Fuel Tank
- 7 Fuel Tanks
- Forward 1300 lbs
- Header Tank 204 lbs
- Aft Tank 790 lbs
- Outboard/Inboard Left Wing 735 lbs
- Outboard/Inboard Right Wing 735 lbs
- Usable Fuel CAP = 3764 lbs
- Unusable Fuel = 50 lbs
Throttle Detents
Flight Idle Stop
Ground Idle Stop
DEEC
Digital electronic Engine Controller
EGTS
Exhaust Gas Temperature Sensors
Never Exceed Speed
230 KIAS
250 KIAS
Manuvering Speed @ MAX Weight
158 KIAS
(Decreases aprox 4.5 KTS per 500 lb less than MAX gross weight)
MAX Flap Extension Speed
120 KIAS
MAX Gear in Transit Speed
135 KIAS
MAX Gear Extended Speed
160 KIAS
MAX Ramp Weight
10500 lbs
MAX Landing Weight
8500 lbs at 498 FPM
MAX Fuel Weight
3835 lbs
Electrical System Components
-Batteries - 6 - two sets of 3
- Primary Power 28 VDC
- 24 VDC
-PPDM (2) - BUS 1 of PPDM 40 AMP
- BUS 2 of PPDM 10 AMP
-EFIU
-RCM
-FJA (2) - Battery Juncton Assemblies 1& 2
- Battery 1,3,5
- Battery 2,4,6
-GCU
-DEEC
-ESM
The Landing GEar Switch automatically sends a gear up/down command when toggled.
False
The nose gear has a shock absorber.
True
The Aileron Servo CPU disables and freezes the servo when current exceeds ___________.
10 AMPS
The YAW Control capabilities of the ruddervators acts as a backup for the ventral rudder. When?
50 % of the rudder inputs are mixed into the ruddervator commands.
Manual control of the flaps is possible when airspeed drops below 117 KIAS and _________.
Gear is down and airspeed remains less tan 121 KIAS.
and
Gear is up and Airspeed HOLD is OFF.
The RCM Automatically decambers the wings using ____________.
Ailerons and Flaps.
The Flap slew rate is ________.
5 degrees/sec.
Aileron upward deflection is 2.5 times greater than downward deflection. Why?
To reduce adverse YAW.
If an aileron fails the stanby aileron is engages.
FALSE
The Throttle has __________ detents.
TWO
How many fuel tanks does MQ9 have?
7
What is the usable fuel capacity of the MQ9?
3764 lbs
How often do he Fuel Pumps cycle?
Every 10 mins with a 5 sec overlap.
How many Jet Pumps are installed?
4
When fuel jettison is activated, where does the fuel exit the Aircraft?
From the left wing trailing edge between the airlerons and flaps.
Which of the following will activate both fuel pumps:
Fuel pressure < 18 psi
and
Activating Fuel Jettison
On VIT Screen 1 "Fuel Remainin" s calculated from ____________.
-Fuel mass flow to engine.
-Level sensor readings before ignition on.
-Measured Header Tank Level.
A RED Warning for Header Tank overpressure indicates the _________________.
Header tank pressure has exceeded 5.0 psi.
When Fuel Jettison is selected in Automatic mode the following events occur:
Fuel jettison stops at 600 lbs measured.
The instantaneous accuracy of the MASS Flow sensor is _______.
+/- 0.5% lbs/hr
The MQ9 utilizes a TPE331-10Y Engine with an EFIU for engine control.
FALSE
During an engine failure an Oil Level of 60% in conjunction with Engine Oil Quantity Low message indicates _______________.
The unfeathering pump has pumped too much oil from the oil tank.
Beta Mode indicates.
A High Oil Pressure
The Throtle is not advanced past the 2nd detent.
All RED OIL Temperature warnings are....
50 degrees C and 115 degrees C
The operation of the condition lever in the TPE331-10YGD engine is ______________.
The same for DEEC Mode & backup mode.
In Backup mode, there are no Automatic engine limitations.
