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94 Cards in this Set
- Front
- Back
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Describe the basic requirements for each of the following Navy Occupational Safety and Health (NAVOSH) Programs:
1. Respiratory Protection Program 2. Hearing Conservation Program 3. Sight Conservation Program 4. Personal Protective Equipment (PPE) |
1. a program which identifies employees as requiring respirator protection equipment due to the nature of their work or job.
2. a program that surveys and identifies potentially hazardous noise levels and personnel at risk. 3. a program that surveys all activity work areas equipment and processes to determine which are eye hazards, which personnel require eye protection and what type of protection is required. 4. a program, which assesses all workplaces to determine if hazards are present, that necessitate the use of PPE |
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Identify the F5 E/F areas.
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Flammable liquids, compressed gasses - Areas - including hydraulic reservoirs, fuel tanks, nitrogen charge struts, high-pressure accumulators. Canopy, seat and explosive devices - many explosive devices are located throughout the airframe, which have rocket motors, initiators, and thrusters also controls that require special handling. Engine - Radar antenna - moveable surfaces. (Flaps, stabs, rudder, speed brakes, tailhook, drag chute doors, landling gear doors...)
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Identify the minimum safe distances from turning aircraft intakes/exhaust at the following power settings:
1. Idel 2. Military (MIL) 3. Maximum (MAX) |
Idle - 15 ft radius from intake 20-30 ft from exhaust.
MIL - 20 ft radius from intake 60 ft from exhaust MAX - 25 ft radius from intake 60-80 ft from exhaust. |
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State the purpose and Identify the location of the aircraft step, no step areas.
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To avoid damaging the thin skin and honeycomb construction through out the aircraft structure.
Areas to avoid are your leading edge flaps, trailing edge flaps, horizontal stabilators, ailerons, and radome surfaces. Areas that are designated as walkways will have a non-skid on the surface. Also the wings themselves are considered walkways. Protective shoe coverings should always be used when walking on aircraft. |
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State the general safety precautions associated with applying and removing external power.
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Circuit breakers and switches must be positioned as specified in the required MIMs.
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State the number of tie-down points on the F5 E/F and identify their locations.
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3 tie down points -
1 aft of nose landing gear 1 forward of each of the main landing gears. |
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State the proper procedures for aircraft grounding.
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Ground to earth first then to one of the A/C grounding points.
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State the purpose of aircraft plugs and covers:
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To protect A/C openings and protruding surfaces from physical damage, environmental damage, and FOD intrusion.
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Discuss the requirements, duties and responsibilities of the following Aircraft Handling Team personnel: 6 people are required to move any A/C:
Move Director |
Prime responsibility lies with the director for the aircraft movement.
- Ensures a qualified brake rider mans cockpit. - Ensures tow bar is secure prior to movement. - Ensures A/C is ready for the move - Ensures A/C has enough brake pressure - Ensures enough clearance all around the A/C for and during the move. - Sets the pace to a slow walking speed |
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Discuss the requirements, duties, and responsibilities of the following Aircraft Handling Team Personnel:
Brake Rider |
Conducts a pre-movement inspection of A/C ensuring A/C has all safety equipment installed (Seat pins/landing gear safety pins).
- Ensure A/C is free from servicing equipment/external cords. - Ensures A/C has enough brake pressure - Stays alert during entire A/C move while not leaving the cockpit until A/C is final spotted. |
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Discuss the requirements, duties, and responsibilities of the following aircraft handling team personnel:
Chock Walker |
- pulls and installs chocks when instructed by the director
- stays alert to director's signals - ensures A/C is ready for move and free of any chains, power cords, and servicing equipment. - watches out for ground obstacles and warns the director accordingly - stay in a relatively safe position away from aircraft wheels |
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Discuss the requirements, duties, and responsibilities of the following aircraft handling team personnel:
Safety Observer (wing-walker/tail-walker) |
- conduct's a pre-tow inspection of the A/C
- ensures safety pins are installed - ensures A/C is ready for move - ensures A/C is free of chains, cable cords, and support equipment - ensures A/C will clear all obstructions during movement |
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Discuss the requirements, duties, and responsibilities of the following aircraft handling team personnel:
Tractor Driver |
- Tows A/C at a slow walking speed avoiding sudden stops or starts
- Pre-ops tractor ensuring the support equipment is operational and ready - Follows instructions from the director while avoiding any and all obstructions |
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Discuss towing preparations:
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Minimum structural access doors must be installed to prevent damage to A/C. Radome must be closed and secured (if installed). Ensure A/C is clear of all obstacles and support equipment.
