Allstar PZL Glider SZD-54-2 Perkoz Technical specifications

Doc No. 542.4.01
Issue II April 2014
corrected
Allstar PZL Glider
Sp. z o.o.
FLIGHT MANUAL
for a sailplane
Model: SZD-54-2 „Perkoz”
Serial No.:
Registration:
THIS FLIGHT MANUAL IS A DIRECT TRANSLATION FROM THE EASA APPROVED POLISH
VERSION
TRANSLATION OF THIS DOCUMENT AND CONVERSION OF TECHNICAL DATA HAVE BEEN
DONE BY BEST KNOWLEDGE AND JUDGMENT
IN ANY CASE OF DISCREPANCIES IN TRANSLATION THE POLISH VERSION SHOULD BE USED
THIS SAILPLANE IS TO BE OPERATED IN COMPLIANCE WITH INFORMATION AND LIMITATIONS
CONTAINED HEREIN.THIS DOCUMENT SHOULD BE ALWAYS STORED ON BOARD.

corrected
Note to English version, Issue II ‒ April 2014, corrected:
By the way of the Revision No. 2 implementation, the whole Flight Manual
in English was checked and corrected in order to eliminate mistakes found and to be
in line with Polish version. The corrections are not indicated to achieve compatibility
with Polish version, however all pages are marked with “corrected” in the footer to
distinguish them from previous not corrected editions. Therefore this edition of the
Flight Manual replaces the previous one as a whole.
Intentionally left blank

SZD-54-2
„Perkoz”
FLIGHT MANUAL
SECTION 0.
ISSUANCES
Issue II April 2014
Revision
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
page 0.1
corrected
SECTION 0.
ISSUANCES
0.
0.1. Record of revisions................................................................................... 0.2
0.2. List of effective pages............................................................................... 0.4
0.3. Table of contents...................................................................................... 0.5
0.4. Table of figures ........................................................................................ 0.6

SECTION 0.
ISSUANCES
FLIGHT MANUAL
SZD-54-2
„Perkoz”
page 0.2
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
Issue II April 2014
Revision No. 2 May 2017
corrected
0.1. Record of revisions
Any revision of the present Manual, except actual weighing data, must be
recorded in the following table and endorsed by the Agency (EASA).
The new or amended text in the revised page will be indicated by a black
vertical line in the outer margin and the Revision No. The number and date of the last
revision will be shown in the footer of the page.
With every revision implementation, the pages affected with this revision and
listed in the following table must be replaced.
Rev.
No.
Affected
Section
Affected Pages
Date of
Issue
No. and Date of
Approval
Insertion
Date & Signature
1
0
4
0.2, 0.4
4.2, 4.4, 4.5
July
2015
10056004
14.12.2015
Valid for serial number
542.A.15.010 and next as
well as for previous S/N
with a change implement-
ed acc. to am. Approval
2
0
1
2
3
4
5
6
7
0.2, 0.4
1.4
2.2, 2.3, 2.4, 2.5,
2.6, 2.8, 2.9, 2.10
3.5
4.14, 4.15, 4.17
5.5
6.3, 6.8, 6.9
7.4, 7.8, 7.10,
7.11, 7.12, 7.13
May
2017
10062739
10062741
26.07.2017

SZD-54-2
„Perkoz”
FLIGHT MANUAL
SECTION 0.
ISSUANCES
Issue II April 2014
Revision
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
page 0.3
corrected
Rev.
No.
Affected
Section
Affected Pages
Date of
Issue
No. and Date of
Approval
Insertion
Date & Signature

