts of excitation-coil B(3 or 13XAA). The main contacts now connect the ALT 1 (2) with the AC BUS 1 1XP (AC BUS 2 2XP) and the ALT is switched in. If a failure is found in the system during the operation, the logic of the ACU 2XA (12XA) interrupts the voltage to the excitation-coil A in the ALR 3XA (13XA). The light FAIL 2XW (FAIL 1XW) comes on (amber) and indicates the failure of the ALT 1 (2). Thus the AC BUS 1 1XP (AC BUS 2 2XP) is no longer supplied. When the switch/light TIE 2XR which belongs to the AC electrical load distribution system is pushed, the excitation-coil B of the ALR 3XA (13XA) is supplied and locked via the closed auxiliary contacts of the excitation-coil A. The main contacts now connect the AC BUS, which is no longer supplied, to the ALT which is still in operation. The light 7XX (white) now indicates (with a bar symbol) that the TIE connection is made.

3 2 E f f 8 -1 e c t 0 0 vi i M t y : o d .1 0



I s s u e : 0 1 / 9 6 P E a T g M e : 2 / E 4 T -1 X 7

a d T h d e i t i A o n C a r l e l y l a f e y a b t u o r x e s c t h o n e t a c u i n r r s e t n h t e t r h a i n g s f h o c r m u r r e e r n s t s a e l n t s e e r n t h a e t o c u r l r r i n e n e t e r f l l a o w y s i n , t h t h e e e x s u t p e p r n l a y l l i n a n e d s . t h e T R U r e l a y . A s

2VEA

2VE

1 T 1 L A L L O O D R R T N T 1 N U N T O O L O C R C - G - A L U - C I C C T A G D B F I * H * D * F *

X X X L 7 X A 1 7 N C C R T T 1 E B T T - B L L L X A A A - E N N L I C G G T I I A F B S S

D N 2 U T O L R A G L - I C A D F

2 T L L A A I N L S O C R T T 2 B N T Y L O L C - P - A L P C I T U A B F S

J E * G * * * C

Q * * R

T * S * N *

BUS 1

3XA F H K

G J L

B

A

60

EE

5XA 2XD

2VEA

A

A

ALT. 1

EXTERNAL- LIGHT

A

B

B

C

EXT. POWER


C 4XA B B

F i g . 8 A C R e l a y B o x 2 V E

A B C

A

D

B

2VEA

A

A

G

C

H

B

J

ALT. 2

A 14XA

K B

A SENSING GCU 1

EXTERNAL- SIGNAL

2VEA

4XA*A

CURRENT-TRAFO

*G

13XA

B

4XB

C

B A D C 14XA*A

5

2VEA

8XB

2VEA

L

5

M N A

B

CURRENT-TRAFO

P D E

15

2VEA

CONNECTOR 2VEA: MS3470W-22-55PN CONNECTOR 2VEB: MS3470W-14-4PN

A T V U * V 5 1 1 L O R T N O C U R T

E V R E S E R

2XB

A

B

C

TRU

F

60

B P 2VEC X Y S R 2VEB Z W * * V 5 1 1 D N U O R G

E V R E S E R

2 V U 5 L 1 R 1 T O R Y L L T O P N R P O T U C N S O U C - C U G R T

15XA

C

B

BUS 2

A

SENSING GCU 2

D o r n i e r



DORNIER LUFTFAHR


SYSTEM INDICATIONS CAS FIELD Indication

MFD PAGE Indication

AMBER

AMBER

L/R ALT FAIL

ALT LH/RH FAIL

Fault or Condition

LH/RH Alternator off

AMBER

Phase fail LH/RH Alternator

L/R AC VOLT FAIL

-

BUS 1

115 V

FAIL

OFF

AC–POWER

ESS–DC

115

V

BUS 2

FAIL

EXT TRU

ALT LH FAIL

Fig. 9 AC System Indications

ALT RH


TRAINING MANUAL


24-22 AC AC INVERTER SYSTEM GENERAL C / B SIDE PANEL RH 10VE – INV 2 CIRCUIT CIRCUIT BREAKER 25XR – 28 VDC NON ESS BUS 2 5PP RELAY BOX 4VE – CURRENT RELAY 21XR, 26XR – RELAY 23XR, 28XR 28XR – CIRCUIT BREAKER BREAKER 3XE, 4XE, 5XE, 6XE – DIODE D1, D2 D2 – CAPACITOR 24XR, 29XR INVERTER 2XE INVERTER 1XE

ELECTRIC

DC NON-ESS 1

O

BUS 1

B US US 2

N ON ON -E -E SS SS 2

O

AC BUS 1

BUS 2

FAIL

FAIL


DORNIER LUFTFAHR


The AC inverter system has the following main components: - Switch Switch/lig /light ht INV1 INV1 22XR 22XR,, INV2 INV2 27XR 27XR - Inv Inverte erterr 1XE 1XE,, 2XE 2XE - Curre Current nt rela relay y 21XR 21XR,, 26XR 26XR - Rela Relay y 23XR 23XR,, 28X 28XR R FIN

Component

1XE 2XE 3XE 4XE 5XE 6XE 20XR 21XR 22XR 23XR 24XR 25XR 26XR 27XR 28XR

Inverter 1 Inverter 2 Circuit breaker 1A Circuit breaker 2A Circuit breaker 1A Circuit breaker 2A Circuit breaker INV 1/7,5 A Current relay 1 Switch light INV LH Relay 1 Capacitor 1 Circuit breaker INV 2/7,5 A Current relay 2 Switch light INV RH Relay 2

Panel

Zone

Access Door

4VE 4VE 4VE 4VE 12VE 4VE 30PP 4VE 4VE 10VE 4VE 30PP 4VE

221 221 221 221 221 221 210 221 210 221 221 210 221 210 221

222-AZF 222-AZF 221-BZF 221-BZF 221-BZF 221-BZF 221-BZF 221-BZF 221-BZF 221-BZF 221-BZF


TRAINING MANUAL


FUNCTIONAL DESCRIPTION General

During normal operation two static inverters supply the 26 V and 115 V/400 Hz to the AC consumers. The output has a stabilized voltageand frequency.Each of the two identical INV supply two AC bus-bars via two outputs.When one of the INVs (1XE or 2XE) malfunctions, the relay 23XR or 28XR automatically switches to the AC voltage supply of the INV which is still in operation. The relays 23XR and 28XR are controlled by the fault monitor output of the respective inverter. Inverter 1XE, 2XE

The 125 VA static inverter converts DC electrical power into single phase, sinewave, regulated AC electrical power. The nominal input DC power is 28 V and the nominal outputs of the INV are 115 VAC and 26 VAC.The generation of the alternating signal and the regulation are accomplished by a single integrated regulating pulse width modulator circuit. The quasi-square wave output of the integrated circuit is amplified and filtered by a tuned transformer to provide a low distortion sinewave output. The output signal is used for both current and voltage sensing circuits to provide the necessary information to the regulating control circuits of the integrated circuit. The INVs are installed internally under the floor assembly in the fuselage.


