Cpt 1-5

Front 1

Starter hangup is a type of malfunction wherein the
starter fails to drop out during engine start. Starter
dropout should occur at approximately _______
rpm. TF33-P-3 engines are subject to “hung” starts
at temperatures of _______ and below.

Back 1

35% to 45%, 45°F (75°C)

Front 2

Hung starts are usually characterized by failure of
the engine to accelerate beyond ____ rpm. The EGT may rise slowly but should not be allowed to exceed
the starting limit.

Back 2

40%

Front 3

In the event starter cartridge does not fire:

Back 3

pilot designates engine on which cartridge did not fire to ground crew over interphone.

Copilot places that starter switch to OFF.

Cartridge will not be removed until there is no evidence of exhaust smoke at the starter exhaust duct and minimum time interval has elapsed since initiation.

Prior to removal of a cartridge, ensure that the start selector
switch is in FLIGHT and the engine ignition circuit breakers are pulled.

The ground crew must observe the handling precautions outlined
in Section V.

Wear leather gloves when removing cartridge.

Do not point screened end of cartridge at personnel or equipment.

Pilot makes entry on Form 781.

Front 4

All cartridge start restrictions will be observed unless the alert is
determined to be __________ or _________ makes moving the aircraft necessary.

Under these conditions, if a malfunction occurs in both cartridges, the waiting period between start of initiation and removal of unfired cartridge may be
reduced to not less than ____ minute provided the specific ground handling precautions outlined in
Section V are met.

Back 4

actual EWO; an impending
disaster; 1

Front 5

A delay in the functioning of a propelling charge at the time of firing.

There will be evidence of smoke at the starter exhaust duct.

The engine rpm will increase rapidly and the cartridge will give evidence of nearly normal operation. In this type malfunction, the energy is expended and presents no hazard to engine operation.

Back 5

Hangfire

Front 6

A cartridge that fails to ignite. There will be no physical evidence of smoke at the starter exhaust
duct and no engine rotation. If a ________ occurs, observe the proper waiting period from start of
initiation prior to removing the unfired cartridge. Upon removal of the defective cartridge, a normal
pneumatic start can be accomplished. For actual EWO or if an impending disaster makes moving the aircraft necessary, no attempt should be made to
remove the defective cartridge provided the affected engine can be expeditiously started by other means.

Back 6

Misfire

Front 7

The pneumatic starters have the following limitations:

1. Maximum continuous operation

2. Minimum rest after 2-minute continuous operation

3. Minimum rest after two 2-minute cycles

during flight, if the system has not been energized,
ignition may be used continuously for a period of __
minutes or in excess of this period during emergencies.
The system should not be energized longer than
necessary, but with __ minutes or more of continuous
operation, the ignition system will be turned off
for a cooling period of at least __ minutes.

Back 7

– 2 minutes
– 3 minutes
– 10minutes
- 10

Front 8

The cartridge-pneumatic starters have the following limitations:

1. Not more than ____ cartridge starts shall be made in any period of ___ minutes.

2. After normal cartridge firing, at least ___ minutes shall elapse before removing the breech cap, inserting another cartridge, and initiating another cartridge start. If the cartridge malfunctioned (misfired
or hangfired), wait at least __ minutes before attempting
to remove the cartridge, except as noted below.

3. Not more than ___ pneumatic starts shall be made in any period of __ minutes.

4. If cartridge starts and pneumatic starts are interspersed, no more than ___ starts shall be made within a ___-minute period. ___ of these starts may be cartridge starts provided the limitations
noted previously are not exceeded.

Back 8

- two, 60;
- 5
- three, 15
- three, 15, Two

Front 9

When a hangfire/misfire occurs during EWO conditions, a ___-minute wait before removal is recommended. However, this time limit may be waived by the unit commander based on his assessments of the situation
provided the following conditions are met:

Back 9

2;
• No smoke can be observed from starter exhaust.
• Starter breech cover is not hot to the bare hand.
• There is no evidence of pressure inside breech chamber. (Breech cover offers no undue resistance to removal.)
• Cartridge screen end is pointed away from aircraft, equipment, or personnel.
• Cartridge is treated as a potential hangfire (fire hazard) for a period of 10 minutes after removal from breech.

