Full transcript
0:02[Music]
0:12thank you
0:15discuss the electrical system AC power
0:19sources DC power sources power source
0:23priority
0:24generator control unit GCU electrical
0:28panel emergency electrical power panel
0:31ecam electrical page external power
0:35panel and circuit breakers
0:42the aircraft electrical system is
0:44comprised of AC and DC Systems the AC
0:48system is three-phase 115 200 volts
0:52and the DC system is 28 volts
0:59the aircraft AC electrical power sources
1:02are two engine driven AC generators one
1:06apu-driven AC generator
1:09an emergency AC generator powered by the
1:12ram air turbine via the blue hydraulic
1:14system and external power
1:18if all other power sources are
1:20inoperative a static inverter will
1:22convert battery DC power into AC power
1:25for limited use
1:30the aircraft DC electrical power is
1:33supplied through two main Transformer
1:35rectifiers or TRS which convert AC power
1:38to 28 volt DC power
1:41the DC system has a backup essential
1:44Transformer rectifier which will power
1:46the essential DC system from the
1:49emergency generator in the event of
1:51failure of the three main generators or
1:54if tr1 and tr2 are faulty
1:58as a backup two batteries can power some
2:01of the DC circuits if all other power
2:03sources are an operative
2:07each of the two engine driven generators
2:10or the Apu generator is capable of
2:13supplying the entire aircraft network if
2:16all three main generators fail the
2:18emergency generator can supply part of
2:21the AC and DC Systems
2:27when there is more than one power source
2:29available the power source chosen to
2:31Supply electrical power depends on its
2:34priority
2:35when operating the engine driven
2:37generators have priority over the Apu
2:40generator and over external power
2:43external power has priority over the Apu
2:46generator when the external power push
2:49button switch is selected on
2:51the emergency generator and batteries
2:53have the lowest priority
3:00the electrical generators are
3:02automatically controlled and monitored
3:04by generator control units or gcus and
3:08external power is controlled by a ground
3:11power control unit or gpcu
3:14the gcus and gpcu determine which power
3:19source takes priority by controlling the
3:21generator line contactors
3:25the electrical control panel is located
3:27on the overhead panel
3:33the emergency electrical power panel is
3:36located on the left side of the overhead
3:38panel
3:43the ecamm electrical page is
3:46automatically displayed in the event of
3:48an electrical fault or can be displayed
3:50by pressing the electrical push button
3:52switch on the ecam control panel
3:58the external power connector is located
4:01forward of the nose Gear with external
4:04power available and not in use lights
4:06located on the interphone panel
4:12the various aircraft electrical
4:14components are protected by two main
4:17types of circuit breakers or CBS
4:20the green or monitored CBS will trigger
4:23the ecamm warning CB tripped if the CB
4:27is out for more than one minute
4:29the black Seabees are unmonitored
4:33the red Seabees are for the wingtip
4:35brakes which can only be reset by
4:38maintenance on the ground
4:43[Music]
4:55in this lesson we will discuss engine
4:58generators Apu generator generator
5:02control unit GCU
5:04line contactors generator 1 and 2 push
5:09button switches
5:10integrated Drive generator 1 and 2 push
5:13button switches
5:15Apu generator push button switch and
5:18ecam indications
5:24the electrical system is normally
5:26powered by two engine driven integrated
5:28Drive generators or idgs
5:32the generator is driven at a constant
5:34speed by the integrated drive to supply
5:37the electrical system with up to 90 KVA
5:40of power at 115 and 200 volts with a
5:44frequency of 400 Hertz
5:49the 115 volt Supply is used to power
5:52normal electrical components with 200
5:55volts supplying higher load components
5:57such as hydraulic pumps
6:00the engine generators have priority over
6:02all other electrical sources and cannot
6:05be connected in parallel
6:11a third generator driven directly by the
6:14Apu without an integrated Drive produces
6:17the same power as each engine driven
6:19generator
6:20the Apu generator can replace either or
6:24both engine driven generators at any
6:26time in flight or on the ground
6:29the Apu generator is normally used on
6:32the ground when Ground power is not
6:34available and the engines are not
6:36running
6:39each generator has an Associated
6:42generator control unit or GCU
6:45the function of the GCU is to control
6:48the generator voltage and frequency
6:50output to control the generator priority
6:53to protect the generator and the
6:55electrical network and to supply
6:57indications and warnings
7:00the GCU controls the connection of the
7:03generator to the electrical system by
7:05the generator line contactor or GLC
7:12line contactors are used to connect and
7:15disconnect various power sources to the
7:18electrical system and are controlled by
7:20the gcus
7:22the ecamm electrical page displays the
7:24line contactors by Green lines when they
7:27are closed the green line is not
7:29displayed when it is open
7:36the generator 1 and Generator 2 push
7:39button switches located on the overhead
7:41electrical control panel control the
7:44engine driven generators their
7:46respective generator control units and
7:48Generator line contactors
7:54when the generator push button switch is
7:57in its normal on lights out position the
8:00generator will be energized and if the
8:03generator electrical output is within
8:05limits the generator line contactor will
8:08close
8:09with the generator push button switch
8:11selected to the off position the
8:14generator field is de-energized and the
8:17generator line contactor opens