SECTION 0.
ISSUANCES
FLIGHT MANUAL
SZD-54-2
„Perkoz”
page 0.4
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
Issue II April 2014
Revision No. 2 May 2017
corrected
0.2. List of effective pages
Section
Page
Date of Issue
Section
Page
Date of Issue
0
0.1
April 2014
4
4.17
May 2017
2
2
0.2
May 2017
4.18
April 2014
0.3
April 2014
2
0.4
May 2017
5
5.1
April 2014
0.5
April 2014
5.2
April 2014
0.6
April 2014
5.3
April 2014
5.4
April 2014
1
1.1
April 2014
5.5
May 2017
2
1.2
April 2014
5.6
April 2014
1.3
April 2014
5.7
April 2014
2
1.4
May 2017
5.8
April 2014
1.5
April 2014
1.6
April 2014
6
6.1
April 2014
6.2
April 2014
2
2.1
April 2014
6.3
May 2017
2
2
2.2
May 2017
6.4
April 2014
2
2.3
May 2017
6.5
April 2014
2
2.4
May 2017
6.6
April 2014
2
2.5
May 2017
6.7
April 2014
2
2.6
May 2017
6.8
May 2017
2
2.7
April 2014
6.9
May 2017
2
2
2.8
May 2017
6.10
April 2014
2
2.9
May 2017
2
2.10
May 2017
7
7.1
April 2014
7.2
April 2014
3
3.1
April 2014
7.3
April 2014
3.2
April 2014
7.4
May 2017
2
3.3
April 2014
7.5
April 2014
3.4
April 2014
7.6
April 2014
2
3.5
May 2017
7.7
April 2014
3.6
April 2014
7.8
May 2017
2
7.9
April 2014
4
4.1
April 2014
7.10
May 2017
2
1
4.2
July 2015
7.11
May 2017
2
4.3
April 2014
7.12
May 2017
2
1
4.4
July 2015
7.13
May 2017
2
1
4.5
July 2015
7.14
April 2014
4.6
April 2014
4.7
April 2014
8
8.1
April 2014
4.8
April 2014
8.2
April 2014
4.9
April 2014
8.3
April 2014
4.10
April 2014
8.4
April 2014
4.11
April 2014
4.12
April 2014
9
9.1
April 2014
4.13
April 2014
9.2
April 2014
2
4.14
May 2017
9.3
April 2014
2
4.15
May 2017
9.4
April 2014
4.16
April 2014
List of pages for Supplements is enclosed in page 9.3

SZD-54-2
„Perkoz”
FLIGHT MANUAL
SECTION 0.
ISSUANCES
Issue II April 2014
Revision
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
page 0.5
corrected
0.3. Table of contents
SECTION 0. ISSUANCES
SECTION 1. GENERAL
SECTION 2. LIMITATIONS
SECTION 3. EMERGENCY PROCEDURES
SECTION 4. NORMAL PROCEDURES
SECTION 5. PERFORMANCE
SECTION 6. MASS AND BALANCE
SECTION 7. SAILPLANE AND SYSTEMS DESCRIPTION
SECTION 8. SAILPLANE HANDLING, CARE AND MAINTENANCE
SECTION 9. SUPPLEMENTS

SECTION 0.
ISSUANCES
FLIGHT MANUAL
SZD-54-2
„Perkoz”
page 0.6
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
Issue II April 2014
Revision
corrected
0.4. Table of figures
Fig. 1-1. 3-view drawing.......................................................................................... 1.5
Fig. 2-1 Airspeed indicator colour marking.............................................................. 2.3
Fig. 4-1. Wings rigging............................................................................................ 4.5
Fig. 4-2. Assembling winglets or plane wingtips ..................................................... 4.6
Fig. 4-3. Assembling long wingtips ......................................................................... 4.8
Fig. 4-4. Detail A of the wing –long wingtip connection.......................................... 4.9
Fig. 4-5. Detail B of the wing –long wingtip connection.......................................... 4.9
Fig. 4-6. Horizontal tailplane assembling.............................................................. 4.11
Fig. 5-1. AIS calibration –normal flight................................................................... 5.3
Fig. 5-2. AIS calibration –inverted flight ................................................................. 5.4
Fig. 5-3. Speed polar without winglet...................................................................... 5.6
Fig. 5-4. Speed polar with winglet........................................................................... 5.7
Fig. 5-5. Speed polar with long wingtips (65,62 ft wing span)................................. 5.8
Fig. 6-1. CG range limits for a sailplane without pilots............................................ 6.3
Fig. 6-2. Scheme to sailplane CG calculation......................................................... 6.5
Fig. 6-3. Table of individual loading plan with sample values ................................. 6.8
Fig. 6-4. Sample of individual loading plan table..................................................... 6.9
Fig. 7-1. Cockpit equipment and controls................................................................ 7.3
Fig. 7-2. Instrument panel at front seat................................................................... 7.6
Fig. 7-3. Instrument panel at rear seat.................................................................... 7.6
Fig. 7-4. Scheme of electric installation .................................................................. 7.8

