*2. Check oil pressure; if oil pressure is normal, continue operations
IF RED OIL PX WARNING ILLUMINATES AND/OR AMBER OIL
PX CAUTION REMAINS ILLUMINATED FOR 5 SECONDS:
*3. PCL - Minimum necessary to intercept ELP; avoid unnecessary
*4. PEL - Execute
Low Fuel Pressure
*1. PEL - Execute
OBOGS System Malfunction
*1. PCL - Advance
*1. GREEN RING - PULL (AS REQUIRED)
*1. EJECTION HANDLE - PULL (BOTH)
*1. Airspeed - 125 KIAS prior to extending landing gear
*2. EMER LDG GR handle - Pull (as required)
*3. Airspeed - 120 KIAS minimum until intercepting final; 110 KIAS minimum on final
*4. Flaps - As required
Precautionary Emergency Landing (PEL)
*1. Turn to nearest suitable field
*2. Climb or accelerate to intercept ELP
*3. Gear, flaps, speed brake - UP
1. Hydraulic pressure – Check
2. Electrical systems – Check
3. Fuel quantity/balance – Check
4. OBOGS – Check flow indicator for normal operation (BOTH)
5. Engine instruments – Check
6. Pressurization – Check
PRE-STALLING, SPINNING, AND AEROBATIC CHECKS
1. Loose items – Stowed (BOTH)
2. Engine instruments – Check
(Verify caution and warning messages are extinguished)
3. Fuel balance – Check less than 50 pounds
1. DEFOG switch – OFF
2. Engine instruments – Check
3. Gear – DOWN (press down firmly) (BOTH) (Check three green annunciators illuminated)
4. Brakes – Check, as required
(Verify positive pressure by actuating toe brakes.)
5. Flaps – As required (BOTH)
6. Speed brake – Verify retracted
Land As Soon As Possible
An emergency shall be declared and a landing accomplished at the nearest suitable landing area considering the severity of the emergency, weather conditions, field facilities, ambient lighting, and command guidance.
Land As Soon As Practical
Emergency conditions are less urgent and, although the mission is to be terminated, the degree of the emergency is such that an immediate landing may not be necessary.
Aggravated spins past two turns
Spins with PCL above idle
Spins with landing gear, flaps, or speed brake extended
Spins with PMU off
Spins below 10,000 feet pressure altitude
Spins above 22,000 feet pressure altitude
Abrupt cross-controlled (snap) maneuvers
Aerobatic maneuvers, spins, or stalls with a fuel imbalance greater than 50 pounds between wings
ACCELERATION LIMITATIONS Symetric
Clean +7.0 to -3.5 G's
Gear and flaps extended +2.5 to 0.0 G's
ASYMMETRIC (ROLLING G’S)
Clean +4.7 to -1.0 G's
Gear and flaps extended +2.0 to 0.0 G’s
For uncoordinated rolling maneuvers initiated at -1 G, the maximum bank angle change is 180 degrees.
Maximum ramp weight - 6950 pounds
Maximum takeoff weight - 6900 pounds
Maximum landing weight - 6900 pounds
Maximum zero fuel weight - 5850 pounds
Maximum weight in baggage compartment - 80 pounds
Maximum crosswind component for dry runway - 25 knots.
Maximum crosswind component for wet runway - 10 knots.
Maximum crosswind component for icy runway - 5 knots.
Maximum tailwind component for takeoff - 10 knots.
Starter duty cycle (start attempts and/or engine motoring) is limited to four 20-second cycles as follows:
First - Motor 20 seconds then, 30-second cooling period.
Second - Motor 20 seconds then, 2-minute cooling period.
Third - Motor 20 seconds then, 5-minute cooling period.
Fourth - Motor 20 seconds then, 30-minute cooling period.
PROPELLER GROUND OPERATION LIMITATIONS
Sustained propeller operation on the ground between 62 and 80% NP is prohibited to prevent damage from ground resonance.
1. PFD – Check (BOTH)
2. Altimeters – Set (BOTH)
3. DEFOG switch – As required
4. MASTER ARM switch – As required
5. Vent control lever – As required
CLIMB (PASSING 10,000 FEET)
1. OBOGS – Check flow indicator for normal operation
2. DEFOG switch – As required
3. Vent control lever – As required
4. Pressurization system – Check
If readings other than 3.6±0.2 psi are
encountered at or above 18,069 feet MSL,
notify maintenance after landing.
With canopy defog ON, expect an increase inITT of up to 40 °C for a given PCL setting.Cockpit noise will also increase. Performancewill decrease with defog on. A DUCTTEMP indication is likely at climb or cruisepower with canopy defog ON and cockpittemperature controller set to AUTO orMANUAL HOT. Refer to EnvironmentalSystems Duct Overtemp procedure in SectionIII.
1. EICAS display – Check (BOTH)
2. PROBES ANTI-ICE switch – ON
3. Transponder – Mode to ALT
4. Landing/taxi light – ON
5. Nose wheel steering – Off
Torque Max Transient
131 (20 sec) (8)
8. Torque at 131% is a materials limit above which damage to the engine may occur. Torque above 102% is indicative of a system malfunction
B) Max/TO 820
Start 1000 (5 sec)
Transient 870 (20 sec)
Max/ TO 104
IDLE: 60 Min (ground)/ 67 Min (flight)
Transient 102 (20 sec) 110 (3)
3. Permissible at any power setting for completion of in-flight emergency.
Oil Pressure psi
IDLE 90 minimum
5. Operation in this range permitted only during aerobatics or spins, and 15 to 40 psi for 5 seconds with PCL at IDLE.
Oil Temp °C
C) TO/Max 10 to105
Idle 10 to 105 (flight), -40 to 105 (ground)
Start -40 minimum
Transient 106-110 (10 minutes, ground ops only below 20% torque)
Zoom capability at 200 knots will vary from 603 to 915 feet of altitude gained. Zoom capability at 250 knots will vary from 1180 to 1576 feet of altitude gained.