Systems Flashcards by Mack Smith

What is the wingspan of the T-38? (TO 1T-38C-1TO: 1-5)

25 feet 3 inches

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What is the length?

46’4”

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What is the gross weight of the T-38? (TO 1T-38C-1TO: 1-5)

12,800 pounds

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Sea level, standard day, static thrust for each installed engine is ____ lbs at MIL power and ____ lbs at MAX power. (TO 1T-38C-1TO: 1-7)

2200 / 3300

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The exhaust gas sensing system (T5) varies the nozzles to keep the EGT between ____ and ____ at both MIL and MAX. (TO 1T-38C-1TO: 1-7)

630o / 650o C

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Momentarily pushing the start button arms the ignition circuit for approx. _____ seconds.
(TO 1T-38C-1TO: 1-7)

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Throttle bursts are defined as __________. (TO 1T-38C-1TO: 1-8)

Throttle movement in 1 second or less from idle to MIL

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Avoiding throttle bursts helps to minimize ______ . (TO 1T-38C-1TO: 1-8)

The possibility of compressor blade failures

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The Electronic Engine Display (EED) is powered by ________. (TO 1T-38C-1TO: 1-11)

Right Essential DC power

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Which sensors on the EED require AC power? (TO 1T-38C-1TO: 1-11)

Oil Pressure, Fuel Flow and Fuel Quantity

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Normally which EED operates as the Master and which EED operates as the Slave?

FCP EED is the Master, RCP EED is the Slave. (TO 1T-38C-1TO: 1-11)

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Erroneous or fluctuating engine sensor data on the Master EED should be confirmed by the other cockpit by __________. (TO 1T-38C-1TO: 1-11)

Switching the Master/Slave relationship on the EED

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When the EED is powered either ON or OFF, the EED momentarily activates the _____ caution light.

FUEL LOW. (TO 1T-38C-1TO: 1-13)

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If the ambient temperature is below 32o F, the EED may take up to _____ minutes to turn on.

(TO 1T-38C-1TO: 1-13).

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The digital readout of the Engine Tachometer (RPM) is from _____ to _____ rpm in ____% intervals.

0% to 110% RPM in 1% intervals. (TO 1T-38C-1TO: 1-14)

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The digital readout for Exhaust Gas Temperature is from ____ to _____ o Celsius in ____ degree increments. (TO 1T-38C-1TO: 1-15)

0 to 1200o C in 5o C increments

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If an EGT exceedance of greater than 650o C but not greater than ____oC occurs without an EGT OVERTEMP CAUTION, the mission may be continued. (TO 1T-38C-1TO: 1-15)

665oC

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Describe the EGT overtempt as depicted by the EED:

Red EGT symbol in the lower left hand corner, as well as red pointer and red digital number readout.

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Describe a latched EGT as depicted by the EED:

Red EGT symbol in the lower left hand corner, white pointer and white digital numbe readout.

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The digital readout for Nozzle position on the EED is from _____ % to _____ % in _____ % increments. (TO 1T-38C-1TO: 1-16)

0-99% in 1% increments

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The digital readout for Oil Pressure is from ____ to _____ psi in _____ psi increments.

0-80 psi in 1 psi increments (TO 1T-38C-1TO: 1-17)

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Under what two conditions would the Oil Pressure latch? (TO 1T-38C-1TO: 1-17)

Oil pressure < 5 PSI for 30 seconds continuously with weight-off-wheels
≥ 56 PSI for 30 seconds continuously with weight-off-wheels

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For both the left and right FF indicators to operate normally, the FF power supply requires _________. If this power is absent, both the left and right FF indicators will display ______. (TO 1T-38C-1TO: 1-19)

DC power from the left essential DC BUS. 0

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Does the increased Fuel Flow due to Afterburner operations get provided or displayed to/by the EED?

No. (TO 1T-38C-1TO: 1-19)

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The FUEL LOW caution light illuminates when either fuel tank registers _____ lbs or less for _____ seconds or more.

