NATOPS Flashcards
T/O weight normal
164,000 lbs
T/O weight alternate
175,000 lbs
Landing weight recommended
142,000 lbs
Landing weight normal
164,000 lbs
Landing weight alternate
175,000 lbs
Fuel tank limits 1,4 2,3 ext aux
1,4 = 8310 2,3 = 7,650 Ext = 8,900 Aux = 5,810
Takeoff and Landing Fuel Management
- Max usable fuel weights in fuel weight limits
- # 1/#4 500-1000# more than #2/#3
- Main tanks are full, except for fuel used to taxi, t/o, and climb but not less than 7,060 in 1/4 and not less than 6,410 in 2/3 when ext contain usable fuel
- Fuel unbalance w/in limits
- refer to charts
Enroute fuel management
seeks to maximize the weight in the outboard fuel tanks as long as possible but does not take mission constraints into consideration while doing so. Improves wing-loading and efficiency during long transit legs; it also extends airframe service life, especially with medium to heavy cargo loads.
10% flaps
220 kias
20% flaps
210 kias
30% flaps
200 kias
40% flaps
190 kias
50% (takeoff/approach)
183 kias
60% flaps
165 kias
70% flaps
155 kias
80% flaps
150 kias
90% flaps
145 kias
100% flaps (landing)
145 kias
Landing gear extended
168 kias
Landing lights extended
250 kias
Cargo door open and locked; ramp up and locked
250 kias
Cargo door (all positions and motions)
250 kias
Ramp (all positions and motions)
250 kias
Paratroop air deflectors open
150 kias
Paratroop doors open and locked
250 kias
Paratroop doors opening/closing
150 kias
High-speed drogue operations
185-250 kias
Low-speed drogue while extending/retracting/engaging
105-120 kias
Low-speed drogue receiver engaged, maximum speed
130 kias
Severe turbulent air operation
180 kias
Inoperative windshield anti-icing below 10,000 feet
187 kias
Landing gear door removed and gear up
200 kias
Nose gear deflection of 20 degrees max speed of ___ knots
20 knots
Nose gear deflection of 60 degrees max speed of ___ knots
5 knots
Gross weight up to 164,000 pounds taxi limit speed
10 knots
Over 164,000 pounds observe the following taxi limitations:
- Taxi / t/o on smooth surface
- Max taxi speed 10 knots
- Taxi shortest distance possible
- Min braking during taxi operations
- light braking during turning
- limit nose gear steering angle to 20 degrees
- avoid abrupt or hard uneven application of brakes
Maximum tire speed (nose)
139 knots true ground speed — 12-ply rating
Maximum tire speed (main)
174 knots true ground speed — 26-ply rating
With any flap extension, the maximum maneuver load factor is ___ g in symmetrical and ___g in unsymmetrical maneuvers
2.0 and 1.5
High bank-angle limitations
Maneuvers beyond 60 degrees angle of bank with flaps retracted or beyond 45 degrees angle of bank with flaps extended
Prohibited maneuvers:
- aerobatics and spins
- practice stalls with power above 1,000 hp
- practice asymmetric power stalls
- Intentional zero or negative g maneuvers lasting longer than 7 seconds
- sustained airspeed below stick pusher speed
- Intentionally maneuvering the a/c into sideslip left/right rudder alert
- abrupt longitudinal control inputs at high speeds
- rapid roll reversals
- At airspeeds above 150 kias, moderate to large rudder input held until sideslip peaks followed by opposite rudder
Apu starter duty cycle
1 minute on and 4 minutes off. There is no limit to the number of duty cycles.
Aux boost pump pressure
28 to 40 psi
Ext boost pump pressure
28 to 40 psi
Main boost pump pressure
15 to 24 psi
Main (transfer) boost pump pressure
28 to 40 psi
Fuel unbalance limits
- 1,000 pounds between tanks of a symmetrical pair (main or external)
- 1,500 pounds between the left and right wings except as stated in item 3.
- One aux tank full and other aux tank empty, provided all other tanks are symmetrically fueled or unbalanced toward the opposite side within the above limits.
