Test 2 C-12 AQC Flashcards
IAW the operator’s manual, what weight and balance class is the Army C-12 U1 model?
Class 2
What is the formula for determining CG on the DD Form 365-4?
Moment / Weight = CG
What is the zero fuel weight limitation for the C-12 U1?
11,000 lb
For cargo loading purposes, the floor is designed to support _____lb/ft^2 when supported by the seat tracks, whereas the areas where seat track support is not possible will support 100 lb/ft^2 floor landing.
200
The ___________ position of the emergency locator transmitter (ELT) readies the ELT to transmit when an impact force occurs.
ARM
If the aircraft attitude reaches extreme limits, all scales, pointers, and annunciations not related to attitude are removed from the electronic Attitude Director Indicator (EADI). What is the bank limit that will cause this to hapen?
65 Degrees
On the Electronic Attitude Director Indicator (EADI), what will the FMS vertical deviation pointer do to alert the approach of a vertical path waypoint?
Flash
The radar altitude readout automatically shows on the Electronic Attitude Director Indicator (EADI) when the aircraft is at or below _________ AGL
2500
The Electronic Horizontal Situation Indicator (EHSI) has a wind arrow, how many knots of wind does each full feather on the arrow represent?
10
What provides control inputs to the EADI and EHSI?
Display Control Panel (DCP)
On the Turn and Slip indicator, where would the ball be during a skid?
On the outside of the turn
What provides the pitch and roll references for the standby attitude indicator?
Self-contained gyro
Which of the following is NOT a capability of the FMS 3000?
Auto-Land
_____________ processes transmissions from multiple GPS satellites simultaneously to calculate navigation solutions.
FMS 3000 Flight Management System
Which of the following is NOT a component of the FMS 3000?
Flight Data Recorder (FDR)
___________ accepts data from the GPS and computes a position estimate.
Flight Management Computer (FMC)
Each ________ provides an interface with the Flight Management Computer (FMC).
CDU-2000 Control Display Unit
All FMS data is visually displayed on _____________.
MFD, EADI, EHSI, and CDU
Which of the following is NOT a part of the initialization process of the FMS 3000?
Checking RAIM
Which of the following is NOT a guideline for programming an airway leg on the FMS 3000?
Both entry and exit waypoint need not be on that airway
To exit FMS holding function, press ____________ HOLD on the LEGS or HOLD page.
EXIT
When programming the FMS direct to a flight plan waypoint, press the ____________ key. Then select the waypoint from flight plan list and press EXEC.
DIR
To add/change an approach procedure in FMS, you will press the ________________ function key. Select key adjacent to desired approach and press EXEC.
DEP ARR
Which of the following is NOT a correct statement for missed approach procedures defined in the FMS 3000?
Missed approach procedures are automatically deleted from flight plan.
What is the definition for Vyse?
Best single-engine, rate-of-climb speed
What is the definition for Vx?
Best angle-of-climb speed (obstacle clearance speed)
How can the most accurate performance data be obtained?
By using existing conditions
When computing takeoff power engine ice vanes shall be retracted above what temperature?
15 deg C
You must re-compute a new TOLD card anytime conditions increase by?
1000 feet PA, 10 deg C, or 500 lbs gross weight
Where is the HOT Battery Bus physically located on the aircraft?
Located under the right wing center section
The aircraft battery provides _____ power to the electrical system.
24 VDC
What is the maximum generator load allowed at FL250?
100%
What is the starter limitation during the first start attempt?
40 seconds on, then 60 seconds off
How many times should you reset a circuit breaker for an essential circuit?
One Time
The BATTERY CHARGE annunciator should extinguish within approximately how many minutes after engine start?
5 minutes
The C-12 fuel system consists of __________ wing tanks.
five interconnected
If either auxiliary transfer system fails to operate, the fault condition is indicated by two illuminated MASTER CAUTION annunciators on the glareshield and a steady illuminated yellow __________ light on the Master Caution/Advisory annunciator panel.
1 or #2 NO FUEL XFR
Normal gravity transfer of the main wing fuel into the nacelle tanks will begin when __________ is exhausted.
Auxiliary fuel
The _____________ and ______________ in each fuel system provide inlet head pressure to the engine driven primary high-pressure fuel pump.
engine-driven fuel boost pump; standby fuel pump
When the #1 or #2 NAC LOW annunciator on the caution/advisory panel illuminates there is approximately ______________ of usable fuel remaining at sea level normal cruise power consumption rate for the applicable engine.
30 minutes
Illumination of the No. 1 or No. 2 FUEL PRESS warning light usually indicates failure of the respective?
Engine-driven boost pump
A _______________ system is installed in each engine to detect external engine fire and provide alarm to the pilot.
Flame surveillance.
Infrared radiation exposure activates the relay circuit of a __________, which causes signal power to be sent to cockpit warning systems.
control amplifier
Pulling the __________ will electrically arm the extinguisher system and close the fuel firewall shutoff valve for that particular engine.
fire control handle
Pressing the lens of the __________ switch will fire the squib, expelling all the agent in the cylinder at one time.
PUSH TO EXTINGUISH
Which system is NOT part of the Pneumatic system?
Air-conditioning system
The rudder boost system is ____________.
An aid for maintaining directional stability during engine failure or large power variation between engines
During simultaneous operation of the brake deice and surface deice systems, maintain the N1 at __________% or higher. If adequate pneumatic pressure cannot be provided for simultaneous operation fo the brake deice and surface deice system, turn the BRAKE DEICE switch to _____________.
85%, OFF
Bleed air is supplied to the landing gear power pack to _______________.
Prevent pump cavitation
The poly-flow is used for which system?
Bleed air warning system
The gyro suction gauge normal range above 15,000 feet is?
2.8 to 4.3 inHg
Pitot heat should not be used for more than ____________ minutes while the aircraft is on the ground. Overheating may damage the heating elements.
15
To help prevent windshield cracking, windshield heat should be placed in the NORMAL position for at least ____________ minutes prior to using the HIGH position
15
