Term
An emergency shall be declared and a landing accomplished
at the nearest suitable landing area considering the severity
of the emergency, weather conditions, field facilities, ambient
lighting, and command guidance. |
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Definition
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Term
Emergency conditions are less urgent and, although the mission
is to be terminated, the degree of the emergency is such
that an immediate landing may not be necessary. |
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Definition
| Land As Soon As Practical |
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Term
|
Definition
hard surface runway, taxiway, or
under/overrun. Landing on an unprepared surface or ditching
is not recommended. |
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Term
Essential steps or items which are to be checked in both
cockpits, if occupied, are indicated by (BOTH) following the
step. |
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Definition
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Term
| RESETTING A CIRCUIT BREAKER |
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Definition
If the mission can be continued or the aircraft safely recovered
without the affected equipment, the circuit breaker
should not be reset. |
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Term
In the AUTO start mode, if a no start is detected or if a hung or hot start is projected, the ___ should terminate the start
sequence. |
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Definition
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Term
| the engine start should be aborted manually in the following situations: |
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Definition
ITT rate of increase appears likely to exceed 1000 °C
(hot start)
• Normal N1 increase is halted (hung start)
• No rise of ITT is evident within 10 seconds after fuel
fuel flow indications (no start)
• BAT BUS annunciator illuminates during the start
sequence
• PCL is moved or the ST READY annunciator extinguishes
during the start sequence |
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Term
| If a start using _________ is aborted (PMU or manual abort), do not attempt subsequent starts. |
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Definition
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Term
During ground starts, what parameters
may cause the PMU to abort a battery start attempt. Though these parameters are not directly monitored by the PMU, they cause a rate of rise in N1 and/or ITT that are indicative of an impending
hung or hot start. |
|
Definition
-weak battery
-high OAT
-high pre-start ITT
-high density altitude
-tailwind |
|
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Term
| If a battery start was aborted connect ________ (if available) and perform Motoring Run Procedure |
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Definition
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Term
| Perform this procedure after any aborted start during which fuel was introduced: |
|
Definition
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Term
| What does motoring the engine do? |
|
Definition
| clear residual fuel and/or lower the ITT |
|
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Term
| The primary indications of an engine fire are: |
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Definition
| illumination of the FIRE and MASTER WARN annunciators |
|
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Term
| When should you do an emergency engine shutdown on the ground? |
|
Definition
-engine fire
-prop strike
-chip light
-likely to depart the prepared surface
-pilots discretion
-fuel flow in excess of 800pph |
|
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Term
The decision to takeoff or abort should be
based on the following: |
|
Definition
-Runway length and condition, terminal weather conditions and area traffic.
-If any system emergency affecting safety of flight is experienced prior to liftoff, the takeoff should be
aborted. |
|
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Term
| After a stop which required maximum effort braking and if overheated brakes are suspected what shouldnt you do? |
|
Definition
-Do not taxi into or park in a congested area until brakes have had sufficient time to cool
-Do not set parking brake |
|
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Term
| What is the T-6 stance on Barrier engagement? |
|
Definition
| Aircrews will not call for a raised barrier in the event of an aborted takeoff. If a raised barrier is already up, aircrews will steer around it, to include departing the prepared surface if necessary, or ejecting before engagement |
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Term
| What should you do if you encounter a tire failure during takeoff? |
|
Definition
-abort if possible
-do not change gear and flap position
-execute a straight in landing on the side corresponding to the good tire |
|
|
Term
| Initial indications of engine failure/flameout are: |
|
Definition
-loss of power and airspeed
-rapid decay in N1, torque, and ITT
-propeller movement towards feather due to loss of oil pressure.
-N1 will indicate 0% within
approximately 5 seconds, even though the gas generator core may not have seized. Torque will be indicating 0%. . |
|
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Term
N1 does not indicate speeds
below ___. |
|
Definition
|
|
Term
| Secondary indications of engine failure/flameout are: |
|
Definition
-rapidly decreasing ITT
-lower-than-normal oil pressure. |
|
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Term
| What annunciators can you expect to see illuminate with a loss of engine? |
|
Definition
-GEN
-FUEL PX
-OIL PX
-followed by the OBOGS FAIL
-PMU FAIL and CKPT ALT annunciators may illuminate. |
|
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Term
The zoom to eject is accomplished by pulling up to a ___ climb angle and ejecting before a sink rate
develops. |
|
Definition
|
|
Term
Zoom to eject allows the pilot to add ___ feet of altitude increase above the altitude gain noted in the zoom
chart due to not pushing over. |
|
Definition
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Term
If attempting an airstart or positioning to land, the following
procedures should be followed: |
|
Definition