250 pounds or less for 7.5 seconds or more (TO 1T-38C-1TO: 1-20)

The fuel quantity imbalance indicator follows what schedule i.e. when does it display an imbalance, and when does it turn red? (TO 1T-38C-1TO: 1-20)

No Display: 0 − 50 pounds difference, White: 60 − 190 pounds difference, Red: ≥ 200-pound difference

Turning on pitot heat or exterior lighting (i.e. Landing/Taxi and Formation Lighting) may cause up to ____ pound change in displayed fuel quantity depending on internal/external power sources.

+/-100 pounds (TO 1T-38C-1TO: 1-20)

Changes of greater than +/- 100 pounds are indicative of ___________. (TO 1T-38C-1TO: 1-20)

Fuel quantity probe failure

If an EED overtemperature occurs, EED brightness is reduced by ____ % (Day Mode Only) and “EED HOT” is displayed in the EED message window.

50%. (TO 1T-38C-1TO: 1-20)

What functions does the main fuel control perform? (TO 1T-38C-1TO: 1-29)

1. Regulates engine speed based on the selected throttle setting. 2. Manages main engine fuel flow at all points of engine operations such as start and rapid throttle movement to ensure consistent thrust levels. 3. Provides protection from over-temperatures, engine stalls, and flameouts. 4. Limits main engine fuel flow at low throttle settings to ensure proper fuel-air ratios for low power and engine restarts during flight. 5. Correctly positions the compressor inlet guide vanes and air bleed valves.

At the full MAX position, at sea level and standard day conditions, total fuel flow for each engine is ____ PPH at rest and ____ PPH at Mach 1.0.

