Technical Interview - Type specific questions

Question 1

What are the dimensions of the wing?

Answer 1

Span: 93’6”
Height: 25’5”
Length: 96’5”
Min turning circle diameter: 112’ based on 80 degree nose wheel deflec

Question 2

Describe the G550 engine

Answer 2

BMW / RR Engine
Model BR-710
Takeoff thrust 15,385 lb/fr
Takeoff thrust to weight ratio is .338

Question 3

G550 BOW

Answer 3

48,300 lbs empty

Question 4

Maximum payload?

Answer 4

6,200 lbs at BOW empty 48,300 lbs

Question 5

Max fuel capacity verses max usable fuel capacity?

Answer 5

Max fuel cap is 41,700 lbs

Max usable fuel capacity is 41,300 lbs or 20,650 in each tank

Question 6

Flight control gust lock does what?

Answer 6

The gust lock will prevent flight control movement during wind speeds up to 60knots.

If gust lock is engaged, a mechanical interlock within the cockpit pedestal prevents advancing the power levers more than 6 % forward of ground idle.

Question 7

What does the fuel system comprised of?

Answer 7

Fuel system consists of 2 wing fuel tanks, a series of pumps and lines to supply fuel to the APU and engines, and indicators to monitor the airplane fuel status.

Question 8

What does the fuel hopper do and where is it located?

Answer 8

The fuel hopper is located at the wing root and is the lowest point of the fuel tank.

Fuel hopper can contain 190 gallons or 1283 lbs.

The fuel hopper also houses a heat exchanger to cool hydraulic fluid.
The right hopper cools the left hydraulic SYS and vice versa.

Question 9

Describe the hydraulic system on the G550?

Answer 9

The G550 has 2 independent hydraulic systems, L / R, each powered by an engine driven pump installed on the respective Engine that pressurizes fluid in dedicated reservoirs.

These pumps operate as long as the engine are not shut down with the cockpit fire pull handles.

Question 10

What is unique about the L Hydraulic system?

Answer 10

The fluid from the L side is pressurized by 2 sources other than the engine driven pump.
1 the electric driven AUX Pump
2. The PTU driven by the R hydraulic side

Question 11

What are the components of the Left Hydraulic system?

Answer 11

Engine driven Hydraulic Pump
Aux Pump
PTU
Fluid lines, Reservoir, Gage's
HMG
Systems displays

Question 12

What aircraft systems do the L HYD SYS power?

Answer 12

Landing gear
Brakes
Nose wheel stearing
Flaps 
Ground and flight spoilers
Yaw Damp 1 and Rudder
Elevators and ailerons

Question 13

What is the HMG?

Answer 13

The HMG is a piston motor that uses left hydraulic pressure to rotate a generator shaft at 8,000 rpm to produce AC alternating current.

Question 14

What is a limit on the ICE Detection system and why?

Answer 14

Automatic anti-icing is not available below 1500 ‘ because full engine capacity is reserved for takeoff and landing.

It is not available above 35,000’ since moisture content is low, and it will dedicate all energy to pressurization of aircraft. If you want it then you must manually turn it on.

Question 15

What are the primary flight controls of the G550?

Answer 15

Elevator for pitch
Rudder for yaw
Aileron for roll

Question 16

What are the secondary flight controls for the G550?

Answer 16

Wing flaps… to enhance lift
Flight and Ground Spoilers…to reduce wing lift and add overall drag
Movable Horizontal Stabilizer…aligns the elevator with a/c AOA.
Yaw Damper…uses the autopilot rudder servo to moderate a/c heading oscillation.

Question 17

What safety features does the flight controls system include?

Answer 17

Stick shaker warning
Stick pusher stall prevention actuator.
Gust Lock

Question 18

Describe the Fire Protection in General

Answer 18

Fire protection system has sensors to detect excess heat levels associated with fire in the APU, a/c interior, and smoke detectors.

Question 19

What sub-sections are there in the fire protection system?

Answer 19

Engine and APU Fire and Overheat Detection and Warning

Engine and APU Fire Extinguishers

Aircraft interior Overheat and smoke detectors, Smoke evacuation and portable and Fixed Fire Extinguishers.

Question 20

Describe the primary AC Electrical Power System

Answer 20

It has 3 IDGs, one on each engine high speed fan, and one on the APU.

Produces 3 phase 115/200V AC at 400 HZ

Question 21

What are the IDGs rated at?

Answer 21

Rated at 40 Kva

Question 22

What happens if no AC power can be generated?

Answer 22

An emergency inverter powered by DC from the aircraft batteries thru the L and R ESS DC bus can supply single phase to operate equipment on the ESS AC Bus.

Question 23

Describe the DC Electrical Power System?

Answer 23

Direct current is obtained by transforming and rectifying aircraft AC power into DC power.

5 TRUs powered by the a/c AC Buses will produce DC power at 28 volts

Question 24

What happens if all AC power on the a/c is lost?

Answer 24

The TRUs will be inoperative and DC power for essential flight functions is provided by he 2 a/c batteries.

Question 25

What battery does the G 550 have?

Answer 25

NICAD batteries rated at 53 amps / hour and supply 24 volts of DC power.

The aircraft batteries are normally used for starting the APU or for powering the ground service bus.

Question 26

Describe the G550 wing?

Answer 26

The wings are swept back 27 degrees and are cantilevered with a 3 degree dihedral.