Above 150 KIAS, initiate a zoom climb using a 2 G pull up to a 20° climb angle until approaching the desired glide airspeed (use approximately
20 KIAS lead point) and then initiating a 0 to +0.5 G pushover
to capture desired glide airspeed |
|
|
Term
| Below ___ KIAS, the benefits of a zoom climb are negligible |
|
Definition
|
|
Term
Zoom capability at 200 knots will vary from ___ to ___ft of altitude gained. Zoom capability at 250 knots will vary
from ___ to ___ft of altitude gained |
|
Definition
|
|
Term
At 125
KIAS, an engine which has flamed out will rotate below __% N1 and indicate __% N1. |
|
Definition
|
|
Term
The
engine oil pressure indicator may display oil pressures up to __ psi with an N1 of 0% |
|
Definition
|
|
Term
Airstart procedure is not recommended
below ____ feet AGL |
|
Definition
|
|
Term
| Three airstart procedures are approved for this aircraft: |
|
Definition
PMU NORM
PMU OFF
Immediate Airstart (PMU NORM). |
|
|
Term
airstarts have only been demonstrated
at _____feet MSL and below |
|
Definition
|
|
Term
useful power will be
available after ___ seconds from starter engagement |
|
Definition
|
|
Term
Approximately
____ feet of altitude will be lost during an airstart attempt
performed at the best glide speed of 125 KIAS |
|
Definition
|
|
Term
airstart envelope (125-200 KIAS for sea
level to 15,000 feet, or 135-200 KIAS for
15,001-20,000 feet). |
|
Definition
-125-200 KIAS for sea level to 15,000 feet
-135-200 KIAS for 15,001-20,000 feet |
|
|
Term
| If N1 does not rise within ___ seconds, discontinue the airstart attempt and proceed to IF AIRSTART IS UNSUCCESSFUL |
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Definition
|
|
Term
Movement of the PCL above IDLE before
N1 stabilizes at approximately ___% will cause an increase in fuel flow which may cause engine failure due to a severe ITT overtemperature. |
|
Definition
|
|
Term
| If there is no rise in ITT within ___ seconds after fuel flow indications, place the PCL to OFF and abort the start |
|
Definition
|
|
Term
| %The propeller will unfeather and accelerate to operating RPM approximately ___ seconds after N1 reaches __%. |
|
Definition
|
|
Term
If generator will not reset, verify the
STARTER switch is in NORM. The starter
will drain battery power in ___ minutes if left in MANUAL |
|
Definition
|
|
Term
T/F: It is possible to start with the bleed air inflow switch out of
OFF and the boost pump switch in ARM (PMU OFF AIRSTART) |
|
Definition
|
|
Term
| With the bleed air inflow switch in NORM or HI, the starting ITT may be up to ___ °C warmer than with bleed air inflow OFF |
|
Definition
|
|
Term
T/F: Continuous operation with the BOOST
PUMP switch in the ON position will cause
damage to the engine-driven low pressure
fuel pump |
|
Definition
|
|
Term
If the PMU does not remain on line,
anticipate a _____________ as the fuel metering nit reverts to the nominal condition for manual control |
|
Definition
| step change in engine power |
|
|
Term
| A loss of thrust caused by uncommanded propeller feathering may be the result of an |
|
Definition
an errant electrical signal to the
feather dump solenoid causing reduction in oil pressure to the propeller pitch control mechanism |
|
|
Term
| opening the PROP SYS circuit breaker will remove power from the feather dump solenoid and allow oil pressure to return, which brings the propeller out of a fully feathered state in ___-___seconds |
|
Definition
|
|
Term
Indications of propeller feathering
will be: |
|
Definition
-rapid reduction in propeller RPM (NP)
-high torque
-increase in propeller noise
-loss of thrust
-engine/airframe vibrations |
|
|
Term
During a prop-sleeve touchdown, the propeller moves toward _____ due to a temporary loss of oil pressure to the propeller pitch control mechanism. This malfunction manifests
itself with _______ These fluctuations may be erratic but should be temporary (usually less than ___ seconds),
and may be accompanied by a ____ detector warning. |
|
Definition
-feather
-fluctuations in NP, torque increasing, thrust decreasing, engine vibrations
-20sec
-CHIP |
|
|
Term
Ground idle will not be available during landing rollout and taxi. Plan for __________ due to higher IDLE N1
(approximately ___%). |
|
Definition
-increased landing distances
-67% |
|
|
Term
| With constant airspeed and torque, RPM can be considered stable if below 40% with no upward change for a ___-second period |
|
Definition
|
|
Term
| T/F: A fire warning light with no accompanying indication is a confirmed fire |
|
Definition
|
|
Term
| The standby attitude indicator will provide accurate indications for at least __ minutes after a loss of all electrical power. |
|
Definition
|
|
Term
| PMU FAILURE indications include: |
|
Definition
-simultaneous illumination of PMU FAIL and PMU STATUS annunciators
-possible step change in engine power |
|
|
Term
|
Definition
-PMU STATUS
-The PMU has detected a discrepancy in the weight on wheels switch. A reset is not possible |
|
|
Term
| Illumination of both red and amber OIL PX annunciators while the oil pressure gage indicates normal pressure indicates an __________. |
|
Definition
|
|
Term
| The generator will remain offline if the starter is in the MANUAL position and the starter will drain battery in less than ______ if left on |
|
Definition
|
|
Term
| With the bus tie closed, the generator and battery buses will remain powered until ___ volts. However, the EADI and EHSI will go off line at ___ volts. |
|
Definition
|
|
Term
| T/F: OBOGS will be inoperative once the main battery is depleted or with battery failure & cockpit will depressurize when power to the battery bus is lost. |
|
Definition
|
|
Term
| The GEN BUS annunciator will illuminate if the ___ circuit breaker on the generator bus circuit breaker panel in the front cockpit is open, or if there is an actual loss of the generator bus (and the associated avionics buses). |
|
Definition
|
|
Term
The BAT BUS annunciator will illuminate if the ___ circuit
breaker on the battery bus circuit breaker panel in the
front cockpit is open, or if there is an actual loss of the battery
bus (and the associated avionics buses), or if the current
limiter on the battery bus side has failed. |
|
Definition
|
|
Term
EADI will be inop if the ____ fails.
EHSI will be inop if the ____ fails.
____ will alleviate the problem if either fails. |
|
Definition
EHSI (gen fail)
EADI (bat fail)
EADI/EHSI composite mode |
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