202: Propulsion System
References:
(a) NAVAIR 01-85ADC-2-8, Maintenance Instructions Organizational, Power Plants and Related Systems, Navy Model EA-6B Aircraft
(b) NAVAIR 01-85ADC-2-9, Maintenance Instructions Organizational, Fuel and In-Flight Refueling Systems, Navy Model EA-6B Aircraft
(c) NAVAIR 01-85ADC-2-1, Organizational Maintenance, General Information and Servicing, Navy Model EA-6B Aircraft
(d) NAVAIR 01-85ADC-1, NATOPS Flight Manual, Navy Model EA-6B
202.1 SYSTEM COMPONENTS AND COMPONENT PARTS
Referring to a standard print of this system or the actual equipment, identify the following system components and component parts and discuss the designated items for each.
202.1.1 Engines:
A. Starter - Turns engine over during starting; center front accessory drive pad on generator.
B. Fuel Control - Lightweight, hydromechanical, high capacity, fuel flow metering unit that permits selection of a desired engine thrust level and provides automatic compension through the full range of thrust for existing ambient operating conditions; located on the left rear pad of the accessory gear box.
C. Power level control quadrant - Provides control of the engine throughout the range of operation and automatically sequences ignition and fuel during the starting cycle; located forward cockpit on pilots left hand console.
D. Engine oil system - Supplies oil under pressure to lubricate the main bearings, the engine and accessory drive; located in the main gear box.
E. Fire overtemperature detection system - Provides cockpit indication of a fire or overtemperature or either engine compartment, aft equipment bay or nosewheel well.
F. Engine indicating system:
(1) Oil Pressure Indicator - Receives a signal from the engine mounted oil pressure transmitter indicating operating pressures; located on pilots instrument panel lower left hand side.
(2) Fuel Flow Indicator - Receives a signal from engine mounted fuel flow transmitter and displays it in PPH (Pounds Per Hour); located on pilots instrument panel right hand side.
(3) Engine speed (rpm) indicator - Tachometer generator sends a signal to cockpit mounted indicator and is read in percentages; located on pilots instrument panel left hand side.
(4) Exhaust Gas Temperature (EGT) indicator - 6 thermocouples mounted on the exhaust case sense the temperature and send it to cockpit mounted gauge; located on pilots instrument panel left hand side.
202.1.2 Fuel System:
A. Forward fuel cell - Self sealing type, capacity of 392 gallons (2,666 lbs) of fuel. Contains the following , dual seat shutoff valve, piot valve (non-modulating), transfer and dump pump, two fuel quantity probes, float vent valve, acceleration check valve, catapult check valve (inertia) and a catapult vent check valve; located behind ECMO 2 and 3 seats and directly under TB #1.
B. Mid fuel cell - Bladder type cell with a 256 gallon (1741 lbs) capacity of fuel, contains a pilot valve, two fuel quantity units and catapult vent check valve; located directly behind forward fuel cell.
C. Aft fuel cell - Self sealing type having a capacity of 643 gallons (4372 lbs) of fuel. Contains a dual seat shutoff valve, pilot valve, transfer and dump pump, fuel booster pump, defueling check valve, two fuel probes, forward baffle check valve, aft baffle check valves. Located directly behind the mid fuel cell under TB #3.
D. Wing tanks - Structurally integral tanks. There is two outboard wing tanks and one inboard wing tank; located outboard and inboard wings.
E. AERO-1D drop tank - Drop tanks are installed on wing and fuselage stations to provide an extra source of fuel; located on any of the 5 station pylons.
202.2 PRINCIPLES OF OPERATION - None to be discussed
202.3 PARAMETERS/OPERATING LIMITS
202.3.1 State the maximum limit as the apply to:
A. Attempted engine starts:
(1) 1 minute on and 1 minute off (2) 1 minute on and 1 minute off (3) 1 minute on and 30 minutes off
B. AERO-1D drop tank capacity - 295 gallons
C. Internal fuel tank capacity:
(1) Wings (977 gallons) (2) Main Bags (1291 gallons)
202.4 SYSTEM INTERFACE
202.4.1 How does the engine bleed air interface with the engine starting?
A. Either engine can be started with the other engines bleed air by cross bleeding.
202.5 SAFETY PRECAUTIONS
202.5.1 What safety precautions must be observed during engine ground turn-up?
A. Personnel shall stay clear of danger areas such as intakes, exhaust and rotation line of starter and engine turbine blades, ear protection shall be worn in the area of engine operation.
202.5.2 What special safety precautions apply to :
A. Fueling - During hot pumps do not fuel aircraft outboard wings with wings folded due to fire hazard. Aircraft needs to be grounded and flight line fire extinguishing agent present. Personnel need to wear proper personnel protective equipment. No radio or radar activity within 100 feet of aircraft.
B. Defueling - Ensure that aircraft is properly grounded and all personnel are wearing the proper personnel protective equipment. No radio activity within 100 feet and no radar activity within 300 feet.
wattsx3@naswhidbey.net
AZ2(AW) Will Watts
DSN: 820-2307 Comm: 360-257-2307
flygal46@yahoo.com
or, AZ1(AW/NAC) Kimberly Herring DSN: 739-7800 ext 212
Comm: 817-782-7800 ext 212