FALSE
Single RED Line control in the TPE 331-10YGD engine is performed by the ____________.
DEEC
Igniters are automatically enabled _____________.
Between 10% & 60 % RPM during normal engine start.
During in-flight restarts.
In backup mode the TPE331-10YGD engine SRL is controlled by the ___________.
There is no SRL Control in backup mode.
The DEEC inflight engine operating range is ________.
82% to 100% RPM.
The interstage fuel pressure is __________.
Monitored by the EFIU
&
Is normally 35 psi over inlet pressure.
The purpose of the on-engine oil/fuel heat exchanger is to __________.
Stabilize fuel temperature.
The function of the primaries-only-solenoid is to provide additional fuel pressure to he primary nozzles during the start sequence.
TRUE
The DEEC interface with the RCM is a _________.
ARINC 429
To maintain a constant RPM, _____________.
Engine power must equal propeller load.
How many electrical power distribution buses are on the aircraft?
2
What is the Prmary Power System Voltage on Bus 1?
28 VDC
What is the voltage on each of the Batteries?
24 VDC
How many batteries are contained in each set of Batteries?
3
How many sets of Batteries are installed in the aircraft?
2
Power is supplied to the aircraft from ____________.
- A Ground Power Unit (GPU)
-Two sets of three batteries per set
-The Starter Generator
What type of processing does the RCM use?
MLV (Mid Level Voting)
Fault tolerant components are connected to both UARBS.
TRUE
What communication interface is used by the FCA;s to share sensor data?
Cross-Channel Data Link
How many FCA's are in command during flight?
One
The MCS compares the quality of the data from the FCAs and the VP to determine which VP data the fault tolerant components will use.
FALSE
The RCM uses 3 FCA's and two Vote Processors to produce identical, command data sets.
TRUE
The RCM converts the _________ measurements to digital data.
Alpha Probe
The EGI Navigation DATA provides __________.
Better instantaneous accuracy, and more stability over time.
When any FCA resets during flight the warning message "FLight computer reset detected by UAV" is displayed.
FALSE
FCA Autopilot and Navigation Sensor Data is displayed on ____________.
VIT's 40, 41, 42
The A/C has no Lightening Protection.
TRUE
Add ______ percent of gust factor up t a MAX of ______ knots to rotation speed during crosswind takeoffs.
50, 10
Excessive roll and/or pitch angles can cause loss of LOS datalink.
TRUE
EGT protects the engine from overheating by overriding the throttle command.
TRUE
A Header Tank level of 208 lbs prompts emergency procedures for ___________.
A Fuel Header tank level or Pressure low condition.
The Overhead Approach is the only method Available to the Pilot during a Forced Landing.
FALSE
In performing an Engine Air Restart ___________.
Do not engage the starter during an air start.
An Engine Failure or a Generator Failure may require performing a Forced Landing procedure.
TRUE
CAPs for an Engine Failure include:
-Establishing a glide.
-Selecting a landing site.
-Placing the condition lever to the Aft Position.
Loss of Control may be indicated by complete failure of the Aircraft to respond to pilot control commands.
TRUE
Throttle-Full Reverse (P) and Brakes-Applied are CAPs for ___________.
ABORT procedures during take-off.
Land as soon a possible" applies to emergency conditions that are less urgent, and although the mission should be terminated, the degree of the emergency is such that an immediate landing at the nearest adequate facility is not necessary.
FALSE
What are Critical Action Procedures?
Steps that must be performed immediately with out reference to a written check list.
EGT Protects the engine from overheating by overriding the throttle command.
TRUE
Excessive roll &/or pitch angles can cause loss of LOS datalink.
TRUE
Add _____ percent of gust factor up to a max of _____ knots to rotation speed during crosswind takeoffs.
50, 10
MAX Fuel Weight is
3000 lbs
The Aircraft has no lightening protection.
TRUE
What is maneuvering speed at max gross weight?
158 KIAS
Operation of A/C into areas of lightening activity is prohibited.
TRUE
Rain increase stall speed by up to
10%
Ice, Snow or frost can reduce wing lift by as much as __________. Drag can increase by ___________.