SZD-54-2
„Perkoz”
FLIGHT MANUAL
SECTION 1.
GENERAL
Issue II April 2014
Revision
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
page 1.1
corrected
SECTION 1.
GENERAL
1.
1.1. Introduction .............................................................................................. 1.2
1.2. Certification basis..................................................................................... 1.2
1.3. Warnings, cautions and notes.................................................................. 1.2
1.4. Description and technical data................................................................. 1.3
1.5. Three-view drawing.................................................................................. 1.5

SECTION 1.
GENERAL
FLIGHT MANUAL
SZD-54-2
„Perkoz”
page 1.2
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
Issue II April 2014
Revision
corrected
1.1. Introduction
The flight manual has been developed to provide pilots and instructors with
information for the safe and efficient operation of the SZD-54-2 "Perkoz” sailplane.
This manual includes primarily the material required to be furnished to the pilot
by Certification Specifications CS–22 Subpart G. It also contains supplemental data
supplied by the sailplane producer.
1.2. Certification basis
The SZD-54-2 „Perkoz” sailplane model has been approved by European
Aviation Safety Agency (EASA) in accordance with CS–22, Amendment 2 of 5 March
2009, and has gained Type Certificate No. EASA.A.574.
Category of Airworthiness:
U - Utility
A - Aerobatic
1.3. Warnings, cautions and notes
The warnings, cautions and notes used in the Flight Manual are defined as
follows:
WARNING : means that the non-observation of the corresponding procedure
leads to an immediate or considerable degradation of the flight
safety.
CAUTION : means that the non-observation of the corresponding procedure
leads to a minor or to a more or less long term degradation of the
flight safety.
NOTE : draws the attention on any special item not directly related to
safety but which is important or unusual.

SZD-54-2
„Perkoz”
FLIGHT MANUAL
SECTION 1.
GENERAL
Issue II April 2014
Revision
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
page 1.3
corrected
1.4. Description and technical data
SZD-54-2 „Perkoz” is a two-seat sailplane for primary schooling and training,
including basic and advanced aerobatics and cloud flying in the scope allowed by
operation rules.
The sailplane is made of composite: primary structure in glass-epoxy, with
some components (exchangeable wingtips, canopy frame, rudder) in carbon-epoxy.
Monocoque structure fuselage, integral with fin. The cockpit with tandem seats
arrangement equipped with one-piece canopy, side-opening to the right. Emergency
jettison mechanism located on canopy frame, on the right hand side. The canopy
equipped with “Röger hook”.
Seated pilot attitude in a cockpit. Fixed back rest at front seat with no
regulation. Seat pan of rear seat adjustable on ground (vertical position and distance
from pedals). Pedals at front seat adjustable in-flight, pedals at rear seat –fixed. At
both seats additional back cushions are provided, not fastened to back rest, to
enhance comfort for short pilots. Both seats equipped with 5-point safety harness,
plus optional second set of lap belts.
Monorail, fixed landing gear. Main wheel equipped with shock absorber and
hydraulic brake. Nose and tail wheels non-cushioned, without brakes.
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.
Two-plate airbrakes protruding from wing top surface only. Ailerons of 20 %
wing chord ratio, sandwich structure. Long wing tips ailerons with constant chord.
Tail unit in conventional arrangement, with horizontal tailplane shifted slightly
to the rear. Stabilizer and fin of sandwich structure. Elevator of sandwich structure,
mass balanced. Composite carbon-epoxy rudder with horn type balance –
aerodynamic and mass. In a fin an antenna for radio transceiver is provided.
Instrument panels located at front and rear seat, the latter –optional. Efficient
cockpit venting is ensured by nose air intake with adjustable dumper, and by side
windows with deflectable ventilation tabs.
Control systems for elevator, ailerons and airbrakes –pushrod type. Rudder
control system mixed: cable/pushrod. Longitudinal trim control –spring type. Tow
release control –cable type. Wheel brake operated with Bowden cable.

