What is the Landing gear transfer unit (LGTU) for?
When is it activated?
Uses system B fluid to raise gear when:
- airborne
- landing gear lever UP
- either main gear NOT up
- Eng #1 rpm drops (<50% N2)
When does the PTU operate?
- system B pressure drops and
- airborne and
- flaps <15 but not up
Standby Hydraulic pump automatically activates when:
- FLT CONTROL A or B switches ON
- loss of system A or B pressure, and
- airborne with flaps extended or
- on the ground w/ wheel speed >60kts
or - FFM trips
Rudder Pressure Reducer activated when:
-speed >135kts, hydraulic systems A and B pressure reduced by 25%
Do NOT DISPATCH/TAKEOFF items:
- ELEC light
- ENGINE CONTROL light
- CDS FAULT on PFD (amber)
- PSEU light, depending on how when it comes on
Autopilot disconnect methods:
Manually:
- manual trim activation
- autopilot disconnect switches (on yoke or MCP)
- override force applied to control column
- MCP A/P disconnect bar
- STAB TRIM CUTOUT switches - OFF
Automatically:
- TO/GA pressed in SINGLE CH
- TO/GA pressed after touchdown during dual A/P approach
- IRS fail
- Loss of respective hydraulic system
- loss of electrical power
- 2 sec after VOR LOC capture with RA inop
-Any attempt to override dual A/P
Assumed Temp Method (ATM) and fixed derate:
When allowed?
ATM not allowed when:
- anti-skid inop
- contaminated runways
Can use fixed DR on contaminated runways.
No greater than 25% total reduction from rated TO thrust.
Nose wheel well horn sounds when:
- battery drain condition exists
- E&E bay over temp condition on ground (equipment cooling fan failure)
- GRD CALL button pushed.
PSEU light comes on when:
On ground only:
- fault detected in PSEU or
- main cargo door switch failed giving false door position indication during recall
-Inhibited from thrust lever advance for take off until 30 secs after landing
IRS lights
ALIGN:
ON DC:
FAULT:
DC FAIL:
ALIGN:
steady:
-align mode or shutdown cycle
Flashing:
-alignment can not complete due to:
—aircraft movement
—difference between a/c position and last position
—no present position entered
FAULT:
-fault in related system
ON DC:
- related IRS operating in DC power from Switched Hot Battery bus (AC power not normal)
- (on ground) nose wheel call horn sounds due to battery discharge
- momentarily on during self-test
- R IRS will shut off after 5mins on BAT
DC FAIL:
-dc power for related IRS not normal
REVERSER light:
- TR isolation or control valve not in commanded position
- TR sleeve not in commanded position
- auto-restow activated
- failure of sync shaft lock
ENGINE CONTROL light:
A/C not dispatchable due to faults
Comes on when:
- aircraft on ground and
- engine operating, and
- <80kts before take off, or
- 30secs after landing
Flight recorder test switch:
NORMAL:
In flight
And on ground
In flight:
-operates anytime electrical power
On ground:
- either engine must be running
When fire switch illuminates, what happens?
Fire handle/switch is unlocked
What happens when a fire switch is pulled?
- closes spar and engine fuel sov’s
- closes engine bleed air sov’s
- closes engine driven hydraulic pump SOV and deactivates respective LOW PRESSURE hyd light
- trips generator control relay and breaker
- disables respective thrust reverser
- arms one squib on each bottle
- allows fire switch to be rotated
Speed Trim System operates when?
Frequently during takeoffs, climbs, and go-arounds (particularly at low gross weight and aft CG).
System active:
- speed 100kts - .60M (fade out by 0.68M)
- 10s after takeoff
- 5s after trim release
- A/P disengaged
- trim sensing requirement
Mach Trim operates when:
Activated above .615M
What is on hydraulic system B?
Flight controls
- aileron, elevator & elevator feel, rudder
- autopilot B
Systems used in flight
- TE flaps and LE devices, auto slats*
- main yaw damper*
- flight spoilers (2 on each side)
On the ground
- Normal Brakes
- #2 thrust reverser
Backup
- Landing gear transfer unit*
- ALT nose wheel steering*
What is in hydraulic system A?
Flight controls
- aileron, elevator & elevator feel, rudder
- Autopilot A
Systems used on ground
- landing gear*
- normal nose wheel steering
- ground spoilers *
- flight spoilers (2 on each side)
- #1 thrust reverser
Backup
- PTU power*
- ALT brakes*
What is on standby hydraulic system?
- Rudder
- L and R thrust reverser
- ALT LE devices
- Standby Yaw damper
Engine:
Warmup time?
Cool down time?
2 min warm up
3 min cool down
Engine Start Switches
GRD:
OFF/AUTO:
CONT:
FLT:
GRD:
- opens start valve
- closes engine bleed valve
- arms selected igniters on ground, arms both igniters in flight, to ignite when Engine Start Lever moved to IDLE
- release to OFF at start valve cutout (56% N2)
OFF/AUTO:
-normal position
-both igniters activated when start lever in IDLE and:
—uncommanded rapid decrease in N2 or,
—N2 between 57%-50% or,
—in flight - N2 between idle and 5%
AUTO: (same as off except:)
-provides automatic ignition to selected igniters when:
—engine running and,
—flaps not up below 18,000ft or,
—engine anti-ice selected ON
CONT:
-provides ignition to selected igniters when engine operating and engine start levers in IDLE
—in flight - provides ignition to both igniters when N2 below idle and start lever in IDLE
FLT:
-provides ignition to both igniters when engine start lever is in IDLE
What does the PSEU monitor?
PSEU monitors:
-takeoff config warnings
-landing config warnings
-landing gear
-air/ground sensing
What will cause a take off config warning?
—incorrect flaps
—trailing edge flaps skew or asmtry
—leading edge devices
—speed brake lever not down
—Spoiler control valve not pressurized
—parking brake
—main deck cargo door not secure
—incorrect trim settings