30%, 40%
LAND AS SOON AS POSSIBLE" Applies to Emergency Conditions that are less urgent, and although the mission should be terminated, the degree of the emergency is such that an immediate landing at the nearest adequate facility is not necessary.
FALSE
Throttle-Full Reverse (P) and Brakes-Applied (P) are CAPs for _____________.
Abort procedures during takeoff.
Loss of Control may be indicated by complete failure of the aircraft to respond to pilot control commands.
TRUE
An Engine Failure or a Generator Failure may require performing a forced landing procedure.
TRUE
In performing an Engine Air Restart ________.
Do not engage the starter during an air start.
The overhead approach is the only method available to the pilot during a forced landing.
FALSE
A Header Tank level of 208 lbs prompts emergency procedures for _________.
A fuel Header Tank level or pressure low condition.
ENGINE FIRE/ENGINE RPM DECAY ON THE GROUND
(steps)
1. GCS Ignition - COLD (P)
2. Condition Lever - AFT as required (P)
3. EGT - Monitoring decrease (P)
4. RPM - Monitoring decrease (P)
5. Electrical Load - Reduced (P, SO)
if conditions permit, complete after landing & shutdown check lists after engine sto
ABORT
(steps)
1. Throttle - Full reverse (P)
2. Brakes - Applied (P)
if A/C will depart the prepared surface
3. GCS Ignition - Cold (P)
4. Condition Lever - AFT as required (P)
Loss of Control Prevent
(steps)
1. Landing Configuration - Commanded (P)
2. Payload - Position Mode (SO)
if A/C control is regained:
3. Refer to the AOA Sensor Failure, Airspeed or Pitot/Static Failure, Auto Pilot Sensor Failure, Air Frame Icing, or Structural Failure Ck lists - as Requ
Auto Pilot Sensor Failure
(steps)
1. AP Sensor - Verified Auto (P)
2. A/C - Land as soon as practical (P)
*if all auto Pilot sensors have failed
3. SAS - OFF (P)
4. Controllability CK - Performed (P)
5. A/C - Land as soon as possible (P)
*if unable to maintain A/C Control:
6. Gear - Down
UARB Failure
(steps)
1. UARB Select- Verified auto (P)
2. Aircraft - Land as soon as practical (P)
FCA Failure
(steps)
1. Processor Select - Verified Auto (P)
2. A/C - Land as soon as practical (P)
Engine Failure
(steps)
1. Glide - Establish (P)
2. Landing Site - Selected (P)
3. Condition Lever - AFT as required (P)
if time & cond permit, attempt restart (refer to Engine Air Restart Ck List)
if restart not poss or unsuccessful, prepare for Forced Landing:
4. Electrical Lo
Engine Air Restart
(steps)
1. Fuel Mode - Auto (P)
2. Condition Lever - Full Forward (P)
3. GCS Ignition - Verified Hot (P)
4. Airspeed - 100 to 180 KIAS (P)
5. Throttle - 20% (P)
6. Speed Lever - High (P)
7. RPM - Increaseing (P)
8. EGT - Monitoring increase (P)
9. Oil Pressure -
Generator Failure
(steps)
1. Generator - Reset (P)
*If reset was successful:
2. A/C - Land as soon as practical (P)
*If reset was unsuccessful.
3. Electrical Load - Reduced (P, SO)
4. Generator - Reset (P)
*If reset was successful:
5. Aircraft - Land as soon as practical (P)
*If r
Engine Overheat
(steps)
1. Throttle - As required to obtain/maintain Safe Altitude (P)
2. Aircraft - Land as soon as Possible (P)
Engine Fire
(steps)
1. GCS Ignition - As Required (P)
2. Condition Lever - AFT as Required (P)
3. Aircraft - Land as soon as possible (P)
*If Engine is shut down, refer to Engine Failure Checklist.