Autopilot limitations
- T/o and landing
- airspeeds above Vh
- ils coupled approach below 200 feet, below MDA on a non-precision approach, or when flying over the localizer transmitter
- during IPRA coupled approach below 200 feet HAT
- at or below 500 feet AGL for nonapproach operations
- RVSM + or - 65 feet of altitude
- At gross weights above 164,000 lbs – below 1,000 ‘ AGL, during configuration changes, during approach operations
Battery voltage AV and UTIL
22 Vdc
G limits symmetrical in area A
-1.0 to 3.0 g
G limits rolling in area A
0.0 to 2.33 g
G limits symmetrical in area B
0.0 to 2.5 g
G limits rolling in area B
0.0 to 2.0 g
CG limits
15 - 30 % MAC
Primary fuels
JP-5, JP-8, F-24, TS-1
Engine
four AE 2100D3 turboprop engines
Engine three major assemblies
- power section (two-rotor system with a free power turbine)
- propeller gearbox (plus propeller)
- torquemeter (shaft and interconnecting struts)
ATCS scheduling
50 to 100 percent of takeoff power over a 40 knot range
Oil system specs
independent oil systems, one for each engine, lubricate the engine power section and GMAD/PGB
20-gallon tank in each nacelle above the engine
12-gallon oil capacity with 8-gallons used for air space
.66-gallon dedicated reservoir for emergency feather pump oil supply
Oil flow
Oil gravity fed from the tank, through a shutoff valve to the GMAD/PGB pump and filter and engine power suction pump. The engine power section pump supplies pressurized oil through the engine oil filter to engine components requiring lubrication. The GMAD/PGB pump and filter supply oil for the prop gearbox, generator cooling, and propeller operation. Scavenged oil from the GMAD/PGB and engine power section is returned to the engine oil tank through independent air oil seperators, an oil filter, a fuel cooled oil cooler, and an air oil cooler.
Engine fuel system
Delivers filtered metered fuel for combustion, provides pressurized fuel to operate the CVG system, and provides supplemental cooling for engine return oil. Major system components include: the FPMU, CVG hydraulic actuator, the FCOC, fuel flow sensor, and fuel nozzles.
Green B in center of the HP dial
propeller blade angle is between 23 and 10.5 degrees
FADEC has not detected any failures preventing ground range operation and speed is below 145 KTAS
White BETA label is displayed below the affected engine HP display
blade angle is less than 10.5
Minimum bleed air pressure for sustaining a start is __psi
22 psi
Do not select the START position if MGT is above ___degrees C
175 degrees C
Engine start sequence:
- starter light next to ENG START switch illuminates
- 14% NG, FADEC arms the fuel and ignition control circuits. 4 secs later ignition is energized and the fuel latching shutoff valve opens to start fuel flow (fuel flow may not be indicated until 40% NG) ~20-25 seconds
- Starter cuts out at 65% NG, starter light extinguishes, continuous ignition terminates at 65% NG
- Starter switch to NP on speed ~ 30 secs
- Hyd op px should be indicated w/in 30 sec NP on speed
If fuel has been sprayed into the engine without ignition
Motor the engine for atleast 30 seconds with the ENG START switch held in MOTOR
When restarting an engine on the ground, wait __ seconds after NG indicates _ percent before attempting a restart.
30 seconds ; 0 percent
FLCV’s – #1/#4
Three
Two compensate for wing flex and allow a greater fuel load in flight, the third is installed but not operational
FLCV’s – AUX, EXT, #2/#3
Each contain one FLCV
AUX tank details
Bladder-type left and right aux tanks installed in the wing center section.
EXT tank details
two all-metal 1,309 gallon mounted under each wing on pylons between the inboard and outboard engines.
Partially compartmented for CG control. A surge box in the tank center compartment contains two pumps, providing dual reliability.
All fuel tanks are vented to the ___ to equalize pressure at all times.
atmosphere
Tanks #2/#3 and left and right aux tanks vent system
Wrap around vent system
Tanks #1/#4 vent system
Vented by float-controlled vent valves to prevent fuel loss overboard on the ground when the aircraft is not in a wings level attitude
Each main tank has a __ to __ psi ac-powered boost pump
An additional __ to __ psi ac-powered transfer pump
15 to 24 psi
28 - 40 psi
Left and right aux tanks have one __ to __ ac-powered transfer pump
28 to 40 psi
External tanks have __ transfer pumps with only __ pump used for normal operations.
two ; one
Minimum crew requirement?
Aircraft commander
Copilot
Crewmaster
How many combat troops?
78
How many ground troops?
92
How many paratroops?
64
How many litters/attendants?
70/6
74/2
Aircraft dimensions:
Width: 132’ 7”
Length: 97’ 9”
Height: 39’ 2”
10% flaps speed
220 KIAS
20% flaps speed
210 KIAS
30% flaps speed
200 KIAS
40% flaps speed
190 KIAS
50% flaps speed
183 KIAS
60% flaps speed
165 KIAS
70% flaps speed
155 KIAS
80% flaps speed
150 KIAS
90% flaps speed
145 KIAS
100% flaps speed
145 KIAS
Landing gear extended speed
168 KIAS
Landing lights extended speed
250 KIAS
Cargo door open and locked; ramp up and locked
250 KIAS
Cargo door (all positions and motions)
250 KIAS
Ramp (all positions and motions)
250 KIAS
Paratroop air deflectors open
150 KIAS
Paratroop doors open and locked
250 KIAS
Paratroop doors opening/closing
150 KIAS
High-speed drogues
185-250 KIAS
Low-speed drogues while extending/retracting/engaging
105-120 KIAS
Low-speed drogue receiver engaged, maximum speed
130 KIAS
Severe turbulent air operation
180 KIAS
Inoperative windshield anti-icing below 10,000 feet
187 KIAS
Flaps up g-limits up to Vh (symmetrical)
-1.0 to 3.00 g’s
Flaps up g-limits up to Vh (rolling)
0.00 to 2.33 g’s
Starter duty cycle (engine starter limits)
70 seconds on, 60 seconds off for 5 cycles, then a 20 minute cooling time is required.