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State the purpose of the landing gear aircraft ground safety pins:
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Landing gear safety pins safeties nose and main landing gear in the down position, preventing gear retraction.
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State the purpose of a hydraulic patch test.
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Patch testing is the primary contamination measurement method used at all levels of maintenance. Aids in determining fluid contamination level, ensuring a high level of fluid purity.
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State the purpose of a tactical paint scheme.
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Are applied to an A/C to lessen the probability of visual or photgraphic detection. Used for deception, reduction of detection range, or to confuse and mislead observers.
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State the purpose of the NAVAIR 01-1A-509 and its application to the F5 E/F.
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Provides information on material and procedures for the prevention and repair of corrosion damage to equipment on land and sea.
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State the three types of wheel brake systems.
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Independent-type brake system.
Power boost brake system. Power brake control valve system. |
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Discuss the following classification of repairs:
1. Temporary Repair 2. One-Time Flight 3. Permanent Repair |
1. one which may allow aircraft to be flown until permanent repair can be made.
2. Repair made to restore limited load carrying requirements to allow an aircraft to be flown to a repair station for permanent repairs. 3. Repair equals or exceeds strength of original structure or component with no adverse affects on structural integrity, fatigue life, safety, or flying characteristics. |
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State the type of engine and major sections used in the F5 E/F.
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Two J85-GE-21 afterburning turbojet engines mounted nearly parallel to each other, one on each side of the keel in the aft part of the fuselage.
The major sections are: front frame, compressor assembly, main frame, combustor assembly, turbine section, and the afterburner/exhaust nozzle. |
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State the composition and purpose of the internal fuel tanks.
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Three rubber-impregnated, bladder type, nylon fabric fuel tanks with explosion-suppressant foam material. Provides independent fuel supply system for each of the two engines.
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Explain the purpose of the single point fueling system.
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So the internal and external fuel cells can be filled simultaneously.
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State the difference between a barometric (pressure) and radar (absolute) altimeter.
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Barometric Altimeter - uses pitot-static pressure to indicate altitude above sea level. The scale for barometric altimeter starts at 29.92 inches in mercury.
Radar Altimeter - uses radio echos to determine altitude above ground level. (Terrain) |
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Define the following terms:
1. Azimuth 2. Bearing |
Azimuth - angular measurement in the horizontal plane in a clockwise direction.
Bearing - is the horizontal direction of one terrestrial point from another. |
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State the purpose of the following:
1. A/C Power System 2. D/C Power System 3. Static Inverter |
1. A/C Power System - is supplied by two 13/15 KVA 320-480 Hz generators, one operating from each engine. Each generator functions independently and supplies 115/200 volt 3 phase power to the A/C buses.
2. D/C Power System - is obtained from each A/C system thru a transformer - rectifier, which converts A/C to D/C. A 24 volt, 11 ampere-hour nickle-cadmium battery serves as a standby source of power for all D/C circuits and is charged by the transformer-rectifiers. 3. Static Inverter - powered by the dc bus, converts 24 volt dc from the battery to 115 volt ac for an alternate source of ac power to start engines, operate left engine instruments and utility hydraulic pressure indicator during start of left engine. Powers fuel and oxygen. |
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State the objective of the Explosive Handling Qualification and Certification Program.
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To ensure military and civilian personnel are qualified/certified in the safe handling, stowage and transportation of ordnance in which they are associated with.
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State the purpose of suspension equipment.
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To suspend single stores, bombs, and a variety of missile launchers.
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State the purpose of a Cartridge Actuated Devices. (CADs)
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To eject single stores and a variety of weapons from the aircraft.