8:19anytime a generator push button switch
8:22is selected off the fault circuit is
8:24reset
8:26touch the generator 1 push button switch
8:28to turn it off
8:37the generator 1 or generator 2 push
8:40button switch will indicate fault if its
8:43Associated generator control unit
8:45detects a fault within the generator
8:47thus opening the generator line
8:50contactor or if the generator line
8:53contactor opens when the generator push
8:56button switch is in the on position
9:02when the generator 1 or generator 2 push
9:05button switch is on the ecam electrical
9:08page displays gen 1 or Gen 2 in white
9:12changing to Amber if generator load
9:15voltage or frequency are outside set
9:18limits
9:19the indication for load voltage and
9:22frequency are normally green when within
9:25limits changing to Amber if its limit is
9:28exceeded
9:32when the generator push button switch is
9:34selected off the generator parameters
9:36are replaced with a white off and gen is
9:40displayed in Amber
9:41the number one or two will be displayed
9:43in white if the engine is running and
9:46Amber if shut down
9:52when an idg malfunctions it can be
9:55disconnected from the engine through the
9:57use of its respective idg push button
10:00switch on the electrical panel
10:02the guarded idg-1 and idg2 push button
10:06switches will indicate fault and an ecam
10:09caution is generated if the idg outlet
10:12oil overheats or idg oil pressure is low
10:17the low oil pressure warning is
10:19inhibited when Engine N2 is low to
10:22prevent nuisance warnings
10:24touch the idg-1 push button switch to
10:27disconnect idg-1
10:36the spring-loaded idg push button switch
10:39will disconnect the respective idg from
10:42its drive shaft when pressed momentarily
10:44and should not be held for longer than
10:47three seconds to prevent damage to the
10:49disconnect mechanism
10:51maintenance personnel only can reconnect
10:54the idg
10:55en do not press the idg push button
10:59switch if the engine is not running or
11:02is windmilling as the idg will be
11:04damaged when the engine is started
11:09the ecam electrical page displays the
11:13label idg normally in white changing to
11:16Amber if the idg outlet oil temperature
11:19exceeds 185 degrees Celsius the idg is
11:24disconnected or idg oil pressure is low
11:28the idg oil temperature normally green
11:31will change to Amber if the idg outlet
11:34oil is above 185 degrees Celsius
11:39is displayed in Amber if the idg is
11:42disconnected and low pressure is
11:44displayed in Amber if idg oil pressure
11:47is low
11:49the one or two Legend is white if the
11:52associated engine is running and Amber
11:54if it is not when the fade deck is
11:56powered
12:02with the Apu generator push button
12:04switch in its normal on lights out
12:06position the generator is energized and
12:10the generator line contactor will close
12:12if the generator parameters are normal
12:14and external power is not selected on
12:18the Apu will not supply an electrical
12:21system that is powered by an engine
12:23driven generator as they have priority
12:25over the Apu generator
12:28selecting the Apu generator push button
12:30switch to off will de-energize the
12:33generator and open the generator line
12:35contactor
12:37the fault circuit is reset anytime the
12:39push button switch is selected off
12:42touch the Apu generator push button
12:44switch to turn it off
12:57the Apu generator push button switch
13:00will indicate fault when the Apu
13:02generator control unit detects a fault
13:05or if the Apu generator line contactor
13:08opens except when the Apu generator push
13:11button switch is selected off
13:14the Apu fault light is inhibited
13:16whenever the Apu speed is low or if the
13:20Apu generator line contactor opens
13:23when a power source with a higher
13:25priority is connected such as external
13:28power or an engine driven generator
13:34the ecamm electrical page will display
13:37the label Apu gen in white when the Apu
13:41master switch is off
13:45with the Apu master switch selected on
13:48and the Apu generator push button switch
13:51selected off the label apugen will
13:55appear in Amber and off will appear in
13:58white
14:02when the Apu is running normally and the
14:05Apu generator push button switch is on
14:07the ecamm electrical page will display
14:10Apu gen in white changing to Amber if
14:14Apu generator load voltage or frequency
14:18are outside set limits
14:20the indications for load voltage and
14:23frequency are normally green when within
14:26limits changing to Amber if its limit is
14:29exceeded
14:35[Music]
14:47in this lesson we will discuss AC bus 1
14:50and 2. bust eye contactors bust tie push
14:55button switch
14:56AC essential bus
14:58AC essential feed push button switch
15:02AC essential shed bus
15:05Galley push button switch and ecam
15:08indications
15:13the AC buses AC bus 1 and AC bus 2
15:18Supply various components of the
15:20electrical system
15:22normally generator 1 supplies AC bus 1
15:26through its generator line contactor
15:28which then supplies tr1 and the AC
15:32essential bus
15:36generator 2 supplies AC bus 2 through
15:39its generator line contactor which
15:42supplies tr2 and the AC ground flight
15:45bus
15:48the ecam electrical page displays ac-1
15:51and ac2 normally in green changing to
15:55Amber when the corresponding bus is off
16:00AC bus 1 and 2 each have an Associated
16:04bus tie contactor which allows them to
16:07be powered by different power sources
16:10the bus tie contactors are controlled by
16:12the bus tie push button switch located
16:15on the electrical panel
16:19the bus tie push button switch is
16:22normally in its Auto lights out position
16:25the bust eye contactors open or close
16:27automatically to maintain power supply
16:30to both AC bus 1 and AC bus 2.
