Mahindra GIPPSAERO GA8-TC 320 - General Description

C01-01-08 5 Feb 2009 Page 1-5
Section 1
Model GA8-TC 320 General
1.2. GENERAL DESCRIPTION
1.2.1. Aircraft
The GA8-TC 320 aircraft is a strut braced, high wing, xed tricycle landing gear, single engine,
eight seat cabin aircraft that has been designed primarily for passenger and utility operations.
The fuselage is an all alloy stressed skin construction and is fully corrosion protected. The
oor of the passenger cabin is provided with a quick release system to allow rapid conversion
from freight to passenger or combi congurations. The engine cowlings are manufactured from
composite materials and feature large, easily removable access panels.
The cockpit is designed to accommodate the pilot in command on the left side and all controls,
instruments, selectors and switches are located so as to be within easy reach of the occupant
of that seat. A second set of ight controls and instruments are tted to the right side front seat
position. The centrally located control pedestal, radio stack and overhead switch panel are
accessible from either of the two cockpit seats. The cockpit is accessed by forward hinging
doors that are located on each side. The main cabin is provided with a large sliding door on the
left side at the rear of the fuselage.
The wings are of all metal stressed skin construction with full corrosion protection, and are
braced on each side by a single streamlined bracing strut. A single integral fuel tank is located
in each wing between the fuselage and the strut. The ailerons and wing aps are of metal
construction and operate in a conventional sense.
The empennage is also all metal stressed skin construction and is fully corrosion protected.
A variable incidence stabiliser is incorporated to provide a wide trim range with maximum
aerodynamic efciency. The vertical surfaces feature a half span rudder which is located on the
lower portion of the n.
1.2.2. Engine
The engine is a six cylinder, horizontally opposed, air cooled, turbo-charged fuel injected
Lycoming TIO-540-AH1A with a Maximum Continuous (MCP) power rating of 300 BHP at
38 in Hg manifold pressure at 2500 RPM. The engine also has an Alternate Take-Off Power
rating (ATOP) of 40 in Hg manifold pressure at 2500 RPM. Operations at ATOP are limited to a
maximum of 5000 foot pressure altitude. Above this altitude take-off power is limited to 38 in Hg
manifold pressure.
NOTE:
For engine power data refer to Lycoming curve No. 13525-A of the Lycoming
Operator’s Manual Part No. 60297-23A at latest revision.