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Define the following acronyms:
1. AIM 2. AGM 3. CATM 4. HERO |
1. AIM - Air launched intercept-aerial guided missile (Air intercept missile) (Air to Air)
2. AGM - Air launched surface attack guided missile (Air to ground) 3. CATM - captive air training missile. (Heat seeker) 4. HERO - hazards of electromagnetic radiation to ordnance. |
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Explain the significance of the following color coding on missiles:
1. Yellow 2. Brown 3. Blue |
1. Yellow - missile is high explosive. (Can be seen from afar).
2. Brown - missile has a live rocket motor. 3. Blue - inert and for training use only. |
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Define the following types of weapon guidance systems:
1. Active 2. Semiactive 3. Passive |
1. Active - missile is self-guiding and works by itself. Sends and receives its own signal.
2. Semi-Active - Needs independent or external source to track and lock on target. Any A/C can send out a signal to target and missile receives the signal back to lock on to target. (AIM 7 sparrow) 3. Passive - Heat seeking infrared or radar signals. Locks onto heat. (A-9s) |
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State the basic armament configuration of the F5 E/F aircraft.
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Consists of two 20-millimeter M-39A3 guns, installed in the high nose section. Bombs, rockets and missiles are externally carried, delivered and launched from 5 pylon (2 on each wing and 1 on the centerline)and 2 wingtip positions).
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State the basic characteristics of the following air to air missiles:
1. AIM-9 series (sidewinder) guided missile. |
Supersonic, air-to-air weapons with passive heat seeking detection, proportional navigation guidance, and torque-balance control systems.
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Identify the minimum requirements for aircrew personnel protective equipment (PPE)
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Flight suit, aircrew flier's boots, anti-g garment, helmet, survival radio/beacon, aviator flight gloves, anti-exposure suit, identification tags (dogtags), survival knife and sheath, personal survival kit, signal device, flashlight, life preserver, laser eye protection.
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State the purpose of the Environmental Control System (ECS)
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Provides aircrew confort (i.e.. pressurization/temp control) and avionics cooling. (Has 14 subsystems)
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State the purpose of the following personal flight equipment.
1. Oxygen mask 2. Oxygen regulator 3. Life preserver 4. Anti-gravity |
1. Oxygen Mask - designed to be worn over the face, forming a seal to the cheeks over the bridge of the nose and under the chin. Used with a regulator, which provides breathing gas upon demand at a pressure schedule dependent on the altitude. Used for helmet retention when properly fitted. Used for the valsalvo movement.
2. Oxygen Regulator - Reduce and regulates supply oxygen pressure for breathing. 3. Life Preserver - designed as a constant wear item for use with the SV-2B survival vest or integrated torso harness and provides a minimum of 65 lbs of buoyancy. 4. Anti-Gravity Suit - provides protection for the aircrew against the effect of the high g-forces experienced in high performance aircraft. |
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State the objective of the Egress System Checkout Certification Program.
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To thoroughly familiarize personnel working in or around the cockpit with the ejection systems. Any special hazards associated with those systems and to routinely monitor all such qualified personnel.
All maintenance personnel must qualify upon arrival to command prior to working on A/C. All qualified personnel must re-qualify every 6 months. TAD personnel must re-qualify after being away from command for 90 days. |
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State the purpose of the ejection seat.
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Supplies a place for the aircrew to sit during normal conditions and for propelling an occupant out and away from the aircraft in an emergency condition.
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Define the following conditions:
1. Hypoxia 2. Anoxia |
1. Hypoxia - the higher the altitude the amount of oxygen per unit of volume of air decreases, there for the oxygen intake is reduced unless the individual breaths additional oxygen the eyes, body, and muscles will fail.