16:34both bust eye contactors will close to
16:37allow both AC buses to be powered when
16:40there is only one power source such as
16:42when external power is supplying power
16:45the Apu generator is supplying power
16:48one engine driven generator is supplying
16:51power
16:52only one bust eye contactor will close
16:54when there are two power sources
16:56supplying power as for example one
16:59engine generator and the Apu generator
17:03with the bus tie push button switch
17:04selected off both bus tie contactors
17:08open
17:09touch the bus tie push button switch to
17:12select It Off
17:17with only external power the Apu or one
17:21engine powering the electrical system
17:23both bus tie connectors will close
17:26powering both AC bus 1 and AC bus 2.
17:30with one engine running and powering its
17:33Associated AC bus and the Apu generator
17:36available only one bus tie connector
17:38will close to allow the Apu to power the
17:41other AC bus
17:46the AC essential bus is normally powered
17:49by AC bus 1. in the event of a failure
17:52of AC bus 1 the AC essential bus may be
17:56powered by AC bus 2 through the AC
17:59essential feed contactor
18:01it is controlled by the AC essential
18:04feed push button switch located on the
18:07electrical panel
18:08touch the AC essential feed push button
18:11switch to supply the AC essential bus
18:13from AC bus 2.
18:21with the AC essential feed push button
18:23switch in its normal lights out position
18:25the AC essential bus will be supplied by
18:29AC bus 1.
18:31by selecting the AC essential feed push
18:33button switch to alternate the AC
18:36essential bus will be supplied by AC bus
18:392.
18:40touch the AC essential feed push button
18:43switch to select alternate
18:49the AC essential feed push button switch
18:52will indicate fault in Amber with an
18:55ecam caution message if the AC essential
18:58bus does not have an electrical supply
19:01if there is a total loss of the main
19:03generators the AC essential bus is
19:06automatically supplied by the emergency
19:08generator or by the static inverter if
19:12the emergency generator is not available
19:17when powered normally the AC essential
19:20bus indication will be displayed in
19:22green changing to Amber if the AC
19:25essential bus is not powered or is
19:27malfunctioning
19:31the AC essential shed bus is powered by
19:34the AC essential bus
19:36in Flight the AC essential shed bus will
19:39automatically shed if only battery power
19:42is available in order to reduce the load
19:44on the electrical system
19:48the only ecamm indication for the AC
19:51essential shed bus is an Amber shed if
19:54the AC essential shed bus has been
19:57automatically shed due to battery power
19:59only
20:02when the galley push button switch
20:04located on the electrical panel is in
20:07its normal Auto lights out position the
20:10main and secondary electrical circuits
20:12of the galleys are supplied with
20:14electrical power
20:15in flight and on the ground with only
20:18one engine generator operating the main
20:21Galley circuit will be shed to reduce
20:23electrical loads
20:25selecting The Galley push button switch
20:27to off will disconnect all power from
20:29the main and secondary galleys
20:34The Galley push button switch will
20:36indicate fault and an ecam caution
20:39generator overload when the Apu
20:42generator or an engine driven
20:44generator's load is greater than 100
20:47percent
20:51the ecam displays Galley shed in white
20:54when the galley push button switch is
20:56selected off or if the main galleys are
20:59automatically shed due to the electrical
21:01system being powered by only one engine
21:04generator
21:08[Music]
21:18thank you in this lesson we will discuss
21:22Transformer rectifiers TRS essential
21:26Transformer rectifier DC batteries
21:29battery one and two panel indications
21:32battery one and two push button switches
21:36static inverter and ecam indications
21:42Transformer rectifiers or TRS convert
21:46115 volt AC power to 28 volt DC power
21:51the electrical system has two main TRS
21:54tr1 and tr2 which Supply up to 200
21:59amperes of DC current
22:02tr1 is powered by AC bus one ntr2 is
22:06powered by AC bus 2.
