Immediate Action Exams

ABORT

*1. Throttles-Idle

*2. Speed Brakes- As desired

*3. Brakes- Apply

*4. Stick - Aft below 100kts (if required)

*5.Hook Handle- Down (if required)

OCF RECOVERY

*1. Controls- release, feet off rudder pedals, Speed Brakes check in

If still out-of-control -
*2. Throttles-Idle

*3.Alt, AOA, A/S and Yaw Rate - Check

If command arrow present -
*4. Lateral stick - full with Arrow

When command arrow removed -
*5. Lateral Stick - Smoothly Neutral

When recovery indicated by AOA and yaw rate
tones removed, side forces subsided, and
airspeed accelerating above 180 KCAS -
*6. Recover

Passing 6,000 feet AGL, dive recovery not
initiated -
*7. Eject

LOSS OF DIRECTIONAL CONTROL DURING TAKEOFF
OR LANDING (BLOWN TIRE, NWS FAILURE) / PLANING LINK FAILURE
If detected after touchdown and flyaway airspeed available –
*1. Go Around

If flyaway airspeed not available –
*1. Select Emergency Brakes (if appropriate)

*2. Hook Handle- Down (if required)

LOSS OF CABIN PRESSURIZATION
OBOGS Aircraft –
*1. Emergency Oxygen Green Ring(s)- Pull

*2. Oxy Flow Knob- Off

ALL Aircraft

*3. Initiate Rapid Descent Below 10,000' Cabin Altitude

HYPOXIA / LOW MASK FLOW / NO MASK FLOW

*1. Emergency Oxygen Green Ring(s)- Pull

*2. Oxy Flow Knob / Oxygen Supply Lever- Off

*3. Initiate rapid descent to below 10,000' cabin altitude

Normal brake pressure is supplied by ________ I-2-66

Emergency brake pressure is supplied by ________. I-2-67

The hydraulic system contains a pressure regulating system that
maintains about _______. I-2-42

The RLS system shuts off, and re-opens appropriate hyd systems
when the HYD reservoir fluid levels reach %, %, and %
of full. I-2-42

T / F In flight with an APU ACCUM caution not related to emergency gear/probe extension or APU start, do not select ­­­­HYD ISO ORIDE as this may result in additional loss of HYD 2B fluid. V-12-8
True False

What may a BRK ACCUM caution in flight indicate?
____________________________________ V-12-12

A L or R BOOST LO caution associated with GEN, and both HYD circuit cautions, may indicate what?. _____________ V-12-12

With one engine failed, maintain engine with operating HYD system at or above ____% when practical to avoid going into MECH. V-16-3

Aside from the primary flight controls, name five systems that HYD2 provides hydraulic power for?
1. __________________ 2. ____________________
3. __________________ 4. ____________________
5. __________________ I-2-44

How many Hydraulic Filters ( P’s) are there in each wheel well? _______ I-2-42

Below ______ psi, a circuit pressure switch causes the MASTER CAUTION Light and the appropriate HYD caution displayed on the DDI. I-2-42

How many applications of the Emergency Brakes do you have if the Brake Accumulator is at 2000psi? ____ I-2-67

T / F The aircraft is uncontrollable with HYD1A, HYD2A, HYD2B failures. V-15-12

APU FIRE LIGHT
INFLIGHT or on GROUND

*1. APU fire Light - Push

*2. Fire Extiguish Ready Light- Push

GROUND

*3. Throttles- Off

DUAL L BLEED and R BLEED WARNING LIGHTS /
L/R ATS CAUTION / DUAL L/R BLD OFF CAUTION

IN FLIGHT

*1. Throttles- Min Practical

OBOGS Aircraft -
*2. Emergency Oxygen Green Ring(s)- Pull

All Aircraft -
*3. Bleed Air Knob- Off (do not cycle)

*4. Initiate rapid descent to below 10,000' cabin altitude

SINGLE L BLEED or R BLEED WARNING LIGHT

IN FLIGHT

*1. Throttle affected engine- Idle

*2. Bleed Air Knob- (L) off / (R) off (do not cycle)

If light still on, do the following in order until light goes out -
*3. Throttle affected engine- Off

OBOGS Aircraft –
*4. Emergency Oxygen Green Ring(s)- Pull

All Aircraft -
*5. Bleed Air Knob- Off (Do not Cycle)