Front 10

Except in an emergency, engine operation is prohibited when a ____ or _____ cartridge
is installed in the starter.

Back 10

live or misfired

Front 11

Before placing start selector switch to CARTRIDGE, check throttles fully
______ to ensure starter cartridge firing/ignition.

Back 11

closed

Front 12

Engine Fire on the Ground

Back 12

THROTTLE(S) - CLOSED
FIRE SHUTOFF SWITCH(ES) - PULL

Front 13

An engine fire on the ground may be originated and supported by fuel, oil, or hydraulic fluid. When an indication of engine fire is evidenced, the affected engine throttle will be closed. If practicable, the throttle for the ________ engine should be closed to aid personnel in putting out the fire.

Back 13

adjacent

Front 14

___ should not be directed into the engine air inlet or tailpipe unless fire is restricted to those areas and is of serious proportions. Shut down the
engine if possible, in order to minimize engine damage if ____ is to be applied. _______, if available, may be directed into the engine air inlet or tailpipe.

Back 14

CO2; CO2; HALON

Front 15

Wheel Brake System Failure

Back 15

ANTISKID SWITCH - OFF (IF APPLICABLE)
BODY SYSTEM STANDBY PUMP SWITCHES - STBY
THROTTLES 1,2,3,6,7,& 8 - CLOSED
THROTTLES 4 &5 - CLOSED

Front 16

With normal body system hydraulic indications and when ineffective or inadequate braking situations arise during
high speed aborts or landings, and stopping on the remaining runway is in doubt, the use of this checklist would likely begin with the...

Back 16

closing of selected throttles.

Front 17

__________ or ___________ may prevent transfer of the antiskid system from the “airborne” mode to the “ground” mode.

Back 17

Improper servicing of the shock struts or a malfunctioning landing gearsafety switch

Front 18

When the antiskid is OFF, braking action depends entirely on the _______ applied to the brake pedals. Do not ________ when only accumulator pressure is available.

Back 18

pressure; pump brakes

Front 19

While taxiing on a slippery surface, it is possible to lose up to ___% of the effective braking due to locked wheel conditions; however, for this condition
leaving the switch ___ provides more effective braking action than full braking without antiskid.

Back 19

50; ON

Front 20

WHEEL BRAKE SYSTEM FAILURE

If steering is not available and the previous procedures do not slow the aircraft...

Back 20

shut down remaining
engines.

Front 21

Takeoff will not be aborted after S1 unless, in the opinion of the pilot, the emergency renders
the aircraft _______ unsafe to attain _________. In those cases
where the pilot attempts to abort after S1, the aircraft will _______ fail to stop within
the confines of the runway.

Back 21

definitely; emergency bailout altitude; probably

Front 22

The drag chute will be deployed at airspeeds above __ knots. The maximum drag chute deployment
speed is ___ knots.

Back 22

70; 135

Front 23

A ground loop should not be attempted at heavy gross weights since structural failure may occur at speeds above ___ knots. A turn of any kind should not be attempted unless conditions straight ahead appear more
hazardous.

Back 23

30

Front 24

The brake energy limit is ___ million foot-pounds total for eight brakes. This is the maximum energy the brakes can absorb before becoming ineffective and is the stopping capability limit.

Back 24

298

Front 25

Above ___ million foot-pounds
accumulation, fire and tire explosion are ______ and above ___ million foot-pounds accumulation, fire and tire explosion are _______.

Back 25

230, imminent; 150, possible

Front 26

The internal heat generated by the brakes does not reach the outer surface of the brake assembly for several minutes whereas the ground roll requires only a few seconds; therefore, all but an insignificant amount of
the heat generated by the brakes remains in the brake assembly for the duration of the
ground roll. Peak temperatures are reached in the tire bead seat of the wheel as late as
___ minutes after stopping.

