Vocabulary Flashcards for King Air 350 Quick Ref Study Guide

Flashcards for King Air 350 Quick Reference Study Guide, focusing on vocabulary.

King Air 350 Airframe

All-metal, low-wing, mono-plane. Cantilevered wings, T-tail empennage. Fuselage is a conventional monocoque structure using high strength aluminum alloys.

NASA Winglets

Decrease wingtip vortices and increase aspect ratio, improving fuel performance and efficiency.

Strakes (Ventral Fins)

On the underside of the empennage, allow flight up to FL190 without the use of YD. Without, YD is required above 5,000ft.

Diagram shaft, Four inspection ports, Two hook engagement inspection openings

Visual confirmation that the Airstair Door is properly latched closed.

Electrical System

System is completely a 28 volt DC system, powered by two 28 volt, 300 amp starter/generators (connected in parallel).

Generator Control Unit (GCU)

Maintains a constant voltage to the respective Gen Bus during variations in engine speed and electrical load requirements. Limits generator’s output to 400 amps or less during cross-generator engine starts. Closes both Gen Bus Ties when it’s generators output voltage is within 0.5 volts of aircraft bus voltage. Won't close both Gen Bus Ties if generator fails.

L DC GEN and R DC GEN annunciators

Illuminates when the respective generators are offline (either fails or is turned OFF).

Bus Tie System

Protects the Electrical system from excessively high current flow in the event of a short in the system.

BUS SENSE switch - RESET

Used to reset (close) the Ties when they have been opened either manually or as a result of load shedding.

BUS SENSE switch - TEST

Used to test the HED’s ability to protect the Electrical system.

GEN TIES switch – MAN CLOSE

Closes both Gen Ties when the Electrical system is on Battery power only, allowing the Battery to power both Gen Buses through the Center Bus.

Hall Effect Device (HED)

Solid-state devices that sense current flow in one direction, providing protection from shorts in either Gen Bus.

Load Shedding

Electrical system automatically removes excess loads (both Gen Buses), when the power source is reduced to Battery only. All other Buses will remain energized.

Warning Annunciator

System faults that require immediate attention and reaction of the pilot, triggers both MASTER WARNING to flash and may be accompanied by an aural warning.

Caution Annunciator

System faults that only require immediate attention of the pilot, triggers both MASTER CAUTION to flash.

Advisory Annunciator

Confirms that an operation initiated by the pilot did occur as required.

Status Annunciator

Indicates functional situation which do not demand the immediate attention of the pilot. They can be normal or abnormal and may or may not have been initiated by the pilot.

Fuel System

Each engine has it’s own independent and isolated fuel system, with crossfeed capability during single engine operations.

Jet Transfer Pump

Transfers fuel from the auxiliary fuel tank to the nacelle tank, powered by motive flow from pressure supplied by the Engine-Driven Boost Pump or Electrical Standby Boost Pump

Flow Control Units

Provides regulated engine bleed air for the ECS and Pressurization systems.

Air-to-air Heat Exchangers

Are used to cool environmental air from the electronic Flow Control Units to mixing plenum.

Fuel Manifold Purge

Consists of a small air tank that is pressurized with unregulated (P3) engine bleed air.

Power Plant

2 Pratt and Whitney PT6A-60A reverse flow, free-turbine turboprop engine driving a four-bladed McCauley propellers.

Module 1: Power Turbine

First stage of the engine that consumes 40% of the exhaust gas energy and drives a reduction gearbox through planetary gearing.

Module 2: Gas Generator (N1)

Second stage of the engine that exhausts through a turbine section to create gases that blow over the power turbine through a reduction gearbox.

Compressor Bleed Valve

Compensates for this excess airflow by bleeding off axial stage air to reduce back pressure on the axial stages and prevents compressor stalls.

Low Pitch Stop Solenoids

The purpose of having a Ground Idle propeller pitch angle is to increase drag after landing thereby aiding in aircraft deceleration.

Load Shedding

Electrical system will automatically remove excess loads (both Gen Buses), when the power source is reduced to Battery only. All other Buses will remain energized

Auxiliary Fuel Transfer Motive Flow System

Fuel is transferred from the auxiliary tank to the nacelle tank through a jet transfer pump located in the sump of the auxiliary tank.

L NO FUEL XFR or R NO FUEL XFR indication

If the motive Flow Pressure Switch senses insufficient pressure and the float switch senses that the tank is not empty

Power Plant

2 Pratt and Whitney PT6A-60A reverse flow, free-turbine turboprop engine driving a four-bladed McCauley propellers

MODULE 1: POWER TURBINE

Two stages, consumes 40% of the exhaust gas energy. Power Turbine reduction ratio (power turbine shaft to propeller): 17.6 to 1.

MODULE 2: GAS GENERATOR (N1)

Consists of a (three-stage axial/single-stage centrifugal) compressor section and a (single-stage) turbine section

Compressor Bleed Valve

At low N1 rpm, the compressor axial stages produce more compressed air than the centrifugal stage can use.

Igniters

The combustion chamber has two spark-type igniters to provide positive ignition during engine start and for auto-ignition.

Lubrication

Dual purpose: 1. Cool and lubricate engine bearings. 2. Provide oil for the prop governors and prop reversing controls

Magnetic Chip Detector

Located in the bottom of the front accessory drive of each engine. Activates the respective L CHIP DETECT or R CHIP DETECT annunciator

Engine Fuel System

Increases or decreases fuel flow to the engine to maintain selected engine operating speeds.