Can't wait... 7 more days then I get to meet my new baby... Miss Clio badly though. :(
Wednesday, April 29, 2009
Jojo's new car
Can't wait... 7 more days then I get to meet my new baby... Miss Clio badly though. :(
Wednesday, April 15, 2009
跟你 真沒默契
If someone is on your frequency, he doesnt need to create a conversation and he doesnt have to try so hard, just one look or one word... He'll move right into your heart.
人跟人之間 合就是合 用眼神也可以溝通
人跟人之間 有默契就是有默契 用圖案也可以傳達訊息
但是 磁場不對的人 就算是天天見面 天天看著對方 心也不會在一起的 可惜阿
人跟人之間 合就是合 用眼神也可以溝通
人跟人之間 有默契就是有默契 用圖案也可以傳達訊息
但是 磁場不對的人 就算是天天見面 天天看著對方 心也不會在一起的 可惜阿
Tuesday, April 14, 2009
What Jojos learnt from the jet today
When both generators fail - battery supplies for 30 min in flight. battery cutoff light comes on.
pico fuse -
remote control circuit breaker - 10A-100A. indicator control unit, manually resetable when tripped.
Bilateral thermall indicating device - current measure to the the RCCB to pop or not. (latch type)
Shunt measures the current to trip the relay with the CB for reset purpposes - Non latching type.
Simplified Battery feeder fault protection system - current transformers dectects the current of the system. if one of the transformers detect that the current is abnormal, fault relay trips, therefore tripping the battery relay. Battery FDR light comes on. Reset the system by turning it off and on again.
Lead Acid battery installation - 24VDC 40AMP/HR
battery feed test - ct gives out current to interferre to deliberately unbalance the current flow to test if the feeder protection system trips.
battery FDR CB out, Emergency bus feeder RCCB tripped and when the FDR is operating = FDR Lt on.
starter gen - 400amp, 28VDC. limited to 280A due to decrease cooling airflow. Magnetic pickup to the Generator control unit.
Terminal block :
B + positive
E - Negative
A Shunt field
D Interpole sense Radio noise filter
Shear section protects the starter generator by shearing the s3haft off at abnormal conditions.
1000hrs overhaul the starter and inspection and ground run needs to be performed. 1/4inch of the brush mark left, the starter brush needs to be removed from service and replaced.
simplified generator field control system: detects the start gen's current by the field power amp, adjustments is measured by the shunt field winding. Reset is possible at the field power amp.
Line contactor control system - Engine start control relay is energized during engine start ---> Gen control --> gen relay, Main bus.
if the transformers at the main junction box detects abnormal current, genrator control unit trips to protect the system.
Remember to torque the nuts on the interpoles.
at N2 35-40%RPM, GCU automatically cuts off current through to the starter generator @ normal position of the S.Gen switch.
shunt measures the current of the system --->positive and negative at the instrument cluster.
Middle of the switch would be viewing the battery voltage.
left Gen would be viewing the left generator voltage.
Right Gen would be viewing the right generator voltage.
External power - Receptacle - battery feeder protection system
- External power RCCB --->overvolt detector with the sensor --> overvoltage switch module -> at normal operating --> external power relay --> therefore sending current to start bus.
if the left and right generator are on line, external power unit can not be used. therefore the geneator switches must be in the off position.
When start with the External power unit - both external power and the battery feeds through to the main bus. since the external power does not have its own switch on the 400xp model.
3 RCCB if left one fails, warning light left FDR fail illuminates.
SDU no.2 feeds on the left radio bus.
toggle switch - acts as a cb but it pops right out.
Non essential bus - left and right load shed from generators and relays to for example, Galley power.
emergency bus - emergency power relay - copilot stby radio, cvr, nav no 1, aural warn, sdu no1, copilot, flt data recorder, emergency warning light, thrust reverser, emergency landing gear, emergency stall, flood light, trim warning, landing gear safety switch, fire bell, oxygen control, door seal, hyd shutoff valves, fire extinguisher, turbines, rpm indicator, ignition, fuel shutoff valves, fdr.
standby power battery - 50 amp/hr. heating resister heats up and tests the protection capability of the system.
cell test can be done on the standby power battery with each individual cell. 24 above is normal. PS- 835D (series)
oil pressure and flap degrees indicator --- alternating current
no.1 inverter --- primary bus
no.2 inverter --- secondary bus also act as an emergency if no.1 fails.