2. Anoxia - complete lack of oxygen. |
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Identify the two types of Aviator's Breathing Oxygen (ABO)
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Gaseous oxygen (type I)
Liquid Oxygen (type II) |
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Define the following acronyms:
1. WAS 2. CAP 3. FCF 4. VMC 5. IMC 6. VFR 7. IFR |
1. WAS - War At Sea. Bombing ships
2. CAP - Combat Air Patrol 3. FCF - Functional Check Flight. Checking A/C to ensure everything is working correctly. There are four types - A, B, C, D. Type A must be done if A/C is not flown for 30 days. 4. VMC - Visual Meteorological Conditions. Expressed in terms of visibility, distance, from clouds and ceiling equal to or better than specified minimums. (Blue Sky) 5. IMC - Instrument Meteorological Conditions - expressed in terms of visibility, distance from clouds and ceiling less than the minimums specified. 6. VFR - Visual Flight Rules - rules that govern the procedures for conducting flights under visual conditions. (1) Flying in accordance with the see-and-avoid concept. (2) Pilot is responsible for his/her own separation from other aircraft under most circumstances. (3) Certain weather minimums are required for such flights. 7. IFR - Instrument Flight Rules - rules for governing the procedures for conducting instrument flight. (1) Pilots must comply with IFR procedures when operating their A/C in weather conditions that are less than VFR minimums. (2) Pilots are encouraged to use IFR procedures when their flight is conducted within the Federal Airway System. |
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Discuss the purpose of the Air Intercept Control (AIC)
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AIC personnel operate radar and NTDS consoles to direct air intercepts and within their capability, ensure the flight safety of all aircraft under their control.
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Airframe System
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Fuselage is a semimoncoque construction consisting of stressed skins supported by frames, longerons, and bulkheads.
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Radome
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Provides an electrically transparent window for transmission and reception of radar signals.
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Forward Fuselage
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Consists of compartments for electrical equipment, electronic equipment, nose landing gear, air-conditioning equipment, two 20-millimeter cannons and loading equipment, and a pilot's compartment.
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Center Fuselage
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Contains the wing attach provisions, main landing gear stowage, engine air inlet ducts, engine forward compartments, fuel cell compartments, and provisions for support of the vertical stabilizer.
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Aft Fuselage
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Consists of the engine aft compartment drag chute container, and support for the horizontal tail.
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Wing
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Is a thick skin, multispar-type construction. Provides lift for the aircraft, stores fuel, houses Ailerons, allows for attachment of non-jettisonable pylons for weapons/fuel stores. Attached to the center fuselage by wall lugs, which mate lugs on the wing main torque box.
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Flight Control Surfaces Ailerons
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In flight, the ailerons are commanded asymmetrically to produce roll motion. The ailerons are located on the outboard trailing edge of each wing.
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Flight Control Surfaces:
1. Leading Edge Flaps 2. Trailing Edge Flaps 3. Stabilators 4. Rudders 5. Speed Brake |
1. Leading Edge Flaps - When taking off or landing the leading edge flaps deflect symmetrically to change lift enabling the pilot to control the A/C easier at lower speeds. The leading edge flaps are located on the leading edge of each wing.
2. Trailing Edge Flaps - When taking off or landing the trailing edge flaps deflect symmetrically to change lift enabling the pilot to control the A/C easier at lower speeds. The trailing edge flaps are located on the inboard trailing edge of each wing. 3. Stabilators - (Horizontal Tail) the stabilators deflect symmetrically to produce movement on the pitch axis. The stabilators are located on either side of the aft fuselage section of the aircraft. 4. Rudders - Hinged to the vertical stabilizer controls aircraft movement in the yaw axis. 5. 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 bottom of center fuselage section outboard of the center line station. |
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Hydraulics
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There are two independent, piston-type engine-driven systems.
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Hydraulic System Right
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Drives the flight control system pump, by providing half of the hydraulic power to operate the primary flight controls; however, if either system fails there is adequate hydraulic power for the flight controls. The right system is located outboard of the right engine.
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Hydraulic System Left
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Drives the utility system pump for the landing gear, speed brakes, wheel brake system, nosewheel steering, gun gas purging system sctuators, gun gas deflectors, and stability augmenter system. And supplies half the hydraulic power for the primary flight controls. The left system is located outboard of the left engine.
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Landing Gear
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Hydraulically operated, fully retractable, tricycle-type.
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Nose Landing Gear
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Provides landing, takeoff and taxi energy absorption, tire/runway compliance, and steering during ground taxi. Located on the underside of the forward fuselage.
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Main Landing Gear
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Provides a stable platform for shore based operations. Also absorbs the energy from ground loads during landing and taxi operations. Located on the underside of the center fuselage.
