Sportine Aviacija LAK-17A mini Sailplane Technical specifications

This Manual should always be kept on board of the sailplane
Joint Stock Company "SPORTINĖ AVIACIJA ir Ko"
Pociūnų km., Ašminto en., LT-59327, Prienai, Republic of Lithuania
tel.: [phone] ● fax:[phone] ● e-mail: [email protected] ● www.lak.lt
FLIGHT MANUAL
LAK-17A mini Sailplane
I ue No. 1
Type: LAK-17
Model: LAK-17A
Variant: LAK-17A mini
Serial Number: _______________
Regi tration: _______________
Date of I ue: _______________
Page identified by “Appr.” are approved by the European Aviation Safety Agency.
Original date of approval: 01 July 2021
EASA TCDS No. EASA.A.083, I ue 08
Thi ailplane i to be operated in compliance with the regulatory information and
limitation contained herein.

LAK-17A mini Flight Manual
Chapter 0
0.1 Record of revisions
Any revi ion of the pre ent manual, except actual weighing data, mu t be recorded
in the following table and in the ca e of approved Chapter , endor ed by the
re pon ible airworthine authority.
The new or amended text in the revi ed page will be indicated by a black vertical
line in the left hand margin, and the revi ion number and date will be hown on the
bottom left hand of the page.
Rev.
No.
Affected
Chapter
Affected
Page
Date of I ue Approval Date of
approval
Date of
In ertion
Signature
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0.2 List of effective pages
Chapter Page Date of I ue Chapter Page Date of I ue
0 i 02 Jul 2019 3 3-1 02 Jul 2019
ii 02 Jul 2019 3-2 02 Jul 2019
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iv 02 Jul 2019 3-4 02 Jul 2019
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Table of contents
Chapter
GE ERAL (a non-approved chapter).............................................................1
LIMITATIO S (an approved chapter)...........................................................2
EMERGE CY PROCEDURES (an approved chapter)...............................3
ORMAL PROCEDURES (an approved chapter)........................................4
PERFORMA CE (a partly approved chapter)..............................................5
WEIGHT A D BALA CE / EQUIPME T LIST
(a non-approved chapter)..................................................................................6
SAILPLA E A D SYSTEMS DESCRIPTIO
(a non-approved chapter)..................................................................................7
SAILPLA E HA DLI G, CARE A D MAI TE A CE
(a non-approved chapter)..................................................................................8
SUPPLEME TS (a non-approved chapter)...................................................9
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Chapter 1
GENERAL
Table of Contents
1.1 Introduction....................................................................................................1 - 2
1.2 Certification ba i ...........................................................................................1 - 2
1.3 Warning , caution and note .........................................................................1 - 2
1.4 De criptive data..............................................................................................1 - 3
1.5 Three-view drawing.......................................................................................1 - 5
1.6 Abbreviation ..................................................................................................1 - 6
1.7 Unit conver ion..............................................................................................1 - 6
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1.1 Introd ction
The ailplane flight manual ha been prepared to provide pilot and in tructor with
information for the afe and efficient operation of the LAK-17A mini ailplane.
Thi manual include the material required to be furni hed to the pilot by CS-22. It
al o contain upplemental data upplied by the ailplane manufacturer.
1.2 Certification basis
Thi type of ailplane ha been de igned in accordance with CS 22 Certification
Specification for Sailplane and Powered Sailplane , Amendment 2, 5 March
2009.
Category of Airworthine : Utility.
1.3 Warnings, ca tions and notes
The following definition apply to warning , caution and note u ed in the flight
manual:
Warning
Mean that the non-ob ervation of the corre ponding procedure
lead to an immediate or important degradation of the flight
afety.
Ca tion
Mean that the non-ob ervation of the corre ponding procedure
lead to a minor or to a more or le long term degradation of
the flight afety.
Note
Draw the attention on any pecial item not directly related to
afety by which i important or unu ual.
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1.4 Descriptive data
The LAK-17A mini i a modification of the ingle eat high performance ailplane
of FAI 15 m – 18 m cla LAK-17A de igned according to CS-22, category “U”
pecification . It i a mid-wing powered glider with flap , T-tail, retractable main
landing gear and 82 (optionally 134) liter [21.6 (optionally 35.4) US gal] water
balla t.
The ailplane i made of hybrid compo ite material (Kevlar, carbon and
fibergla ). The wing par i made of modern carbon rod (3.16 x 3.16 mm) and
ha a double T ection. The airbrake are located on the upper wing urface only.
The wing airfoil are de cribed in Table 1.4-1.