22:09a third TR the essential TR Powers the
22:12essential DC from the AC essential if
22:15either or both tr1 and tr2 fail and
22:20Powers DC essential from the emergency
22:22generator if AC bus 1 and 2 fail
22:28the label tr1 or tr2 is displayed in
22:33white changing to Amber if voltage or
22:35current limits are exceeded
22:37TR voltage and current are normally
22:40displayed in green becoming Amber when
22:43normal operating limits are exceeded
22:49the essential TR has the same ecamm
22:52indication as the main TRS the voltage
22:55and current are not displayed when the
22:58essential TR contactor is open
23:03there are two DC batteries each
23:06permanently connected to its respective
23:08hot bus
23:09each battery has a battery charge
23:11limiter or BCL which controls battery
23:15charging and the battery contactor
23:20the electrical panel displays the
23:23battery voltage for battery 1 and
23:25Battery 2 in white even if the aircraft
23:28is not powered by an electrical source
23:35battery one and two push button switches
23:38control the operation of the battery
23:40charge limiters
23:41in their normal Auto lights out position
23:44the bcl's automatically control the
23:47connection of the DC batteries to the DC
23:50battery bus by opening and closing the
23:53battery line contactors
23:55the batteries are connected to the DC
23:58battery bus for Apu starting or if
24:01battery voltage is below 26.5 volts so
24:05the battery can charge
24:07the batteries are also automatically
24:09connected to the DC battery bus with the
24:12loss of all normal and emergency power
24:14below 100 knots
24:16touch the battery one push button switch
24:19to turn it off
24:24when a battery push button switch is
24:26selected off the respective battery line
24:29contactor will open and off illuminates
24:32in white if the DC battery bus is
24:34supplied however the hot buses always
24:38remain powered
24:41the battery push button switch will
24:44indicate fault in Amber with an ecam
24:46caution when the charging limit of the
24:49battery is outside the set limits
24:52when the fault is triggered the battery
24:54line contactor opens to disconnect the
24:56battery from the DC battery bus thus
24:59preventing any further charging
25:03the labels bat 1 and bat 2 are displayed
25:07in white changing to Amber if the
25:10associated voltage or current are
25:12outside limits
25:14battery voltage and current are normally
25:16displayed in green becoming Amber when
25:20normal operating limits are exceeded
25:22with the battery push button switch
25:24selected off
25:26is displayed in white replacing the
25:29voltage and current readings
25:34the ecam displays the various
25:36connections of the batteries to the
25:38battery bus by lines or arrows
25:41indicating the charging status of the
25:43batteries
25:44the green arrow to the battery indicates
25:47the battery contactor is closed and the
25:50battery is being charged with a current
25:51greater than one ampere
25:54the Amber Arrow away from the battery
25:56indicates the battery is supplying power
25:58and the current is greater than 1 ampere
26:02the arrow changes to a green line if the
26:05current is less than one ampere and
26:07there is no line displayed if the
26:09battery contactor is open
26:14the static inverter can transform DC
26:17power from Battery 1 to single phase 115
26:21volt AC power if there is no other
26:24source of AC power on the aircraft then
26:27below 50 knots and if both battery push
26:29buttons are Auto the static inverter is
26:32connected to battery one and its output
26:35supplied to the static inverter bus
26:37above 50 knots with no other source of
26:40AC power on the aircraft and regardless
26:43of battery push button position the
26:45static inverter is connected to battery
26:47one and its output in addition is
26:50connected to part of the AC essential
26:52bus
26:55voltage and frequency of the static
26:57inverter are normally displayed in green
27:00becoming Amber when normal operating
27:03limits are exceeded
27:06foreign
27:08[Music]
27:21we will discuss the external power panel
27:25external power push button switch
27:27external power ecam indications and the
27:31maintenance bus switch
27:36a ground power connector located forward
27:39of the nose wheel allows external power
27:42to supply the entire aircraft electrical
27:45system
27:46a ground power control unit or gpcu
27:49protects the electrical system by
27:52controlling the external power line
27:53contactor
27:56the interphone panel located next to the
27:59ground power connector has two lights
28:01allowing ground Personnel to monitor the
28:04status of the external power
28:06the available light will illuminate if
28:08external power is within limits
28:11and the not in use light indicates that
28:13external power is not being used and can
28:16be removed
28:21the external power momentary action push
28:23button switch is located on the
28:26electrical panel the push button switch
28:28will not have any lights illuminated if
28:31external power is not connected
28:33it will display available in green if
28:37external power is connected and within
28:39limits and on in blue if external power
28:43is selected on and powering the
28:45electrical system
28:49with the external power push button
28:51switch indicating available pressing it