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Wheel Brakes
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Provides pilot individual wheel-controlled braking. Located on the main landing gear wheels.
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Arresting Hook
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Provides a means of stopping the aircraft where normal runway landings are not available. Located on the underside of the aft fuselage. Not for use in carrier landings.
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Environmental Control Systems:
1. Bleed Air System 2. Air Cycle Air Conditioning System 3. Anti-Gravity System 4. Oxygen System |
1. Bleed Air System - Engine bleed air is extracted from the ninth compressor stage of both engines, regulated and routed to the air cycle air conditioning system.
2. Air Cycle Air Conditioning System - Cools and conditions hot bleed air for use in various aircraft systems. 3. Anti-Gravity System - Automatically regulates the air to the pilot's anti-g suit to increase pilot tolerance to high acceleration levels. 4. Oxygen System - Provides breathing oxygen for use in the aircraft. Supported from a 5-liter LOX converter unit were liquid-to-gaseous oxygen conversion occurs. |
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Briefly discuss the basic operation of the flight control system.
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The primary flight controls are operated from the cockpit thru the use of hydraulic pressure from the utility and flight control hydraulic systems. Movement of the control stick or rudder pedals actuates a closed cable system, which operates the servovalves in the actuating cylinders at each control surface.
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Anti-Skid System
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The anti-skid system provides protection against landing with wheels locked, or locking wheel brakes and/or tire skid during ground roll. Powered by 28 vdc and actuated by utility hydraulic pressure, the system consists of main gear wheel speed sensors, brake hydraulic pressure control valve, electronic control box, system on-off switch, and an anti-skid caution light.
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Fire Detection System
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Identical for each engine and are pneumatically pressure-actuated. Provides fire warning lights in cockpit when sensors detect excessive heat in the engine compartments.
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Egress Systems:
1. Ejection Seat System 2. Emergency Oxygen System 3. Canopy System |
1. Ejection Seat System - Provides support for the crewmember during normal flight conditions and a method of escape from the aircraft during emergency conditions.
2. 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. 3. Canopy System - Provides entry to the cockpit and protects the crewmember from the elements with an airtight seal for pressurization. May be operated manually or can be jettisoned in an emergency. |
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Discuss emergency extension of the landing gear.
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Consists of a handle in the cockpit outboard of the left vertical control panel and a system of cable controls connected to the main gear inboard door locks, main gear up-locks and the nose gear and nose gear forward door over-center mechanisms. Pulling of the handle to its full travel releases the main gear in-board door locks, the main gear up-locks, and the nose gear forward door and nose gear from an over-center-position. Gear doors open and the landing gear extends to the down position, assisted by gravity, airloads, and a spring bungee at each landing gear strut.
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What special safety precautions apply to:
1. Ejection Seat 2. Canopy Jettison System 3. Canopy Normal System 4. Liquid Oxygen (LOX) |
1. Seat Safety Pin: Holds right legbrace handgrip down anytime aircraft is on the gound. It ensures inadvertent firing of the ejection seat. It is inserted down through the hole forward of the right handgrip.
2. Canopy Jettison Safety Pin: Installed adjacent to the canopy jettison T-handle on the right vertical panel in the cockpit to prevent accidental jettisoning of the canopy. Canopy can also be jettisoned from D-handle and cable located one on each side of the fuselage behind access doors. 3. Canopy handles are for actuation of the locking mechanism only. Do not use the handle to lift canopy it may cause damage to the idler crank splines and cause on out-of-rig condition. Canopy must be closed and locked in winds over 60 knots. Snow must be removed prior to opening. Inspect canopy sills and dorsal deck for foreign objects prior to closing canopy. 4. Oxygen in its liquid form has a temp of -297. Do not touch implements containing LOX or wear clothing not specified in the NA13-1-6.4. 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 LOX system. Many materials will burn violently when saturated with LOX. 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. Do not let LOX come in contact with petroleum products. |
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What safety precautions must be observed during:
1. Flight Control Check 2. Landing Gear Operational Check |
1. Do not perform procedure with aircraft armed. When movement of any controls or switches or the application of electrical power and/or hydraulic pressure would endnager personnel or equipment, a warning placard will be placed conspicuously on the aircraft.
