مساعده في بحث جزاكم الله خيراً

[alansari]

السلام عليكم ورحمة الله وبركاته

اخواني اللي يقدر يساعدني في هذا البحث جزاكم الله خيراً

البحث يقول:

Investigate the methods used to ensure the continuing integrity and safety of aircraft power supply systems in the event of primary system failure

اللي يقصده اذا واحد من المحركات تعطل بالتحديد(hydrolic,electric,pneumatic)

اذا واحد منهم تعطل كيف الثاني يقدر يغطي لمواصلة الرحله امنه

وياليت بالانجليزي

وشكراُ لكم

[mechanic]

وجدت مجموعة من الروابط

أتمنى تجد فيها إجابتك

http://www.iflyamerica.org/engine_failure.asp

http://www.fromthecockpit.com/Engine_Failure.html


http://www.freepatentsonline.com/5363317.html


http://www.geocities.com/khlim777_my/questionsviaemail.htm


http://www.flydamnit.com/2006/06/27/engine-failure-after-v1/


وبالتوفيق إن شاء الله

تحياتي

mechanic

[ykoheel]

ELECTRICAL POWER - INTRODUCTION

General

The electrical power system makes, supplies, and controls electrical power to the airplane. The system has these subsystem:

External power
Generator drive system
AC generation
ELMS
Distribution
DC generation
Indication.
Abbreviations and Acronyms

AFDC - automatic flight director computer
AFDS - automatic flight director system
APB - auxiliary power breaker
AUTO - automatic
AVAIL - available
BAT - battery
BPCU - bus power control unit
BTB - bus tie breaker
BU - backup
CCB - converter circuit breaker
CONV - converter
CPT - captain
CPU - central processing unit
CSD - constant speed drive
CTRL - control
DISC - disconnect
EDIU - engine data interface unit
EEC - electronic engine control
EEU - ELMS electronic unit
ELCU - electrical load control unit
ELMS - electrical load management system
EMI - electro-magnetic interference
EP - external power
EPC - external power contactor
ESDS - electro-static discharge sensitive
ETOPS - extended twin operations
FBW - fly by wire
FCDC - flight controls dc
FLT - flight
FNC - fiber nickel cadmium
F/O - first officer
GCB - generator circuit breaker
GCR - generator control relay
GCU - generator control unit
GEN - generator
GH - ground handling
GHR - ground handling relay
GND - ground
GSSR - ground service select relay
GSTR - ground service transfer relay
HDLG - handling
IDG - integrated drive generator
ILS - instrument landing system
INST - instrument
I/O - input/output
ISLN - isolation
LRM - line replaceable module
LRU - line replaceable unit
PEPC - primary external power contactor
PFC - primary flight computer
PMG - permanent magnet generator
POR - point of regulation
PRI - primary
PSA - power supply assembly
PSU - power supply unit
PWR - power
QAD - quick attach/detach
RAT - ram air turbine
RLY - relay
SCM - signal conditioning module
SEC - secondary
SEPC - secondary external power contactor
STBY - standby
SVC - service
TBB - transfer bus breaker
TRU - transformer rectifier unit
UB - utility bus
UTIL - utility
XFR - transfer

AC GENERATION - FUNCTIONAL DESCRIPTION


General

The BPCU and GCUs automatically control the power source selection for each main ac bus. The power sources for a main ac bus have this priority:

Related IDG
APU generator
Opposite IDG.
External power has priority over other sources when you manually choose it with the external power switch.
APB Control

When the APU is running, the APU GCU closes the APB. This permits the APU to supply power to the tie bus. If the left main ac bus has no power, the left GCU closes the left BTB. This connects the tie bus to the left main ac bus.
If the right main ac bus has no power, the right GCU closes the right BTB. This connects the tie bus to the right main ac bus.
GCB Control

When the left IDG operates, the left GCU closes the left GCB. This permits the IDG to supply power to the left main ac bus.
When the right IDG operates, the right GCU closes the right GCB. This permits the IDG to supply power to the right main ac bus.
BTB Control