ESS - BUS 3PP NON - ESS - BUS 2 5PP

INV 1

7,5 20XR DAY/ NIGHT 2LF

3

OFF D2

1

5


FAIL

ON D1

OFF A1

D3

ON A2 27XR

3

1 2

D1

INV 2

26V

115V

5

M O F N A U I T L O T R

2XE

INV 1

115V

DAY/ NIGHT 2LF

INV 2

26XR

A3

1XE

26V

OFF

ON

A3

3 23XR

B1

B3

A2

A1

A3

B2

21 28XR

1

A2

B2

1 5XE 2

1 6XE

ON

2

4XE

2

1

2

2

2

EICAS 1TUB/A011 C2 23XR

J 3 XP

C3

4XP

115V 24XR

X1 23XR X2

+

AC MASSE

6XP

115V

21 C3

26V

11TU

DAU 1

EICAS 11TUB/A011 C2

K

5XP

26V

1TU

DAU 2

X1 28XR X2

AC MASSE

+ 29XR

4VV

3 2 8 -1 E 0 0 f f M e c t o i v d i .1 t y 0 :

1

2

3

4 SO 9 9 1111 2

5

6

7

8

9

10

11

OFF

27XR

1

3XE

FAIL

B1

B3

22XR 1

D o r n i e r


SEE 331A0902 42vv/1F LAMP TEST

OFF A1

OFF

2

22XR

2

D2

R T O L T U I A N F O M

F i g . 1 1 I n v er t er C i r c u i t

25XR

7,5 PHASE LOCK

21XR


O P E R A T I O N

12

13

14

15

16

17

18

19

20

21 SO 1414 1616 23

22

23



TRAINING MANUAL


Power Supply

Component

BUS

Circuit Breaker

Power Supply Inverter 1

ESS 3PP

INV 1 20XR

Power Supply Inverter 2

NON ESS 2 5PP

INV 2 25XR

No.

Inverter Circuit

The INVs are identical in operation. Thus only the INV 1XE is described. When the switch/light INV1 22XR is pushed, ground is connected to the remote ON/OFF circuit and the INV 1XE is switched on. If the output voltage and the frequency of the INV are within the tolerance, the output voltage of the fault monitor energizes the coil of relay 23XR. The relay 23XR switches the output voltage (115 VAC and 26 VAC/400 Hz) to the AC-BUS 3XP and AC BUS 4XP. At the same time the white light OFF 8XX goes off. The AC BUS 5XP and AC BUS 6XP are supplied by the INV 1XE as long asthe relay 28XR is de-energized and the INV 2XE is not switched on. If the INV 1XE malfunctions, the output voltage of the fault monitor is zero. The relay 23XR is deenergized and disconnects the faulty INV from the AC BUS 3XP and 4XP. At the same time the amber light FAIL 3XW comes on, and the de-energized relay 23XR connects the AC BUS 3XP and 4XP to the voltage supply of the INV 2XE. If the cause of the inverter failure is in the AC voltage supply network, the INV is switched off by an internal switching circuit. If there is a short circuit of the AC system in the AC electrical load distribution system, the increased current on the DC side energizes the current relay 21XR (> 6A). The closed contacts prevent the deenergizing of the relay 23XR until the circuit breaker on the AC side is opened.The capacitor 24XR provides a drop-out delay-function.

G E N E R A L


EXT

GEN I GCU



F i g . 1 3 D C G e n er a t i o n B a s i c C o n f i g ur a t i o n

G

G

GEN I CONT

HOT-BUS II

BATT I CONT

GCU

G

GCU

BATT II 7PP

BATT II CONT

GEN II CONT

D o r n i e r


GEN CONT

TIE GEN 1-BUS

GEN 2-BUS

NON-ESS1 CONT

NON-ESS2 CONT

1PP NON-ESS-BUS 1

3 2 8 -1 E 0 0 f f M e c t o i v d i .1 t y 0 :

BATT I HOT-BUS I

6PP

EXT CONT

APU (OPTION) GEN

GEN II

2 4 3 0 D C G E N E R A T I O N

2PP BUS I

3PP ESSENTIAL-BUS

4PP BUS II

5PP NON-ESS-BUS 2



TRAINING MANUAL


This section provides information on the DC generation subsystem. The DC power supply is provided by two DC starter/generators. Two batteries charged with generator voltage also supply additional DC current. If the two DC starter/generators fail, a transformer/rectifier unit supplies the most important DC consumers. The chapter is divided into the following sub-subsystems: - DC starter/generator - Battery system - Emergency DC power system Fig. 15 gives an overview over DC Voltage supply and distribution. It must be considered that relays, monitored by the electronic units of the electrical system, control the (dis-)connection of buses und suppliers.

FUNCTIONAL DESCRIPTION DC Starter/Generators

The starter/generator system, with each of its two starter/generators (S/G), provides a separate DC MAIN BUS with 28.5 VDC. The bus TIE relay, which is open during normal operation, permits the parallel operation of the two SGs when in the closed condition. At the same time the relay connects the bus-bars and ensures the supply from one of the S/Gs. Battery System


DORNIER LUFTFAHR


24-31 DC STARTER/ GENERATOR SYSTEM GENERAL STARTER / GENERATOR 1PC-2

HALL EFFECT SENSOR 4PC-2

DC POWER CONTROL UNIT 1VE – CIRCUIT BREAKER 6PC, 7PC, 8PC (16PC, 17PC, 18PC) – HALL EFFECT SENSOR 3PC (13PC) – GENERATOR LINE RELAY 5PC (15PC) – 28 VDC MAIN BUS 1 (2) – CIRCUIT BREAKER 2PR, 5PR STARTER / GENERATOR 1PC-1 HALL EFFECT SENSOR 4PC-1

ELECTRIC

DC NON-ESS 1

O F F

BUS 1

B US 2

ESSENTIAL

N ON- ES S 2

O F F

AC BUS 1

BUS 2

FAIL

FAIL

OFF ALT LH

OFF TRU

ALT RH


TRAINING MANUAL


FIN

Component

Panel

Zone

21PC 22PC 1PC-1 1PC-2 2PC 12PC 3PC 13PC 4PC-1 4PC-2 5PC 15PC 20PC 6PC 7PC 8PC 16PC 17PC 18PC 9PC

GEN LH Switch/Light GEN RH Switch/Light Starter/Generator (LH) Starter/Generator (RH) Generator Control Unit (LH) Generator Control Unit (RH) Hall Effect Sensor (LH) Hall Effect Sensor (RH) Hall Effect Sensor (LH) Hall Effect Sensor (RH) Generator Line Relay (LH) Generator Line Relay (RH) Bus Power Control Unit Circuit Breaker 3A Circuit Breaker 15A Circuit Breaker 3A Circuit Breaker 3A Circuit Breaker 15A Circuit Breaker 3A GCU 1 Circuit Breaker 10A

30PP 30PP

210 210 410 420 210 210 221 221 410 420 221 221 210 221 221 221 221 221 221 210

1VE 1VE

1VE 1VE 1VE 1VE 1VE 1VE 1VE 1VE 12VE

Access Door

412-CR 422-BR 213-DZW 213-DZW 221-LZF 221-LZF

221-LZF 221-LZF 213-DZW 221-LZF 221-LZF 221-LZF 221-LZF 221-LZF 221-LZF


DORNIER LUFTFAHR

When the N1-rotational speed of 5400 + 100 rpm is reached the start procedure is completed. Engine Fire Extinguishing (Chapter 26 - FIRE PROTECTION)

If the fire extinguishing procedure on the left (right) engine is triggered, the control and excitation of the S/Gs operation as a generator is interrupted by the pushbutton ENG LH FIRE 2WB (ENG RH FIRE 42WB). Landing Gear (Chapter 32 - LANDING GEAR)

The relay 32GA supplies the GCU 2PC (12PC) and the relay 31GA of the BPCU 20PC with control signals via the air/ground operation of the DC starter/generators. They interrupt the procedure switching for the external voltage supply on the ground. DC Electrical Load Distribution

The digital voltmeters 20PX and 21PX installed in the FIELD ELECTRIC (on the overhead panel) permit a check of the generator voltage supplied to the DC MAIN BUS 1 and DC MAIN BUS 2. Control and dimming (Chapter 33 - LIGHTS)

The brightness or dimming of the lights in the switch/lights GEN LH and GEN RH, is controlled by the switch DAY-NIGHT (in field INT-LIGHT) on the overhead panel. The lights are connected to the dimmer 2LF. A check of the lights is made with the pushbutton TEST which is also installed in the field INT-LIGHT. The lights are switched on via the diode U1.