*6. Initiate rapid descent to below 10,000' cabin altitude

FIRE LIGHT
GROUND
*1. Throttles- Off

*2. Fire light affected engine- Push

*3. Fire extiguish ready light- Push

4. Batt Switch- Off

INFLIGHT
Dual FIRE lights -
*1. Throttles- Min Practical

Single FIRE light or Dual when side confirmed -
*2. Throttle affected engine- Off

*3. Fire light affected engine- Push

*4. Fire extinguish ready light- push

*5. Hook Handle- Down

ENGINE CAUTIONS/ ENGINE STALL
L/R EGT HIGH, L/R FLAMEOUT, L/R IN TEMP (IN FLIGHT),
L/R OIL PR, L/ R OVRSPD, and L/R STALL

*1. Throttle affected engine- idle

HOT START
If EGT climbs rapidly through 750˚ C -
*1. Throttle affected engine- Off

SINGLE ENGINE FAILURE IN LANDING CONFIGURATION

*1. Throttles- MIL or MAX

*2. Flap Switch- Half

*3. Maintain On-speed AOA and Balanced Flight

What two fuel valves close when an engine fire light is pressed.
I-2-16 _____________________________

Which one of the following caution and advisory displays will not activate the “engine left / right” voice alert? I-2-8

a. L or R Overspeed
b. L or R EGT HIGH
c. L or R BOOST LO
d. L or R OIL PR

T/F The internal wing tanks contain foam for fire/explosion protection. I-2-10
True False

Attempting to restart an engine that has flamed out for no apparent reason may result in what? V-15-5 _______________________

A lockup device in the main fuel control prevents thrust reduction below military if aircraft speed is _____________. I-2-2

To prevent running engagements during APU coast-down and to
prevent APU exhaust torching, a minimum of minutes must
elapse between APU shutdown and another APU start. III-7-15

Actuation of the engine crank switch above ____% rpm may shear
the air turbine starter shaft. I-2-3

An AMAD caution indicates what: ___________________ I-2-28

An AMAD PR caution indicates what: _______________ I-2-28

Max N2:102%
Ground Idle (400):61-72%
Flight Idle:68-73%
Max N2 fluctuation stabilized power:+/-1%
Ground Idle Oil Pressure (warm oil):45-110 psi
Inflight Idle Oil Pressure:55-110psi
Mil power Oil Pressure:95-180psi
For ambient air temp. above 0 degrees F, Oil pressure must peak
below 180 and start to decrease within 30 sec after reaching idle
RPM, and continue to decrease to steady-state limits.

FLIGHT CONTROL CAUTIONS
DEL ON, MECH ON

*1. Speed Brake- Check In

*2. Slowly Decelerate to below 400kts or .80 MACH

FLAPS OFF CAUTION

*1. Maintain airspeed above 300kts and balanced flight

DOUBLE GENERATOR OR DOUBLE TRANSFORMER-RECTIFIER FAILURE
If BATT SW caution light not on –
*1. Batt Switch- Oride

With generator switch in NORM, at approximately what % N-2 does the Generator turn on? ____ % I-2-30

A ground engine start without the parking brake set results in illumination of the _______________ caution. I-2-31

T / F With a single transformer-rectifier failure, no cockpit warning is provided. I-2-31
True False

When the U Batt charge falls below _____ volts for ____ sec, the E BATT automatically takes over the essential 24/28 DC bus. I-2-35

The battery automatically cuts off after ____minutes once internal or external power is removed and battery switch is ON.
I-2-35

Starting on the left and going counter-clockwise, name the eight circuit breakers in order. I-2-37
1. _______________ 5. _______________
2. _______________ 6. _______________
3. _______________ 7. _______________ 4. _______________ 8. _______________

How can you recognize dual generator failure? _______________. V-15-16

T / F A Double Generator failure may be caused by a fault within the radar. In this case the generators will not reset until the radar is turned OFF. V-15-19
True False

With a Double Gen or Double TR Fail, the U BATT and E BATT will provided limited DC power for about _______minutes. V-15-19

T / F With Both TR’s Inoperative, Both Gen’s Operative and Batteries in a High State of Charge, you should still have a TACAN. V-15-23

The AMAD can operate for _____minutes after loss of oil without catastrophic failure, but the generator will fail ________ after loss of oil. V-15-26

How can you recognize dual transformer-rectifier failure? _______________________________________________________. V-15-19

LOSS OF CABIN PRESSURIZATION
OBOGS Aircraft –
*1. Emergency Oxygen Green Ring(s)- Pull