Back 26

20

Front 27

If the calculated total of brake energy previously used and to be used in a refused takeoff exceeds 298 million footpounds,
allow brake cooling time of ___ minutes for each ___ million foot-pounds the calculated sum exceeds 298 million foot-pounds.

Back 27

6; 8

Front 28

If a stop has been made exceeding ___ million foot-pounds and an immediate takeoff is accomplished, leave the gear extended __ minutes for
each ___ million foot-pounds in excess of ___ million
foot-pounds unless climb rate is critical. If it is necessary to retract the gear, extend as soon as practical to meet cooling criteria.

Back 28

100; 2; 8; 100

Front 29

The brake energy charts in figure 5-13 should be used whenever...

Back 29

a takeoff is aborted, for all flaps-up landings, for all normal flaps-down landings at gross weights over 300,000 pounds, for takeoff subsequent
to an abort or braked landing, and when the pilot suspects that the combination of gross weight, runway altitude, temperature, runway grade, IAS, and
the number of stops and decelerations will result in
brake energy reaching the Caution or Danger Zone.

Front 30

If a fire warning light comes on after takeoff is committed, do not retard the throttle for the engine
on fire if its thrust is needed for takeoff unless the engine is ____________. When the _________, retard throttle to CLOSED and use EMERGENCY SHUTDOWN procedure, this section.

Back 30

vibrating seriously; landing gear and wing flaps have been retracted and a safe altitude is reached

Front 31

When the yaw forces exceed the capability of rudder/steering, the
pilot has two options to maintain aircraft control:

Back 31

1)reduce asymmetric thrust, or

2) increase flight control effectiveness.

Front 32

Proper _______ control is the pilot’s most expeditious method to increase airspeed.

Back 32

pitch

Front 33

Emergency Engine Shutdown

Back 33

THROTTLE(S) - CLOSED
FIRE SHUTOFF SWITCH(ES) - PULL

Front 34

After closing the throttle and pulling the fire shutoff switch, if fire warning light continues to
illuminate, shut down _______. If fire warning light _______, do not restart either engine in nacelle. If fire warning light ________, both engines should normally remain shut down. However, multiple failures may cause the pilot to consider restarting an engine shutdown for precautionary reasons (so long as no additional indications of fire or overheat are noted), e.g., a critical need for electrical power, or for thrust when a marginal go-around capability
exists.

Back 34

adjacent engine in nacelle; goes out; does not go out

Front 35

Except on engine(s) shut down for ________, windmilling above ___% rpm, have fuel available to the firewall fuel shutoff valve, push the engine fire shutoff switch in, and advance the throttle to IDLE for __ minutes out of every to prevent overheating the _______. If the _________ circuit breaker has been pulled during shutdown of engines, the respective ___________ circuit breaker must be reset in order to obtain fuel to the engine.

Back 35

fire or fuel leak; 25; 3, hour; fuel control unit; firewall fuel shutoff valve

Front 36

If engine 1, 3, 4, 5, 6, or 7 is still windmilling after the fire is extinguished, the hydraulic shutoff valve can be reopened to prevent damage to the pump
by pulling the corresponding _________ circuit breaker and
returning the engine fire shutoff switch to the NORMAL position. Before reopening the hydraulic shutoff valve, ensure that the......

Back 36

firewall fuel shutoff valve;
starter switch is OFF and the respective engine ignition circuit breaker is pulled.

Front 37

When an excessively high oil temperature occurs following an engine shutdown that is not due to engine _______, the firewall fuel shutoff valve may be returned to NORMAL position and the throttle advanced
beyond IDLE provided the...

Back 37

fire or fuel leak;
starter switch for the affected engine is OFF.

