Electrical

BUS L EMER AC OFF

1. EMER PWR SELECTOR - OFF

Move the EMER PWR SELECTOR to the OFF position

DISPLAY UNITS 1 AND/OR 3 OPERATING

IF DISPLAY UNITS 1 AND/OR 3 ARE NOT OPERATIONAL, SKIP TO STEP 2

NOTES

When display unit 1 and/or 3 are operating, the left emergency AC bus is powered.
The left emergency AC bus sensing circuit has failed.
“BUS L EMER AC OFF” level 2 alert and “EMER PWR SW OFF” level 1 alert will be displayed for the remainder of the flight.

If subsequent electrical malfunction(s) occur requiring use of emergency power, rotate EMER PWR selector to ARM or ON and deploy the ADG.

NOTE

The emergency power system is designed to provide power for approximately 15 minutes until the ADG is deployed

No further crew action required.

[END OF BUS L EMER AC OFF CHECKLIST]

2. LAND AT NEAREST SUITABLE AIRPORT

Landing at the nearest suitable airport for aircraft repair.

3. CAPTAIN'S EIS SOURCE SELECTOR - AUX (OR 2)

Move the Captain's EIS source selector to AUX (OR 2)

3. CAPTAIN'S CADC SWITCH - CAPT ON 2

Move the Captain's CADC switch to CAPT ON 2 position.

4. CAPTAIN'S IRS SWITCH - CAPT ON AUX

Move the Captain's IRS switch to the CAPT ON AUX position

ENG IGN NOT ARMED ALERT DISPLAYED

IF ENG IGN NOT ARMED ALERT DOES NOT DISPLAY, SKIP TO IF SUSBEQUENT ELECTRICAL MALFUNCTIONS OCCUR

5. ENG IGN SWITCH - SELECT B

Select ENG IGN switch B.

If subsequent electrical malfunction(s) occur requiring use of emergency power, rotate the EMER PWR selector to ARM or ON and deploy the ADG.

NOTE

The emergency power system is designed to provide power for approximately 15 minutes until the ADG is deployed.

[END OF BUS L EMER AC OFF CHECKLIST]

BUS L EMER DC OFF

1. EMER PWR SELECTOR - OFF

Move the EMER PWR SELECTOR to the OFF position

CAPTAIN'S FLIGHT DIRECTOR AND / OR AUTOPILOT 1 OPERATIONAL

IF CAPTAIN'S FLIGHT DIRECTOR AND / OR AUTOPILOT 1 ARE INOPERATIVE, SKIP TO STEP 2

NOTES

When Captain's flight director and/or AUTOPILOT 1 are operating, the left emergency DC bus is powered.
The left emergency DC bus sensing circuit has failed.
“BUS L EMER DC OFF” level 2 alert and “EMER PWR SW OFF” level 1 alert will be displayed for the remainder of the flight.

If subsequent electrical malfunction(s) occurs requiring use of emergency power, rotate EMER PWR selector to ARM or ON and deploy the ADG.

NOTE

The emergency power system is designed to provide power for approximately 15 minutes until the ADG is deployed.

No further crew action required.

[END OF BUS L EMER DC OFF CHECKLIST]

2. LAND AT NEAREST SUITABLE AIRPORT

Landing at the nearest suitable airport for aircraft repair.

If subsequent electrical malfunction(s) occur requiring use of emergency power, rotate EMER PWR selector to ARM or ON and deploy the ADG.

NOTE

The emergency power system is designed to provide power for approximately 15 minutes until the ADG is deployed.

[END OF BUS L EMER DC OFF CHECKLIST]

ELEC ALERTS

NOTE

Under certain conditions ELEC PANEL may be partially inoperative.

AIRCRAFT ON GROUND

IF IN AIR, SKIP TO BAT BUS OFF LIGHT ILLUMINATED

1. CONTACT MAINTENANCE

Contact maintenance for aircraft repairs.

[END OF ELEC ALERTS CHECKLIST]

BAT BUS OFF LIGHT ILLUMINATED

IF IN AIR, SKIP TO STEP 3

2. LAND AT NEAREST SUITABLE AIRPORT

Landing at the nearest suitable airport for aircraft repair.

Battery bus is not powered

Electrical system is in manual mode, but MANUAL light will not be illuminated.