TRAINING MANUAL


Starter/Generator 1PC-1 (1PC-2)

+ Speed Sensor 1 2 3

A Red Mark

D S/G

White Mark


DORNIER LUFTFAHR

A mounting adaptor, which is installed between the engine and the S/G, permits the outlet of the cooling air and the installation of the air deflection tube. On the ground, an installed fan ensures adequate cooling. The flexible torsion-driveshaft with damper compensates for any unusual effects which occur on the drive side. A pre-determined break-point (18,4 mkg) protects against excessive torque. The starter/generator thermal protection contact closes when the temperature of the winding reaches 165.5°C and an appropriate visual indication shows up on OHP,CAS Field and System Page. At 149.5 °C normal operation is reinstalled. Generator Control Unit 2PC (12PC)

The generator control unit (GCU) controls and protects the starter/generator. The voltage of the shunt generators is regulated by field weakening through the GCU and is kept constant independent of the rotational speed. In addition, the GCU has the following protective function during the starter and generator operation: Starting Phase - Speed sensing circuit - Field weakening - Overspeed protection - Starter relay control and automatic starter cut-out - Starter-control failure-annunciation Generating Mode - DC voltage regulation - Load sharing during parallel operation - Generator current limiting


TRAINING MANUAL


OPERATION Power Supply

Component

BUS

Circuit Breaker

Power Supply GCU 1

BUS 2 4PP

GCU 1 9PC

Power Supply GCU 2

BUS1 2PP

GCU2 19PC

Starter/Generator 1PC-1 (1PC-2)

Starter Performance - Maximum input current: 1700 A with return to 1400 A within 1.5 sec. Generator Performance -

Rated terminal voltage : 30 VDC Rated load current : 400 A Rated Output: 12kW (400 A 30V DC) Rated Speed Range:7200 to 12300 rpm Overload Current:600 A during 2 minutes, 800 A during 8 sec's. Overspeed:14000 rpm during 2 minutes

No.

I P s a s u g e : e : 0 2 1 4 / 9 3 6 2 E T M / E T X

9PP MAIN-BUS 1

4PR 11PP 150A

3 BB

1PP

2PP

5PC 3PC

F i g . 1 6 S t ar t er / G e n er a t or S y s t e m

2 A

9 1 / 2 T E E H S

1 A

1TUA

3 6PC

10PP-A

3PA BATT 1

12PP 150A

(+)

B T 2WW 1TUB * H *A A V P 16 A038 1 O 2WW 1TU WARN DAU1 PANEL 500A

12VV-3

10 BPCU 24PC

11PA*A (+)

11PA

ESSENTIAL-BUS 3PP

(-)

(-)

1PA*A SHEET 2/23

14PP 150A

SHEET 2/38

11PA*A 500A

4PP

15PP 150A

5PP

SHEET 2/40 3

18VE

*W

10 GCU 1 9PC 2WW 11TUB T B * H A *A V P 1 21 A038 O 1 2WW 11TU WARN D AU 2 PANEL 12PA

18PC 15PC 13PC 2 AG 1 A

15 17PC


BUS-POWERCONTROL UNIT

1PC-1 B (+)

3 16PC


11TU DAU2

B CROSS-START START START INIT n>61,5 % END OF LOADSHED INHIB. GCU OVERLOAD

Sp D A * 1 C A P 1

S/G

2PC

GEN.1 BUS

4PC-1

BATT 2

7PP

1PA

2PA

7PR

15 7PC

1TU DAU1

E (-)

13PA

16PP 150A

10 BPCU 23PC

OVHT

1TU DAU1

D A * 2 C P A 1

12PC

S/G

GEN.2 BUS 11TU DAU2

9PP TIE

OVHT

E

(-)

1 A 4PC-2 2 A

2 A

1VE*A

(+)

1PC-2

Sp

20PC

1 A

LOADSHARING

3 2 8 -1 E 0 0 f f M e c t o i v d i .1 t y 0 :

10PP-B

13PP 150A

6PP 1PA*A

10 GCU 2 19PC

8PC


MAIN-BUS 2 TIE

SHEET 2/19


D o r n i e r


1VE*A

LOADSHARING

Z 1VE*B Y

APU-GCU, A008 001A491A0901, SHEET 1



TRAINING MANUAL


The operation of the left and right starter/generator is identical. The subsequent text describes the operation of the left starter/generator. The figures in brackets refer to the system components of the right starter/generator. The S/G 1PC-1 (1PC-2) is ready for operation when the switch/light GEN LH/21PC (GEN RH/22PC) is pushed. The white light OFF/3PX (OFF/4PX) contained in the switch/light comes on as long as the GLR 5PC (15PC) is not energized, or the pole-reversal procedure from starter operation to generator operation is not completed. When the required engine rpm(N3 = 7380 ± 60 rpm) is reached, and all the protection and regulation functions in the GCU 2PC (12PC) are correct, the GLR 5PC (15PC) is then energized. It now connects the generator voltage to the DC MAIN BUS 1(DC MAIN BUS 2) and the OFF light goes off. The voltage (28,5 VDC) of the shunt-wound generator is regulated by field weakening through the GCU and is kept constant independent of the rotational speed. In addition the BPCU 20PC monitors the current and voltage condition in the system and that of the DC bus bar. If the S/Gs malfunction (overvoltage, excess or reverse current, or complete failure) the GCU 2PC (12PC) disconnects the defective generator from the DC MAIN BUS 1 (DC MAIN BUS 2). At the same time the amber light FAIL 3PW (FAIL/4PW) comes on. When the related switch/light TIE 1PR for the DC electrical load distribution system is pushed, the bus TIE relay 9PP is energized via the BPCU 20PC. It makes sure there is parallel operation of thetwo S/Gs or that there is a series connection (between the DC MAIN BUS 1 and DC MAIN BUS 2) if one of the generators fails. The white light 6PX shows the TIE connection is made by displaying a bar-symbol.

