SPYDER ELECTRICAL

AC power is provided by (BLANK), one on each engine, by the (BLANK), or from (BLANK). (1.20) (p 1-265)

Four IDGs; APU generator; external power

The 28 VDC power is normally provided by (BLANK) that convert AC power from the AC system to DC power. (1.20) (p 1-265)

Two Regulated Transformer-Rectifier Units (RTRUs)

Two (BLANK) augment the DC power system. (1.20) (p 1-265)

24-volt batteries

What is an IDG? (1.20.1.1) (p 1-266)

The Integrated Drive Generator is a Constant Speed Drive (CSD) and an AC generator 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.

What does the GCU do? (1.20.1.2, p 1-266)

Protect from: over/underexcitation, over/under voltage, over/under frequency unbalanced current, neutral current faults, differential faults

How many AC Buses compose the AC Electrical System? (1.20.1.6, p 1-269)

17 AC buses

What does a GEN OUT light mean? (1.20.1.8, p 1-272)

A fault is preventing the GR from closing, indicating that IDG or GCU is not operating within its specified limits.

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 from electrical system if the oil temperature rises above a preset limit.

When does the EMERG GEN EMERG PWR light come on? (1.20.1.8, p 1-273)

Emergency generator is operating & supplying power to the associated buses

DC power is normally supplied by (BLANK) operating in parallel. (1.20.2, p 1-273)

2 Regulated Transformer Rectifier Units (RTRUs)

The battery is capable of supplying DC power to the Isolated DC, Avionics Isolated DC, Emergency DC, & Battery busses for a min of (BLANK) minutes. (1.20.2.1) (p 1-274)

30

The BCEM (Battery Control Electronics Module) is programmed to perform the what three functions? (1.20.2.2) (p 1-274)

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

Which two buses are "hot-wired" to the battery and subsequently also powered during 7 and 3 bus ops? (1.20.2.3)

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

How many DC Buses compose the DC Electrical System? (1.20.2.3, p 1-275)

16 buses

Principal components of the emergency power system include what 4 components? (1.20.3) (p 1-278)

Hydraulic Motor Generator (HMG)

Battery (54 amp-hr)

BCEM

Emergency RTRU (100 amp)

The hydraulic motor generator (HMG) is powered by hyd system # (BLANK). (1.20.3) (p 1-278)

2

With a loss of ALL AC power, will the Emergency Generator automatically come on? (1.20.3) (p 1-278)

YES

With a loss of ALL DC power (no loss of AC power), will the Emergency Generator automatically come on? (1.20.3) (p 1-278)

NO

What are the minimum speeds required for the RAT to drive the emergency generator and to operate the flight controls? (3.23) (p 3-66.2)

Below 15,000 ft - 175 KCAS

Above 15,000 ft - 190 KCAS

155 KCAS minimum is required to power flight instruments from the emer AC, iso AC, avionics iso AC buses

During 7 bus ops, what are the only reliable displays? (3.33, p 3-92)

Pilot Left & Center MFDUs & CPs Left MFDU

During 3 bus ops, what are the only reliable displays? (Figure 3-28, p 3-302)

Pilot Left & Center MFDUs are only reliable displays

On the Electrical Fire checklist, why do you turn off the autopilot BEFORE turning the emergency generator on? (3.33, p 3-89)

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

During 7 bus ops, which indicators may be unreliable in icing due to loss of pitot heat? (3.33, p 3-92)

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

On the Electrical Fire checklist, what should you do before telling the engineer to turn the generators off? (3.33, pg 3-92)

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

With a loss of DC power (no AC loss), the battery will be supplying power to what 5 things? (3.78.4) (p 3-295)

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

What makes the emergency generator come on (3 times)? (3.78.9, p 3-298)

Loss of power to the Emergency Bus Power Relay

Lose all 4 generators

Place the Instrument Power Switch to ON

What are the pilot indications of loss of normal DC power? (no ref)

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

Name the 3 buses powered during 3 bus ops: (3.78.9, p 3-298)

