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C-5 Eval Guide > Electrical > Flashcards

Electrical Flashcards

1
Q

AC power is provided by _________, one on each engine, by the ________________, or from _____________.

A

Four IDGs; APU generator; external power

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2
Q

The 28 VDC power is normally provided by ___________________________ that convert AC power from the AC system to DC power.

A

Two Regulated Transformer-Rectifier Units (RTRUs)

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3
Q

Two ____________ augment the DC power system.

A

24-volt batteries

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4
Q

How much power is produced by each generator?

A

90 KVA continuous steady state, the overload and fault current capacity is based on 75 kVA.

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5
Q

How much power is produced by each APU generator?

A

6.5 KVA, provides up to 3.0 kVA emergency power to the isolated and emergency AC buses, and up to 3.5 kVA emergency power through the 100 AMP, 28 VDC emergency power RTRU to the isolated DC, emergency DC, and battery buses.

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6
Q

Does the C-5M have CSDs?

A

No, the C-5M has IDGs (4)

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7
Q

What is an IDG?

A

 The Integrated Drive Generator is a CSD and an AC generator mounted side by side in a common housing mounted on the accessory pad of each engine, and cannot be disconnected from the engine.
 The IDG converts a variable input speed, mechanical power, to constant frequency 400 Hz AC electrical power.
 Each IDG contains a PMG which supplies, through its associated Generator Control Unit (GCU), an independent source of power for control and excitation.

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8
Q

What does the GCU do?

A

Protect from: over/underexcitation, over/under voltage, over/under frequency unbalanced current, neutral current faults, differential faults
perform voltage regulation, contactor control, and protection functions for each generating channel in conjunction with the controls located at the flight engineer electrical panel.

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9
Q

How many AC Busses compose the AC Electrical System? What are they?

A

There are 17 AC buses that are used to distribute power to airplane equipment:
 8 main buses (forward and aft for each generator)
 2 monitor buses (one each for generators No. 2 and No. 3)
 4 avionics buses (avionics AC buses 1, 1A, 2, and 2A)
 2 isolated buses (isolated AC bus and avionics isolated AC bus)
 1 emergency AC bus

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10
Q

What does a GEN OUT light mean?

A

The IDG uses dual protection against mechanical failure. The input drive shaft is designed to shear if the IDG bearings fail completely. The IDG drive mechanism is automatically disconnected if the oil temperature rises above a preset limit. In either case, the GEN OUT light on the AC Electrical System panel illuminates upon disconnect.

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11
Q

When does the EMERG GEN EMERG PWR light come on?

A

When the emergency generator is operating and supplying power to the associated busses

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12
Q

DC power is normally supplied by _____ operating in parallel.

A

Regulated Transformer Rectifier Units (RTRUs)

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13
Q

The battery is capable of supplying DC power to the Isolated DC, Avionics Isolated DC, Emerg DC, & Battery busses for a min of _____ minutes.

A

30

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14
Q

The BCEM (Battery Control Electronics Module) is programmed to perform the what three functions?

A

 Normal control of airplane battery charging
 Normal and emergency control of battery relay No. 1
 Emergency control of battery fill-in power to the emergency DC bus

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15
Q

Which two buses are “hot-wired” to the battery and subsequently also powered during 7 and 3 bus ops?

A

Hot battery bus connected directly to battery & Avionics battery bus-connected to hot battery bus thru a circuit breaker

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16
Q

How many DC Busses compose the DC Electrical System? What are they?

A

There are 15 buses in the DC system (16 buses IRCM installed):
 2 main DC buses
 5 avionics DC buses (avionics DC buses 1, 1A, 2, 2A, and 2B)
 2 isolated DC buses (avionics isolated DC bus and isolated DC bus)
 1 emergency DC bus
 2 battery buses (airplane and APU)
 1 hot airplane battery bus
 1 avionics battery bus
 1 APU control bus
 1 IRCM DC bus (IRCM installed)

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17
Q

Principal components of the emergency power system include what 5 components?

A 
 Hydraulic Motor Generator (HMG)
 Generator Control Unit (GCU)
 Battery (54 amp-hr)
 BCEM
 Emergency RTRU (100 amp)
18
Q

The hydraulic motor generator (HMG) is powered by hyd system # ____.

A

2

19
Q

With a loss of ALL AC power, will the Emergency Generator automatically come on?

A

YES

20
Q

With a loss of ALL DC power (no loss of AC power), will the Emergency Generator automatically come on?

A

NO

21
Q

The emergency bus power relay (EBPR) is normally controlled by the main generators through the:

A

1 power transfer relay (PTR)

22
Q

What are the minimum speeds required for the RAT to drive the emergency generator and to operate the flight controls?

A

 Below 15,000 ft - 175 kts
 Above 15,000 ft - 190 kts
 155 kts minimum is required to power flight instrumentation (connected to the emer AC, iso AC, avionics iso AC busses)

23
Q

During 7 bus ops, what are the only reliable displays?

A

Pilot Left & Center MFDUs & CPs Left MFDU

24
Q

During 3 bus ops, what are the only reliable displays?

A

Pilot Left & Center MFDUs are only reliable displays

25
Q

On the Electrical Fire checklist, why do you turn off the autopilot BEFORE turning the emergency generator on?