*2. Oxy Flow Knob- Off
ALL Aircraft

*3. Initaite rapid descent below 10,000' cabin altitue

The aircraft may be uncontrollable on which single hydraulic circuits? _______________. V-15-12

True/False: If the right engine is being rotated with crossbleed to provide normal systems operation and fuel flow on the left engine is reduced below 2,000 pph (as during landing) the right engine hydraulic pump may not provide sufficient flow for NWS and normal brakes. V-15-3
True False

What two methods may be used to retain both hydraulic systems if the engine core is rotating: V-15-3

The HYD 2 priority valves close at approximately _______psi.
I-2-42

The hydraulic pumps are located on the _______________ and maintain the hydraulic pressure at approximately ___________psi.
I-2-42

The engine accessory gearbox, driven by the compressor rotor powers I-2-1 _________,_____________ , ___________, _____________ and ____________.

True/False: V-15-5 If an engine stall does not clear itself, a prompt chop to idle may clear it
True False

Each AMAD mechanically drives a ________,_________, and ___________. I-2-27

True/False: If a stalled engine will not clear, you should shut down the engine and attempt a restart. V-15-5
True False

What airspeed may be required to maintain 12% windmilling rpm? __________ V-15-5

True/False: The most probable source of visible smoke or fumes in the cockpit is from the engine bleed or residual oil in the ECS ducts. V-15-30
True False

What failures will illuminate the emergency instrument light and the BATT SW caution light? I-2-40 __________________________________

What does the BATT SW light coming on in the air with the battery switch on indicate? I-2-36 _________________________________

True/False: With both generators inoperative and good batteries, your hydraulic pressure indicator will be inoperative. V-15-22
True False

On aircraft with CG control, if tank 4 fuel transfer fails tank 1 will not transfer fuel until the ___ ____ caution comes on. I-2-12

On deck, what may the pilot need to do with high ambient temperature and low fuel flow (idle rpm) to help prevent a FUEL HOT caution? _________________________ I-2-16/17

List 4 events that will cause fuel dumping to cease: I-2-17
1. ____________________________________
2. ____________________________________
3. ____________________________________
4. ____________________________________

When the fuel level in either feed tank drops to __________ LBS a FUEL LO light on the caution lights panel comes on. I-2-17

A FUEL Advisory will appear on the DDI if any of the following cautions do not appear within 15 seconds after initiating FUEL quantity BIT: ____________________________________. I-2-19

Fuel dump rate is _____________lbs/min. I-2-17

L/R BOOST LO caution, L/R AMAD caution, Fuel LO caution
may all be indications of what? _________________. V-15-15

What is the max capacity of each fuel tank (using JP5): I-2-23/201
Tank 1: 2800 (A/C) 2100 (B/D)
Tank 2: 1800lbs
Tank 3: 1400lbs
Tank 4: 3600lbs
Wing tanks: 580lbs each side

Normal internal fuel transfer is accomplished by ______________.
I-2-11

The fuel recirculation system cools what? I-2-16
1. _______________________________
2. _______________________________

What is the primary and two backup modes of the flight control system? I-2-43
a. _______ b. ________ c. ________

What does pressing the T/O trim button in-flight do? I-2-47___________________________________________________

Rudder toe-in/toe-out is a function of ______ with maximum toe-in_______. I-2-53

T/F. The FCS I-BIT cannot be performed with nose wheel steering engaged. I-2-171
True False

During BEFORE TAXI checks, if a TRIM advisory does not appear when the T.O. trim button is pressed, what action should the pilot take? ___________________III-7-20

For post departure dive recovery, minimum altitude loss is achieved by advancing throttles to MAX and maintaining what AOA? ______ IV-11-10

T/F During recovery from a fully developed spin, full lateral stick should be maintained in the direction of the command arrow until the arrow disappears. IV-11-14
True False

Takeoff with any ______ axis failed

Full or partial lateral stick and/or rudder pedal input over ____ ° roll/yaw.

Negative g for more than ____ seconds (with AFC 053).

Pulling any __________ in flight except as directed in NATOPS

Selection of gain ORIDE above ______ knots/ Mach ______ or above ______ ° AOA

What is the maximum crosswind component for takeoff and flared landings? ______ kts.

What is the maximum crosswind component for section landing/takeoffs and normal landings? ______ kts.