Emergency AC

Emergency DC

Battery Bus

Name the 7 buses powered during 7 bus ops: (3.78.9, p 3-298)

Isolated AC

Avionics Isolated AC

Emergency AC

Isolated DC

Avionics Isolated DC

Emergency DC

Battery Bus

FYI → What do you have with 7 bus operations? (3.78.9, p 3-298)

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. Must manually extend landing gear: (1-290)

a) Gear Handle (uses Main DC...inop on 7-bus)

b) Emer Ext Switches (uses Main DC...inop on 7-bus)

c) Emer Ext Motors (uses Main AC...inop on 7-bus)

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 - Normal Power

2. VIA 2 - Alternate Power

3. SCADC 1

4. Pilot CCD / Pilot CNP

5. TCAS

6. Backup Integrated Processor (BIP)

7. Master Caution System

8. Interphone & Bailout alarm

9. Engine Instrumentation (if selected)

10. RAT Control

11. Manual Pitch Trim only

12. Engine 1, 2, 3, 4 start ignition

13. SAI (Battery bus & Emer DC bus)

14. PRESS DOOR, UNPRESS DOOR, MAIN SUMP LOW all ON

What major items do you lose with 7 bus operations? (Figure 1-79, pages 1-281 thru 1-293)

a. Engine anti-ice

b. Windshield heat

c. AFCS

d. Augmentation system

e. Engine fire detection

f. Thrust reversers

g. Taxi/leading edge/landing lights

h. ADFs & TACANs

i. Stallimiter

j. Normal/emergency gear extension

k. Flap asymmetry protection

l. Slats will decouple on first extension/retraction

m. Flap/Slat position indicators (consider lowering incrementally)

What do you have with 3 bus operations? (3.78.9, Figure 3-28) (p 3-302 thru 3-304)

a. INSTRUMENTATION:

1. Pilot Center and Left MFDUs

b. NAVIGATION:

1. Basically VFR → vectors via UHF #3

2. IFF & MIRS

3. SAI

4. EGI #1

5. Mag compass

c. COMMUNICATIONS:

1. UHF No. 3 only

d. PILOT/COPILOT LIGHTING:

1. Pilot instrument flood light

2. Mag compass light

e. LANDING GEAR:

1. Must manually "button down" extend landing gear: (1-290)

a) Gear Handle (uses Main DC...inop on 7-bus)

b) Emer Ext Switches (uses Main DC...inop on 7-bus)

c) Emer Ext Motors (uses Main AC...inop on 7-bus)

f. FLAPS AND SLATS:

1. Landing conditions permitting, consider 40% flap approach

2. No flap/slat protection and no detection

3. Slats will overrun and decouple on first movement

g. FIRE PROTECTION:

1. Engines & APU = protection only, no detection

h. MISCELLANEOUS:

1. Manual Pitch trim ONLY (hot lever, triggers not required)

2. Left AC pack only (no temp control)

3. Pitot heat

4. RAT control - AUTO & MANUAL

What major items do you lose with 3 bus operations? (3.78.9), Fig. 3-28, p 3-302 thru 3-304

a. Airstart capability

b. Fire Suppression system (FSS)

c. Flap asymmetry detection and protection

d. Yaw aug manual trim

e. Flight augmentation (1-281)

f. Gear position indicators or warning systems

g. Floor heat and Right AC pack

h. Anti-skid brakes

i. V/UHF #1

j. P CNP

k. CP MCDU & Left MFDU

l. BIP capability

m. Normal and Alternate Pitch Trim (Manual Levers only)

The generator control unit will enter a shutdown state if it does not sense the correct frequency and voltage within approximately 10 seconds after starting the generator. How do you restart the emergency Generator? (3.78.9, p 3-298)

Placing the INST POWER switch to OFF and then EMERG.

If the emergency generator does not come on automatically following a power failure you should: (3.78.9) (p 3-298)

Turn the INST POWER Switch to OFF, then EMERG.

What is the maximum time for the landing lights if they are not fully extended? (1.21.1.1) (p 1-360)

25 minutes