NOTES

The following systems are inoperative:

Standby attitude indicator
Overspeed aural warning
MASTER WARNING/MASTER CAUTION lights
Engine and APU fire detection
Ignition override
APU
ELEC synoptic

Some subsequent electrical system faults will not present alerts on EAD or illuminate MASTER CAUTION lights.

If indications of equipment failure in other systems are received, observe overhead ELEC control panel for possible bus failure to determine if new alert is primary or only a result of a faulted electrical bus.

If "BUS L EMER AC OFF" and/or "BUS L EMER DC OFF" alerts are observed, use appropriate Abnormal procedure.

NOTE

Subsequent alerts from other systems may be displayed as a result of not being inhibited.

[END OF ELEC ALERTS CHECKLIST]

3. FIRST OFFICER'S EIS SOURCE SELECTOR - AUX (OR 1)

Set the First officer's EIS SOURCE Selector to the AUX (OR 1) position.

ELEC ALERTS REMAINS DISPLAYED

IF ELEC ALERTS DO NOT REMAIN DISPLAYED, SKIP TO Electrical alerts and system display will operate normally.

4. FIRST OFFICER'S EIS SOURCE SELECTOR - ORIGINAL POSITION

Return the First officer's EIS SOURCE Selector to it's original position.

NOTES

Some subsequent electrical system faults will not present alerts on EAD or illuminate MASTER CAUTION lights.
Electrical system may be in manual mode

If "BUS L EMER AC OFF" and/or "BUS L EMER DC OFF" alerts are observed, use appropriate Abnormal procedure.

NOTE

Subsequent alerts from other systems may be displayed as a result of not being inhibited.

[END OF ELEC ALERTS CHECKLIST]

Electrical alerts and system display will operate normally.

[END OF ELEC ALERTS CHECKLIST]

GEN ALL OFF

CAUTION

With all generators off, the HYD, AIR and FUEL panel illumination will not be functioning. Operation of switches on these panels could change system configuration. These changes would not be indicated to the crew.

NOTES

Battery emergency power is limited to 15 minutes until ADG is deployed.
Autothrottles and autopilot will disconnect and red warning boxes on the FMA will flash.
“GEN ALL OFF” alert will be displayed on the EAD. The EAD is powered by the left emergency AC bus.

1. ENG IGN OVRD SWITCH - OVRD ON

Set the ENG IGN OVRD switch to the OVRD ON position.

AIRCRAFT ALTITUDE > 38000 FEET

IF AIRCRAFT IS BELOW 38000 FEET, SKIP TO ELEC SYSTEM MANUAL

While continuing this procedure, begin descent to an altitude of 38,000 feet or less.

NOTE

Engines may not sustain fuel suction feed at altitudes above 38,000 feet.

ELEC SYSTEM MANUAL

IF ELEC SYSTEM IS NOT IN MANUAL MODE, SKIP TO STEP 6

2. GEN SWITCHES WITH OFF LIGHT ILLUMINATED - PUSH TO RESET

If any gen switches with off light illuminated are present, move the associated switches to PUSH TO RESET position.

CAUTION

Only one reset attempt is permitted.

GENERATOR BUSES 1 AND 3 POWERED

IF GENERATOR BUSES 1 AND 3 ARE NOT POWERED, SKIP TO STEP 6

3. EMER PWR SELECTOR - OFF THEN ARM

Set the EMER PWR SELECTOR to the OFF then ARM positions.

4. IF REQUIRED, RESTART ENGINE 2 REFER TO ABNORMAL NON-ALERT PROCEDURE - ENGINE RESTART IN FLIGHT

If required, restart engine 2. Refer to Abnormal Non-Alert procedure - ENGINE RESTART IN FLIGHT.

5. LAND AT NEAREST SUITABLE AIRPORT

Landing at the nearest suitable airport for aircraft repair.

[END OF GEN ALL OFF CHECKLIST]

6. ADG - DEPLOY

Set the ADG to DEPLOY.

7. ADG ELEC SWITCH - ON

Set the ADG ELEC switch to the ON position.

NOTE

Horizontal stabilizer trim is available only through the LONG TRIM handles on the pedestal.

8. CAPT SISP FMS AND APPR SWITCHES - PUSH

PUSH the CAPT SISP FMS and APPR switches.

NOTE

SISP lights will not illuminate; however, the switches are functional.

