End of nose radome to fwd. edge of panel 26. Includes the windshield, canopy, cockpit, leading edge extension, and nose landing gear.
From edge of panel 26 to aft edge of panel 55L/R. Includes main landing gear, intake ducts, external stores stations, fuselage fuel tanks and airframe mounted accessory drive.
From panel 54L/R to end of aircraft. Includes engines, speed brake, vertical and horizontal stabilizers, and arresting hook.
Provides lift for the aircraft, stores fuel, houses ailerons. Outer wing tip stations are 1&9. Attached to center fuselage
Leading Edge Extension (LEX)
Provides added lift at high angles of attack. Mounted on either side of the wing leading edge.
Leading edge flaps
Deflect symmetrically to change lift. Also deflet asymmetrically to aid ailerons in producing roll. Located on the inboard and outboard leading edge of each wing.
Trailing Edge Flaps
Deflect symmetrically to change lift. Independently deflect asymmetrically to aid the alilerons in producing roll. Located on the trailing edge of each wing.
Deflect symmetrically to produce pitch, and asymmetrically to produce roll. Located on either side of the tail of the aircraft.
Toe-in to increase lift and improve stability, toe-out to improve stability. Symmetrically to produce yaw. Located on the rear of each vertical stabilizer.
Hydraulic System 1
Provides hydraulic fluid pressure to the primary flight controls either as a primary or backup source. Contians pump manifold, pump reservoir, filter unit, case drain filter, oil fuel heat exchange, and related indicators.
Hydraulic System 2
Same as system 1. Provides hydro. fluid pressure to the primary flight controls either as primary or backup source. Also supplies pressure to all other non-flight control systems
Auxiliary Power Unit Accumulator
Gas Charge cylinder provides required fluid pressure to the APU start motor and emergency hydraulic systems.
Allows backup hydraulic pressure to replace the primary hydraulic pressure, if the primary hydraulic pressure fails.
Nose Landing Gear
Provides landing, takeoff, and taxi energy absorption, tire/runway compliance. Located on the underside of the fwd. fuselage.
Main Landing Gear
Provides a stable platform for aircraft carrier and shore based operations. Absorbs the energy from ground loads during landing and taxi operations. Located on the underside of the center fuselage.
Provides pilot modulated individual wheel-controlled braking. Located on the main landing gear wheels.
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 fwd. side of the nose landing gear shock strut.
Hydraulically controlled arm attached to the underside of the aft fuselage.Assists with stopping of aircraft.
Bleed Air System
Extracted from the last compressor stage of both engines, regulated and routed to the air cycle air conditioning system.
Air Cycle Air Conditioning System
Cools and contitons hot bleed air for use in various a/c systems such as fuel pressurization, canopy seal, anti-g, throttle boost, anti ice, rain removal, avionics and cabin cooling.
Automatically regulates the air to the pilots's anti-g suit to increase pilot tolerance to high accleration levels.
Oxygen is routed from the left console to the ejection seat, thru the survival kit to the pilot's oxygen regulator connector.
On-Board Oxygen Generating System
Removes nitrogen and other contaminants from engine bleed air. Resultant gas is an O2 rich breathing mixture for pilots' use.
Ejection Seat System
Place to sit and launches pilot in emergency situations. Made up of main beam, parachute, seat bucket, survival kit, and catapult.
Emergency O2 System
Emergency oxygen bottle, actuated automatically upon ejection of manually in case of an O2 system failure. Pull green ring on left side of seat pan assembly.
Fire Detection System
Provides warnings for the APU bay, left and right AMAD bays, and aft engine bays.
Fire Extinguishing System
Puts out fires in various compartments of the aircraft. APU shuts down then puts out fire with extinguishing agent.
Electronic Flight Control System
The 2 flight control computers combine inputs w/air data and inertial inputs and provide electrical signals to servo actuators.
Purpose of the Backup Mechanical System
Provides automatic connection of a direct mechanical link from the stick to the differential stabilizer servo actuators. Provides limited pitch and roll control after a complete electrical failure or complete failure of both flight control computers.
Emergency Extension of the Landing Gear
Serves to unlock the landing gear lock up mechanisms and aid in landing gear down lock.
Main firing handle safety pin: Safeties the ejection control handle during all ground parking, servicing and towing.
Canopy Jettison System
Canopy Jettison Ground Safety Pin: safeties lever, perventing accidental canopy jettison by movement of internal CANOPY JETT lever. Pin must penetrate internal CANOPY JETT lever mounting plate and initiator lever to prevent accidental canopy jettison.
Canopy Normal System
If an electrical or mechanical failure occurs when canopy is open don't close canopy manually, unless weather conditions exists that required it