201.1 System Components and Component Parts
201.1.1 Aircraft Structure
A. Radome: Provides an electrically transparent window for transmission and reception of radar signals. Spans from Y coordinate 60.50 to Y coordinate 128.50.
B. Forward Fuselage: Spans from Y coordinate 128.50 to Y coordinate 383.00 or from the end of the Nose Radome to the forward edge of panel 26.
C. Center Fuselage: Spans from Y coordinate 383.00 to Y coordinate 557.50 or from the forward edge of panel 26 to the aft edge of panel 55L/R.
D. Aft Fuselage: Spans from Y coordinate 557.50 to the end of the aircraft or from panel 54L/R to the exhaust nozzles.
E. Wing: Provides lift for the aircraft, stores fuel, houses LEF's, TEF's and Ailerons, outboard section folds for carrier operation, allows for attachment of non jettison able pylons for weapons/fuel stores. Attached to the center fuselage by wall lugs which mate lugs on the wing main torque box.
F. Leading Edge Extension (LEX): Provides added lift at high angles of attack. Mounted on either side of the Forward Fuselage they are an extension of the wing leading edge. The port LEX houses the Boarding Ladder.
201.1.2 Flight Control Surfaces
A. Ailerons: In flight, the ailerons are commanded asymmetrically to produce roll motion. The ailerons are located on the outboard trailing edge of each wing.
B. Leading Edge Flaps: When taking off or landing the leading edge flaps deflects symmetrically to change lift. In flight they deflect asymmetrically to aid the ailerons in producing roll motion. The leading edge flaps are located on the inboard and outboard leading edge of each wing.
C. Trailing Edge Flaps: When taking off or landing the leading edge flaps deflects symmetrically to change lift. In flight they independently deflect asymmetrically to aid the ailerons in producing roll motion. The trailing edge flaps are located on the trailing edge of each wing.
D. Stabilators: The stabilators deflect symmetrically to produce pitch motion and asymmetrically to produce roll motion. The stabilators are located on either side of the tail of the aircraft.
E. Rudders: During take off or landing when the AOA is less than 8 degrees the rudders toe-in to increase lift and improve stability, when AOA is more than 8 degrees the rudders toe-out to improve stability. In flight the rudders are commanded symmetrically to produce yaw motion. The rudders are located on the rear of each vertical stabilizer.
F. Speed brake: Under certain conditions the speed brake may be extended into the air stream creating drag and slowing the aircraft's airspeed. The speed brake is located on top of the Aft Fuselage between the vertical stabilizers.
A. Hydraulic System 1: Provides hydraulic fluid pressure to the primary flight controls either as a primary or backup source.
B. Hydraulic System 2: Provides hydraulic fluid pressure to the primary flight controls either as a primary or backup source. The system also supplies pressure to all other non-flight control systems.
C. Auxiliary Power Unit Accumulator: Provides required fluid pressure to the APU start and emergency hydraulic systems.
D. Switching Valves: Each switching valve allows backup hydraulic pressure to replace the primary hydraulic pressure, if the primary hydraulic pressure fails. If primary hydraulic is restored, the switching valve shifts to normal operating position.
201.1.4 Landing Gear
A. Nose Landing Gear: Provides landing, takeoff and taxi energy absorption, and tire/runway compliance. Located on the underside of the Forward Fuselage.
B. Main Landing Gear: Provides a stable platform for aircraft carrier and shore based operations. Also absorbs the energy from ground loads during landing and taxi operations. Located on the underside of the Center Fuselage.
C. Wheel Brakes: Provides pilot modulated individual wheel-controlled braking. An anti skid system is combined with the normal system to prevent wheel skid. Located on the main landing gear wheels.
D. Launch Bar: Provides a means of steering the aircraft during carrier deck tracking and engages the catapult, applying catapult tow forces to the aircraft. Located on the forward side of the nose landing gear shock strut.
E. Arresting Hook: Provides a means of stopping the aircraft where normal runway landings are not available. Located on the underside of the Aft Fuselage.
201.1.5 Environmental Control Systems
A. Bleed Air System: Engine bleed air is extracted from the last compressor stage of both engines, regulated and routed to the air cycle air conditioning system.