Table 1.4-1
[m] c [m] Airfoil
13.5 m
0.28 0.729 LAP 92-130/15mod
0.48 0.729 LAP 92-130/15
4.6 0.625 LAP 92-130/15
6.635 0.35 LAP 90-150/15
The cockpit i of monocoque con truction. The manually controlled eat back and
an adju table head re t together with optimally arranged control offer notable
comfort for the long flight . The one piece Plexigla canopy hinge forward. On
the left ide there i a liding window for additional ventilation. The in trument
panel fold up together with a canopy.
The retractable landing gear with hock ab orber ha a 4.00-4" 8 PLY To t Aero
tire. The BERINGER main wheel brake i actuated by the lever on control tick, or
via the airbrake control handle (optionally). The rudder pedal are adju table in
flight. All control , including the water balla t y tem, hook up automatically or
emi-automatically. Towing hook are mounted: near the main landing gear (C.G. /
winch / auto-tow hook) and/or in front of the pilot cockpit at the bulkhead (aero
tow hook). Both towing hook are operated by the ame handle. The wing
incorporate fork-type par tip , joined with two pin .
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The T-tail (fixed tabilizer with elevator) of the LAK-17A mini provide table and
re pon ive pitch characteri tic . The elevator hook up automatically during
a embly. The glider i fitted with a fin balla t tank of 8 ltr (2.11 US gal) capacity
in order to adju t the optimum C.G. po ition. The antenna i mounted in the
vertical fin.
Technical data of the LAK-17A mini ailplane i hown in Table 1.4-2.
Table 1.4-2
Wing pan 13.5 m (44.29 ft)
Fu elage length 6.53 m (21.42 ft)
Height 1.32 m (4.33 ft)
Max gro weight 350 kg (771.6 lb )
Mean aerodynamic chord 0.638 m (25.12 in)
Wing area 8.41 m2 (90.52 ft2)
Wing loading (minimum) 26.6 kg/m2 (5.45 lb /ft2)
Wing loading (maximum) 41.61 kg/m2 (8.52 lb /ft2)
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1.5 Three-view drawing
6530
1322
13500
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1.6 Abbreviations
CAS calibrated air peed mean indicated air peed of a ailplane, corrected
for po ition (due to po ition of pre ure port on ailplane) and
in trument error. Calibrated air peed i equal to true air peed in
tandard atmo phere at ea level
C.G. center of gravity
daN decanewton
h hour
IAS indicated air peed mean the peed of a ailplane a hown on it pitot
– tatic aircraft indicator and i uncorrected for the y tem error
m meter
kg kilogram
km kilometer
econd
ltr liter
1.7 Unit conversion
1 bar = 14.5 pound per quare inch (p i);
1 decanewton (daN) = 2.25 pound force;
1 kilogram (kg) = 2.2 pound (lb );
1 meter (m) = 39.4 inche (in.) = 3.28 feet (ft.);
1 millimeter (mm) = 0.0394 inche (in.);
1 liter = 0.2642 U.S. gal;
1 quare meter (m2 ) = 10.764 q. ft;
1 kg/m2 = 0.204 lb / q. ft;
1 m/ = 1.944 knot (kt );
1 km/h = 0.5396 kt ;
1 kW = 1.34 HP.
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Chapter 2
LIMITATIONS
Table of Contents
2.1 Introduction....................................................................................................2 - 2
2.2 Air peed..........................................................................................................2 - 2
2.3 Air peed indicator marking ...........................................................................2 - 3
2.4 Ma (weight).................................................................................................2 - 4
2.5 Center of gravity.............................................................................................2 - 5
2.6 Approved maneuver ......................................................................................2 - 5
2.7 Maneuvering load factor ...............................................................................2 - 5
2.8 Flight crew......................................................................................................2 - 5
2.9 Kind of operation..........................................................................................2 - 6
2.10 Minimum equipment....................................................................................2 - 6
2.11 Aero tow, winch and auto tow launching.....................................................2 - 6
2.12 Other limitation ...........................................................................................2 - 7
2.12.1 Cro wind ...........................................................................................2 - 7
2.12.2 Water balla t........................................................................................2 - 7
2.13 Limitation placard .......................................................................................2 - 7
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LAK-17A mini Flight Manual
2.1 Introd ction
Chapter 2 include operation limitation , in trument marking and placard
nece ary for afe operation of the LAK-17A mini powered ailplane, it motor,
tandard y tem and tandard equipment.
The limitation have been approved. Compliance with the e limitation i
mandatory.
2.2 Airspeed
Air peed limitation and their operational ignificance are hown in Table 2.2-1.
Table 2.2-1
Speed IAS [km/h / (kt )] Remark
13.5 m
VNE Never exceed peed Do not exceed thi peed
in any operation and do
not u e more than 1/3 of
control deflection at:
230 / (124)
220 / (119)
210 / (113)
195 / (105)
170 / (92)
0 – 4000 m (0 – 13100 ft)
up to 5000 m (16400 ft)
up to 6000 m (19680 ft)
up to 8000 m (26250 ft)
up to 10000 m (32800 ft)
VRA Rough air peed 170 / (92)
Do not exceed thi peed
except in mooth air and
then only with caution.