What is a primary fuel and what are the US mil codes?
A fuel that the aircraft is authorized to use for continuous unrestricted operations.
JP-5, JP-8, F-24
Minimum crew currency requirement
5 hours total pilot time, 2 takeoffs and 2 landings in the past 45 days
If you don’t have passenger weights and/or baggage weights what shall be used?
200 pounds per person
70 pounds per baggage
Long range cruise operation–constant altitude operation, decrease power settings for each ____ pounds of fuel burned.
5,000 pounds of fuel burned
What are the factors affecting range?
F. Fuel temperature A. Alternate Fuels I. Icing T. Temperature H. High speed cruise P. Partial power cruise A. Altitude W. Winds/Weight
Factors affecting range:
Fuel temperature
Maximum range is affected by fuel temperature variation because of the change in fuel density.
Factors affecting range:
Alternate fuels
Alternate fuels, because of their density, also vary range capabilities.
Factors affecting range:
Icing
Since the aircraft pressurization and wing and empennage anti-icing is accomplished with hot bleed air from the engine compressor, a power loss occurs when these systems are used. The pressurization power loss is small, but the anti-icing power loss under severe conditions can result in losses up to 25 to 30 percent. Normally the aircraft will cruise above the altitudes where most icing weather occurs.
Maximum anti-icing will increase fuel flow 15% for the same cruise flight condition.
Factors affecting range:
Temperature
Non-standard temperature – refer to the perf man
Range will increase 2 percent for each 10 degrees C above standard temp, and decrease 2 percent for each 10 degrees below standard temperature.
Factors affecting range:
High-speed cruise
Fly constant maximum cruise power. Range will increase 5% for each 10 degrees C above standard and decrease 5% for each 10 degrees C below standard
Factors affecting range:
Partial power cruise
Maximum range is obtained by four-engine operation at optimum cruise altitude.
Factors affecting range:
Altitude
Since engine specific fuel consumption improves with increasing altitude, maximum range is obtained by four-engine cruise-climb operation.
Factors affecting range:
Weight/Wind
If HW of more than 70 knots are encountered, increase airspeed by 4 knots for every 10 knots above 70 knots.
Weight, a new power setting should be set for each 5,000 pounds of fuel burned.
Fuel requirements for all flights:
- Avg fuel for taxi and runup is 500 pounds
- If an alternate is not required, t/o to destination, plus a reserve of 10% of planned fuel requirements. If an alternate is required, t/o to IAF at destination, then to an alt airfield, plus a reserve of 10 percent of planned fuel requirements.
- Approach and landing fuel of 1,000 pounds
- Holding fuel of 1,334 pounds (20 minutes of fuel at 10,000 feet maximum endurance, four engines)
- Overwater flights where no alt is available, holding fuel increase to 2 hours at MAX END, at 20k feet
Additional overwater requirements for ETP
ETP will be calculated at cruise alt and 10k feet, and use 245 KTAS is recommended since it is the average TAS on four engines, long range cruise
What is ETP defined as?
Defined as the point at which the aircraft will be required to spend the same amount of time continuing to destination or returning to the departure point.
What is Point of Safe Return?
PSR is the point along the planned route at which the aircraft can return to the departure airfield and arrive with no more and no less than required fuel. PSR should be calculated for all overwater flights.
What is Point of No Return?
PNR is the point along the planned route at which the aircraft can return to the departure airfield and land with zero fuel. If the aircraft were to proceed beyond the PNR and attempt to return to the departure airfield, it would run out of fuel prior to arrival. PNR should be calculated for all overwater flights.
What characterizes a high speed landing?
- 100% flap landing above 155,000 pounds
- 50% flap landing above 130,000 pounds
- All 0% flap landings
- All landings at field elevation greater than 4,000’ MSL
- Temp greater than ISA +15degrees C, all landings at field elevation greater than 2,000’ MSL
Do not move the power levers below FLT IDLE above ___KIAS during a high speed landing. What happens?
145 KIAS
An over-frequency will occur causing the engine-driven generators to trip off-line, which leads to a lost in anti-skid protection.
TAWS colors:
High density red
More than 2,000 feet above current altitude
TAWS colors:
High density yellow
Between 1,000 and 2,000 feet above current altitude
TAWS colors:
Low density yellow
Between 250 feet below and 1,000 feet above current altitude
TAWS colors:
High density green
Between 250 feet below and 1,000 feet below current
TAWS colors:
Low density green
Between 1,000 feet and 2,000 feet below current altitude
TAWS colors:
Black
Terrain is more than 2,000 feet below reference altitude
TAWS colors:
Magenta
Unknown terrain