28:54momentarily closes the external
28:56Powerline contactor allowing external
28:59power to supply the electrical system
29:02the available light goes out and the
29:04blue on light illuminates
29:06touch the external power push button
29:09switch to connect external power
29:16with the external power push button
29:18switch indicating on momentarily
29:20pressing it opens the external power
29:23line contactor the on light goes out and
29:26the available light illuminates
29:28touch the external power push button
29:30switch
29:36the ecamm electrical page does not
29:39display any external power indications
29:41when external power is not connected to
29:44the aircraft
29:49when external power is available the
29:52label external power is normally
29:54displayed in white changing to Amber if
29:57voltage or frequency exceed limits
30:00voltage and frequency are normally
30:02displayed in green changing to Amber
30:04when normal operating limits are
30:06exceeded
30:09when external power is selected on the
30:12ecam electric page displays the external
30:15Powerline contactor as a green line
30:21foreign the maintenance bus switch is
30:24used to power only the electrical
30:26systems used for ground servicing
30:28without powering the entire aircraft
30:30electrical system
30:32the maintenance bus switch is located in
30:34the forward Galley ceiling just inside
30:37of the forward entry door
30:41on the ground only the equipment
30:43required for servicing the aircraft can
30:46be supplied directly through the
30:47maintenance bus switch without powering
30:50the entire aircraft
30:52with the external power switch
30:53indicating available the maintenance bus
30:56switch when selected on will be
30:58magnetically held in the on position
31:00until ground power is removed
31:03in the on position only the AC and DC
31:07ground flight buses have power which
31:10will supply the cabin cargo hold and
31:12landing gear compartment lighting the
31:14cockpit flood lighting the vacuum
31:16cleaner sockets
31:18the yellow electric pump for cargo door
31:21operation the refueling panel and fuel
31:24quantity indications the ground call
31:26system and the navigation lights
31:31with the maintenance bus switch selected
31:33off and the external power selected on
31:36the entire aircraft electrical system is
31:39powered by external power and the AC and
31:42DC ground flight buses are powered by AC
31:45bus 2 and DC bus 2 respectively
31:53[Music]
32:05in this lesson we will discuss the
32:08emergency generator Ram Air turbine ret
32:12ower emergency electrical power panel
32:16and ecam indications
32:23if both AC bus 1 and AC bus 2 lose power
32:28the ram air turbine or rat automatically
32:32extends if aircraft speed is greater
32:35than 100 knots to power an emergency
32:37generator at a constant speed through
32:40the blue hydraulic system
32:43the emergency generator is controlled by
32:46a generator control unit to produce 5
32:49KVA of three-phase 115 200 volt 400
32:54Hertz power
32:56if the rat stalls or if the aircraft is
32:59on the ground with the speed of less
33:01than 100 knots the emergency generator
33:04will no longer provide electrical power
33:07and the emergency electrical system will
33:09transfer to the batteries and static
33:11inverter
33:15the two batteries are capable of
33:17temporarily powering some of the
33:19emergency generation Network through a
33:22static inverter when no other electrical
33:24power source is available such as during
33:27rat extension which lasts about eight
33:30seconds or after the aircraft lands when
33:33the emergency generator was powering the
33:36system
33:40the emergency electrical power panel is
33:43located on the overhead panel to the
33:46left of the electrical panel it contains
33:49controls and indicators for the rat and
33:52emergency generator
33:54caution do not confuse the rat and
33:57emergency generator manual on push
34:00button with the hydraulic rat manual on
34:03push button located on the hydraulic
34:05panel and vice versa
34:10the manual on push button switch is
34:13normally in its guarded Auto position
34:15which allows automatic rat extension in
34:19case of both AC bus 1 and 2 not being
34:22powered when the aircraft speed is above
34:25100 knots
34:27the rat Powers the blue hydraulic system
34:29which drives the emergency generator
34:32when the emergency generator parameters
34:35are within limits it is automatically
34:37connected to the electrical system
34:40lifting the guard and pressing the
34:42manual on push button switch extends the
34:45rat at any time and connects the
34:48emergency generator after a three second
34:50delay
35:01the rat and emergency generator light
35:04will indicate fault in red if the
35:07emergency generator is not supplying
35:09power when AC bus 1 and AC bus 2 are not
35:14powered
35:16the guarded emergency generator test
35:19push button is used for maintenance
35:21purposes only to test the emergency
35:23electrical system
35:27the Gen 1 line push button switch will
35:30indicate smoke in Amber with an ecam
35:33caution message if smoke is detected in
35:36the avionics compartment
35:39in the avionics smoke procedure the Gen
35:431 line push button switch is selected
35:45off which opens the generator 1 line
35:48contactor
35:49generator 1 continues to run and
