Beechcraft King Air 300/350 Pilot Training Manual - Aircraft Systems (Volume 2, copyright 2001)

This Volume 2 FlightSafety International pilot training manual (approx. 500-page PDF, P/N: FSI-BE300-VOL2) provides the definitive system architecture references for the Beechcraft King Air 300 and 350 turboprops (2001). Designed specifically for BE-300 type-rated operations, it documents essential airframe specifications, electrical power routing, and powerplant parameters. Before interacting with any high-voltage or pressurized systems detailed in this volume, verify all parameters against current, approved safety protocols to prevent equipment damage or personal injury.

Having this exact system architecture on hand provides a massive advantage for daily workshop life. Accurately tracing a fault through the triple-fed bus or identifying an environmental flow control unit issue using these references cuts out hours of troubleshooting trial-and-error, directly reducing aircraft downtime. While this document is not a heavy teardown manual, it does contain highly detailed procedures for the Ni-Cad Battery Condition Check, the Autofeather System Test, and the VIR-32 Navigation Receiver Self Test. Utilizing these exact functional sequences establishes a reliable maintenance foundation, saving aircraft owners costly trips to an outsourced aviation service facility.

Key technical contents include:

• 57 detailed electrical system schematics
• 17 system chapter breakdowns focusing on aircraft configuration
• 2 extensive load management tables

Crucial avionics and powerplant features explored:

• Uncovering advanced PT6A-60A turboprop engine operational logic
• Tracing multi-bus electrical distribution networks effectively
• Understanding Hartzell four-blade reversing propeller governing principles
• Examining sophisticated environmental flow control units
• Isolating pneumatic surface and brake deice mechanisms
• Outlining autofeather and synchrophaser system operations

Specific aircraft assemblies detailed:

• Collins Pro Line II avionics integration
• EFIS-85B electronic flight instrument system configurations
• Auxiliary Power Unit (APU) parameters
• Master warning system annunciator circuits
• Fuel transfer motive flow network
• Fire protection and extinguishing lines

System Coverage Overview

Technical descriptions focus entirely on internal systems organized for structural familiarization. Major chapters break down the electrical power networks, master warning systems, fuel management, and powerplant operation. The manual dives deep. It outlines fire protection, pneumatic systems, ice and rain protection, air conditioning, and pressurization. You will also find comprehensive overviews of the hydraulic, landing gear, and braking systems, alongside avionics configurations and flight controls. Included within the mechanical and electrical sections are vital Wiring diagrams and concrete visual references, such as the Fuel System Schematic Diagram, Power Distribution Schematics, Brake System Schematic, Air-to-Air Heat Exchanger Diagram, and the Surface Deice System Diagram.

Specification and Reference Data

Performance tables compare FAR certification requirements while documenting specific system loads for both the 300 and 350 variants. The electrical power section is highly specific. It documents bus architecture, detailing the center bus, the triple-fed bus, and the exact distribution differences between the two configurations. Expect hard numbers. The text details starter and generator limits of 300 amperes alongside voltage regulation at 28.25 VDC. Battery charge monitor thresholds and bus tie protection settings are clearly defined at 275 amperes. This structure emphasizes system identification and normal operation logic without serving as a step-by-step diagnostic or repair guide.

When isolating King Air 300/350 electrical anomalies, technicians often misdiagnose bus tie failures by overlooking the directional Hall Effect sensors; a tripped sensor requires a specific manual reset sequence via the BUS SENSE switch to avoid an unnecessary component replacement. Furthermore, uncommanded autofeather system disarming is frequently chased through the fuel control unit, whereas the root cause is typically a failing torque transmitter sending erroneous signals to the APC-65J computer. Grasping these exact component relationships prevents hours of wasted labor during a grounded aircraft situation.