One IDG can supply power to both main ac buses at the same time. For example, if the right IDG fails, the right GCU opens the right GCB and closes the right BTB. The left GCU closes the left BTB. This connects the left main ac bus to the right main ac bus.
Ground Service and Ground Handling Buses

When the right main ac bus has power, it supplies power to the ground service bus. When the right main ac bus has no power, the BPCU selects primary external power or the APU generator as the power source.
Primary external power or the APU generator also supply power to the ground handling bus through the ground handling relay.
If both the APU generator and primary external power are available, primary external power has priority.
Backup Generator Power

The backup power system supplies power to one or both transfer buses during these conditions:

Loss of all main ac power
Single main generator operation
Autoland
Backup system test after engine start.
The backup generator converter controls the TBBs and CCBs. For example, if the left main ac bus has no power, the converter opens the left TBB and closes the left CCB. This permits the converter to supply power to the left transfer bus.
BITE

The GCUs and backup converter protect and monitor the ac power systems for faults. They perform three kinds of tests:

Continuous
Power-up/manually-initiated
Fault-initiated.
The GCUs and the converter send the test fault data to the AIMS.
Training Information Point

There is a short time delay between when the engine reaches idle and when the IDG starts to supply power. The length of the time delay depends on engine idle speed data from the engine data interface unit (EDIU).
On the ground, if the GCU gets a satisfactory engine idle speed signal from the EDIU, the IDG starts to supply power in 6 seconds. If there is not a satisfactory engine idle speed signal from the EDIU, the GCU gets a different engine speed signal from its own PMG. In this case, the IDG starts to supply power in 16 seconds.
In the air, if the GCU gets a satisfactory engine idle speed signal from the EDIU, the IDG starts to supply power in 10 seconds. If it must get an engine
speed signal from the PMG, the IDG starts to supply power in 20 seconds.

http://sapilot.com/ykoheel/Discu/elect%201.JPG


DC GENERATION - FUNCTIONAL DESCRIPTION

Normal Power

The dc generation system normally receives power from these ac power sources:

Left transfer bus
Right transfer bus
Ground service bus
Backup generator PMGs.
Four TRUs change the ac power from the transfer buses to dc power. Most of the dc loads on the airplane use this power.
The standby ac bus uses power directly from the left transfer bus.
Two battery chargers change the ac power from the ground service bus to dc power. This dc power charges the main and APU batteries. It also supplies power to the hot battery bus loads.
Three PSAs change the ac power from the backup generator PMGs to dc power. Flight control components use this dc power.
Standby Power

When all ac power is lost, the main battery supplies power to the standby loads of the dc generation system until the RAT deploys (except those on the first officer's flight instrument bus). The standby loads are on these buses:

Hot battery
Battery
Battery No. 2
Captain's flight instrument
First officer's flight instrument
Standby ac.
After the RAT deploys, its generator supplies all of the power for the standby loads through the two center TRUs.
Control

The ELMS controls all the dc power system relays. (The RAT GCU can also control the TRU C1 relay.) The battery switch and the standby power switch supply manual control inputs to the ELMS.
The ELMS decreases the effect of faults in the dc generation system by normally keeping dc buses isolated. But, if there is a power loss to a dc bus, the ELMS can supply power to that bus from another dc bus. It does this by connecting the two buses. The ELMS uses these relays to connect dc buses:

DC bus tie
Main battery
Battery-captain's isolation
Captain's-first officer's bus tie
Ground power battery.
Fault Isolation - DC/Standby Self-Check

The dc subsystem card does a check of the dc system. This is called a dc/standby self-check. It does these tests:

Makes sure all dc/standby system relays operate correctly
Makes sure the ac standby bus has power (this does a check of the static inverter).
A dc/standby self-check can start either manually or automatically. You manually start the self-check when you set these conditions:

The airplane is on the ground
Left and right ac transfer buses have power
The battery switch is in the ON position
The standby power switch is in the BAT position (momentary).
The self-check starts automatically when these conditions occur:

There are more than 72 hours since the last dc system test occurred
The airplane is on the ground
Left and right ac transfer buses have power.
The test takes less than ten seconds. If the system passes the test, no message shows on the EICAS display. If the system fails the test, the advisory message ELEC STANDBY SYS shows.