Chapter 23 - Communication
Radio Tuning Unit - Frequency controller = ATC Identify, DME, Com, ADF Test (Bearing swing 90 and audible 1KHZ ) deg, star on the display automatically returns to pre line when no commands been given. ATC STBY (on/off) DME HOLD would keep the current DME frequency before adjusting to another frequency when the button is pressed on. Com preset key - Com frequency can be set before use.
Radio Sensor System Control Panel -
RTU
No1 + 2 at normal - left RTU controls no 1, right controls no 2.
Remote (RMT) Tune DSABL - FMS CDU controls when switch is at normal position. RTU controls when the RMT Tune is disabled.
Markerbeacon Hi - Outter and inner
Ground comm push button gives you direct communication to the ATC.
FMS computer and control display unit CDU
pilot audio control panel - NAV, DME and MKR, AUTO COMM, nob with o2 mask or audio. speaker, interphone, voice identification with voice or audible codes, atc id press confirms the aircraft with the atc. Communication nob - Comm1, 2 and with the cabin. Audio emergency is louder at broadcasting frequency.
Volume control - COM, DME, NAV, ADF.
CVR - 6 Channels,
1 not used
2 co-pilot
3. pilot ---- middle channel is the most secure and protected from breaking
4. area mic
5. combination
6. cockpit area mic
ulb - underwater location beacon - transmit 30 days. Battery still working??
CVR Test button - press for 2 sec and audible low pitch sound, test meter in good area = functioning.
Erase - press and audible sound
Impact switch when damaged auto pops the circuit breaker to protect the cvr.
cabin pressure lo - cab altitude higher that 9500ft
Cab pressure hi - press differential excceeds 11psi
left and right fire detector fail
left and right windshield temp hi (overheat)
horizontal stabilizer de-ice sys failure.
left and right oil pressure lo
left and right fuel pressure lo
flap asym - will stay as is without moving outwards anymore because the flap is 6.5 degrees different from eachother.
fuel feed - 5 min
fuel level lo - 30 min
fuel transfer pressure low - when sensed 3.5psi light comes on, auto shutoff transfer pump.
wing tanks over pressure - more than 3.5psi.
left and right fuel filter bypass - filter may be clogged.
left and right hydraulic pump press lo - failure of hyd pump
left and right engine eec is operative - failure of engine electrical control
left and right stall warning fail
left and right generator fail
Left and right feeder bus fail - if one of the 3 feeders fail, the emergency one is in use.
battery cutoff - battery relay has relaxed open
emergency bus fdr fail - emergency bus has lost the normal power source.
no 1 and 2 inverter fail
left and right de ice temp low
Airconditioner fail - over pressure or over temperature ACM (engine) electrical would be vapour cycle machine
Ice detector just above the avionic bays in front of the windshield - has just failed.
bleed air duct fail - from leaking pressure
door unlock - entrance is not closed/locked properly.
defog air ov ht - defog air temperature is high
pitot ht off - pitot heater is off or pitot heater switch is on but failed to operate.
hyd level lo
antiskid fail
rudder boost fail - rudder boost inoperative. (when both engines thrust is different or unequal, automatically corrects the yaw effect.)
Engine sychronization - No1 and No2 N1 or N2 synchronize. No 2 engine will sychronize with number no.1.
emergency light no arm - emergency battery not charging.
25.6sec landing light delay and wing ice temp lo.
Avionics
Intergrated avionics processor system
ICC IAPS Card Cage
IOC Input output concentrator
IEC IAPS Environmental controller - maintains a set temperature of the IAPS
LHP Lightening protection
CSU Configuration strapping unit
MDC Maintenance Diagnostic computer
FCC Flight control computer - controls and signals automatic trim coupler
ATC Automatic trim coupler *roll* monitor and auto trim servo
ARP Referrence panel -
PFD Primary Flight Display
MFD - Multifunction display - Weather radar, TCAS etc
RTU - Radio tuning unit
SDU - sensor display unit
CDU control display unit
AAP - altitude awareness panel
APP Autopilot panel
CHP course heading panel
ARP Air data referrence panel
RRP Radio reversion panel
FmC flight management computer - flight plan management
mdc maintenance diagnostic computer - trouble shooting false signals - everything on the annuciator panel
TCAS ToP Antenna (Directional)
TCAS bottom Antenna (OMNI Directional)
Multifunction display - TAT total air temperature is normally higher - SAT normally below 0 degrees static air temperature
REV - controls the co-pilot (opposite side)side of the CDU
pilot left static port top - right static port bottom (cross)
pico fuse -
remote control circuit breaker - 10A-100A. indicator control unit, manually resetable when tripped.