I P s a s u g e : e : 0 2 1 4 / 9 3 6 4 E T M / E T X

6PP

10

MAIN - BUS 1 BPCU

6PP

10

5

2PR

4PA


3PP

5

BATT. 1

DC TIE IND

3

BATT. 2

14PA

8PR

23PC SHEET 1/11 1TU DAU 1

PANEL LIGHT 23PX

1TU DAU 1

2LF

B079

F i g . 1 7 D C P o w er M o n i t or i n g S y s t e m

L I A F

2LF

OFF A2

A1

B2

A3

GEN LH

WOW D3

11TU DAU 2

1TU DAU 1

2LF

22PX

2LF


7PP

D o r n i e r


B1

C1

B3

C3

WOW

D1

A3

32GA D2

WOW

A1

B1

A2

NON ESS. 1

F F O

B3

31GA

B2

3PR

B3 B1

A3

BATT. 1

L I A F

F F O

BATT. 2 A3

A1

B3 B1

C3 C3

B3

A3

C1

B1

A1

C1

A1

F F O

TIE

L I A F

A3 A1

5PA

15PA

1TUB A3

A1

B1

B3

A2

7PD

B2

FIRE

B1

15PD

B3

3PD

C2

D2

DC/EXT

B2

4PR

9PP

D3

C3

20PC

2PC

20PC

GCU 1

BPCU

NON ESS. 1

TIE

BATT. 2

BATT. 1

20PC BPCU

E -

21PX V

A3

+

A1 B1 9XB B2

A2

1TUB B B 1TU DAU 1

3 / 1 T E E H S

19PC 10

+ 8PC 3

5PC

+

-

BUS 1=2PP

B3 TRU

5XB

4PR

+

-

10PP

GCU 2

-

+

+

3PA

-

+

+

-

+ +

-

9PP

13PA

-

MAIN BUS 1

SEE A280A0901 SHT.2 19

3 2 8 -1 E 0 0 f f M e c t o i v d i .1 t y 0 :

B3

B1

1PR

SEE SHEET 1 SEE 001A244A0901 SEE 001A801A0901

20

21

22

23

24

25

GEN LH W

S

D

3 20 23 23 11

26

W

S

D

12 2424

W

S

27

28

29 NON ESS. 1

CHANGE OVER D

16 2727

S

D

5 26 26 28 28

30

31 BATT. 1 W

S

D

32

BATT. 2 W S

D

9 12 29 29 33 33 20 29 20 33

33

34 TIE W S D 14 14 35 35 35 35

35



TRAINING MANUAL


Hall Effect Sensors 3PC (13PC), 4PC-1 (4PC-2)

+

I d

X

U H

_ Fluxdensity B Hall-Effect


DORNIER LUFTFAHR

HECS are made from very thin semiconductor material (5µm to 10µm) which is vacuum metalized on ceramic waver plates. With a voltage supplied to the plate, a current is flowing. An additional magnetic field causes the electrons to move towards one side of the plate. Thus a voltage, dependant on force and direction of the magnetic field, can be measured. In the case of the Do 328 the magnetic field is caused by the current flowing on the plus and minus side of the generator. The measured hall voltage indicates size and direction of the actual current and is used by the GCU for monitoring and by the EICAS for indication purposes.

3 2 E f f 8 -1 e c t 0 0 vi i M t y : o d .1 0

R E W O P T X E

H L E N E G A M T Z V X * Y U W Y P R A * * * * * A * M 1VEA 1VEC

1VE

1 T T A B A V B X W * *

C J H N F L T A B E K C D U S G M *

1VEA

H R E N E G

2 T T A B

1VEA

K M J N * * * * * 1VEB

E H * C D G * * * *

S B C *

1VEC

F A B E C D G

13PC

+ REV.



I s s u e : 0 1 / 9 6 P E a T g M e : 2 / E 4 T 3 X 7

5PD

F i g . 2 0 D C R e l a y B o x 1 V E

15 7PC 3 6PC

+

PP BB *F

F A B E C D G

+ REV.

3PA

17PC 3 16PC *T *U *W *V

+

15PC

-

-

A E V 1

B E V 1

E B C E V 1


15

13PA

+

5PC

1VEB F A B E C D G

F A B E C D G

3PC

U P A

Z Y X J * L F E A K D H G M * *

C

1VEB

D C R e l a y B o x ( 1 V E )

D

9PP + -

5 3 10 1XR 8PC 2PR

10

3

5

5PR 18PC 5XR

C E V 1

B E V 1 *A V

4PR

+

+

-

-

+

10PP-A

+

10PP-B

7PR

-

X W HH Z *B

150A 11PP

1VEA I J E * * K N D G * * * * N

1 S U B S S E N O N

150A 12PP

1 S U B

H N * R Q M * * * *

1VEA S *

150A 13PP

1VEA 16PP J K L F E P C H D G J Z H * L F E C D G K

150A

S U B

S U B

S S E

S S E

1VEB T F Y P S R U N *

150A 14PP

150A 15PP

2 S U B

2 S U B S S E N O N

D o r n i e r



DORNIER LUFTFAHR


The DC relay box contains as DC electrical heart all high power relays and some additional features like the HECS in the plus line and the reverse current protection. The energizing controls are connected with the GCU or BPCU.


MFD PAGE Indication

AMBER

AMBER

L/R DC GEN FAIL

GEN LH/RH FAIL

AMBER

AMBER

L/R DC GEN OVHT

GEN LH/RH OVHT

NON–ESS1

1

Fault or Condition Generator off

Generator off

DC–POWER

2

NON–ESS2

ESSENTIAL 28.5 V

200 A FAIL

28.5 V

200 A FAIL


TRAINING MANUAL


24-32 BATTERY SYSTEM

BATTERY 11PA FUSE 12PA DC POWER CONTROL UNIT 1VE – BATTERY RELAY 3PA, 13PA – 28 VDC MAIN BUS 1 (2)

BATTERY JUNCTION BOX RH 7VE – DC HOT BUS 2 7PP – BAT2 CIRCUIT BREAKER, 14PA

FUSE 2PA BATTERY JUNCTION BOX LH 6VE – DC HOT BUS 1 6PP – BAT1 CIRCUIT BREAKER, 4PA

BATTERY 1PA

ELECTRIC

DC NON-ESS 1

O F F

BUS 1

BUS 2

ESSENTIAL

NO N- ESS 2

O F F

AC BUS 1

BUS 2

FAIL

ALT LH V

FAIL

OFF

OFF TRU

ALT RH


DORNIER LUFTFAHR


The battery system has the following main components: - Switch/light BAT 1/5PA, BAT2/15PA - Battery relay 3PA, 13PA - Battery 1PA, 11PA - Bus power control unit 20PC. FIN

Component

Panel

Zone

Access Door

5PA 15PA 3PA 13PA 1PA 11PA 20PA 4PA 14PA 2PA 12PA

Switch light BAT 1 Switch light BAT 2 Battery relay (1) Battery relay (2) Battery (1) Battery (2) Bus power control unit Circuit breaker 5A Circuit breaker 5A Fuse 150A Fuse 150A

30PP 30PP 1VE 1VE

210 210 221 221 130 130 210 130 130 130 130

221-LZF 221-LZF 131-BL 132-BR 213-DZW 131-BL 132-BR 131-BL 132-BR

6VE 7VE

INTERFACE TO OTHER SYSTEMS Indicating (Chapter 31 - INDICATING/RECORDING SYSTEMS)


