-
Engine
J85-GE-5R eight-stage, axial-flow, turbojet
-
MIL Power Thrust (standard day, SL)
2200 pounds
-
MAX Power Thrust (standard day, SL)
3300 pounds
-
Ignition cycle time
30 sec
-
Temps above __ degrees F result in EED activation within __ seconds. Below that temperature it may take __ minutes.
-
Before engine start EED FF indicator should read no higher than
60 PPH
-
Fuel Low light comes on when
Fuel quantity is 250 pounds or less for 7.5 seconds
-
MAX AB fuel flow at rest
7300 PPH
-
MAX AB fuel flow at Mach 1
11,400 PPH
-
Oil reservoir normal capacity
4 quarts
-
Oil reservoir air expansion space
1 quart
-
Oil consumption through engine operation and overboard venting should not exceed
1 pint per hour
-
Flight above __ feet and below __ IMN increases susceptibility to compressor stall/flameout
-
With airspeeds below __ above altitudes of __ maintain rpm at __ or above to avoid engine RPM dropping below ground idle.
-
Above __ feet, cockpit displays provide estimates of
- Black Stripe Altitude
- Min Mach
-
FUEL PRESS Light comes on below __ (normal is __)
-
Total fuel with single point refueling (JP-8)
- 583 gal
- 3906 lbs
- 1990 lbs right side
- 1916 lbs left side
-
Total fuel with manual refueling (JP-8)
3866 lbs (subtract 6 gal or 40 lbs)
-
Below __ lbs fuel, boost pump output is reduced to __
- 650 lbs (either system)
- 40%
-
Taxi operations with less than __ lbs in either system could cause cavitation of the boost pump
150 lbs
-
Gravity fuel flow only guaranteed below __
6,000 feet
-
AC Electrical power provided by:
Two AC busses powered by 2 engine-driven AC generators
-
DC Electrical power provided by:
2 50-amp DC transformer-rectifiers or a 24-volt battery power 2 essential DC busses and 1 nonessential DC bus
-
Non-essential DC bus drops offline when DC Voltage drops from __ to __ (dual TRU failure)
-
RPM required for generator operation
43-48%
-
AC generator voltage
115 ± 2 V
-
AC Generator gearbox shifts at __ Engine speed to maintain output within limits
65-75%
-
When AC voltage drops below __ the affected TRU triggers RECTIFIER FAILURE PFL
180 ± 2 V
-
The caution light may take up to __ to illuminate after a generator failure
2.5 sec
-
When either TRU output falls below __ for more than __ a RECTIFIER FAILURE PFL and AVIONICS advisory are triggered
-
Min voltage to close the battery relay (and apply external power)
18 V
-
The battery should remain on until the voltage drops below
10 V
-
In the event of a TRU failure the battery supplies power to the two essential busses for __
15 min
-
Static inverter converts DC BUS voltage to __
115 VAC
-
Static inverter activated when:
- Engine start button pressed
- OXY/FUEL switch held in GAGE TEST
- OXY/FUEL switch held in QTY CHECK
- Either throttle moved to MAX (in flight)
-
Hydraulic system pressure
3000 PSI
-
Hydraulic caution light activation occurs when:
- Pressure is 1500 PSI and below (goes out when restored to 1800 PSI)
- Fluid overtemperature detected
-
Left engine hydraulic system
Utility
-
Right engine hydraulic system
Flight control
-
Landing gear warning conditions
- Below 210 KCAS
- Below 10,000 feet
- Throttles below 96% RPM
-
Red light extinguishes during gear extension
All three gear down and locked
-
Red light extinguishes during gear retraction
All three gear doors closed
-
Gear caution voice message activated
- With nose gear down and locked above 240 KCAS
- With nose gear down and locked between 220 and 240 KCAS increasing at 2 kts/sec
-
Time window for alternate gear extension
15-35 sec
-
Nose gear extension 3/4 or less limits rudder deflection to __
6 degrees
-
Nose gear extension more than 3/4 allows full rudder deflection of __
30 degrees
-
Rudder trim deflection
2 degrees
-
Pneumatic System (HC-CAGED)
- Hydraulic reservoir
- Canopy Seal
- Cabin pressurization
- Air Conditioning
- G-Suit
- Engine anti ice
- Defog
-
Cabin pressure scheduling
- 0 PSI differential up to 8000 feet
- 8000 ± 1000 feet up to 23,000 feet
- 5 PSI differential (±2000 feet) above 23,000
-
Cabin altitude above 23,000 feet
(Altitude 6k)/2
-
RAM DUMP deactivates the following systems (C-CAG-D)
- Cabin pressurization
- Canopy seal
- Air Conditioning
- G-suit
- Defog
-
Defog Thermostat Temperature
200°F
-
Defog Overheat Thermostat Temperature
280°F
-
Placing ENG ANTI-ICE to MAN ON results in EGT increase of __ at speeds of __
-
The anti-ice valve is always open below engine speeds of __
65% RPM
-
Loss of thrust with ENG ANTI-ICE on (Thrust, % MIL, % MAX)
- 180 ±10 pounds
- 8.5% loss in MIL
- 5.5% loss in MAX
-
Items de-iced with PITOT HEAT switch
- Pitot boom
- AOA vane
- Total Air Temperature (TAT) probe
-
Do not exceed __ with pitot heat on during ground operations
30 sec
-
OXYGEN Caution Light illuminates with less than __ LOX
1 Liter
-
OXYGEN Caution Light can flicker due to sloshing with less than __ LOX
3 Liters
-
-
-
Optimum Approach AOA
0.55 to 0.65
-
Approach to Stall Warning AOA
0.80 to 0.99
|
|