9. IF REQUIRED, RESTART ENGINE 2 REFER TO ABNORMAL NON-ALERT PROCEDURE - ENGINE RESTART IN FLIGHT

If required, restart engine 2. Refer to Abnormal Non-Alert procedure - ENGINE RESTART IN FLIGHT.

NOTES

Landing gear position indications on the instrument panel and configuration synoptic are not available when DC bus 2 and DC bus 3 are not powered.
Flap position indications on the PFD and configuration synoptic are not available when AC bus 1 and AC bus 3 are not powered.

10. LAND AT NEAREST SUITABLE AIRPORT

Landing at the nearest suitable airport for aircraft repair.

GEN ALL OFF ALERT IS REMOVED

IF GEN ALL OFF REMAINS DISPLAYED, SKIP TO AISPEED KNOWN AT TIME OF FAILURE

NOTES

The ADG output will be lost during the landing roll at approx. 80 kt. Consequently the RH EMER buses will become unpowered and the F/O's DUs are lost.
Fly approach using LOC/TRK and FPA or do not use autopilot(s) below 1.500 ft RA to avoid temporary loss of AP 2 and FD as a result of bus splitting.

[END OF GEN ALL OFF CHECKLIST]

AIRSPEED KNOWN AT TIME OF FAILURE

IF AIRSPEED WAS UNKNOWN AT TIME OF FAILURE, SKIP TO WHEN AIRSPEED WAS UNKNOWN

Refer to following table for maximum flap landing setting:

AIRSPEED AT TIME OF FAILURE	MAXIMUM FLAP LANDING SETTING
At or above 221 KIAS	20°
211 KIAS to 220 KIAS	25°
191 KIAS to 210 KIAS	28°
176 KIAS to 190 KIAS	35°
At or below 175 KIAS	50°

When airspeed was unknown at time of failure, plan a 20/EXT approach and landing.

APPROACH ASPECTS

Use Normal Descent and Approach Checklist

NOTE

Fly approach using LOC / TRK and FPA or do not use autopilot(s) below 1,500 ft RA to avoid temporary loss of AP 2 and FD as a result of bus splitting.

Refer to NORMAL & ABNORMAL CONFIGURATION REFERENCE SPEED (VREF) table located under the PERFORMANCE tab.

Check calculated landing distance (m) table valid for landing with flaps 20:

WEIGHT (1000 KG)	150	160	170	180	190	200	210	220
Braking Action Good	2420	2530	2640	2750	2880	3000	3130	3230
Braking Action Medium	3350	3520	3680	3850	4030	4210	4390	4540
V_APP per kt above V_MIN + 5	+50
Per 1,000ft press altitude	+130
Per 10°C above ISA	+150
Per 0.1% UP / DOWN slope	-25 / +65
Per kt HEAD / TAIL wind	-20 / +40

LANDING ASPECTS

Landing gear indications are inoperative.
Flap and slat indications are inoperative.
RA auto call-out is inoperative.
GPWS is inoperative.
For landing use only a slight flare.

ROLL-OUT ASPECTS

Reversers are inoperative.
Select spoilers manually after nose gear touchdown.
Anti-skid is operative. Gradually increase brake pedal force until a moderate deceleration is felt.
The ADG output will be lost during the landing roll at approx. 80 kt. Consequently the RH EMER buses will become unpowered and the F/O's DUs are lost.

QRH LANDING CHECKLIST

[END OF GEN ALL OFF CHECKLIST]

GEN BUS 1 / 2 / 3

ELEC SYSTEM MANUAL

IF ELEC SYSTEM IS NOT IN MANUAL MODE, SKIP TO GEN BUS 1 FAULT AND / OR GEN BUS 3 FAULT DISPLAYED

1. ASSOCIATED GEN SWITCH - PUSH TO RESET

PUSH the associated gen switch to reset.

CAUTION

Only one reset attempt is permitted.

GEN BUS POWERED

IF GEN BUS IS NOT POWERED, SKIP TO GEN BUS 1 FAULT AND / OR GEN BUS 3 FAULT DISPLAYED

EMER PWR ON ALERT DISPLAYED AND / OR EMER PWR ON LIGHT ILLUMINATED

IF EMER PWR ON ALERT IS NOT DISPLAYED AND / OR EMER PWR ON LIGHT IS NOT ILLUMINATED, SKIP TO NO FURTHER CREW ACTION REQUIRED

2. EMER PWR SELECTOR - OFF THEN ARM

Set the EMER PWR SELECTOR to the OFF then ARM positions.