SECTION 1.
GENERAL
FLIGHT MANUAL
SZD-54-2
„Perkoz”
page 1.4
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
Issue II April 2014
Revision No. 2 May 2017
corrected
BASIC TECHNICAL DATA:
Span
57,42
65,62
[ft]
Length
27,69
[ft]
Height (fin with tail wheel)
6,73
[ft]
Wing aerofoil
NN8
Root chord
4,27
[ft]
Mean standard chord (MSC)
38,976
37,756
[in]
Wing area
176,10
186,22
[ft2]
Aspect ratio
18,70
23,135
Tailplane span
11,15
[ft]
Sailplane empty mass
(new sailplane with minimum equipment)
827 + 22
838 + 22
[lb]
Maximum in-flight mass
Category „U”
1356
1356
[lb]
Category „A”
1301
----
[lb]
Maximum wing loading
7,70
7,28
[lb/ft2]
2

SZD-54-2
„Perkoz”
FLIGHT MANUAL
SECTION 1.
GENERAL
Issue II April 2014
Revision
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
page 1.5
corrected
1.5. Three-view drawing
Fig. 1-1. 3-view drawing

SECTION 1.
GENERAL
FLIGHT MANUAL
SZD-54-2
„Perkoz”
page 1.6
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
Issue II April 2014
Revision
corrected
Intentionally left blank

SZD-54-2
„Perkoz”
FLIGHT MANUAL
SECTION 2.
LIMITATIONS
Issue II April 2014
Revision
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
page 2.1
corrected
SECTION 2.
LIMITATIONS
2.
2.1. Introduction .............................................................................................. 2.2
2.2. Airspeed limitations................................................................................. 2.2
2.3. Airspeed indicator markings..................................................................... 2.3
2.4. Mass......................................................................................................... 2.4
2.5. Centre of gravity....................................................................................... 2.4
2.6. Approved manoeuvres............................................................................. 2.5
2.7. Manoeuvring load factors......................................................................... 2.6
2.7.1. Accelerometer markings................................................................... 2.6
2.8. Flight crew................................................................................................ 2.7
2.9. Kinds of operation .................................................................................... 2.8
2.10. Equipment................................................................................................ 2.8
2.11. Aero-tow and winch-launching................................................................. 2.9
2.11.1. Aero-tow........................................................................................... 2.9
2.11.2. Winch-launched take-off................................................................... 2.9
2.12. Other limitations ....................................................................................... 2.9
2.13. Limitation placards ................................................................................... 2.10

SECTION 2.
LIMITATIONS
FLIGHT MANUAL
SZD-54-2
„Perkoz”
page 2.2
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
Issue II April 2014
Revision No. 2 May 2017
corrected
2.1. Introduction
Section 2. includes operating limitations, instrument markings, and basic
placards necessary for safe operation of the sailplane, its standard systems and
standard equipment.
The limitations included in this section and in Section 9. are subject to
approval (by EASA).
2.2. Airspeed limitations
Airspeed limitations and their significance for sailplane operation are defined
as follows:
SPEED
kn (mph) IAS
Category:
REMARKS
U
A
VNE
Never exceed speed
132
(152)
145
(167)
Do not exceed this speed in any operation and
do not use more than 1/3 of control deflection.
VRA
Rough air speed
90
(103)
105
(121)
Do not exceed this speed except in smooth air,
and then only with caution.
Examples of rough air are lee-wave rotors,
thunderclouds etc.
VA
Manoeuvring speed
90
(103)
105
(121)
Do not make full or abrupt control movement
above this speed, because under certain
conditions the sailplane may be overstressed by
full control movement.
VT
Maximum aero-towing
speed
89
(102)
89
(102)
Do not exceed this speed during aero-towing
VW
Maximum winch-
launching speed
78
(89)
78
(89)
Do not exceed this speed during winch-
launching
In the following table the allowed VNE values for various flight altitudes are
given:
Flight altitude
[1000 ft]
0 9,8
13,1
16,4
19,7
23,0
26,2
29,5
32,8
U
VNE IAS kn (mph)
132
(152)
125
(144)
119
(137)
112
(129)
106
(122)
100
(115)
94
(109)
89
(102)
A
VNE IAS kn (mph)
145
(167)
138
(158)
131
(150)
124
(142)
117
(135)
110
(127)
104
(120)
98
(113)
2
2

SZD-54-2
„Perkoz”
FLIGHT MANUAL
SECTION 2.
LIMITATIONS
Issue II April 2014
Revision No. 2 May 2017
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
page 2.3
corrected
2.3. Airspeed indicator markings
Airspeed indicator markings and their colour-code significance are shown below:
Marking
IAS value or range
kn (mph)
Significance
GREEN arc
46 (53) ÷ 90 (103) - Cat. „U”
46 (53) ÷ 105 (121) - Cat. „A”
from 90 (103) dashed line
Normal operating range.
Lower limit is 1.1·VS1 at maximum
mass and most forward CG
upper limit is rough air speed.
YELLOW arc
90 (103) ÷ 132 (152)
to 145 (167) - dashed
Manoeuvres must be conducted with
caution and only in smooth air.
radial RED line
132 (152) Category „U”
145 (167) Category „A”
Maximum speed for all operations
for the given sailplane Category.
YELLOW triangle
57 (65)
Approach speed at maximum mass
VS1 = sailplane stalling speed at given mass, with airbrakes retracted.
Fig. 2-1 Airspeed indicator colour marking
2
2