A

To prevent abrupt pitch oscillations when power is removed from avionics DC busses #1 & #2

26
Q

During 7 bus ops, which indicators may be unreliable in icing due to loss of pitot heat?

A

Standby Attitude Indicator (SAI) & Nav altimeter/airspeed indicator

27
Q

On the Electrical Fire checklist, what should you do before telling the engineer to turn the generators off?

A

Establish level flight to ensure suction fuel feed into engines (will lose fuel tank boost pumps)

28
Q

The IDG 1 (2, 3, or 4) OIL caution will display if:

A

 IDG oil pressure is low
 oil differential is high due to a clogged filter
 oil temperature is high

29
Q

What makes the emergency generator come on (3 times)?

A

 The Emergency Bus Power Relay is de-energized
 Lose all 4 generators
 Place the Instrument Power Switch to ON

30
Q

With a loss of DC power (no AC loss), the battery will be supplying power to what 5 things?

A

Hot battery bus, Battery bus, Emergency DC bus, Iso DC bus and Avionics Iso DC bus

31
Q

What are the pilot indications of loss of normal DC power?

A

 Slats indicate INTRANSIT
 Flap points off scale (11 o’clock –A; 9 o’clock – B)
 Airspeed indicator on PFD goes RED
 P right MFDU & MCDU inop; jump seat MCDU inop
 CP center & right MFDU, CCD & CNP inop

32
Q

Name the 3 buses powered during 3 bus ops:

A

 Emergency AC
 Emergency DC
 Battery Bus

33
Q

Name the 7 buses powered during 7 bus ops:

A 
 Isolated AC
 Avionics Isolated AC
 Emergency AC
 Isolated DC
 Avionics Isolated DC
 Emergency DC
 Battery Bus
34
Q

FYIWhat do you have with 7 bus operations?

A

a. INSTRUMENTATION:
1) Pilot Center and Left MFDUs
2) Copilot Left MFDU (can show ENG display using CCD x-side)
3) Copilot MCDU

b. NAVIGATION:
1) EGI No. 1
2) IFF
3) Micro IRS
4) MMR No. 1

c. COMMUNICATIONS:
1) V/UHF No. 1
2) UHF No. 3
3) Pilot/FE Interphone
4) Flight Station Interphone
5) Forward Cargo/Troop Compartment Interphone

d. PILOT/COPILOT LIGHTING:
1) Pilot Instrument Flood Light
2) Annunciator Control
3) Master Caution Control

e. LANDING GEAR:
1) Antiskid
2) Gear handle & emergency extend switches – inop (must manually extend gear)

f. FLAPS AND SLATS:
1) Landing conditions permitting, consider 40% flap approach.
2) Flap Asymmetry Protection – inoperative
3) Slats will overrun and decouple on first movement

g. FIRE PROTECTION:
1) APU Fire Detection and Protection
2) Engine Fire Protection
3) Engine Fire Detection – inoperative
4) FSS

h. MISCELLANEOUS:
1) VIA 1
2) VIA 2 – Alternate Power
3) SCADC 1
4) Pilot CCD
5) Pilot CNP
6) TCAS
7) Backup Integrated Processor (BIP)
8) Master Caution System
9) Interphone & Bailout alarm
10) Engine Instrumentation (if selected)
11) RAT Control
12) Manual Pitch Trim only

35
Q

What major items do you lose with 7 bus operations?

A

a. Engine anti-ice
b. Windshield heat
c. AFCS
d. Engine fire detection
e. Thrust reversers
f. Taxi/leading edge/landing lights
g. ADFs
h. TACANs
i. Stallimiter
j. Normal/emergency gear extension
k. Flap asymmetry protection
l. Slats will decouple on first extension/retraction

36
Q

What do you have with 3 bus operations?

A

a. ENGINE INSTRUMENTS – None initially (can be put on Pilot left MFDU)

b. FIRE PROTECTION:
1) Engines & APU = protection only, no detection
2) FSS = Protection (detection only when FSS armed using NW panel)

c. LIGHTS:
1) Pilot’s flood lights
2) Approach plate holder
3) Mag compass light

d. MISC:
1) Manual Pitch trim
2) Left AC pack only (no temp control)
3) Pitot heat
4) RAT control – AUTO & MANUAL
5) Manual gear extension; indicators dont work (must button gear down)
6) Slats will decouple on first extension/retraction

37
Q

What major items do you lose with 3 bus operations?

A

a. Airstart capability
b. Flap asymmetry detection and protection
c. Yaw aug manual trim
d. Master caution warning system
e. Flight augmentation
f. Gear position indicators or warning systems
g. Floor heat
h. Anti-skid brakes
i. Slats will overextend and decouple or retract and decouple depending on when failure occurs

38
Q

When the HMG (emergency generator) is in use and the GCU detects a fault (such as a lack of #2 hydraulic system pressure and/or voltage/frequency out of parameters) the GCU shuts down. What do you have to do to restart the HMG?

A

Recycle the INST POWER switch to OFF and then to NORM or EMERG, as required.

39
Q

What is the maximum time for the landing lights if they are not fully extended?

A

25 minutes

40
Q

Emergency exit lights are powered for how long? How long does it take to charge them?

A

About 45 minutes; 16 hours

C-5 Eval Guide (17 decks)

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