Board Prep Flashcards
APU in “arm” does what?
- Nosegear uplock bypassed to energize GOB
- APU load control valve disabled
- APU scissor switch relay bypassed to allow APU ops during emergencies
—IF switch in ARM—
-Ground AC and engine starting unavailable from APU
Generators produce: __v, ___phase, ___Hz
120, 3, 400
The brushless generator incorporates 3 sub generators, these are:
PMG, Exciter, Main Generator
Hyds pumps: Type, #, Output, Low Px, Temp High, Shutoff Temp
- Vickers variable displacement
- 3
- 8 gpm
- 1800 PSI
- 150*F
- 380*F
Runaround Relays located where?
Purpose?
Power Source?
MLC - 7,4,3,6,2,5
Supply power to MEAC/FEAC
Do not require a power source, self rectifying.
GOB powered by ____ provides the GOB relay is deenergized. This relay can be deenergized 3 ways:
GOB has no backup power source
- Place nosegear uplock switch in the “Not Up” position
- Place APU arming switch to Arm
- Pull GOB relay CB on FEDC
RAWS provides flashing red lights and an intermittent tone under the following conditions:
- 3 sec warning @ 380 +/- 20
- Continuous warning @ 170 +/- 10
- Power interrupted to radalt @ any altitude
- Radalt becomes unreliable
Conditions for Autofx
Priority
- System is armed
- Less than 500# of thrust
- Above 60* +/- 2 coordinator
- No other engine has feathered
4,1,3,2
16% switch…
Opens the fuel SOV and energized the ignition relay
—IGN RELAY—
1. Energizes the igniters (cams 2 + 5)
2. Energizes paralleling valve solenoid
3. Energizes fuel manifold drain valve
4. If prime selected: energizes enrichment valve solenoid
Functions of the E-Handle
Shuts off Fuel @ FCU (E/M) Closes Fuel tank emergency SOV (M) Actuates FX system (E) Moves Feather valve to FX (M) Closes Bleed air SOV (E) Closes Oil tank SOV (E) Closes Gen cooling air SOV (M) Dumps EDC & closes FWSOV (E)
Accessory Drive:
FCU Engine driven pumps Speed sense control Speed sense valve Main oil pump Oil filter Scavenge pump
RGB:
Starter Tach gen Oil pump/filter( 1 main, 2 scavenge) Generator EDC
Usable engine oil tank capacity: Foaming Space: Tank volume capacity: Unusable oil: Tank px to: Drain down:
- 8.65 gal
- 5.7 gal
- 15.75 gal
- 1.4 gal
- 4.5 psi above ambient
- Oil draining into RGB/Pwr section. Requires motor over to pump the oil back to the tank
Engine brief:
- T56-A-14, single spool axial flow has turbine engine connected to RGB @13,820 rpm nominally.
- 14 stage axial flow compressor convergent in design, divergent in operation 9.64:1 ratio.
- 5th & 10th Open to relieve px during starts
- 25% of Air for combustion, 75% for cooling and flame control
LGWS actuation speeds, sound, cancellable?
-<153 +/- 3 AND PL < 48* coord — cancellable -<142 +/- 3 AND PL < 60* coord —cannot be canceled -Flaps Land —cannot be cancelled
Prop protective devices
2BA2PLAND Beta Follow Up Prop Brake Auto Feather Pitch lock Pitch lock reset Low pitch stops 45° Air Start NTS Decoupler
Prop Brake
Friction Type Cone Applied, locked, released >21% rpm and >50psi in RGB Prevents backwards spinning and windmilling Made of Brass
NO FLUID REQUIRED
NO ELECTRICITY REQUIRED
Beta Follow up
Stops loss of pitch caused by gradual power loss and high power settings. It’s a secondary variable low pitch stop, designed to maintain a min. blade angle based on coordinator setting.
34-68° coord = 11° blade angle
Linear increase from 68°-88°
88°+ coord = 22.5° blade angle
Reverse SHP, Fuel Gov Checks also verify this is working by checking for a min of 1500 SHP as you bring back PLs
FLUID REQUIRED
NO ELECTRICITY REQUIRED
Auto Feather
EMDC
Used during T/O to autofx a malfunctioning engine.
-Power Lever > 60° coord
-No other engine feathered
-Autofx system armed
-<500# thrusts
Feathers based on P-factor effect, 4-1-3-2 low to high effect.
FLUID REQUIRED
ELECTRICITY REQUIRED
Pitchlock
Limits prop over speed by preventing a decrease blade angle following an over speed or loss of fluid px.
-Cammed out below 17° to allow reverse
-Cammed out above 57° coord to allow FX
Over speed of 103.5% unseats the valve allowing teeth to touch.
NO FLUID REQUIRED
NO ELECTRICITY REQUIRED
DVFR
Defense Visual Flight Rules
“Refers to the type of flight plan that will be operating VFR in and around ADIZ or restricted air space (such as an oil platform with ADIZ boundary)
On flight plan instead of “I/V” file as “D”
*Operating Due Regard w/in ADIZ wont be within tolerances.
Symptoms of a pitchlocked prop
- RPM follows Power Lever movement.