Front 38

When fuel is available to an engine, even with some failures of the fuel control unit, restart could occur if the starter switch is placed to _____ and
the throttle is moved out of the _______ position. Continuous ignition will occur regardless of throttle position if the ________ circuit breaker is out and the starter switch is placed to _____.

Back 38

START; CLOSED; firewall fuel shutoff valve; START

Front 39

An engine air start after an emergency shutdown should not be attempted unless it is ascertained that it is __________ to do so. A recurrence of the emergency condition could be more serious than the first occurrence.

Back 39

reasonably safe

Front 40

Runaway or Unscheduled Stabilizer Trim

Back 40

AUTOPILOT - DISENGAGE AND OFF
STABILIZER TRIM CUTOUT SWITCH - CUTOUT

Front 41

The application of _____ pounds of control force in
opposition to the unscheduled trim will open the force switch(es) and interrupt the trim input only as long as the column force is present. To prevent reinitiation of the unscheduled trim input when control column
force is reduced pull the circuit breaker marked ________ on the MISCELLANEOUS section of the pilot’s circuit breaker panel.

Back 41

24 to 36; TRIM CONTR

Front 42

If unscheduled pitch-inputs are observed, accomplish the following:

1. Disengage the autopilot. If oscillations do not cease immediately, place the pitch SAS switch to ______.

2. If oscillations cease upon disengaging the pitch SAS, leave pitch SAS switch disengaged and ________. Autopilot may be reengaged to ascertain if malfunction was in the SAS pitch control, and left engaged if no further oscillations are experienced.

Back 42

DISENGAGE; continue
mission

Front 43

Unscheduled _____ oscillations of small amplitude from the SAS are classified as a nuisance factor and do not affect safety. If such a condition occurs, continue the mission; however, the following instructions will apply:

Back 43

yaw;
1. Do not disengage the yaw SAS switch to eliminate these nuisance oscillations.

2. The source of the malfunction causing the oscillations should be determined and a Form 781 entry made.

3. If the oscillations are observed with autopilot engaged, it should be disengaged. If oscillations do not cease, place the yaw SAS switch to disengage. If oscillations cease upon disengaging the yaw SAS, the malfunctioning system has been identified. The
yaw SAS switch will be reengaged and left engaged.
The autopilot may be reengaged if the malfunctioning system was identified as the yaw SAS.

Front 44

YAW SAS SWITCH DISENGAGEMENT
If the switch will not engage, leave switch in DISENGAGE. The mission may be continued while observing the following restrictions/instructions.

Back 44

a. Avoid turbulence or any maneuver that could apply unnecessary side loads to the aircraft.

b. Compute an altitude 10,000 feet below the Mach 0.765 line on the BEST RANGE CONSTANT MACH CRUISE ALTITUDE CHART in T.O. 1B-
52H-1-1. Cruise near but not above this altitude.

c. Low level activity will not be continued/attempted.

d. Air refueling will be conducted only when necessary to extend the flight during emergencies.
The air refueling mode of the autopilot will substantially
reduce the loads on the aircraft during refueling and will be used if operative.

e. Do not conduct evasive action or breakaway maneuvers associated with bomb runs.

f. A minimum of 250 knots IAS should be maintained during cruise flight conditions.

g. Low approaches and touch-and-go landings may be accomplished during smooth, stable flight conditions. Do not practice flaps up approaches or
simulated engine out conditions.

Front 45

Complete Failure of all Generators

Back 45

MASTER ISOLATE SWITCH - PUSH IN AND HOLD WHILE PLACING GENERATOR SWITCHES ON

Front 46

If complete ac or forward TR electrical failure occurs, the only fuel available to the engines will be the fuel remaining in the _______. Changes in ________ may cause the main tank boost pumps to become uncovered allowing air to be drawn into
the system, thus causing engine flameout; therefore, crewmembers must anticipate the possible loss of any or all engines any time electrical power
is lost and act accordingly.

Back 46

main tanks;
flight attitude, acceleration forces or unknown fuel quantity