2. Do not perform procedure with aircraft armed. When movement of any controls or switches or the application of electrical power and/or hydraulic pressure would endanger personnel or equipment, a warning placard will be placed conspicuously on the aircraft. Be sure areas around landing gears and landing gear doors are clear of personnel and equipment before operating landing gear system. |
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What special safety precautions apply to:
1. Fueling 2. Defueling |
1. Never fuel/defuel during aircraft maintenance.
2. Aircraft with suspected hot brakes shall not be refueled. 3. Make sure aircraft and fuel servicing equipment are grounded. 4. Make sure fire fighting equipment is available. 5. Inspect refueling nozzle locking device to make sure aircraft ground refuel/defuel receptacle is serviceable. 6. Make sure fueling/defueling is not done within 300 ft of ground radar equipment. 7. Make sure fueling/defueling is not done within 50 ft of other aircraft with engines operating. 8. Loose metal objects, such as knifes, keys, or other objects, which might produce sparks, should not be carried or worn. 9. Never fuel/defuel during electrical storms. 10. Do not carry matches or cigarette lighters. 11. All ordnance shall be safetied 12. Fuel pressure from servicing equipment shall not exceed 55 psi. 13. When defueling is done using a truck, a person will be stationed on top of truck to observe fuel level in truck. |
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Power Plant Systems:
1. Engines 2. Ignition 3. Lubrication 4. Main Fuel 5. Afterburner Fuel |
1. Consists of two J85-GE-21 afterburning turbojet engines to propel the aircraft thru the air. Both engines are mounted nearly parallel to each other, one on each side of the keel in the aft part of the fuselage.
2. Mounted on each engine consists of a start switch, ignition holding relay, ignition time-delay relay, ignition control relay, throttle ignition cutoff switch, throttle afterburner ignition switch, and mounted on the engine, a 115 volt ac ignition exciter, main ignition plug, and afterburner igniter plug. 3. Self contained oil system, consists of an oil reservoir, a combined lubrication and scavenge pump, a vent relief valve, a 40 micron filter with a bypass valve, and an oil cooler with a pressure controlled bypass valve. 4. Regulates the flow of fuel received from the aircraft fuel supply system and injects metered fuel into the fuel control, overspeed governor, fuel oil cooler, fuel pressurizing and drain valve, and main fuel manifold with 12 fuel nozzles. 5. Controls fuel introduced into the engine afterburner section for obtaining additional thrust. Also positions the variable exhaust nozzle power unit thru a mechanical linkage to regulate exhaust gas temperatures. Consists of an afterburner fuel pump, afterburner fuel control, after burner manifold drain valve, pilot fuel mainifold with 4 pilot spraybars, and main fuel manifold with 16 main spraybars. |
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Power Plant Systems:
1. T5 Amplifier System 2. Anti-icing 3. Engine Instrument 4. Throttle |
1. Prevents excessive exhaust gas temperature during military and afterburner operation. Consists of T5 amplifier, T5 motor, and T5 trimmer. EGT=Exhaust Gas Temperature.
2. Accomplished by directing heating 9th stage compressor bleed air to the stationary vanes, inlet guide vanes, and bullet-nose fairing to prevent ice from building up. Consists of an engine anit-ice control switch, caution light, solenoid controlled shutoff valve on each engine, air ducting, and manifold. 3. Provide visual indications of engine operating conditions. Consists of tachometers, exhaust gas temperature indicators, nozzle position indicators, fuel flow indicators, and oil pressure indicator. 4. The engines are controlled by a throttle quadrant in the cockpit with duel levers, one for each engine, thru a cable system, left and right engine bay quadrants, and a push-pull linkage system attached to the main fuel control on each engine. |
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Fuel Systems:
1. Fuel Storage 2. Internal Fuel Transfer 3. Fuel Pressurization and Vent |
1. Fuel is carried internally by three rubber-impregnated bladder - type, nylon fabric fuel tanks. The external fuel system consists of jetisonable 150 gallon and/or 260/275 gallon tanks, suspended from the fuselage centerline and/or wing pylongs.