Rough air i in lee wave
rotor, thundercloud , etc.
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Speed IAS [km/h / (kt )] Remark
13.5 m
VAManeuvering peed 170 (92)
Do not make full or abrupt
control movement above
thi peed, becau e under
certain condition the
ailplane may be over
tre ed by full control
movement
VFE Maximum flap
extended peed.
Flap etting:
Do not exceed the e
peed with the given flap
etting
-1 up to 0
+1 up to L
230 / (124)
170 / (92)
VWMaximum winch
and auto-tow launch
peed
140 / (76)
Do not exceed thi peed
during winch or auto-tow-
launching
VTMaximum aero
towing peed 160 / (86) Do not exceed thi peed during aero towing
VLO Maximum landing
gear operation
peed
170 / (92)
Do not extend or retract
the landing gear above thi
peed
Warning At higher altitude the true air peed i higher than the indicated
air peed and VNE i reduced with altitude.
2.3 Airspeed indicator markings
Air peed indicator marking and their color code ignificance are hown in Table
2.3-1.
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Table 2.3-1
Marking IAS value or range
[km/h / (kt )] Significance
White arc 95...170 / (51...92)
Po itive Flap Operating Range:
lower limit i 1.1 VSO in landing
configuration at maximum weight.
Upper limit i maximum peed
permi ible with flap extended
po itive.
Green arc 100...170 / (54...92)
Normal Operating Range: lower
limit i 1.1 VS1 at maximum weight
and mo t forward C.G. with flap
neutral. Upper limit i rough air
peed.
Yellow arc 170...230 / (92...124) Maneuver mu t be conducted with
caution and only in mooth air.
Red line 230 / (124) Maximum peed for all operation
Yellow triangle 95 / (51) Approach peed at maximum
weight without water balla t
2.4 Mass (weight)
Maximum take-off ma of the LAK-17A mini i :
With water balla t 350 kg (771.6 lb )
Without water balla t 350 kg (771.6 lb )
Maximum landing ma 350 kg (771.6 lb )
Note When landing on a rough and hard urface alway dump all
water balla t before landing.
Maximum ma of all non-lifting part : 274 kg (604 lb );
Maximum ma in baggage area: 7 kg (15.4 lb ).
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Ca tion Heavy piece of baggage mu t be ecured to the baggage
compartment floor.
2.5 Center of gravity
Po ition of C.G. in flight:
front limit: 182 mm aft of wing root rib leading edge
rear limit: 305 mm aft of wing root rib leading edge
Warning The ailplane may be afely operated only when loaded in the
range defined in the Chapter 6 of thi manual.
2.6 Approved mane vers
Thi ailplane i certified for normal gliding in the "Utility" category according to
CS-22. Aerobatic maneuver are not permitted.
2.7 Mane vering load factors
Limit load factor are:
for VA = 170 km/h (92 kt ) air peed +5.3 / -2.65
for VNE = 230 km/h (124 kt ) air peed +4.0 / -1.5
for VNE = 230 km/h (124 kt ), air brake extended +3.5 / 0
for VF = 170 km/h (92 kt ), flap +1, +2, L +4 / 0
2.8 Flight crew
LAK-17A mini i a ingle eat glider. Load in a pilot eat mu t be a follow :
Max load in the eat: 110 kg (242 lb );
Min load in the eat: ee placard in cockpit and weighing report.
With the e load , the C.G. range given in 2.6 will be in the limit if the empty
glider weight and C.G. i in the limit ( ee empty center of gravity chart in Chapter
6).
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2.9 Kinds of operation
Flight mu t be conducted under Day / VFR condition .
Cloud flying i not permitted.
Aerobatic maneuver are not permitted.
2.10 Minim m eq ipment
A minimum equipment only the in trument and equipment pecified herein and
in the equipment li t ( ee Maintenance Manual Section 2) are admi ible:
•air peed indicator, cale 50...300 km/h (27...162 kt ), with range marking ( ee
ection 2.3);
•altimeter with altitude corrector and fine range pointer;
•four point ymmetrical eat harne ;
•power upply;
•out ide air temperature (OAT) gauge (if water balla t i carried);
•emergency locator tran mitter (ELT) (if required by national regulation );
•required placard , check li t and flight manual;
The minimum equipment mu t corre pond with national regulation .
2.11 Aero tow, winch and a to tow la nching
The maximum launch peed are:
Aero-tow: 160 km/h (86 kt );
Winch / auto-tow launch: 140 km/h (76 kt ).
For all of the above launching method a weak link of 500 daN (1100 lb ) mu t be
u ed in the launch cable or towrope.
For aero-tow, the length of the towrope mu t be at lea t 20 m (66 ft.).
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