AIRCRAFT FLIGHT
MANUAL
BRISTELL B23
Document No.: ADXC-73-001-AFM
Non-approved page
Revision: A2
7-3
Date of Issue: 15.04.2021
The wing leading edges feature stall strips to provide benign stall
characteristics. Stall strips are symmetric in spanwise extension, but not
symmetric in placement along the cross section.
7.2.2
Fuselage
The fuselage all-aluminium structure design is formed by bulkheads,
stiffeners and surface sheets. The fuselage consists of the front part
(between firewall and bulkhead aft of the rear windows) and the rear part
(aft of the beforehand mentioned bulkhead).
Cockpit with carbon/aramid composite seats is located in the front part of
the fuselage. The luggage compartment (capacity max 15 kg) is located
behind the seats.
The centre section of the wing is an integral part of the fuselage and
contains the main spar attachments and the rear spar attachments. Main
landing gear attachment points are located behind the main spar.
Top engine mount attachment points are located on the cross channel
(transversal beam) behind the firewall. Bottom attachment points are
located on the cockpit floor and connected with reinforcement channels
under the floor.
The cockpit further consists of a composite structure canopy frame with
an integrated back-rest for pilot and co-pilot.
The rear part of the fuselage has an elliptic cross section. The fin with
rudder attachments and stabilizer attachments is an integral part of the
fuselage. The last two bulkheads form the stabilizer attachment points.
A tail skid is located on the bottom aft fuselage. It is made from
composite material.