- RPM stabilized at fuel topping gov 104.2-106.7%
- ASR (+-+)
- T/O = Power loss, over speed
- Landing = No Beta light, high SHP, Swerve.
Pitchlock Reset
FEDC
Used to reset pitchlock to 109% whenever blade angle is >10° and coord is <28° such as an aborted takeoff. De-energized when blade angle < 10°
FLUID REQUIRED
ELECTRICAL POWER REQUIRED
Horizontal Wx Depiction
Natops 7-2: “All overwater flights SHALL request HWD”
- Forecasted altimeter settings and min altimeter settings on station
- Ditch Headings
- Winds aloft
- Can request from FWB
Low Pitch Stops
Mechanically limits the blade angle to 13°.
It is released by full decrease px. Backup valve opens when power levers < 28° coord allowing the Main And Standby Regulating Valve to sense the demand for elevated px in the decrease pitch lines to break the Low Pitch Stops. Successful release of LPS indicated by a BETA light @ 10° blade angle.
NO FLUID REQUIRED
Runway Environment In Sight
- Approach Lighting System
- Threshold Lights
- Threshold Markings
- Runway Lights
- Runway Markings
- VASI
- Touch Down Zone Lighting
- Touch Down Zone Markings
- REIL
45° Airstart
Backs up NTS during an airstart by maintaining Blade Angle above 45°.
Conditions:
- Fx Button Unfeathered
- PCO not depressed
- Blade Angle < 45°
System operation energizes Airstart control relay, illuminates NTS INOP, and energizes FX valve solenoid causing FX valve to go to FX.
FLUID REQUIRED
ELECTRICAL POWER REQUIRED
Decision Speed
Minimum engine failure speed from which a safe takeoff can still be completed within runway length remaining.
Refusal Speed
The maximum airspeed from which the air craft can abort a takeoff and stop within runway length remaining.
Rotate Speed
Airspeed at which the transition from ground run attitude to climb out attitude has begun.
NTS
Results when the prop drives the engine and creates drag. Negative Torque can create enough drag to threaten controllability. Sensed in the RGB, once a certain value is reached a ring gear moves forward compressing several springs and extending the NTS pushrod. As Power levers are > 24° coord the linkage shifts the FX valve to FX resulting in increased pitch and less negative torque.
FLUID REQUIRED
ELECTRICAL POWER NOT REQUIRED
Decoupler
Physically disconnects the engine from the RGB between -500 to -1700 SHP.
- SHP will read 0 or wandering (unreliable <43%)
- If pitchlock decoupled you will fuel chop once clear of the active.
PROP FLUID NOT REQUIRED
ELECTRICAL POWER NOT REQUIRED
NTS MALFUNCTIONS
Stuck Power Lever - Likely an over rotates alpha shaft, clean up speed up
Plunger stuck extended - Rapid decay of RPM, SHP increasing. Clean up bleeds and e-handle
Weather Watch
SHALL not fly into, unless Storm has not progressed as forecasted AND:
- Able to maintain VFR or,
- Able to maintain IFR with aircraft Wx Radar, or
- IFR in positive control areas and VMC can be maintained, or
- Aircraft performance allows for flight above Wx layers
Fuel Log Requirements
SHALL be done when:
- Greater than 500 NM from nearest “suitable landing” field
- Flight duration > 6 hours
- Fuel gauge failure
- PPC discretion
Entries shall be either hourly or 5,000# increments.
Allows FE to detect fuel gauge malfunctions
On Top Requirements
Alternate not required: Fuel from T/O to destination plus a reserve of 10% of planned fuel req
Alternate Required: Fuel from T/O to destination IAF then to alternate plus 10% of planned fuel requirements
*In no case shall the planned fuel reserve after landing be less than 20 minutes at 10k’ at max endurance
DUE REGARD
- Aircraft SHALL be operated in VMC
- Aircraft SHALL be operated within surveillance and radio/satellite comms of a surface/airborne facility.
- Aircraft SHALL be equipped with airborne radar sufficient to provide separation between them selves, other aircraft, and any aircraft they may be controlling.
- Aircraft SHALL be operated outside of controlled airspace.
* PPC assumes responsibility*
MARSA
GP ch. 6
Military Assumes Responsibility for Separation of Aircraft:
Relieves ATC of separation burden.
I.E. Formations, AR
Command prerogative, not to be invoked by individual pilots
MOSA
Minimum Operational Safe Altitude
1000’ above highest obstacle (rounded up to nearest 100’) within 30 NM.
PRIOR to descending below MOSA, NAV must give bearing, distance, safe alt, and safe heading from “prior to descending below MOSA checklist”
Mando calls, “30, 25,…,10,9,8,…” nm
Calls may be waived by PPC
TFOA
- Notify Tower to sweep runway
- Notify QA, MX, and Safety
- Over water departure/approach if possible
- When in safe area attempt to punch lost cont buoys
- Use AIMS to verify item lost
Low Altitude Limits
N4.7
SYSTEMS DAY/VMC NIGHT/IMC
Radalt ; RAWS 200’ 300’
Updated Baro 300’ 500’
Nothing 500’ 1000’