Bilateral thermall indicating device - current measure to the the RCCB to pop or not. (latch type)
Shunt measures the current to trip the relay with the CB for reset purpposes - Non latching type.
Simplified Battery feeder fault protection system - current transformers dectects the current of the system. if one of the transformers detect that the current is abnormal, fault relay trips, therefore tripping the battery relay. Battery FDR light comes on. Reset the system by turning it off and on again.
Lead Acid battery installation - 24VDC 40AMP/HR
battery feed test - ct gives out current to interferre to deliberately unbalance the current flow to test if the feeder protection system trips.
battery FDR CB out, Emergency bus feeder RCCB tripped and when the FDR is operating = FDR Lt on.
starter gen - 400amp, 28VDC. limited to 280A due to decrease cooling airflow. Magnetic pickup to the Generator control unit.
Terminal block :
B + positive
E - Negative
A Shunt field
D Interpole sense Radio noise filter
Shear section protects the starter generator by shearing the s3haft off at abnormal conditions.
1000hrs overhaul the starter and inspection and ground run needs to be performed. 1/4inch of the brush mark left, the starter brush needs to be removed from service and replaced.
simplified generator field control system: detects the start gen's current by the field power amp, adjustments is measured by the shunt field winding. Reset is possible at the field power amp.
Line contactor control system - Engine start control relay is energized during engine start ---> Gen control --> gen relay, Main bus.
if the transformers at the main junction box detects abnormal current, genrator control unit trips to protect the system.
Remember to torque the nuts on the interpoles.
at N2 35-40%RPM, GCU automatically cuts off current through to the starter generator @ normal position of the S.Gen switch.
shunt measures the current of the system --->positive and negative at the instrument cluster.
Middle of the switch would be viewing the battery voltage.
left Gen would be viewing the left generator voltage.
Right Gen would be viewing the right generator voltage.
External power - Receptacle - battery feeder protection system
- External power RCCB --->overvolt detector with the sensor --> overvoltage switch module -> at normal operating --> external power relay --> therefore sending current to start bus.
if the left and right generator are on line, external power unit can not be used. therefore the geneator switches must be in the off position.
When start with the External power unit - both external power and the battery feeds through to the main bus. since the external power does not have its own switch on the 400xp model.
3 RCCB if left one fails, warning light left FDR fail illuminates.
SDU no.2 feeds on the left radio bus.
toggle switch - acts as a cb but it pops right out.
Non essential bus - left and right load shed from generators and relays to for example, Galley power.
emergency bus - emergency power relay - copilot stby radio, cvr, nav no 1, aural warn, sdu no1, copilot, flt data recorder, emergency warning light, thrust reverser, emergency landing gear, emergency stall, flood light, trim warning, landing gear safety switch, fire bell, oxygen control, door seal, hyd shutoff valves, fire extinguisher, turbines, rpm indicator, ignition, fuel shutoff valves, fdr.
standby power battery - 50 amp/hr. heating resister heats up and tests the protection capability of the system.
cell test can be done on the standby power battery with each individual cell. 24 above is normal. PS- 835D (series)
oil pressure and flap degrees indicator --- alternating current
no.1 inverter --- primary bus
no.2 inverter --- secondary bus also act as an emergency if no.1 fails.
Chapter 23 - Communication
Radio Tuning Unit - Frequency controller = ATC Identify, DME, Com, ADF Test (Bearing swing 90 and audible 1KHZ ) deg, star on the display automatically returns to pre line when no commands been given. ATC STBY (on/off) DME HOLD would keep the current DME frequency before adjusting to another frequency when the button is pressed on. Com preset key - Com frequency can be set before use.
