Airframes Flashcards
Block III EA-18G AIRFRAMES FUNDAMENTALS
State the purpose of the Hydraulic Fluid Contamination Analysis
This contaminate measurement method aids in determining fluid containment level, ensuring high level of fluid purity on Class 5 aircraft and class 3 GSE.
State the purpose of a tactical paint scheme
Lessen the probability of visual and photographic detection.
State the two publications for the EA-18G
- NAVAIR 01-1A-509
- NAVAIR A1-F18EF-IETM
NAVAIR 01-1A-509
Provides information on materials and procedures to prevent, control, and repair corrosion damage to aircraft and avionics on land or on sea.
NAVAIR A1-F18EF-IETM
Provides information to support the diagnostics, maintenance and repair of the EA-18G and F/A-19E/F aircraft systems.
State the three modes of wheel brake operation
Normal
Emergency
Parking
Discuss the purpose of the composite airframes materials
To limit weight, increase strength and decrease effect of corrosion attack.
Temporary Repair
Repairs that are simple and practical as possible, normally restores full load carrying capabilities allowing aircraft to be flown until permanent repair can be made.
One Time Flight
Repair made to restore limited load carrying requirements to allow an aircraft to be flown to a repair station for permanent repairs.
Permanent Repair
Repair meets or exceeds strength of original structure or component with no adverse affects on structural integrity, fatigue life, safety or flying characteristics.
Radome
Covers the radar and provides an electrically transparent window for transmission and reception of radar signals.
Forward Fuselage
From the end of the radome to the aft edge of panel 18; includes the windshield,
canopy,
cockpit,
leading edge extension, and
nose landing gear.
Center Fuselage
From fwd edge of panel 26 to aft edge of panel 55L/R; includes
main landing gear,
intake ducts,
external stores stations,
fuselage fuel tanks and
AMAD.
Aft Fuselage
From panel 62L/R to the exhaust nozzles; includes the
engine,
speed brake,
vertical stabilizers,
horizontal stabilators, and
arresting hook.
Wings
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 pylons for weapons/stores.
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.
Ailerons
In flight commanded asymmetrically to produce roll motion; during takeoff/landing (with flaps switch set to half or full) they deflect symmetrically with the trailing edge flaps up to 45 degrees, trailing edge flap down to change lift. Located on the outboard trailing edge of each wing
Leading Edge Flaps
During takeoff/landing the leading edge flaps deflect symmetrically to change lift, in flight deflect asymmetrically to aid ailerons in producing roll motion. Located on the inboard and outboard edge of each wing
Trailing Edge Flaps
During takeoff/landing the leading edge flaps deflect symmetrically to change lift. In flight they independently deflect asymmetrically to aid the ailerons in producing roll motion. Located on the trailing edge of each wing
Stabilators
Deflect symmetrically to produce pitch motion and asymmetrically to produce roll motion also provides pitch compensation during selection of the lex spoilers. Located on either side of the tail of the aircraft
Rudders
Toe –in to increase lift and improve stability (AOA less than 8 degrees) toe-out to improve stability (AOA more than 8 degrees), in flight commanded symmetrically to produce yaw.
LEX Spoiler
Provide speed brake when commanded by pilot at airspeeds less then Mach 1.5, provides a high nose down pitch movement when transitioning from a high AOA with an aggressive nose down maneuver, left/right of door 22 L/R door 610 L/R.
Hydraulic System 1 (HS1)
Provides hydraulic fluid pressure to the primary flight controls either as a primary or backup source. System contains pump manifold, pump reservoir, filter unit, case drain filter, oil fuel heat exchange, and related indicator.
Hydraulic System 2 (HS2)
Provides hydraulic fluid pressure to the primary flight controls either as a primary or backup source, also supplies pressure to all other non-flight control system.
Auxiliary Power Unit (APU) Accumulator
Gas charge cylinder provides required fluid pressure to the APU start motor and emergency hydraulic systems.
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.
Nose Landing Gear (NLG)
Provides landing/takeoff and taxi energy absorption as well as tire/runway compliance. Located on the underside of the forward fuselage
Main Landing Gear (MLG)
Absorbs the energy from ground loads during landing/taxi operations and provides a stable platform for aircraft carrier and shore-base operations. Located underside of center fuselage
Wheel Brakes
Provides modulated individual wheel-controlled braking combined with an anti-skid system to prevent wheel skid. Located MLG
Launch Bar
Provides a means of steering an aircraft during carrier deck tracking engages the catapult applying catapult tow forces to the aircraft. Located fwd side of NLG strut.
Arresting Hook
Engages an arrestment cable on the carrier deck to stop the aircraft, also provides a means of stopping the aircraft where normal runway landings are not available. Located on the underside of the aft fuselage
Briefly discuss the basic operation of the Electronic 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.
Discuss 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 APU and emergency brake accumulators. It 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.