Fuel Header Tank Level or Pressure Low
(steps)
1. Header Tank Pressure - Verified (P)
*If Header Tank Pressure is above 1.5 PSI:
2. Header Tank Fuel Level - Cont to monitor (P)
3. Aircraft - Land as soon as possible (P)
*If Header Pressure is below 15 PSI:
4. Fuel Mode Manual (P)
5. Manual Tank Select
Fuel Solenoid Failed Open or Closed
(steps)
If Header Tank pressure is greater than 5 PSI refer to Header Tank Over Pressure:
1. Fuel Mode - Manual (P)
2. Manual Tank Select - As required (P)
3. Aircraft - Land As Soon As Possible (P)
Header Tank Over Pressure
(steps)
1. Fuel Mode - Manual (P)
2. Manual Tank Select - None (Header) (P)
When Header Tank Pressure Drops Below 4.0 PSI:
3. Fuel Mode - Auto (P)
4. Header Tank Fuel Level - Verified >208lbs (P)
5. Fuel System - Monitoring (P)
If Header Tank Overpressurizes agai
CG out of LIMITS - Forward, Aft, or Laterally
(steps)
1. Lateral CG - Verified Set (P)
2. Longitudinal CG - Verified set (P)
3. Fuel Mode - Manual (P)
4. Manual Tank Select - As required to maintain CG (P, SO)
5. Weapon - Jettisoned as required to maintain CG (P, SO)
6. Aircraft - Land as soon as possible (P
Total Downlink Failure Below 2000 Feet AGL
(steps)
1. Uplinks - Off (P)
Once the A/C is established in the LL Profile:
2. GDT Uplink TX1 & 2 - Off (P)
3. GDT Power Switch - ON (P)
If Downlink retrns & Aircraft at safe Altitude:
4. Uplink - ON (P)
If Downlink does no return and aircraft is likely to have r
Forced Landing
(steps)
-Decision to force land at an airfield or unpopulated area rests with the pilot.
-Considerations for attempting a forced landing include
-Nature of Emergency
-Weather conditions
-Lighting conditions (day or nigh)
-Battery Life
-Proximity of suitable Landi
Fuel Tank
- 7 Fuel Tanks
- Forward 1300 lbs
- Header Tank 204 lbs
- Aft Tank 790 lbs
- Outboard/Inboard Left Wing 735 lbs
- Outboard/Inboard Right Wing 735 lbs
- Usable Fuel CAP = 3764 lbs
- Unusable Fuel = 50 lbs
Throttle Detents
Flight Idle Stop
Ground Idle Stop
DEEC
Digital electronic Engine Controller
EGTS
Exhaust Gas Temperature Sensors
Never Exceed Speed
230 KIAS
250 KIAS
Manuvering Speed @ MAX Weight
158 KIAS
(Decreases aprox 4.5 KTS per 500 lb less than MAX gross weight)
MAX Flap Extension Speed
120 KIAS
MAX Gear in Transit Speed
135 KIAS
MAX Gear Extended Speed
160 KIAS
MAX Ramp Weight
10500 lbs
MAX Landing Weight
8500 lbs at 498 FPM
MAX Fuel Weight
3835 lbs
Electrical System Components
-Batteries - 6 - two sets of 3
- Primary Power 28 VDC
- 24 VDC
-PPDM (2) - BUS 1 of PPDM 40 AMP
- BUS 2 of PPDM 10 AMP
-EFIU
-RCM
-FJA (2) - Battery Juncton Assemblies 1& 2
- Battery 1,3,5
- Battery 2,4,6
-GCU
-DEEC
-ESM
The Landing GEar Switch automatically sends a gear up/down command when toggled.
False
The nose gear has a shock absorber.
True
The Aileron Servo CPU disables and freezes the servo when current exceeds ___________.
10 AMPS
The YAW Control capabilities of the ruddervators acts as a backup for the ventral rudder. When?
50 % of the rudder inputs are mixed into the ruddervator commands.
Manual control of the flaps is possible when airspeed drops below 117 KIAS and _________.
Gear is down and airspeed remains less tan 121 KIAS.
and
Gear is up and Airspeed HOLD is OFF.