Radio Sensor System Control Panel -
RTU
No1 + 2 at normal - left RTU controls no 1, right controls no 2.
Remote (RMT) Tune DSABL - FMS CDU controls when switch is at normal position. RTU controls when the RMT Tune is disabled.
Markerbeacon Hi - Outter and inner
Ground comm push button gives you direct communication to the ATC.
FMS computer and control display unit CDU
pilot audio control panel - NAV, DME and MKR, AUTO COMM, nob with o2 mask or audio. speaker, interphone, voice identification with voice or audible codes, atc id press confirms the aircraft with the atc. Communication nob - Comm1, 2 and with the cabin. Audio emergency is louder at broadcasting frequency.
Volume control - COM, DME, NAV, ADF.
CVR - 6 Channels,
1 not used
2 co-pilot
3. pilot ---- middle channel is the most secure and protected from breaking
4. area mic
5. combination
6. cockpit area mic
ulb - underwater location beacon - transmit 30 days. Battery still working??
CVR Test button - press for 2 sec and audible low pitch sound, test meter in good area = functioning.
Erase - press and audible sound
Impact switch when damaged auto pops the circuit breaker to protect the cvr.
cabin pressure lo - cab altitude higher that 9500ft
Cab pressure hi - press differential excceeds 11psi
left and right fire detector fail
left and right windshield temp hi (overheat)
horizontal stabilizer de-ice sys failure.
left and right oil pressure lo
left and right fuel pressure lo
flap asym - will stay as is without moving outwards anymore because the flap is 6.5 degrees different from eachother.
fuel feed - 5 min
fuel level lo - 30 min
fuel transfer pressure low - when sensed 3.5psi light comes on, auto shutoff transfer pump.
wing tanks over pressure - more than 3.5psi.
left and right fuel filter bypass - filter may be clogged.
left and right hydraulic pump press lo - failure of hyd pump
left and right engine eec is operative - failure of engine electrical control
left and right stall warning fail
left and right generator fail
Left and right feeder bus fail - if one of the 3 feeders fail, the emergency one is in use.
battery cutoff - battery relay has relaxed open
emergency bus fdr fail - emergency bus has lost the normal power source.
no 1 and 2 inverter fail
left and right de ice temp low
Airconditioner fail - over pressure or over temperature ACM (engine) electrical would be vapour cycle machine
Ice detector just above the avionic bays in front of the windshield - has just failed.
bleed air duct fail - from leaking pressure
door unlock - entrance is not closed/locked properly.
defog air ov ht - defog air temperature is high
pitot ht off - pitot heater is off or pitot heater switch is on but failed to operate.
hyd level lo
antiskid fail
rudder boost fail - rudder boost inoperative. (when both engines thrust is different or unequal, automatically corrects the yaw effect.)
Engine sychronization - No1 and No2 N1 or N2 synchronize. No 2 engine will sychronize with number no.1.
emergency light no arm - emergency battery not charging.
25.6sec landing light delay and wing ice temp lo.
Avionics
Intergrated avionics processor system
ICC IAPS Card Cage
IOC Input output concentrator
IEC IAPS Environmental controller - maintains a set temperature of the IAPS
LHP Lightening protection
CSU Configuration strapping unit
MDC Maintenance Diagnostic computer
FCC Flight control computer - controls and signals automatic trim coupler
ATC Automatic trim coupler *roll* monitor and auto trim servo
ARP Referrence panel -
PFD Primary Flight Display
MFD - Multifunction display - Weather radar, TCAS etc
RTU - Radio tuning unit
SDU - sensor display unit
CDU control display unit
AAP - altitude awareness panel
APP Autopilot panel
CHP course heading panel
ARP Air data referrence panel
RRP Radio reversion panel
FmC flight management computer - flight plan management
mdc maintenance diagnostic computer - trouble shooting false signals - everything on the annuciator panel
TCAS ToP Antenna (Directional)
TCAS bottom Antenna (OMNI Directional)
Multifunction display - TAT total air temperature is normally higher - SAT normally below 0 degrees static air temperature
REV - controls the co-pilot (opposite side)side of the CDU
pilot left static port top - right static port bottom (cross)
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