[END GEN BUS 1 / 2 / 3 CHECKLIST]

No further crew action required.

[END GEN BUS 1 / 2 / 3 CHECKLIST]

GEN BUS 1 FAULT AND / OR GEN BUS 3 FAULT DISPLAYED

IF GEN BUS 1 FAULT AND / OR GEN BUS 3 FAULT IS NOT DISPLAYED, SKIP TO GEN BUS 2 FAULT ALERT DISPLAYED

Generator bus 1 fault condition may cause activation of right stick shaker. Stick shaker may be deactivated by disconnecting cannon plug on control column or pulling F/O STICK SHAKER circuit breaker (E31) on overhead circuit breaker panel.
Generator bus 3 fault condition may cause activation of left stick shaker. Stick shaker may be deactivated by disconnecting cannon plug on the control column or pulling CAPT STICK SHAKER circuit breaker (E1) on overhead circuit breaker panel.

3. ADG - DEPLOY

Set the ADG to DEPLOY.

4. ADG ELEC SWITCH - ON

Set the ADG ELEC switch to the ON position.

GEN BUS 2 FAULT ALERT DISPLAYED

IF GEN BUS 2 FAULT ALERT IS NOT DISPLAYED, SKIP TO CONTINUE WITH AFFECTED CIRCUITS INOPERATIVE

Battery charger is inoperative.

If battery charging is desired, consider deploying the ADG and pushing the ADG ELEC switch to ON to allow the battery charger to be powered by the right emergency AC bus.

Continue with affected circuits inoperative.

5. LAND AT NEAREST SUITABLE AIRPORT

Landing at the nearest suitable airport for aircraft repair.

Review applicable consequences.

NOTES

The ADG output will be lost during the landing roll at approx. 80 kts. Consequently the RH EMER buses will become unpowered and the F/O's DUs are lost.
Fly approach using LOC/TRK and FPA or do not use autopilot(s) below 1.500 feet RA to avoid temporary loss of AP 2 and FD as a result of bus splitting.

[END GEN BUS 1 / 2 / 3 CHECKLIST]

GEN DRIVE 1 / 2 / 3 FAULT

ANY OTHER ENGINE GENERATOR OPERATING

IF NO OTHER ENGINE GENERATOR IS OPERATIONAL, SKIP TO DO NOT DISCONNECT IDG

1. DRIVE SWITCH - DISC

Set the DRIVE switch to the DISC position.

[END GEN DRIVE 1 / 2 / 3 FAULT CHECKLIST]

Do not disconnect IDG. Continue with GEN DRIVE 1 / 2 / 3 FAULT alert displayed.

[END GEN DRIVE 1 / 2 / 3 FAULT CHECKLIST]

GEN LOAD HI

Monitor generator load on ELEC synoptic. Perform following steps only as necessary to reduce generator load to 1.0 or below.

1. ECON SWITCH - OFF

Set the ECON switch to the OFF position.

NOTE

With ECON switch off, fuel consumption may increase up to 1.3%. If desired, increase PERF FACTOR on A/C STATUS page by 1.3 to revise FMS predictions.

If generator load is greater than 1.0, Notify cabin staff to turn off ovens.

If generator load is still greater than 1.0, Notify cabin staff to turn off refrigerators/chillers.

If generator load is still greater than 1.0:

2. GALLEY BUS SWITCHES (ONE AT A TIME) - OFF

Set the GALLEY BUS switches to the OFF position one at a time.

NOTE

Controller may turn generator off when load limits are exceeded. This will cause the “GEN LOAD HI” alert to extinguish and the “GEN 1 / 2 /3 OFF” alert to be displayed.*

[END GEN LOAD HI FAULT CHECKLIST]

GEN 1 / 2 / 3 OFF

1. ASSOCIATED GEN SWITCH - PUSH TO RESET

PUSH to the associated gen switch to the RESET position.

CAUTION

Only one reset attempt is permitted.

If reset attempt is not successful continue flight with generator inoperative.

[END GEN 1 / 2 / 3 OFF CHECKLIST]

Electrical

On this page