SPYDER ENGINES

What type of engines does the C-5 have? (1.2.1)

GE CF6 (CF6-80C2-L1F)

How much thrust does the CF6 engine produce? (1.2.1.1)

51,250 lbs up to 35°C (above 35°C thrust decreases with temperature)

(BLANK) is used to measure thrust (1.2.1.1)

Fan rotor speed (N1)

The fan section supplies (BLANK) of the total engine thrust? (1.2.1.2)

80%

The Low Pressure Compressor (LPC) includes a Variable Bleed Valve (VBV) system that does what? (1.2.1.2)

Improve compressor performance and prevent compressor stalls

The core section provides (BLANK) of the engine thrust and drives the accessories mounted on the Accessory Gearbox (AGB). (1.2.1.2)

20%

The High Pressure Compressor (HPC) includes the Variable Stator Vanes (VSV) system that does what? (1.2.1.2)

Optimze compressor performances and prevent compressor stalls

The annular combustor has (BLANK) fuel nozzles and (BLANK) igniters. (1.2.1.2)

30; 2

The EEC uses (BLANK)as the thrust-setting parameter. (1.2.2.1)

Fan speed (N1)

The EEC calculates five reference fan speeds for the appropriate engine rating and based upon ambient conditions, these five speeds include: (1.2.2.1) (p1-29)

Idle

Maximum takeoff (MTO)

Maximum climb (MCL)

Maximum continuous thrust (MCT)

Maximum reverse

A commanded fan speed is derived by interpolation from the (BLANK) input and the five reference fan speeds. (1.2.2.1)

Throttle Resolver Angle (TRA)

(BLANK) IDLE is a higher idle setting, commanded by the VIA, that is used to accelerate the engine to take off thrust in 8 seconds to satisfy go-around thrust requirements. (1.2.2.1) (p1-29)

Approach

The approach idle parameters are met when the airplane is in air mode and pressure altitude is less than 25,000 feet and either of the following conditions are true: (1.2.2.1) (p1-29)

The left or right flaps indicate greater than 25 degrees

The nose gear down and locked

The AFCS ILS approach mode is selected to ON

Once approach idle is set, the system will reset when the ground/flight status indicates ground and either: (1.2.2.1) (p1-29)

Two reversers are commanded to deploy

The left hand or right hand ground spoiler limit switch indicates extend

The airplane ground speed is less than 60 knots

When in BIP, the engines will default to (BLANK) idle and will enter ALT mode. (1.2.2.1) (p1-29)

Approach

The (BLANK) provides the primary power for the EEC. (1.2.2.2) (p1-30)

Permanent Magnet Alternator (PMA)

During engine start, the ignition exciter box continues to deliver energy until the engine reaches a self sustaining RPM of approximately (BLANK)%. (1.2.2.5) (p1-33)

54

On the ground, the engine start system can only be energized below (BLANK)% N2. (1.2.2.6) (p1-33)

20

For in-flight starting, the engine start system can be energized below (BLANK)% N2 to supplement a windmilling engine if required. (1.2.2.6) (p1-33)

30

Any number of 5-minute start cycles are allowed. A (BLANK)minute minimum cooling period is required after the first two 5-minute cycles and a (BLANK)minute cooling period for each subsequent 5-minute cycle. (1.2.2.6) (p 1-33)

2; 10

When the EEC is in the start mode, a (BLANK) box is centered on the respective engine instrument suite. (1.2.3.3) (p 1-37)

White

When the actual N1 exceeds (BLANK) value with one engine on the ground or with all engines in flight, the engine status timer is shown. (1.2.3.3) (p 1-38)

Maximum Continuous Thrust (MCT)

While in flight, if one engine fails or is shut down after one (or more) of the timers has started counting down from (BLANK) minutes, the remaining time on the operating engine timers will increment by (BLANK) minutes up to a total time of (BLANK) minutes at takeoff power. (1.2.3.3) (p1-38)

4:55; 4:55; 9:55

ENG 1 (2, 3, OR 4) OIL PRESS LO CWA means that engine oil pressure is less than (BLANK)psi for more than 30 seconds. (1.2.3.6) (p1-43)

10

Each engine is equipped with a (BLANK) actuated Thrust Reverser (TR) system installed in the fan duct that reverses fan exhaust only. (1.2.4) (p 1-44)

