AIRCRAFT FLIGHT
MANUAL
BRISTELL B23
Document No.: ADXC-73-001-AFM
Non-approved page
Revision: A2
7-2
Date of Issue: 15.04.2021
7.1
Introduction
This section provides description and operation of the aeroplane and its
systems. Refer to Section 9, Supplements, for details of optional systems
and equipment.
7.2
Airframe
The main airframe of Bristell B 23 aircraft is an aluminium metal riveted
structure.
7.2.1
Wing
The wing is an all-metal structure with 2 spars. The centre section of the
wing is an integrated part of the fuselage. The outer part of the wing
consists of nine ribs and has trapezoid shape. There are 3 main
attachments (positioned on the main spar) and one rear attachment
(positioned on the rear spar) where outer wing is joined with the centre
section.
Fuel tanks are installed in front of the main spar on the inner third of the
outer wing.
Winglets are produced from fibreglass and are riveted on the end of the
wing skin. Position lights and anti-collision beacons are installed on the
winglets.
Both ailerons and flaps are all-aluminium structures. They consist of skin
and ribs (and spar-flaps) riveted together. Ailerons are suspended on the
rear spar of the wing using piano hinges. Flaps are suspended on the
rear spar on three hinges.
The aileron control pushrods are led between the spars. The aileron trim
tab is installed on the left aileron. The trim tab actuator is installed inside
of left aileron.
There is one common flap control actuator which is installed in the
fuselage between the seats and beneath the glove box. It actuates a
central torsion tube to transmit the force to the flap actuation lever
located at the flap inboard root.
Wings are equipped with wing lockers placed between the second and
the third rib aft of the main spar. Capacity of each wing locker is 20 kg.
Access doors are suspended on two hinges. They can be locked with a
latch.
Wing locker drain holes shall be inspected regularly to avoid unnoticed
accumulation of water.