35:52supplies one fuel pump in each Wing tank
35:56the procedure then calls for extension
35:58of the r once the emergency generator is
36:01available the Apu generator and
36:04Generator 2 are selected off which sheds
36:07about 75 percent of all electrical
36:10equipment in an attempt to isolate the
36:12smoke source
36:18the ecam electrical page displays the
36:21label emergency generator in white
36:23changing to Amber if the voltage or
36:26frequency are out of limits the voltage
36:29and frequency of the emergency generator
36:31are normally displayed in green becoming
36:34Amber when normal operating limits are
36:37exceeded
36:38voltage and frequency indications are
36:41not displayed when the line contactor
36:43for the Emergency generator is open
36:47when the rat is extended rat out appears
36:52in Green in the memo section of the
36:54upper ecam display
36:56if the emergency generator is running
36:58Emer gen will also be displayed
37:05[Music]
37:17in this lesson we will discuss
37:19configuration safety check
37:21cockpit Geographic check
37:24pre-start after start and shutdown
37:30the electrical portion of the
37:33configuration safety check is performed
37:36by the first officer only if electrical
37:38power has not been on the aircraft for
37:41more than six hours
37:43this test will ascertain if electrical
37:45power can be applied safely or if
37:48battery charging is required
37:51first with the battery push button
37:54switches off check the battery voltage
37:57on the overhead electrical panel
37:59if the battery volts are above 25.5 then
38:03select battery 1 and 2 push button
38:06switches to auto
38:08note if the Apu is to be started on
38:11batteries alone the Apu should be
38:13started within 30 minutes
38:15if the battery bolts are 25.5 or less
38:19select the battery push button switches
38:21to Auto and establish external power for
38:2420 minutes to charge the batteries
38:27on the ecamm electrical page verify the
38:31batteries are charging and repeat the
38:33test after 20 minutes to confirm proper
38:36battery charge
38:40during the cockpit Geographic check of
38:43the emergency electrical panel check
38:45that the emergency generator test switch
38:47is guarded and that the generator 1 line
38:51push button switch is set to the in
38:53lights out position
38:56check that the rat and emergency
38:59generator fault light is out and that
39:01the manual on push button is in its Auto
39:04guarded position
39:08during the cockpit Geographic check of
39:11the electrical panel the first officer
39:13will pre-select the electrical page on
39:15the ecamm by pressing the electrical
39:18push button on the ecam control panel
39:20touch the electrical push button on the
39:22ecam control panel to display the
39:25electrical page
39:28the captain will select battery 1 and 2
39:31push button switches off pausing until
39:34the batteries indicate off on the ecam
39:37electrical page
39:38touch the battery 1 and 2 push button
39:41switches to turn them off
39:45the battery one and two push button
39:48switches will then be selected back to
39:50the on position while checking on the
39:53ecamm electrical page that both of the
39:55battery charge currents decrease below
39:5860 amps within 10 seconds
40:01touch the battery one and two push
40:03button switches to select them back to
40:06on while checking the battery amps
40:27after the battery test check that the
40:30generator 1 and 2 fault lights are
40:32illuminated as the generators are not
40:34running at this time then check that all
40:38other push button switch lights are out
40:40the external power switch May indicate
40:43available or on depending on whether
40:45external power is connected or selected
40:48on
40:53the Apu should be started a minimum of
40:5610 minutes before departure
40:59with the Apu running and the Apu start
41:02push button switch indicating available
41:04the electrical power can be transferred
41:07to the Apu generator by pressing the
41:09external power push button switch
41:11will disconnect external power and
41:14automatically switch to the Apu
41:16generator
41:17once power is transferred to the Apu
41:20generator the external power can safely
41:23be removed
41:24touch the external power push button
41:26switch to transfer power to the Apu
41:29generator
41:36when the engines are started and the
41:39engine generator output is normal the
41:41associated generator line contactor will
41:44automatically close and connect the
41:46generator to the electrical system as
41:48they have priority over the Apu
41:51generator
41:52when both engine generators are
41:54supplying the electrical system the Apu
41:57master switch may be selected off at
42:00which time the available light will
42:02extinguish
42:03if the Apu was using Apu bleed air the
42:07Apu will keep running at 75 percent
42:09power for a cooling period of 60 to 120
42:13seconds
42:14touch the Apu master switch to shut down
42:17the Apu as the engine generators are now
42:21supplying power
42:26after arrival at the gate if the Apu is
42:30running and available the Apu generator
42:33will automatically Supply the electrical
42:35system as the engines are shut down
42:38if external power only is available or
42:41desired one engine may be shut down
42:43until external power is connected