Leading edge deflections of the inboard / outboard LEF beyond the 4 degrees over-travel stop may result in an uncontrollable configuration below ______ knots.

CG Limitations:
Forward CG:17% MAC
Aft Limit:
FE Config:28%MAC
All other :27-28% MAC

Landing Gear Warning Lights/Tone will go off if the aircraft it below ______kts, altitude less than ____ft, and rate of descent greater than _____feet per minute. I-2-65

T/F Anti-skid is completely inoperative below 35 knots. 1-2-67

ANTI SKID caution will not reappear and brakes may not be available for ____ seconds after cycling the anti-skid switch in flight or _____seconds during landing rollout, until BIT is complete. I-2-67

In LOX aircraft and under less optimal conditions, (low altitude, heavy breathing, loose fitting mask, etc.) as few as _____ minutes of emergency oxygen may be available. In OBOGS equipped aircraft as few as_____ minutes may be available. I-2-155/159

On deck, if AV AIR HOT caution on for more than ­­­___ minutes, do not takeoff. V-12-10

Name 4 systems you lose with both BLD OFF cautions on:
V-12-11

Max engagement speed for E-28 arresting gear is ___ knots groundspeed. V-16-19

Gear extension / retraction: ______ kts

Emergency gear extension: _____ kts (If practical)

Tires Speed: Nose ______ kts Main ______ kts

What does a TANK PRESS HI caution display on the DDI indicate? I-2-11
a. On the ground: _____________________________
b. Inflight: ___________________________________

TRUE/FALSE (F/A-18A), I-2-13 TRUE/FALSE (F/A-18C/D): With external tank control switch in stop transfer and hook handle down, fuel will transfer when the FUEL LO caution display comes on
True False

How is a limited amount of fuel provided for negative G or inverted flight? I-2-16 _______________________

True/False: I-2-17 The fuel low level indicating system is completely independent of the fuel quantity indicating system
True False

How much has the fuel quantity in tank 1 been reduced in the F/A-18D aircraft? I-2-202 ____________.

What is the internal fuel capacity of the F/A-18D? I-2-203 _______lbs JP-5

True/False: : I-2-16 Gravity fuel flow is sufficient to sustain minimum afterburner operation.
True False

True/False: V-15-16 If tank 1 fails to transfer, as much as 700 lbs of fuel, it may not be usable for approach and landing
True False

All external tanks can be pressurized any time by placing either external tank fuel control switch to _______________. I-2-13

What is the FCS reset button used for? I-2-47 _____________________________________________________

True/False: Failure of FCS channels 1 and 3 will not affect the flying qualities of the aircraft. V-15-36
True False

True/False: Once EMERG has been selected on FCS COOL switch, selection of NORM will switch FCC A and right TR cooling back to avionics air. I-1-141
True False

With the spin switch in NORM, when will the spin recovery mode be activated? I-2-49 _______________,______________,______________

Lateral Weight Asymmetry Limitations 1-4-6
1. Field takeoff:22,000ft-lbs.
2. Inflight:26,000ft-lbs.
3. FCLP or carrier landing:17,00ft-lbs < 33,000lbs gross wieght.
4. Field landing (flared) up to 500 fpm sink rate:26,000ft-lbs.
Lateral weight asymmetry AOA limitation:
5. With 6,000-12,000 ft-lbs (>0.8 IMN) , AOA limit is:-6 to 20 AOA
6. With 12,000-26,000 ft- lbs, AOA limit is:-6 to 12 AOA .

Bank angle limits with flaps at half or full:1-4-5
1. FE configuration:over 90 degrees.
2. FE configuration with centerline tank/stores:over 60 degrees.
3. All other configurations: over 45 degrees.

True/False: To extend the landing gear by the emergency method, the gear handle must be in the down position. I-2-65
True False

True/False: The hook light remains on except when the hook is up and latched. I-2-69
True False

True/False: The aft cockpit does not have an internal canopy switch or an internal manual canopy handcrank. I-2-202

True/False: There are no provisions for normal landing gear extension from the rear cockpit. I-2-206
True False

True/False: F/A-18 aerodynamic braking is recommended.
III-7-28
True False

True/False: Antiskid is not available with rear cockpit emergency brake handle in the emergency position. I-2-68
True False

If the cabin temperature knob is full clockwise with the cabin temperature switch in MAN, cockpit temperature can reach as high as _______F. V-15-29

True / False: A flashing NWS cue indicates failed nosewheel steering. V-15-60