TRAINING MANUAL



The battery (1PA and 11PA) is wired in parallel to each of the S/Gs and is connected to the related DC MAIN BUS via the battery relay (BAT RLY). The battery system is monitored by the BPCU 20PC. The batteries are charged during the operation of the two S/Gs and function as a buffer for the DC power supply and also stabilize the electrical load. The reverse-current protection-devices installed in the battery relays prevent excess charging. The battery bus bars (DC HOT BUS 1 and 2) are connected directly to the batteries and supply the most important functions and systems to avoid losses in case of a failure in the DC power supply. Battery 1PA, 11PA

Two identical nickel cadmium batteries (BAT) 24 V/40 Ah are installed in the aircraft. The main terminals are fitted with quick-release connectors. A bi-metal thermostat is fitted to each battery and controls the temperature. The battery covers are airtight and pressure vented. The batteries are located in the forward section of the left and right landing gear nacelles. Bus Power Control Unit 20PC

The BPCU monitors the current and voltage status of the DC bus bars and if an overload or short circuit


DORNIER LUFTFAHR



MFD PAGE Indication

AMBER

AMBER

BATT 1/2 FAIL

BATT 1/2 FAIL

Battery 1/2 disconnected from main bus

RED -

Fault or Condition

Battery overheat warning at 71°C

BATT 1/2 OVHT

NON–ESS1

1

DC–POWER

2

NON–ESS2

ESSENTIAL 28.0 V

28.0 V

200 A

200 A FAIL OVHT

200 A FAIL

OFF

OVHT


TRAINING MANUAL


24-33 EMERGENCY DC POWER SYSTEM GENERAL

RELAY BOX 4VE – RELAY 6XB, 7XB, 9XB

TRANSFORMER RECTIFIER UNIT 1XB AC POWER CONTROL UNIT 2VE – CIRCUIT BREAKER 2XB, 4 XB, 8XB – SUPPLY RELAY 3X B

TRU SWITCH 5XB ELECTRIC

DC NON-ESS 1

BUS 1

B US 2

NO N- ESS 2

AC BUS 1

BUS 2


DORNIER LUFTFAHR


The transformer rectifier unit (TRU) 1XB is supplied from the three phase frequency-regulated 115/200 VAC aircraft power supply, and supplies the DC ESSENTIAL BUS 3PP with 28 VDC if the two DC generators fail. The supply procedure is made with the guarded switch TRU 5XB on the overhead panel. The transformer rectifier unit (TRU) is installed under the floor assembly in the fuselage. The Emergency DC Power System has the following main components: - Switch TRU 5XB - Transformer rectifier unit 1XB - Supply relay 3XB - Relay 6XB, 7XB, 9XB FIN

Component

Panel

Zone

5XB 1XB 3XB 6XB 7XB 9XB 4XB 8XB 2XB 10XR 10XB

Switch TRU Transformer Rectifier Unit Supply Relay Relay Relay Relay Circuit Breaker 5A Circuit Breaker 5A Circuit Breaker 15A Circuit Breaker AC-TRU/7,5 A Fuse 150 A

30PP

210 221 221 221 221 221 221 221 221 210 210

2VE 4VE 4VE 4VE 2VE 2VE 2VE 12VE 12VE

Access Door 221-JZF 221-JZF 221-BZF 221-BZF 221-BZF 221-JZF 221-JZF 221-JZF

O P E R A T I O N

3 2 E f f 8 -1 e c t 0 0 vi i M t y : o d .1 0

ESSENTIAL-BUS 3PP 5



I s s u e : 0 1 / 9 6 P E a T g M e : 2 / E 4 T -4 X 5

4XB

5

1 1 10XR AC 7,5 2 2 TRU

6XB

SEE SHEET 2

F i g . 2 5 T R U C i r c u i t

3A

2A

2B 5XB

3B

1A

44

1B

10XB

SEE SHEET 1

G

TRU

150A

A

B

B

C

C

41

3XBA

3XBA

41

44

3XBB

E 2XB

15

B1 6XB A1

SEE SHEET 1

D

3XBB H

A


B1 7XB A1

AC TRU

1XB

D o r n i e r

DC

A A 3XB

40

INTERLOCK X1 X1

B

X2 6XB

B C 3XB

X2 7XB

41

42

43

44

W S O 5148 51 51

S O 2727 41

S O 2121 44

W S O 5147 51 51

+

X1 9XB

45

46

47

48 S O *25 *26

28V/DC

X2

49

50

51

EICAS

52

53

54

55



DORNIER LUFTFAHR


Power Supply

Component

BUS

Circuit Breaker

TRU Circuit

ESS 3PP

AC TRU 10XR

No.

TRU Circuit

The supply relay is a two-part relay and is equipped with two excitation coils (A and B). It locks in the respective end position. When the guarded switch TRU 5XB is set to one of the AC alternator part-systems which is in operation (1 or 2), the Emergency DC Power System is switched on. The relay 6XB (or 7XB) is supplied with 115 VAC (Phase C) and is energized. It connects via its contacts the voltage supply to the supply relay 3XB and at the same time switches one of the AC alternator part-systems to the DC ESSENTIAL BUS 3PP. When the excitation coil A (or B) is supplied with AC electrical power from the supply relay 3XB, its main contacts supply three phase AC electrical power to the transformer rectifier unit (TRU) 1XB. At the same time the auxiliary contacts of relay 9XB are energized, which automatically interrupt the supply to the change-over relay 10PP-A and 10PP-B (within the DC Electrical Load Distribution). Thus the DC ESSENTIAL BUS 3PP is disconnected from the DC bus-bar network. The 28 VDC supplied by the TRU 1XB is now supplied as an emergency voltage to the DC ESSENTIAL BUS 3PP. Additionally the DC supply for the AC system is switched to the ESSENTIAL BUS 3PP.


TRAINING MANUAL


24-40 EXTERNAL POWER General

This section provides information on the External Power Sub-system. The connection of the AC-GPU is made via the external power plug located on the left side near the main landing gear, and the connection of the DC-GPU via the external power plug located on the fuselage nose section. The External Power chapter is divided into the following sub-subsystems: - AC external power - DC external power AC External Power

AC external power supplies the 115V/400Hz AC Bus 1/2 during maintenance work or AC tests on ground. DC external power

The DC external power supplies the DC electrical load distribution system during maintenance work or starting preparations on the ground. In addition the DC external power is used to supply the AC-inverters and also f or starting the engines.


DORNIER LUFTFAHR


24-41 AC EXTERNAL POWER GENERAL

GROUND POWER PROTECTION UNIT 6XD

AC POWER CONTROL UNIT 2VE – AC EXTERNAL POWER RELAY 2XD – 115 / 200 VAC BUS 1 1XP

RELAY BOX 4VE – RELAY 7XD

AC EXTERNAL POWER PLUG 1XDA – CIRCUIT BREAKER 4XD

ELECTRIC

DC NON-ESS 1

O F F

BUS 1

B US 2

ESSENTIAL

N ON -E SS 2

O F F

AC BUS 1

BUS 2

FAIL

FAIL

OFF ALT LH

OFF TRU

ALT RH


TRAINING MANUAL


- AC external power relay 2XD - Relay 7XD - AC external power plug 1XD. FIN

Component

Panel

Zone

Access Door

5XD 6XD 2XD 7XD 1XD 4XD 3XD

Switch light EXT Ground power protection unit AC-external power relay Relay AC-external power plug Circuit breaker 50A Circuit breaker AC EXT/5A