2. A crossfeed valve is opened to direct fuel from one system to the other to balance fuel quantity. It also allows one system to provide fuel to either or both engines. 3. Provides out-venting of fuel tank air pressure during refueling and in-venting of air pressure during fuel usage and altitude changes. Consists of a common vent which is routed thru a manifold from the three internal fuel tanks to a vent outlet at the vertical stabilizer trailing edge. |
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Fuel Systems:
1. Refuel/Defuel 2. Fuel Quantity and Gauging |
1. Refueling through a single-point adapter on the lower left side of the fuselage at station 295, fills both internal and external fuel tanks. Refueling can be accomplished manually by servicing internal and external fuel tanks individually. The internal fuel system is defueled thru the strainer of either system, with the crossfeed valve open and boost pumps on. Adaption of a defueling hose to the drain valve facilitates removal of fuel. The strainers are on the lower side of the fuselage; the left is behind an access door on the left side at station 439, and the right is behind an access door on the right side at station 439. External tanks are defueled by transferring fuel to internal tanks then drained thru the strainers.
2. Includes 3 capacitance type fuel tank probes, a dual-pointer fuel quantity indicator, and a fuel & Oxygen switch. Each probe measures fuel quantity and is indicated ont he fuel quantity indicators in the right side of the instrument panel. |
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What safety precautions must be observed during engine ground turnup.
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1. Ensure all ground safety pins and chocks are installed.
2. Stay beyond the contours of the engine inlet danger areas when engine is operating. 3. Do not approach engine exhaust area when engine is operating. 4. Maintenance personnel shall wear ear protection equipment when operating the gas turbine engine generator set and/or jet engines. 5. Ensure inlet safety screens are installed on operating engines. 6. Do not stand in line with compressor or turbine are when engine is operating above idle rpm. 7. When using ground interphone during engine run, secure interphone cord to sidebrace of right main landing gear strut to preclude interphone cord being ingested into the engine. |
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Avionics/Electrical System
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Electrical power is supplied by 2 ac systems and 1 dc system. An external receptacle is provided for ac power input to the aircraft when the engines are not in operation. DC power is supplied by a battery and 2 33 ampere transformer-rectifiers.
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Avionics/Electrical System
1. Communication a) Ultra-high frequency (UHF) |
Aircraft are equipped with either the AN/ARC-150 or AN/ARC-164 UHF radio. They provide two-way voice communication at line-of-sight range. 20 UHF frequencies may be preset and selected. Frequency range is 225.00 to 399.975 megahertz.
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Avionics/Electrical System
1. Communication b) Intercommunication and Audio system (IAS) |
Provides headset amplification for the UHF radio, the radio-navigation systems, flaps and landing gear audio warning signals, the AIM-9 missile tones, cockpit-to-ground crew, and cockpit-to-cockpit communications.
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Avionics/Electrical System
2. Navigation a) Tactical Air Navigation (TACAN) |
Aircraft are equipped with either the AN/ARN-65, AN/ARN-84, or AN/ARN-118 TACAN systems. The system provides bearing, range (DME), and course information to a TACAN ground (or airborne) station.
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Avionics/Electrical System
2. Navigation b) Attitude Reference Indicator (ARI) |
Is gyro-stabilized to show aircraft pitch and roll attitude.
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Avionics/Electrical System
3. Instrument Landing System (ILS) |
Provides visual indications of glideslope and localizer course. The system operates on odd decimal frequencies from 108.10 to 111.95 megahertz.
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Avionics/Electrical System
4. Tactical Mission Identification Friend or Foe (IFF) |
Provides automatic identification function for the aircraft. The system receives challenging signals and determines the correct code and mode of challenge, and automatically transmits a coded reply. The system operates in modes 1, 2, and 3a, which are selective identification feature (SIF) modes and in mode C, altitude reporting mode. Mode 4 which is a crypto mode, is available when the mode 4 computer is installed.