http://sapilot.com/ykoheel/Discu/elect%202.JPG

[alansari]

وجدت مجموعة من الروابط

أتمنى تجد فيها إجابتك

http://www.iflyamerica.org/engine_failure.asp

http://www.fromthecockpit.com/Engine_Failure.html


http://www.freepatentsonline.com/5363317.html


http://www.geocities.com/khlim777_my/questionsviaemail.htm


http://www.flydamnit.com/2006/06/27/engine-failure-after-v1/


وبالتوفيق إن شاء الله

تحياتي


mechanic


الله يفرج عنك دنيا واخره

شكراً على مساعدتك وبارك الله فيك

دمت بود

[alansari]

ELECTRICAL POWER - INTRODUCTION


General

The electrical power system makes, supplies, and controls electrical power to the airplane. The system has these subsystem:

External power
Generator drive system
AC generation
ELMS
Distribution
DC generation
Indication.
Abbreviations and Acronyms

AFDC - automatic flight director computer
AFDS - automatic flight director system
APB - auxiliary power breaker
AUTO - automatic
AVAIL - available
BAT - battery
BPCU - bus power control unit
BTB - bus tie breaker
BU - backup
CCB - converter circuit breaker
CONV - converter
CPT - captain
CPU - central processing unit
CSD - constant speed drive
CTRL - control
DISC - disconnect
EDIU - engine data interface unit
EEC - electronic engine control
EEU - ELMS electronic unit
ELCU - electrical load control unit
ELMS - electrical load management system
EMI - electro-magnetic interference
EP - external power
EPC - external power contactor
ESDS - electro-static discharge sensitive
ETOPS - extended twin operations
FBW - fly by wire
FCDC - flight controls dc
FLT - flight
FNC - fiber nickel cadmium
F/O - first officer
GCB - generator circuit breaker
GCR - generator control relay
GCU - generator control unit
GEN - generator
GH - ground handling
GHR - ground handling relay
GND - ground
GSSR - ground service select relay
GSTR - ground service transfer relay
HDLG - handling
IDG - integrated drive generator
ILS - instrument landing system
INST - instrument
I/O - input/output
ISLN - isolation
LRM - line replaceable module
LRU - line replaceable unit
PEPC - primary external power contactor
PFC - primary flight computer
PMG - permanent magnet generator
POR - point of regulation
PRI - primary
PSA - power supply assembly
PSU - power supply unit
PWR - power
QAD - quick attach/detach
RAT - ram air turbine
RLY - relay
SCM - signal conditioning module
SEC - secondary
SEPC - secondary external power contactor
STBY - standby
SVC - service
TBB - transfer bus breaker
TRU - transformer rectifier unit
UB - utility bus
UTIL - utility
XFR - transfer

AC GENERATION - FUNCTIONAL DESCRIPTION


General

The BPCU and GCUs automatically control the power source selection for each main ac bus. The power sources for a main ac bus have this priority:

Related IDG
APU generator
Opposite IDG.
External power has priority over other sources when you manually choose it with the external power switch.
APB Control

When the APU is running, the APU GCU closes the APB. This permits the APU to supply power to the tie bus. If the left main ac bus has no power, the left GCU closes the left BTB. This connects the tie bus to the left main ac bus.
If the right main ac bus has no power, the right GCU closes the right BTB. This connects the tie bus to the right main ac bus.
GCB Control

When the left IDG operates, the left GCU closes the left GCB. This permits the IDG to supply power to the left main ac bus.
When the right IDG operates, the right GCU closes the right GCB. This permits the IDG to supply power to the right main ac bus.
BTB Control

One IDG can supply power to both main ac buses at the same time. For example, if the right IDG fails, the right GCU opens the right GCB and closes the right BTB. The left GCU closes the left BTB. This connects the left main ac bus to the right main ac bus.
Ground Service and Ground Handling Buses

When the right main ac bus has power, it supplies power to the ground service bus. When the right main ac bus has no power, the BPCU selects primary external power or the APU generator as the power source.
Primary external power or the APU generator also supply power to the ground handling bus through the ground handling relay.
If both the APU generator and primary external power are available, primary external power has priority.
Backup Generator Power