30PP

210 221 221 221 130 130 210

221-BZF 221-LZF 221-BZF 131-CL 131-CL

2VE 4VE

18VE

INTERFACE TO OTHER SYSTEMS Indicating

The AC external power system sends a signal to the electronic indicating, caution and advisory system (EICAS). The signal is used to display system status messages. The status messages are displayed on the ELEC page. AC Alternator System


DORNIER LUFTFAHR


OPERATION N

A

B

C

E

4PP

F

1XD

1

3XD 2

5XD 4XD

X

X

X

X

X

X

C3 C2

A B C K L

B3

A3

C1 B2 B1 A2 A1

M

F

N

6XD H

J

D

E

X

7XD

X

H

X

G

2XD


TRAINING MANUAL


SYSTEM INDICATIONS

BUS 1

115 V

AC–POWER

115 V

115 V

115 V

115 V

115 V

ON

BUS 2

ESS–DC

EXT ALT LH

TRU

Fig. 28 External AC Indications

ALT RH


DORNIER LUFTFAHR


24-42 DC EXTERNAL POWER GENERAL FUSE 2PD FUSE 16PD DC EXTERNAL POWER PLUG 1PD DC EXTERNAL POWER PANEL 25VE – SWITCH / LIGHT 10PD – CONTROL CIRCUIT BREAKER 8PD DIODE 6PD, 11PD, 12PD, 13PD, 14PD

O F F

RELAY SUPPORT 5VE – RELAY 7PD, 15PD

ELECTRIC

DC NON-ESS 1

DC POWER CONTROL UNIT 1VE – DC EXTERNAL POWER RELAY 5PD – 28 VDC MAIN BUS 1 – BATTERY RELAY 3PA, 13PA

BUS 1

B US 2

ESSENTIAL

N ON -E SS 2

O F F

AC BUS 1

BUS 2

FAIL

FAIL

OFF

OFF


TRAINING MANUAL


The DC external power system has the following main components: - Switch/light EXT 3PD - Bus power control unit 20PC - DC external power relay 5PD - DC external power plug 1PD - Switch/light 10PD - Relay 7PD, 15PD. FIN

Component

Panel

Zone

3PD 5PD 1PD 10PD 7PD 15PD 20PC 8PD 2PD 16PD 6PD 11PD 12PD 13PD

Switch Light EXT DC-External Power Relay DC-External Power Plug Switch Light Relay Relay Bus Power Control Unit Circuit Breaker 5A Fuse 400A Fuse 400A Diode Diode Diode Diode

30PP 1VE

210 221 123 123 210 210 210 123 123 123 123 123 123 123

25VE 5VE 5VE 25VE

25VV-2 25VV-2 25VV-1 25VV-1

Access Door 221-LZF 123-BL 123-BL

213-DZW 123-BL 211-MZF 211-MZF 211-LZF 211-LZF 211-LZF 211-LZF


DORNIER LUFTFAHR


This section provides information on the DC External Power Sub-subsystem and components. The 28 VDC GPU is connected to the DC external power plug 1PD. When the DC external power system is operated the autonomous power supply is switched off and the priority is given to the external power system. The bus TIE relay 9PP automatically makes the bus-bar contact between the DC MAIN BUS 1 and DC MAIN BUS 2. Bus Power Control Unit 20PC

The BPCU protects the DC electrical power supply against overvoltage and incorrect polarity when an external power source is connected

3 2 E f f 8 -1 e c t 0 0 vi i M t y : o d .1 0

O P E R A T I O N

EXT. 8PD 6PD

1PD

A1

B1

A2

B2

E A1 500A

LT

2PD

E

10PD 20PC

A2



F i g . 3 0 E x t er n a l D C C i r c u i t D i a gr a m

5PD

15PD 11PD

13PD

12PD

14PD

X1

DATA AQUI UNIT (EICAB) SIG 522 (DC EXT. POWER STATUS)

A2 A1

A3

X2

MAIN-BUS 1

3 PA 49

47

50 U1 48

10PX

13PX

12PX

NOT USED

ON

ON

13 PA

11PX -

AVAIL

+ X1


BUS PROTECTION/ CONTROL UNIT

5PD

X2

7

8

9 W S O 24 25

5PD

2LF

7PD 10

11

12

13

14


15 W S O 17 19 40

16

17

18

19 W S O 7 16 16 16

20

D o r n i e r



DORNIER LUFTFAHR

If there is no overvoltage or incorrect polarity (when the DC GPU is connected and switched on) the BPCU 20PCU releases the control for the switch-in. At the same time the relay 7PD is energized which, when the aircraft is without electrical power (if the proximity sensor electronic unit 6GA is not supplied), permits the switch-in of the GPU. The green light AVAIL 11PX comes on. In addition, the annunciator NOT USED 10PX located in the switch/light 10PD (25VE) comes on. It provides optical indication that the aircraft's own power supply is not switched on. If the switch/light EXT 3PD is now pushed, the two batteries and the two S/Gs, if switched in, are disconnected from the DC MAIN BUS 1 and DC MAIN BUS 2. The de-energized contacts of the battery relay 3PA and 13PA connect the positive control to the EPR 5PD. The negative control now switches in the BPCU 20PC. The energized EPR now switches with its main contacts the 28 VDC external power supply to the DC MAIN BUS 1 via the fuse 2PD (600A). At the same time, via auxiliary contacts, the relay 15PD is energized which interrupts the supply circuit to the light AVAIL and permits the white annunciator ON 12PX (and annunciator ON 13PX) to come on. The latter indicate the switched in condition of the DC electrical load distribution system. The bus TIE relay 9PP, which belongs to the DC electrical load distribution system, automatically supplies the DC MAIN BUS 2 (controlled by the BPCU 20PC). The switch/light 10PD located on the DC external panel 25VE permits, when pushed, a check of all the annunciators which are installed in it. The switching off procedure of the GPU must only be made after the aircraft's own system has been switched off, when the S/Gs are going to take over the supply. As a result, the annunciator NOT USED 10PX located on the DC external panel 25VE must come on. Thus a disconnection in the event of an excessive load is prevented.

SYSTEM INDICATIONS


TRAINING MANUAL


24-50 AC ELECTR. LOAD DISTRIBUTION GENERAL C / B PANEL 18VE – 115 VAC BUS 3XP – 26 VAC BUS 4XP – 115 VAC BUS 5XP – 26 VAC BUS 6XP

DC POWER CONTROL UNIT 1VE – 28 VDC MAIN BUS 1 (2) – CIRCUIT BREAKER 1XR, (5XR) C / B AND RELAY PANEL 35VE – 115 / 200 VAC BUS 1 1XP – 115 / 200 VAC BUS 2 2XP

RELAY BOARD 4VE – RELAY 23XR, 28XR

ELECTRIC

DC NON-ESS 1

O

AC POWER CONTROL UNIT 2VE – ALTERNATOR LINE RELAY 3XA (13XA)

BUS 1

BU S 2

N ON -ESS2

O

AC BUS 1

BUS 2

FAIL

FAIL

ELECTRIC PANEL


DORNIER LUFTFAHR


The AC electrical load distribution system has the following main components: - AC BUS 1/1XP and AC BUS 2/2XP (115/200 VAC frequency-unregulated) - AC BUS 4XP and AC BUS 6XP (26 VAC frequency-regulated) - AC BUS 3XP and AC BUS 5XP (115 VAC frequency-regulated) - Switch/light TIE 2XR. FIN