42:46once the external power available light
42:48illuminates external power can be
42:51selected on it will automatically Supply
42:54the aircraft as the second engine is
42:56shut down
43:00[Music]
43:12in this lesson we will discuss the
43:15following ecamm messages
43:17generator 1 fault
43:19integrated Drive generator 1 oil low
43:22pressures
43:23battery two fault
43:25generator 1 overload
43:28AC bus 2 fault
43:30AC essential bus fault
43:33DC bus 1 fault
43:36circuit breaker tripped
43:38emergency configuration and avionics
43:42smoke
43:46A Fault in one of the engine generators
43:49will trigger the generator fault caution
43:52a single chime will sound the master
43:55caution light will illuminate the fault
43:58light on the generator push button
43:59switch will illuminate
44:01the ecamm electrical page will
44:03automatically be displayed and the ecam
44:06memo area will display the required
44:09actions
44:10as can be seen for the generator 1 fault
44:13the number two generator is
44:15automatically supplying both electrical
44:18systems through the bus tie contactors
44:21the main Galley is also automatically
44:23shed due to one generator operation
44:27the ecamm actions are to select the
44:29generator off then on to try and reset
44:33the generator
44:34if the generator does not reset select
44:37the generator off
44:39assuming the generator did not reset
44:41touch the generator 1 push button switch
44:44to turn it off
44:50with the generator 1 push button switch
44:52selected off the ecamm electrical page
44:56will display generator 1 off with
44:59generator 2 supplying both AC bus 1 and
45:03AC bus 2.
45:04the Apu if available may be started and
45:09when the Apu generator is within limits
45:11it would automatically Supply AC bus 1
45:14and recover the main galley
45:17touch the right arrow to display the
45:19ecamm electrical page with the Apu
45:22generator connected
45:27with the Apu generator operating
45:30normally it will automatically connect
45:32to AC bus 1 through the bus tie
45:35contactor replacing generator 1. now
45:39with two generators online the main
45:41Galley will not be shed
45:46if idg oil pressure is low or overheats
45:50the idg oil low pressure or overheat
45:53fault will be displayed in this case the
45:57idg low oil pressure fault is triggered
46:00due to low oil pressure in the idg
46:03the ecamm action is to disconnect the
46:06number one idg drive from the engine
46:09the guarded idg push button switch is
46:12held in until the generator push button
46:15switch indicates fault
46:17do not push the idg push button switch
46:19longer than 3 seconds or damage to the
46:22disconnect solenoid may occur
46:25touch the idg-1 push button switch to
46:28complete the ecamm actions
46:34when the idg is disconnected the fault
46:38light on the generator 1 push button
46:40switch will illuminate
46:42the ecamm electrical page will display
46:44zero voltage and frequency for generator
46:471 and the main Galley is automatically
46:49shed due to one generator operation
46:53the idg indication will display
46:55disconnect in Amber confirming the idg
46:58has been disconnected
47:05the battery fault is displayed if a
47:07battery has excessive charging current
47:10the associated battery contactor
47:12automatically opens disconnecting the
47:15battery from the DC battery bus
47:17this is a crew awareness fault with no
47:20ecamm actions required
47:25if a generator load is above 100 percent
47:27a generator overload fault will be
47:30triggered
47:31the generator 1 overload fault displays
47:34generator 1 at 120 load
47:38the ecam action is to select the galley
47:41push button switch to off reducing the
47:43generator load
47:45touch the galley push button switch to
47:47turn it off
47:56the AC bus fault is the result of an AC
47:59bus losing power due to a fault on the
48:02bus
48:03with an AC bus 2 fault the lower ecam
48:06display is lost as it has no power
48:08supply
48:10the only ecamm action is to select the
48:13extract fan push button switch to
48:15override putting the avionics
48:17ventilation system in the closed circuit
48:20configuration adding air-conditioned air
48:22to the ventilation system
48:25the status page will display a long list
48:28of in-op systems
48:30refer to fcom 3.0 2.24 abnormal and
48:35emergency procedures
48:38to display the ecam electrical page the
48:41electric push button on the ecam control
48:43panel must be held continuously which
48:46will display the electrical page on the
48:49upper ecamm touch the electric push
48:52button on the ecam control panel to
48:54display the electrical page on the upper
48:56ecamm
49:02as can be seen on the ecamm electrical
49:05page the DC essential bus normally
49:08supplied by DC bus 1 is now
49:11automatically supplied by the essential
49:13trdc bus 2 normally supplied by tr2 is
49:18automatically supplied by DC bus 1
49:21through the DC battery bus
49:27a failure of the normal power supply to
49:29the AC essential bus will cause the AC
49:33essential fault to be triggered
49:35the upper ecam display is lost due to no
49:38power supply which causes its display to
49:41be automatically transferred to the
49:43lower ecam
49:44the first dcam action is to select the
49:48AC essential feed push button switch to
49:50alternate to try and restore power from
49:53AC bus 2.