The backup power system supplies power to one or both transfer buses during these conditions:

Loss of all main ac power
Single main generator operation
Autoland
Backup system test after engine start.
The backup generator converter controls the TBBs and CCBs. For example, if the left main ac bus has no power, the converter opens the left TBB and closes the left CCB. This permits the converter to supply power to the left transfer bus.
BITE

The GCUs and backup converter protect and monitor the ac power systems for faults. They perform three kinds of tests:

Continuous
Power-up/manually-initiated
Fault-initiated.
The GCUs and the converter send the test fault data to the AIMS.
Training Information Point

There is a short time delay between when the engine reaches idle and when the IDG starts to supply power. The length of the time delay depends on engine idle speed data from the engine data interface unit (EDIU).
On the ground, if the GCU gets a satisfactory engine idle speed signal from the EDIU, the IDG starts to supply power in 6 seconds. If there is not a satisfactory engine idle speed signal from the EDIU, the GCU gets a different engine speed signal from its own PMG. In this case, the IDG starts to supply power in 16 seconds.
In the air, if the GCU gets a satisfactory engine idle speed signal from the EDIU, the IDG starts to supply power in 10 seconds. If it must get an engine
speed signal from the PMG, the IDG starts to supply power in 20 seconds.

http://sapilot.com/ykoheel/Discu/elect%201.JPG


DC GENERATION - FUNCTIONAL DESCRIPTION

Normal Power

The dc generation system normally receives power from these ac power sources:

Left transfer bus
Right transfer bus
Ground service bus
Backup generator PMGs.
Four TRUs change the ac power from the transfer buses to dc power. Most of the dc loads on the airplane use this power.
The standby ac bus uses power directly from the left transfer bus.
Two battery chargers change the ac power from the ground service bus to dc power. This dc power charges the main and APU batteries. It also supplies power to the hot battery bus loads.
Three PSAs change the ac power from the backup generator PMGs to dc power. Flight control components use this dc power.
Standby Power

When all ac power is lost, the main battery supplies power to the standby loads of the dc generation system until the RAT deploys (except those on the first officer's flight instrument bus). The standby loads are on these buses:

Hot battery
Battery
Battery No. 2
Captain's flight instrument
First officer's flight instrument
Standby ac.
After the RAT deploys, its generator supplies all of the power for the standby loads through the two center TRUs.
Control

The ELMS controls all the dc power system relays. (The RAT GCU can also control the TRU C1 relay.) The battery switch and the standby power switch supply manual control inputs to the ELMS.
The ELMS decreases the effect of faults in the dc generation system by normally keeping dc buses isolated. But, if there is a power loss to a dc bus, the ELMS can supply power to that bus from another dc bus. It does this by connecting the two buses. The ELMS uses these relays to connect dc buses:

DC bus tie
Main battery
Battery-captain's isolation
Captain's-first officer's bus tie
Ground power battery.
Fault Isolation - DC/Standby Self-Check

The dc subsystem card does a check of the dc system. This is called a dc/standby self-check. It does these tests:

Makes sure all dc/standby system relays operate correctly
Makes sure the ac standby bus has power (this does a check of the static inverter).
A dc/standby self-check can start either manually or automatically. You manually start the self-check when you set these conditions:

The airplane is on the ground
Left and right ac transfer buses have power
The battery switch is in the ON position
The standby power switch is in the BAT position (momentary).
The self-check starts automatically when these conditions occur:

There are more than 72 hours since the last dc system test occurred
The airplane is on the ground
Left and right ac transfer buses have power.

The test takes less than ten seconds. If the system passes the test, no message shows on the EICAS display. If the system fails the test, the advisory message ELEC STANDBY SYS shows.

http://sapilot.com/ykoheel/Discu/elect%202.JPG



بارك الله فيك اخي الكريم وشكراً على مساعدتك الرائعه

سيتم ادراج اللازم في بحثي

دمت بود

[majed_999]

يعطيكم العافيه

[موشاكس]

الله يعطيكم العافية ياشباب على هذه المعلومات
والله انهااااااااا مفيده جدااااااااااا
والله يكثر من امثالكم