Component

Panel

Zone

Access Door

1XP 2XP 4XP 6XP 3XP 5XP 2XR

AC Bus 1 115/200 V AC AC Bus 2 115/200 V AC AC Bus 26 V AC AC Bus 26 V AC AC Bus 115 V AC AC Bus 115 V AC Switch Light TIE

35VE 35VE 18VE 18VE 18VE 18VE 30PP

221 221 210 210 210 210 210

221-PZF 221-PZF

INTERFACE TO OTHER SYSTEMS Indicating

The AC electrical load distribution system sends signals to the electronic indicating, caution and advisory system (EICAS). The signals are used:

3 2 E f f 8 -1 e c t 0 0 vi i M t y : o d .1 0

GCU

ALT. 1 ~ D A



B

C

F i g . 3 3 A C D i s t r i b u t i o n

A

INTERLOCK

C D

2XP

A

B C

B

INTERLOCK

1P

A


GCU

ALT. 1 ~

TRU

B BUS 1

O P E R A T I O N

C A

B

C

D

EXT POWER

BUS 2

s i T h d e e w s i u t h p p 2 l 8 y V o f D t h C e . f r e q u e n c y -r e g u l a t e d b u s b a r n e t w o r k o n t h e g r o u n d c a n o n l y b e a c h i e v e d o n t h e i n p u t

f r O o n m t h a e G g P r U o u n v d i a t t h h e e A f r C e q u e x e n t e c r n y a u l p n r o e w g e u l r a p t e l d u g b . u s b a r n e t w o r k c a n b e s u p p l i e d d i r e c t l y w i t h 1 1 5 / 2 0 0 V A C


D o r n i e r



DORNIER LUFTFAHR


AC BUS1/1XP and AC BUS2/2XP (115/200 VAC Unregulated Frequency)

During normal operation, the two AC alternators (1XA-1 and 1XA-2) supply the two three-phase AC bus-bars (AC BUS1 and AC BUS2). If one of the ALTs malfunctions, the AC bus which is no longer supplied can be switched to the ALT which is still in operation via the switch/light TIE 2XR. When the Coil B of the ALR 3XA (or 13XA) is energized, after pushing the switch/light TIE (supplied by the contacts of Coil A), the corresponding ALR (3XA or 13XA) now makes the bus-bar connection. The white light 7XX (in switch/light) now indicates with a bar-symbol that the TIE connection is made. The AC bus-bars of the aircraft's frequency-unregulated AC power supply, and the related circuit breakers, are located in the C/B and relay panel 35VE. AC BUS 3XP, 4XP, 5XP and 6XP (26/115 VAC Regulated Frequency)

During normal operation the two AC inverters (1XE and 2XE) supply the two AC bus-bars with different voltages (26 V and 115 V, 400 Hz). If one of the INV malfunctions there is an automatic switchover, of the AC bus-bar which is no longer supplied, to the INV which is still in operation. If there is a reduction of the DC-voltage on the DC NON ESS BUS2/5PP, the INV 1XE which is still supplied from the DC ESSENTIAL BUS 3PP takes over the supply of the AC BUS 3XP, 4XP, 5XP and 6XP ((DMC D1-A-24-22-00-00Y-099Y-A). The AC bus-bars of the frequency-regulated AC power supply, and the related circuit breakers, are located in the C/B panel 18VE.

SYSTEM INDICATIONS

0 V

AC–POWER

115

V


TRAINING MANUAL


24-60 DC ELECTR. LOAD DISTRIBUTION GENERAL BATTERY JUNCTION BOX RH 7VE – DC HOT BUS 2 7PP – BPCU CIRCUIT BREAKER 24PC

C / B SIDE PANEL RH / 10VE – 28 VDC NON ESS BUS 2 5PP – NON ESS 2 IND CIRCUIT BREAKER 2PX

DC POWER CONTROL UNIT 1VE – 28 VDC MAIN BUS 1 (2) – BUS TIE RELAY 9PP – CHANGE OVER RELAY 10PP-A / 10PP-B – NON ESS BUS RELAY 4PR, 7PR – CIRCUIT BREAKER 2PR, 5PR – FUSES 11PP, 12PP, 13PP, 14PP, 15PP,16PP C/B AND RELAY PANEL 36VE – DC HCT BUS 7PP/1 (DISPLAYS)

C / B SIDE PANEL LH / 11VE – 28 VDC NON ESS BUS 1 1PP – NON ESS 1 IND CIRCUIT BREAKER 1PX

BATTERY JUNCTION BOX LH 6VE – DC HOT BUS 1 6PP – BPCU CIRCUIT BREAKER 23PC

DC VOLTMETER 20PX ELECTRIC

DC NON-ESS 1

SWITCH / LIGHT 6PR (NON ESS 2)

BUS 1

B US 2

N ON- ESS 2

AC BUS 1

BUS 2


DORNIER LUFTFAHR


FIN

Component

Panel

Zone

Access Door

1VE 1VE 12VE 11VE 10VE 12VE 12VE 12VE 12VE 12VE 6VE 7VE 36VE 1VE 1VE 1VE 1VE 1VE 30PP 30PP 30PP

221 221 210 210 210 210 210 210 210 210 130 130 221 221 221 221 221 221 210 210 210

221-LZF 221-LZF

1PP 5PP 2PP 4PP 2PP/1 2PP/2 3PP 6PP 7PP 7PP/1 9PP 10PP-A 10PP-B 4PR 7PR 1PR 3PR 6PR

DC MAIN BUS 1 DC MAIN BUS 2 DC HYD SUB BUS DC NON ESS BUS 1 DC NON ESS BUS 2 DC BUS 1 DC BUS 2 DC EM PWR BUS DC EM PWR BUS DC ESSENTIAL BUS DC HOT BUS 1 DC HOT BUS 2 DC HOT BUS (Displays) BUS TIE Relay Changeover Relay Changeover Relay NON ESS BUS Relay NON ESS BUS Relay Switch/Light TIE Switch/Light (NON ESS 1) Switch/Light (NON ESS 2)

131-BL 132-BR 221-PZF 221-LZF 221-LZF 221-LZF 221-LZF 221-LZF


TRAINING MANUAL


- to display caution messages in the event of a system malfunction (DC bus-bars synoptics) - to indicate the status of the DC TIE by synoptics - to display digital DC power control. Note:

A detailed description of the system malfunctions indicated in the CAS-field (primary EICAS page) is not given here, refer to the related system description The caution messages are displayed on the ELEC page. The status of the DC bus-bars is shown by busbar synoptics. Different colours are used to indicate the status: - amber indicates an abnormal status - green indicates normal status. Control and Dimming (Chapter 33 - LIGHTS)

The brightness or dimming of the lights in the switch/lights 3P3, 6PR (NON ESS 1 and 2) and the switch/light TIE 1PR is controlled by the switch DAY-NIGHT (in field INTLIGHT) on the overhead panel. This also applies for the synoptic presentation DC ESSENTIAL bus in the field ELECTRIC. The annunciators and lights are connected to the dimmer 2LF. A check of the lights can be made with the pushbutton TEST which is also installed in the field INT-LIGHT. The annunciators and lights are switched on via the diode U1. Landing Gear (Chapter 32 - LANDING GEAR)