Pneumatically

Maximum reverse thrust that is equal to approximately (BLANK) % of total forward thrust. (1.2.4) (p 1-44)

60

The inboard TRs may be deployed in-flight but are limited to (BLANK) thrust only. (1.2.4) (p 1-44)

Reverse idle

Once commanded, if the TR is not stowed within (BLANK)seconds the EEC cancels the stow command and generates an ENG 1 (2, 3, or 4) TR FAIL STOW CWA. (1.2.4) (p 1-46)

15

The fire extinguishing system incorporates (BLANK) spherical nitrogen pressurized extinguisher bottles in each engine pylon, connected to a common discharge manifold allowing (BLANK) discharges per engine. (1.3.2) (p 1-67)

Two; two

What does pulling an engine fire handle do? (1.3.2.1) (p 1-68)

Mechanically close fuel supply into nacelle by closing fuel valve on forward wing beam

Electrically closing Hydro Mechanical Unit HPSOV (fuel) and turning off ignition (This DOES shut down the engine)

Signals VIA which sends fire handle status to EEC (but does not shut down engine)

Hydraulic fluid shut off to engine pumps, closes valve on forward wing beam and depressurizes pumps

Isolates IDG

Compressor bleed air shut off by electrically closing the pylon bleed valve

Exposes fire extinguisher button

The APU is controlled by a (BLANK) which maintains steady state speed at 100 percent RPM under all load conditions. (1.4.2.1) (p 1-72)

Full Authority Digital Electronic Control (FADEC)

What are the indications of an ATM fire? (1.4.2.5) (p 1-73)

Same as an APU fire. Fire light in the associated APU fire handle and if on the ground, an audible warning horn

After a failed engine start, what conditions require the engine to be motored? For how long? (2.10) (p 2-105)

If an engine start is discontinued for any reason after placing the Start Switch to START, motoring must be accomplished if fuel flow was observed and the engine did not reach N2 idle.

Once the N2 RPM has dropped below 20 percent, rotate the Start switch to the MOTOR position and hold for 30 seconds.

Engine shutdown may be accomplished 1 minute after completion of the landing roll, provided that the final approach was normal with an EGT less than (BLANK)C. (2.40) (p 2-222)

650

Engine shutdown may be accomplished 1 minute after completion of the landing roll, provided that reverse thrust operation was normal with an EGT less than (BLANK)C, or reverse thrust was not selected. (2.40) (p 2-222)

750

Should the engine temperature limits for engine shutdown be exceeded, operate at or near idle for (BLANK) minutes to thermally stabilize the engine hot section. Taxi power is considered idle for this purpose. (2.40) (p 2-222)

3

Explain takeoff procedure with a loss of an engine after VGO. (3.12, 3.12.1, 3.12.2) (p 3-54)

Ensure throttles are at the planned takeoff thrust setting as a minimum, but they may be advanced to MTO if a MCL takeoff was planned

When not operating in TOGA, the autothrottles are limited to MCL unless using VNAV; as a result, the autothrottles may need to be disengaged to achieve power levels above MCL

Climbout and acceleration with one or more engines inoperative should be accomplished at MTO until expiration of the N1 Engine Status Timer and then at MCT until final level-off altitude is attained.

If engine fails at or above VMCO, continue climbing at the indicated airspeed existing when the engine failed.

Minimum control speed is based on a bank angle of 5 degrees away from the failed engine

Do not retract the landing gear before the airplane is definitely airborne and a positive rate of climb is shown

Bank angles of up to 30 degrees are allowed but climb rate is reduced by approximately 200 fpm.

WARNING: If the gear is not fully retracted 28 seconds after initial liftoff, actual climb profile of the airplane will be lower than the computed profile.

Three-engine range will be reduced by approx. (BLANK)% if a thrust reverser is left deployed on an inoperative engine. (3.21) (p3-63)

15

What is minimum oil pressure? (pg 5-2, Figure 5-1, Sheet 1 of 4)

10 psi

During the Engine Shutdown Checklist, the Engine Start Switches should be placed to STOP immediately after the flight engineer opens all fuel isolation valves to prevent (BLANK). (1SS-41, p2)

engine flameout

During the Engine Shutdown Checklist, if an engine flameout occurs after the lfight engineer opens all fuel isolation valve but before the Engine Start Switch is placed to the STOP position, (BLANK) may result if the EEC attempts a restart. (1SS-41, p2)

engine damage