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Avionics/Electrical Systems
5. Exterior Lighting a) Position b) Rotating Beacon c) Landing/Taxi d) Formation |
a) Consists of primary position lights one on the side of each engine inlet duct, four auxiliary position lights, one on the upper and lower surface of each wing, and two white tail position lights, one on each side of the verticle stabilizer.
b) Red rotating anti-collision beacon in the vertical stabilizer c) Two white landing-taxi lights, one on underside of each engine inlet ducts, are electrically controlled, two position, retractable high and low intensity lights. d) Consists of two white lights, one on each side of dorsal behind the cockpit, and a light on the aft end of each wing tip, launcher (right side is green, left side is red). |
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Pitot Static System
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Measures impact and static air pressure surrounding the aircraft and supplies both to the airspeed-mach indicator and the CADC.
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Central Air Data Computer (CADC)
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Converts raw air data inputs into computed outputs.
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Inertial Navigation System (INS)
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The INS is a self-contained, nonemitting inertial navigation and attitude/heading reference system consisting of an inertial navigation unit, an inertial navigation unit adapter, and a cockpit control-indicator (CI), placarded NAV CONTROL. The inertial navigation unit is a gyro-stabilized sensing accelerometer, which senses, measures, and integrates the accelerations of the aircraft and applies them to present position to maintain a continuously updated store of position and navigation data, which can be monitored. The unit continuously tracks changes to magnetic azimuth and variation through and interface with a precomputed database. The system also computes true course and bearing information (measured from true north) to provide a capability for accurate navigation in latitudes where magnetic variations are excessive (above approximately 70 degrees north and below 70 degrees south). The INS provides attitude, heading, and navigation reference, computation and guidance for maneuvering flight and enroute navigation. INS is installed in the F5N modesl only.
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Armament System
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Consists of two 20-millimeter M-39A3 guns, installed high in the nose section. Bombs rockets, and milliles are externally carried, delivered, and launched from pylon and wingtip positions.
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Fire Control System
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Accomplishes target detection acquisition, and range tracking, lead computation for guns, arming and in-range envelope computation for missiles, and provides a roll stabilized, manually depressible aiming reference for the use of guns, bombs, and rockets against ground targets.
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Fire Control Radar
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The AN/APQ-153 is a light-weight, X-band, air-to-air search and range-tracking fire control radar. The AN/APQ-159(V)3 is a multimode, forward-looking, x-band, air-to-air search and range-tracking fire control radar.
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Lead Computing Optical Sight (LCOS)
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Consists of an optical display unit, and a gyro lead computer. The LCOS provides three modes of operation: air-to-air missile, air-to-air guns, and manual. Performs in-range envelope computations.
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Radar Warning Receiver
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The radar warning system acquires, processes, and identifies emissions from those frequency ranges where the vast majority of radar systems used for military purposes is operated. Looking at the equipment design of the radar warning system, we distinguish here between a Low band and a High band range; the High band range again is subdivided into four subbands.
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Countermeasures Dispensing System
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The AN/ALE-40(v)CDS provides the capability of dispensing flare or chaff payloads as a means of defense against hostile radar or IR missile attack. If a combination of flare and chaff is loaded, the system is capable of dispensing independently both as determined by the cockpit controls and programmer.
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How do the components work together to achieve the system's function
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A fire control system accomplishes target detection, acquisition, and range tracking, and targeting. The three pylon stations and two wingtip positions carry, deliver and launch bombs, rockets, and missiles.
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State and discuss your command's mission statement.
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The mission of the command is to provide the highest quality adversary training to the men and women who, as fleet naval aviators, are the instruments of national will and policy.
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Discuss the role of the F5 E/F aircraft.
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Is to provide a dissimilar aircraft to fly. It is cheaper to operate. And it has a quicker turnaround between flights. Only 3 units: VFC 13, VFC 111, and marines in yuma.
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Discuss the following primary warfare mission areas:
1. TopGun 2. Reserve Air Group (RAG) 3. Airwing Support Operations 4. Strike Fighter Advanced Readiness Program (SFARP) |
1. is an elite group of pilots that go thru training to improve their dog-fighting skills.
2. also referred to as FRS (Fleet Replacement Squadron). The training squadrons that train new pilots to replace the ones that retire or end their service. 3. comes in before deployment we play adversaries. 4. F18 is strike fighter F18's, come to town to hone their skills as a squadron before deployment. |