49:55touch the AC essential feed push button
49:57switch to transfer electrical supply to
50:00AC bus 2.
50:05if the transfer of power to AC bus 2 is
50:09successful the equipment powered by the
50:11AC essential bus will return to normal
50:14if the electric push button on the ecam
50:17control panel is selected the electrical
50:19page will be displayed on the lower ecam
50:23notice that the AC essential bus is now
50:26supplied by AC bus 2 through the AC
50:29essential feed contactor
50:34with the DC bus one fault the DC
50:37essential bus normally supplied by DC
50:40bus 1 is now automatically supplied by
50:43the essential TR
50:45the DC battery bus normally supplied by
50:48DC bus 1 is now automatically supplied
50:52by DC bus 2. there are no ecamm actions
50:56directly related to the electrical
50:57system as all switching is automatic
51:01the status page lists all of the in-op
51:03systems
51:05refer to fcom
51:083.02.24 abnormal and emergency
51:10procedures
51:15if one of the green monitored circuit
51:17breakers should trip for more than one
51:19minute the CB tripped advisory will be
51:22displayed the ecam warning will include
51:25the name of the panel on which the CB is
51:28located
51:29do not attempt a reset in flight
51:34with the loss of AC bus 1 and AC bus 2
51:38the ram air turbine will automatically
51:41extend putting the aircraft in the
51:44electrical emergency configuration
51:47due to the complexity of this fault only
51:49the initial warnings and electrical page
51:52configuration will be covered at this
51:54time
51:55complete coverage will be provided in
51:57simulator lessons
51:59the initial warnings for the electrical
52:02emergency configuration fault are a
52:05continuous repetitive chime
52:10the master warning light
52:12the ecam warning and a momentary fault
52:16light on the rat and emergency generator
52:18push button switch as the emergency
52:20generator comes up to speed
52:23the lower ecam display is lost due to no
52:26power supply
52:28when required the electrical page can be
52:31displayed on the upper ecam display by
52:33pressing and holding the electric push
52:36button on the ecam control panel
52:39touch the electric push button to
52:41display the electrical page
52:47the rat has automatically deployed
52:50driving the emergency generator which
52:52supplies the AC essential bus and the DC
52:55essential bus through the essential
52:58Transformer rectifier
53:00in this configuration numerous systems
53:02are lost which are listed in fcom
53:063.02.24 abnormal and emergency
53:09procedures
53:14if smoke is detected in the avionics
53:16ventilation system the avionics smoke
53:19vault is triggered
53:21due to the complexity of this fault only
53:24the electrical portion will be covered
53:26complete coverage will be provided in
53:28simulator lessons
53:30the ecamm actions for the electrical
53:32portion are performed five minutes after
53:34the avionics ventilation system is put
53:37into the smoke configuration
53:40if there is still smoke after five
53:42minutes the emergency electrical
53:44generator Line 1 push button switch is
53:47selected off which opens the generator 1
53:50line contactor and automatically
53:52connects generator 1 to 1 fuel pump in
53:55each Wing tank
53:57touch the generator Line 1 push button
54:00switch to turn it off
54:05next the emergency electrical power
54:07manual on push button is pressed which
54:11will extend the rat to power the
54:13emergency generator
54:15touch the manual on push button switch
54:18to extend the rat
54:22when the emergency generator is
54:24available the Apu generator and engine
54:28generator 2 are selected off putting the
54:31electrical system into the emergency
54:33configuration which sheds about 75
54:36percent of all electrical equipment in
54:39an attempt to isolate the smoke source
54:42touch the Apu generator and engine
54:44generator 2 push button switches to turn
54:47them off
54:56in-op systems are listed in fcom 3.0
55:002.24 abnormal and emergency procedures
55:04as the lower ecam display has lost power
55:07when required to display the electrical
55:10page the electrical push button switch
55:12on the ecam control panel is pressed and
55:15held which will display the electrical
55:18page on the upper ecam display
55:21touch the electrical push button on the
55:23ecam control panel to display the
55:25electrical page as if all ecam actions
55:28are complete
55:34the electrical page displays the DC
55:37essential and AC essential buses
55:39supplied by the emergency generator
55:42generator 1 is not connected to AC bus 1
55:45but is running and powering one fuel
55:48pump in each Wing tank
55:50before landing gear extension the
55:53procedure calls for the generator 2 and
55:56emergency electrical generator 1 line
55:58push button switches to be selected on
56:01in order to restore normal electrical
56:03power supply for landing
56:09[Music]
56:28foreign
56:30[Music]
56:33foreign
56:36[Music]
56:42[Applause]
56:45[Music]