7300 PPH and 11,400 PPH (TO 1T-38C-1TO: 1-29)

Describe the EED indications before engine start with battery power:

``` OFF indicated for: L/R Oil Px L/R Fuel Flow, L/R Fuel Quantity Total Fuel Quantity ``` (TO 1T-38C-1TO: 1-22)

An airframe mounted gearbox for each engine drives an associated ________and __________.

AC generator and Hydraulic pump (TO 1T-38C-1TO: 1-22)

Gearbox shift occurs between what RPM range?

65-75% (TO 1T-38C-1TO: 1-22)

What is the capacity of the oil system in each engine? (TO 1T-38C-1TO: 1-22)

4 quarts with 1 quart expansion space

Oil consumption engine operation and overboard venting caused by condensation and aerobatic flight should not exceed _____ ounces/hr.

6 ounces/hour. (TO 1T-38C-1TO: 1-22)

A compressor stall at low altitude can be recognized by what indications? (TO 1T-38C-1TO: 1-30)

A pop or bang followed by an audible buzzing sound and vibration, accompanied by a rapid RPM drop and high EGT.

A compressor stall at high altitude can be recognized by what indications? (TO 1T-38C-1TO: 1-30)

An audible chug or pop accompanied by a rapid RPM drop and decreasing EGT.

In both cases, what actions may clear/recover the compressor stall? (TO 1T-38C-1TO: 1-30)

Rapidly retarding the associated throttle to IDLE and pressing the ENGINE START button.

Normally, fuel flow from the boost pumps is sufficient from sea level up to _____ MSL, however it is only guaranteed up to _____ MSL. Flameouts have occurred as low as ______ MSL. (TO 1T-38C-1TO: 1-30)

25,000’ MSL, 6,000’MSL, 7,000’MSL

L/R FUEL PRESS lights may be an indication of boost pump failure if crossfeed is _____, the corresponding fuel shutoff is in _____, and the throttles are out of ______. (TO 1T-38C-1TO: 1-32.1)

OFF, NORMAL, OFF

Placing either fuel shutoff switch to CLOSED shuts off fuel flow to that engine in approx. ____ second(s

1 second. (TO 1T-38C-1TO: 1-32.1)

The fuel quantity indicators should be monitored to ensure the two fuel systems are within _____ lbs of each other to ensure Aircraft Center of Gravity (CG) is within limits. (TO 1T-38C-1TO: 1-32.1)

200 lbs

If either fuel system has less than ____ lbs of fuel, the surface of the fuel falls below the boost pump upper inlet and boost pump output is reduced by _____%.

650 lbs, 40%. (TO 1T-38C-1TO: 1-33)

Taxi operations with less than _____ lbs in either system can cause cavitation of the boost pump of that system, resulting in engine flameout at low power settings.

150 lbs. (TO 1T-38C-1TO: 1-33)

During Single-Engine, Low Fuel operations, and less than 250 lbs in either system, place both boost pumps to _____ and the crossfeed switch to ______ to allow the engine to be fed by both systems simultaneously.

ON, ON (TO 1T-38C-1TO: 1-33)

The DC power system, consisting of the right and left DC buses and the non-essential DC bus, is powered by two ____-amp DC TRU’s or one _____ volt battery.

50 amp TRU / 24 volt battery. (TO 1T-38C-1TO: 1-36)

The two AC generators come online when the respective engine RPM accelerates to approx. ______%

43-48% (TO 1T-38C-1TO: 1-36)

Both generators operate at _____ Volts, providing three-phase AC power.

115 (+/-2) (TO 1T-38C-1TO: 1-36)

Should one generator fail, automatic transfer of the electrical load through the interaction of both protection panels may take up to ____ seconds.

2.5 seconds (TO 1T-38C-1TO: 1-36)

The static inverter converts DC Bus power to _____ volt AC power.

115 volt. (TO 1T-38C-1TO: 1-37)

Aircraft hydraulic power supply systems include a _____ psi utility hydraulic system and a _____ psi flight hydraulic system.

3000/3000 (TO 1T-38C-1TO: 1-44)

A FLIGHT/UTILITY HYDRAULIC light illuminates for what two reasons? (TO 1T-38C-1TO: 1-44)

1. Low hydraulic Pressure (Below 1500 psi) | 2. Hydraulic fluid overtemperature

A FLIGHT/UTILITY HYDRAULIC light will go out if:

1. The hydraulic pressure is restored to 1800psi or higher | 2. The hydraulic temperature cools down below overheat threshold conditions. (TO 1T-38C-1TO: 1-44)

Normal landing gear extension/retraction takes approx. ______ seconds. (TO 1T-38C-1TO: 1-46)

6 seconds

The landing gear warning system is activated when the landing gear is not down and locked and what three conditions exist: (TO 1T-38C-1TO: 1-46)

1. Airspeed is 210 KCAS or less 2. Altitude is 10,000’ MSL or below 3. Both throttles are below 96% RPM

With DC Failure, the RCP ____ gear light does not illuminate due to gear relay wiring. (TO 1T-38C-1TO: 1-47)

Nose Gear

The landing gear alternate extension handle must be pulled to approx. _____ inches. Extension of the main and nose gear required approx.. _____ seconds, but can take up to _____ seconds. (TO 1T-38C-1TO: 1-47)

10 inches, 15 seconds/ up to 35 seconds

After an alternate gear extension, what system is unavailable until the system is re-activated?

Nosewheel steering (TO 1T-38C-1TO: 1-47)

Under what two conditions is NWS automatically turned off? (TO 1T-38C-1TO: 1-47)

1. Selecting MAX on one/both throttles | 2. When A/C weight is not on the nose wheel

With a hydraulic failure, will you lose braking action? Why or why not? (TO 1T-38C-1TO: 1-48)

No. The brakes are powered by a separate, completely self-contained hydraulic system.

When the nose gear is extended ¾ or less, the rudder is limited to ____ degrees from neutral in either direction. (TO 1T-38C-1TO: 1-48)

6 degrees

When the nose gear is extended to more than ¾, the rudder is limited to _____ degrees from neutral in either direction. (TO 1T-38C-1TO: 1-48)

30 degrees

The electrical RUDDER TRIM knob on the YSAS control panel provides the means of trimming the rudder ____ degrees in either direction, provided the DAMPER switch is in the YAW position. (TO 1T-38C-1TO: 1-49)

If one flap motor fails, will you have the use of both flaps? Why or why not? (TO 1T-38C-1TO: 1-52)

Yes, the flaps are interconnected by a rotary shaft. Flap actuation will take longer than usual with one motor inoperative.

What purpose does the Flap-Horizontal Tail (Flap-Slab) Interconnect System provide? (TO 1T-38C-1TO: 1-52)

Compensates for aerodynamic changes caused by flap actuation to provide the same aircraft handling characteristics, regardless of flap position.

Intermediate speed brake positions can be obtained by __________. (TO 1T-38C-1TO: 1-53)

Positioning the switch to the desired direction of movement and then returning to the HOLD (Center) position.

The cabin pressure regulator maintains what schedule for cabin pressurization? (TO 1T-38C-1TO: 1-54)

1. Between 0 – 8000’ = 0 psi (ambient px) 2. Between 8000-23,0000’ = 8000 (+/-1000) feet 3. Above 23,000’ = 5 psi above ambient (+/-2000) (oap-6,000')/2 +/-2000=cabin px

What are the two indications of an air compressor turbine failure? (TO 1T-38C-1TO: 1-54)

Vibrations of the A/C system accompanied by fumes/odors from the A/C system

At engine speeds of 94-98% RPM, and the ANTI-ICE turned to MAN ON, an increase of approx. ____o C of EGT is considered normal. (TO 1T-38C-1TO: 1-55)

15oC EGT

With ANTI-ICE enabled, a loss of 180(+/-10) lbs of thrust is lost. This results in approx. ____% at MIL power and _____% at MAX power. (TO 1T-38C-1TO: 1-55)

8.5% at MIL, 5.5% at MAX

The YSAS may disengage, an ADC PFL generated, TAS may not be available, and all AoA lights may illuminate if the pitot heat is turned on during ground ops for more than ___ seconds. (TO 1T-38C-1TO: 1-55)

30 seconds

What are some conditions that may turn off the Yaw Stability Augmentor System (YSAS)?

1. AC power failure 2. Right essential DC power failure 3. MDP Failure 4. ADC Failure 5. EGI Failure 6. Utility Hydraulic Failure 7. Transfer of ICAO data from the DTS 8. Generator cross-over checks

Describe the different AoA indications available in the T-38 under one of the following conditions:

``` Very High AoA = 0.75 High AoA = 0.65 Optimum AoA = 0.60 Low AoA = 0.55 Very Low AoA = 0.45 ``` (TO 1T-38C-1TO: 1-59)

The front canopy is designed to withstand the impact of a ____ lb bird at aircraft speeds ranging from ____ to ______knots, depending on where the impact occurs. (TO 1T-38C-1TO: 1-60)

4 lb bird at airspeeds between 125-400 knots

possible, avoid opening the canopy when relative wind component exceeds 30 knots. How do you calculate the relative wind? (TO 1T-38C-1TO: 1-60)

Ground speed plus wind component over the nose

The canopy jettison system only works properly with both canopies in what position? (TO 1T-38C-1TO: 1-62)

Down and locked

The Manual Override Handle (MOR) provides manual seat separation capabilities if the automatic seat separator fails or if desired above _____ MSL. (TO 1T-38C-1TO: 1-64)

14,000 feet MSL 8,000'msl in mountainous terrain

During ground egress, what two ways may the leg garters be released? (TO 1T-38C-1TO: 1-66)

1. Individually operating the release button for each line | 2. Operating the quick-release lever on the forward left side of the ejection seat

The emergency oxygen cylinder provides O2 for approx. _____ minute(s), or until aircrew/seat separation.

10 minutes (TO 1T-38C-1TO: 1-66)

Do not operate the seat adjust switch for more than _____ minute(s) in any 8-minute period or the seat actuator could be damaged. (TO 1T-38C-1TO: 1-68)

1 minute