The relay 31GA supplies control signals to the BPCU 20PC about the air or ground operation of the aircraft. It also interrupts the priority switching for the external voltage supply on the ground. In addition


DORNIER LUFTFAHR

Bus Power Control Unit 20PC

With the aid of its electronics the BPCU monitors the current and voltage in the system. It switches all the current and voltage signals in the correct sequence. The control signals have the following functions: - Switch on of the batteries - Control of the TIE relay 9PP - Control of Changeover Relay 10PP-A, 10PP-B (see DC ESSENTIAL BUS 3PP) - Control of Non-Ess Bus Relay 4PR, 7PR (see DC NON ESS BUS 1 and 2) In addition the BPCU automatically triggers switching procedures which, according to the supply of the DC electrical load distribution system, ensure the connection of the bus-bars. The BPCU, controlled by the relay 31GA on the landing system, also recognizes whether the aircraft is operating on the ground or in the air and interrupts the priority operation of the external power supply. If overloading or short circuits occur on one of the bus-bars, or if a malfunction occurs, the fault is localized and the defective DC bus is switched off. The load-shedding is made after a reaction time of 3-4 seconds (for the fuses) and the relays are switched off in a pre-determined sequence (0,3 second cycle). If the supply of the distribution system is made on the ground by a DC GPU the BPCU 20PC protects against reverse polarity and overvoltage. The BPCU is installed in the LH avionic rack.

Dornier 328 DORNIER LUFTFAHRT OPERATION

TRAINING MANUAL



DORNIER LUFTFAHR

DC MAIN BUS 1 and DC MAIN BUS 2

The DC MAIN BUS 1 and DC MAIN BUS 2 is the central supply point for the system. All powergenerating and power-consuming systems are connected via these bus-bars. The DC MAIN BUS 1 supplies the DC NON ESS BUS 1/1PP, the DC BUS 1/2PP and the DC EM PWR BUS 2PP/1. The DC MAIN BUS 2 supplies the DC BUS 2/4PP and the DC NON ESS BUS 2/5PP. The supply of the DC ESSENTIAL BUS 3PP can be made either from the DC MAIN BUS 1 or from the DC MAIN BUS 2 or, if a voltage failure occurs, from the 28 VDC emergency supply (TRU 1XB). The DC MAIN BUS 1 and DC MAIN BUS 2 are installed in the DC Power Control Unit 1VE. DC BUS 1/2PP and DC BUS 2/4PP

The DC Bus 1 is permanently connected via the fuse 12PP (150 A) with the DC MAIN BUS 1, and the DC Bus 2 is connected via the fuse 14PP (150 A) with the DC MAIN BUS 2. If a malfunction of one of the two starter generators occurs, they must remain supplied. Both of the two DC bus-bars and the related circuit breakers are installed in the overhead C/B panel 12VE. DC EM PWR BUS 2PP/1

During emergency operation (when the aircraft's DC voltage supply fails) the DC EM PWR BUS supplies the necessary NAV-systems from the Emergency Power Supply 2FM. During normal operation the emergency power supply (emergency battery) is charged by the DC BUS 1/2PP. The DC EM PWR BUS is installed in the overhead C/B panel 12VE. DC NON ESS BUS 1/1PP and DC NON ESS BUS 2/5PP

The DC NON ESS BUS 1 and DC NON ESS BUS 2 can be switched off and operated manually via the


TRAINING MANUAL


The DC ESSENTIAL BUS is then disconnected from the DC MAIN BUS 1 and DC MAIN BUS 2 (by the Changeover Relay). The bus-bar symbol with the text ESSENTIAL, which is displayed in the field ELECTRIC, is illuminated by the amber lights 22PX, 23PX and stays on as long as the voltage supply is connected. The DC ESSENTIAL BUS and the related circuit breakers are installed in the overhead C/B panel 12VE. DC HOT BUS 1/6PP and DC HOT BUS 2/7PP

The battery bus-bars are connected directly to the batteries. They supply the emergency systems if a total failure occurs. Both the batteries are charged via the battery relays 3PA and 13PA with 28.5 VDC (from the starter/generators) and are protected against reverse current. The DC HOT BUS 1 and the related circuit breakers are installed in the battery junction box LH/6VE and the DC HOT BUS 2 is installed in the battery junction box RH/7VE. DC Hot Bus 7PP/1

This bus is connected via a fuse to the DC HOT BUS 2 and supplies the displays during engine start. DC HYD SUB BUS

The HYD BUS is normally supplied by the ESS BUS or in case of a malfunction by BUS 1 via relay 24DA. Bus TIE Relay 9PP

The bus TIE relay 9PP, which is installed between the DC MAIN BUS 1 and the DC MAIN BUS 2, is open when both of the two starter/generators are operating normally. The white bar-symbol 16PX contained in the switch/light TIE 1PR indicates the disconnected condition of both DC MAIN BUSES. If


DORNIER LUFTFAHR



MFD PAGE Indication

AMBER

AMBER

DC BUS 1 FAIL

Synoptic DC Bus 1

AMBER

AMBER

DC BUS 2 FAIL

Synoptic DC Bus 2

AMBER

AMBER

ESS BUS FAIL

Synoptic ESS Bus

NON–ESS1

1

Fault or Condition Indicates status of DC BUS 1

Indicates status of DC BUS 2

Indicates status of ESS BUS

DC–POWER

2

NON–ESS2

ESSENTIAL 28.5 V

200 A

28.5 V

200 A


TRAINING MANUAL


INDEX AC Alternator System AC ELECTR. LOAD DISTRIBUTION AC External Power AC Inverter System Alternator 1XA-1 (1XA-2) Alternator control unit 2XA (12XA) Battery 1PA, 11PA Battery System Bus Power Control Unit (BPCU) 20PC DC ELECTR. LOAD DISTRIBUTION DC Electrical Load Distribution System

8 57 47; 48 8 12 13 41 25 30 62 53

DC external power 47; 52 DC Relay Box (1VE) 37 DC Starter/Generators 25 Emergency DC Power System 25; 43 Generator Control Unit 2PC (12PC) 30 Ground Power Protection Unit 6XD 49 Hall Effect Sensors 3PC (13PC), 4PC-1 (4PC-2) 30; 35 Inverter 1XE, 2XE 21 Inverter Circuit 23 Starter/Generator 1PC-1 (1PC-2) 29 Siehe TRU Circuit 46

LIST OF ILLUSTRATIONS Fig. 1 Electric Panel................................................................................................................................................................................................5 Fig. 2 Electric Bus System .............................................................................................. .......................................................................................6 Fig. 3 AC Generation - Basic Configuration..........................................................................................................................................................7 Fig. 4 Parts Location - Alternator System.................. .............................................................................................................. ..............................9 Fig. 5 Alternator Function ................................................................................................. .................................................................................. .12 Fig. 6 Alternator Circuit .................................................................................................. ..................................................................................... 14 Fig. 7 ALR Control Circuit .............................................................................................................. .................................................................... 15 Fig. 8 AC Relay Box 2VE....................................................................................................................................................................................17 Fig. 9 AC System Indications .......................................................................................................... .................................................................... 18 Fig. 10 Parts Location - Inverter System..............................................................................................................................................................19 Fig. 11 Inverter Circuit.........................................................................................................................................................................................22 Fig. 12 Inverter System Indications......................................................................................................................................................................23

24 Electrical

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