The RCM Automatically decambers the wings using ____________.
Ailerons and Flaps.
The Flap slew rate is ________.
5 degrees/sec.
Aileron upward deflection is 2.5 times greater than downward deflection. Why?
To reduce adverse YAW.
If an aileron fails the stanby aileron is engages.
FALSE
The Throttle has __________ detents.
TWO
How many fuel tanks does MQ9 have?
7
What is the usable fuel capacity of the MQ9?
3764 lbs
How often do he Fuel Pumps cycle?
Every 10 mins with a 5 sec overlap.
How many Jet Pumps are installed?
4
When fuel jettison is activated, where does the fuel exit the Aircraft?
From the left wing trailing edge between the airlerons and flaps.
Which of the following will activate both fuel pumps:
Fuel pressure < 18 psi
and
Activating Fuel Jettison
On VIT Screen 1 "Fuel Remainin" s calculated from ____________.
-Fuel mass flow to engine.
-Level sensor readings before ignition on.
-Measured Header Tank Level.
A RED Warning for Header Tank overpressure indicates the _________________.
Header tank pressure has exceeded 5.0 psi.
When Fuel Jettison is selected in Automatic mode the following events occur:
Fuel jettison stops at 600 lbs measured.
The instantaneous accuracy of the MASS Flow sensor is _______.
+/- 0.5% lbs/hr
The MQ9 utilizes a TPE331-10Y Engine with an EFIU for engine control.
FALSE
During an engine failure an Oil Level of 60% in conjunction with Engine Oil Quantity Low message indicates _______________.
The unfeathering pump has pumped too much oil from the oil tank.
Beta Mode indicates.
A High Oil Pressure
The Throtle is not advanced past the 2nd detent.
All RED OIL Temperature warnings are....
50 degrees C and 115 degrees C
The operation of the condition lever in the TPE331-10YGD engine is ______________.
The same for DEEC Mode & backup mode.
In Backup mode, there are no Automatic engine limitations.
FALSE
Single RED Line control in the TPE 331-10YGD engine is performed by the ____________.
DEEC
Igniters are automatically enabled _____________.
Between 10% & 60 % RPM during normal engine start.
During in-flight restarts.
In backup mode the TPE331-10YGD engine SRL is controlled by the ___________.
There is no SRL Control in backup mode.
The DEEC inflight engine operating range is ________.
82% to 100% RPM.
The interstage fuel pressure is __________.
Monitored by the EFIU
&
Is normally 35 psi over inlet pressure.
The purpose of the on-engine oil/fuel heat exchanger is to __________.
Stabilize fuel temperature.
The function of the primaries-only-solenoid is to provide additional fuel pressure to he primary nozzles during the start sequence.
TRUE
The DEEC interface with the RCM is a _________.
ARINC 429
To maintain a constant RPM, _____________.
Engine power must equal propeller load.
How many electrical power distribution buses are on the aircraft?
2
What is the Prmary Power System Voltage on Bus 1?
28 VDC
What is the voltage on each of the Batteries?
24 VDC
How many batteries are contained in each set of Batteries?
3
How many sets of Batteries are installed in the aircraft?
2
Power is supplied to the aircraft from ____________.
- A Ground Power Unit (GPU)
-Two sets of three batteries per set
-The Starter Generator
What type of processing does the RCM use?
MLV (Mid Level Voting)
Fault tolerant components are connected to both UARBS.
TRUE
What communication interface is used by the FCA;s to share sensor data?
Cross-Channel Data Link
How many FCA's are in command during flight?
One
The MCS compares the quality of the data from the FCAs and the VP to determine which VP data the fault tolerant components will use.
FALSE
The RCM uses 3 FCA's and two Vote Processors to produce identical, command data sets.
TRUE
The RCM converts the _________ measurements to digital data.
Alpha Probe
The EGI Navigation DATA provides __________.
Better instantaneous accuracy, and more stability over time.
When any FCA resets during flight the warning message "FLight computer reset detected by UAV" is displayed.