SECTION 2.
LIMITATIONS
FLIGHT MANUAL
SZD-54-2
„Perkoz”
page 2.4
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
Issue II April 2014
Revision No. 2 May 2017
corrected
2.4. Mass
[lb]
Maximum take-off mass:
Category Utility (U)
1356
Category Aerobatic (A)
1301
Cat. U
57,42 ft
959
Maximum mass of non-lifting parts (with pilots)
65,62 ft
937
Cat. A
904
Maximum mass in baggage compartment:
44
(with battery and standard equipment tools)
2.5. Centre of gravity
Limits for centre of gravity range (in flight allowed) are defined as follows:
front limit 10,16 in aft of Datum
(22,0% MSC –57,42 ft and 21,6% MSC –65,62 ft),
rear limit 19,49 in aft of Datum
(46,0% MSC –57,42 ft and 46,4% MSC –65,62 ft),
"MSC" stands for Mean Standard Chord
NOTE: Size and position of MSC are different for short and long wingtips.
Datum is the plane perpendicular to wing root aerofoil chords plane, passing
through points on leading edge of root aerofoils.
Method of CG position calculation is given in the item 6.3. Limits of CG
position for sailplane without pilots are given in the item 6.2.
NOTE:
Observation of all limitations relating to sailplane load plan, as well
as these relating to CG range limits of sailplane without pilots,
ensures to maintain the sailplane CG within the range allowed for
flight.
2
2

SZD-54-2
„Perkoz”
FLIGHT MANUAL
SECTION 2.
LIMITATIONS
Issue II April 2014
Revision No. 2 May 2017
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
page 2.5
corrected
2.6. Approved manoeuvres
SZD-54-2 „Perkoz” sailplane is approved for operation in Utility (U) and
Aerobatic (A) Categories.
WARNING:
Performing aerobatic manoeuvres approved for Category A
is allowed on the sailplane equipped with short plane wingtips only
(without winglets)
In Aerobatic (A) Category total mass limited to 1301 lb sailplane is approved
to perform the following manoeuvres (and derivative thereof):
spin
inverted spin
loop
inverted loop
stall turn
inverted stall turn
Immelman turn
lazy eight
slow roll
barrel roll
half roll half loop
controlled half roll half loop
climbing turn
tail slide
Cuban eight
inverted Cuban eight
eight
steep turn
flick roll
inverted flick roll
flick roll downward
inverted flick roll downward
flick roll in downward angle
inverted flick roll in downward angle
In Utility (U) Category total mass limited to 1356 lb sailplane is approved to
perform the following manoeuvres:
loop
stall turn
spin
climbing turn
lazy eight
steep turn
The recommended entry speed for particular manoeuvres is given in Section 4.
(item 4.6.9.).
2
2

SECTION 2.
LIMITATIONS
FLIGHT MANUAL
SZD-54-2
„Perkoz”
page 2.6
Allstar PZL Glider Sp. z o.o.
Doc No. 542.4.01
Issue II April 2014
Revision No. 2 May 2017
corrected
2.7. Manoeuvring load factors
The allowed manoeuvring load factors are:
Aerobatic Category:
up to VNE = 145 kn (167 mph)
allowable positive load factor
+ 7,0
allowable negative load factor
- 5,0
Utility Category:
up to VA= 90 kn
(103 mph)
up to VNE = 132 kn
(152 mph)
allowable positive load factor
+ 5,3
+ 4,0
allowable negative load factor
- 2,65
- 1,5
NOTE :
The above data refer to configuration with airbrakes retracted.
With airbrakes protruded, the maximum limit manoeuvring load factors are:
positive +3,5, negative -1,5 –over the whole range of operation speed.
2.7.1. Accelerometer markings
Marking
Value
Significance
Red line
+ 7,0
- 5,0
Allowable manoeuvring load factors
for Aerobatic Category sailplane
2
2