SZD-54-2
„Perkoz”
TECHNICAL SERVICE MANUAL
SECTION 1.
DESCRIPTION AND
TECHNICAL DATA
Issue II
April 2014
Revision
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.02
page 1.1
corrected
SECTION 1.
DESCRIPTION AND TECHNICAL DATA
1.1. Sailplane description
SZD-54-
2 „Perkoz” is a two-seat sailplane made of composite: primary
structure in glass-epoxy, with some components (exchangeable wingtips, canopy
frame, rudder) in carbon-epoxy, designed according to certification specifications
CS-22.
Two-panel wings of tapered outline with exchangeable wingtips: plane type
(Category U and A), winglets (Category U only) or long with winglets (increasing wing
span to 65,62 ft, Category U only). NN-8 laminar aerofoil. Sandwich skin composite-
foam-composite. Wing spar flanges of glass roving reinforced composite. Spar roots
joined together with horizontal main bolt.
Wing ailerons of 20% chord ratio, sandwich structure, mounted on five hinges,
driven by single input. Long wingtip ailerons with constant chord, sandwich structure,
mounted on two hinges and additionally supported on aileron clutch.
Two-plate airbrakes protruding from wing top surface only. Panels equipped
with adjustable laminate cover straps, tightened with springs.
Connection of aileron and airbrake control systems is done automatically when
wings are mounted to the fuselage.
Monocoque structure fuselage, integral with fin. Central part comprises a
frame with formers (main front former, rear upper and lower former), upper ceiling
and luggage boot floor.
Tail unit in conventional arrangement, with horizontal tailplane shifted slightly
to the rear. Stabilizer and fin of sandwich structure. Elevator of sandwich structure,
mounted on six hinges, driven by single input, mass balanced. Composite carbon-
epoxy rudder with horn type balance
– aerodynamic and mass.
Connection of elevator control system is done automatically by sliding elevator
lever slit over a roller on a lever mounted in the fuselage. System is equipped with
spring type longitudinal trim control (trimmer).
Monorail, fixed landing gear. Shock-absorbed main wheel (
350×135 mm)
equipped with hydraulic brake. Nose (
255×110 mm) and tail (
200×50 mm)
wheels non-cushioned, without brakes.
The cockpit with tandem seats arrangement equipped with one-piece canopy,
side-opening to the right. Rotary hinges situated on RH cockpit board. Mounted to
fittings laminated to fuselage shell. Emergency jettison mechanism located on
canopy frame, on the right hand side. The canopy equipped with “Röger hook”.