FALSE
FCA Autopilot and Navigation Sensor Data is displayed on ____________.
VIT's 40, 41, 42
The A/C has no Lightening Protection.
TRUE
Add ______ percent of gust factor up t a MAX of ______ knots to rotation speed during crosswind takeoffs.
50, 10
Excessive roll and/or pitch angles can cause loss of LOS datalink.
TRUE
EGT protects the engine from overheating by overriding the throttle command.
TRUE
A Header Tank level of 208 lbs prompts emergency procedures for ___________.
A Fuel Header tank level or Pressure low condition.
The Overhead Approach is the only method Available to the Pilot during a Forced Landing.
FALSE
In performing an Engine Air Restart ___________.
Do not engage the starter during an air start.
An Engine Failure or a Generator Failure may require performing a Forced Landing procedure.
TRUE
CAPs for an Engine Failure include:
-Establishing a glide.
-Selecting a landing site.
-Placing the condition lever to the Aft Position.
Loss of Control may be indicated by complete failure of the Aircraft to respond to pilot control commands.
TRUE
Throttle-Full Reverse (P) and Brakes-Applied are CAPs for ___________.
ABORT procedures during take-off.
Land as soon a possible" applies to emergency conditions that are less urgent, and although the mission should be terminated, the degree of the emergency is such that an immediate landing at the nearest adequate facility is not necessary.
FALSE
What are Critical Action Procedures?
Steps that must be performed immediately with out reference to a written check list.
EGT Protects the engine from overheating by overriding the throttle command.
TRUE
Excessive roll &/or pitch angles can cause loss of LOS datalink.
TRUE
Add _____ percent of gust factor up to a max of _____ knots to rotation speed during crosswind takeoffs.
50, 10
MAX Fuel Weight is
3000 lbs
The Aircraft has no lightening protection.
TRUE
What is maneuvering speed at max gross weight?
158 KIAS
Operation of A/C into areas of lightening activity is prohibited.
TRUE
Rain increase stall speed by up to
10%
Ice, Snow or frost can reduce wing lift by as much as __________. Drag can increase by ___________.
30%, 40%
LAND AS SOON AS POSSIBLE" Applies to Emergency Conditions that are less urgent, and although the mission should be terminated, the degree of the emergency is such that an immediate landing at the nearest adequate facility is not necessary.
FALSE
Throttle-Full Reverse (P) and Brakes-Applied (P) are CAPs for _____________.
Abort procedures during takeoff.
Loss of Control may be indicated by complete failure of the aircraft to respond to pilot control commands.
TRUE
An Engine Failure or a Generator Failure may require performing a forced landing procedure.
TRUE
In performing an Engine Air Restart ________.
Do not engage the starter during an air start.
The overhead approach is the only method available to the pilot during a forced landing.
FALSE
A Header Tank level of 208 lbs prompts emergency procedures for _________.
A fuel Header Tank level or pressure low condition.