B. Air Cycle Air Conditioning System: Cools and conditions hot bleed air for use in various aircraft systems.
C. Anti-Gravity System: Automatically regulates the air to the pilot's anti-g suit to increase pilot tolerance to high acceleration levels.
D. Oxygen System: In bunos 161353 thru 164068, oxygen is supplied from a 10 liter liquid oxygen system. Oxygen is routed from the left console to the ejection seat, through the survival kit, to the pilot's oxygen regulator connector.
E. On-Board Oxygen Generating System: On bunos 164196 and up OBOGS removes nitrogen and other contaminants from engine bleed air. The resultant product gas is an oxygen rich breathing mixture for pilots use.
201.1.6 Egress Systems
A. Ejection Seat System: Provides support for the crewmember during normal flight conditions and a method of escape from the aircraft during emergency conditions.
B. Canopy System: Provides entry to the cockpit and protects the crewmember from the elements. May be operated electrically or manually and can be jettisoned in an emergency.
C. Emergency Oxygen System: Oxygen is required at altitudes over 10,000 feet. The emergency oxygen bottle, located in the ejection seat survival kit, is actuated automatically upon ejection or manually in the case of an oxygen system failure.
201.1.7 Fire Systems
A. Fire Detection System: Provides fire warning for the APU bay, left and right AMAD bays and the left and right engine bays. Warning lights in the cockpit and a voice alert indicate fire conditions.
B. Fire Extinguishing System: A one-shot one-bay system using a single fire extinguisher. During ground operation of the APU the system is automatic. During flight the pilot manually selects the bay and discharges the extinguisher.
201.2.1Electronic Flight Control System:
The Electronic flight control system is made up of two flight control computers, control surface servo actuators, air data and inertial sensors and control sensors. The system also includes a built-in test to provide failure warning and fault isolation. The flight control computers combine inputs with air data and inertial inputs and provide electrical signals to servo actuators. The servo actuators move control surfaces the direction and amount required to produce desired aircraft motion.
201.2.2 Purpose of the Backup Mechanical System:
Provides automatic connection of a direct mechanical link from the stick to the differential stabilator servo actuators. This provides limited pitch and roll control after a complete electrical failure or complete failure of both flight control computers.
201.2.3 Emergency Extension of the Landing Gear:
Emergency extension is primarily free fall aided by stored energy in the MLG shock absorber and hydraulic system no. 2B pressure. Hydraulic system no. 2B pressure is supplied by the Auxiliary Power Unit (APU) and emergency brake accumulators and serves to unlock the landing gear up lock mechanisms and aid in landing gear down lock. Emergency extension is controlled by the LDG GEAR control.
201.5 Safety Precautions
a. Ejection Seat
1. Main Firing Handle Safety Pin: Safeties the ejection control handle during all ground parking, servicing and towing. It is inserted through the hole in the base of the ejection control handle.
2. Ejection Seat Safe/Armed Handle: Safeties the ejection control handle, preventing accidental seat ejection. In the safe position it is rotated full up and forward to the locked SAFE position.
b. Canopy Jettison System
1. Canopy Jettison Ground Safety Pin: Safeties the internal CANOPY JETT lever, preventing accidental canopy jettison by movement of internal CANOPY JETT lever. The pin must penetrate internal CANOPY JETT lever mounting plate and initiator lever to prevent accidental canopy jettison.
c. Canopy Normal System
1. Make sure the windshield and canopy static charge is removed.
2. Canopy must be closed and locked in winds over 60 knots.
3. Do not move aircraft until access to cockpit is possible.
4. Snow must be removed prior to opening.
5. Canopy should not be operated when ambient temperature is below 0 degrees F.
6. Inspect canopy sills and dorsal deck for foreign objects prior to closing canopy.
d. Liquid Oxygen
1. Oxygen in its liquid form has a temperature of -297 degrees Fahrenheit. Do not touch implements containing LOX or wear clothing not specified in the NA 13-1-6.4.
2. LOX has an expansion ratio of 862 to 1 and can generate up to 12,000 psi if allowed to evaporate in a sealed container. Do not cap vent ports on liquid oxygen systems.
3. Many materials will burn violently when saturated with liquid oxygen. An enriched-oxygen fire is virtually impossible to extinguish until the oxygen supply is cut off. Hydrocarbons will burn explosively when saturated with oxygen and subjected to mild shock or impact.