ENGINE FIRE/ENGINE RPM DECAY ON THE GROUND
(steps)
1. GCS Ignition - COLD (P)
2. Condition Lever - AFT as required (P)
3. EGT - Monitoring decrease (P)
4. RPM - Monitoring decrease (P)
5. Electrical Load - Reduced (P, SO)
if conditions permit, complete after landing & shutdown check lists after engine sto
ABORT
(steps)
1. Throttle - Full reverse (P)
2. Brakes - Applied (P)
if A/C will depart the prepared surface
3. GCS Ignition - Cold (P)
4. Condition Lever - AFT as required (P)
Loss of Control Prevent
(steps)
1. Landing Configuration - Commanded (P)
2. Payload - Position Mode (SO)
if A/C control is regained:
3. Refer to the AOA Sensor Failure, Airspeed or Pitot/Static Failure, Auto Pilot Sensor Failure, Air Frame Icing, or Structural Failure Ck lists - as Requ
Auto Pilot Sensor Failure
(steps)
1. AP Sensor - Verified Auto (P)
2. A/C - Land as soon as practical (P)
*if all auto Pilot sensors have failed
3. SAS - OFF (P)
4. Controllability CK - Performed (P)
5. A/C - Land as soon as possible (P)
*if unable to maintain A/C Control:
6. Gear - Down
UARB Failure
(steps)
1. UARB Select- Verified auto (P)
2. Aircraft - Land as soon as practical (P)
FCA Failure
(steps)
1. Processor Select - Verified Auto (P)
2. A/C - Land as soon as practical (P)
Engine Failure
(steps)
1. Glide - Establish (P)
2. Landing Site - Selected (P)
3. Condition Lever - AFT as required (P)
if time & cond permit, attempt restart (refer to Engine Air Restart Ck List)
if restart not poss or unsuccessful, prepare for Forced Landing:
4. Electrical Lo
Engine Air Restart
(steps)
1. Fuel Mode - Auto (P)
2. Condition Lever - Full Forward (P)
3. GCS Ignition - Verified Hot (P)
4. Airspeed - 100 to 180 KIAS (P)
5. Throttle - 20% (P)
6. Speed Lever - High (P)
7. RPM - Increaseing (P)
8. EGT - Monitoring increase (P)
9. Oil Pressure -
Generator Failure
(steps)
1. Generator - Reset (P)
*If reset was successful:
2. A/C - Land as soon as practical (P)
*If reset was unsuccessful.
3. Electrical Load - Reduced (P, SO)
4. Generator - Reset (P)
*If reset was successful:
5. Aircraft - Land as soon as practical (P)
*If r
Engine Overheat
(steps)
1. Throttle - As required to obtain/maintain Safe Altitude (P)
2. Aircraft - Land as soon as Possible (P)
Engine Fire
(steps)
1. GCS Ignition - As Required (P)
2. Condition Lever - AFT as Required (P)
3. Aircraft - Land as soon as possible (P)
*If Engine is shut down, refer to Engine Failure Checklist.
Fuel Header Tank Level or Pressure Low
(steps)
1. Header Tank Pressure - Verified (P)
*If Header Tank Pressure is above 1.5 PSI:
2. Header Tank Fuel Level - Cont to monitor (P)
3. Aircraft - Land as soon as possible (P)
*If Header Pressure is below 15 PSI:
4. Fuel Mode Manual (P)
5. Manual Tank Select
Fuel Solenoid Failed Open or Closed
(steps)
If Header Tank pressure is greater than 5 PSI refer to Header Tank Over Pressure:
1. Fuel Mode - Manual (P)
2. Manual Tank Select - As required (P)
3. Aircraft - Land As Soon As Possible (P)
Header Tank Over Pressure
(steps)
1. Fuel Mode - Manual (P)
2. Manual Tank Select - None (Header) (P)
When Header Tank Pressure Drops Below 4.0 PSI:
3. Fuel Mode - Auto (P)
4. Header Tank Fuel Level - Verified >208lbs (P)
5. Fuel System - Monitoring (P)
If Header Tank Overpressurizes agai
CG out of LIMITS - Forward, Aft, or Laterally
(steps)
1. Lateral CG - Verified Set (P)
2. Longitudinal CG - Verified set (P)
3. Fuel Mode - Manual (P)
4. Manual Tank Select - As required to maintain CG (P, SO)
5. Weapon - Jettisoned as required to maintain CG (P, SO)
6. Aircraft - Land as soon as possible (P
Total Downlink Failure Below 2000 Feet AGL
(steps)
1. Uplinks - Off (P)
Once the A/C is established in the LL Profile:
2. GDT Uplink TX1 & 2 - Off (P)
3. GDT Power Switch - ON (P)
If Downlink retrns & Aircraft at safe Altitude:
4. Uplink - ON (P)
If Downlink does no return and aircraft is likely to have r
Forced Landing
(steps)
-Decision to force land at an airfield or unpopulated area rests with the pilot.
-Considerations for attempting a forced landing include
-Nature of Emergency
-Weather conditions
-Lighting conditions (day or nigh)
-Battery Life
-Proximity of suitable Landi