ICA IS-28B2 Lark User manual

H.I.C.H. G.A.B.
INTREPRINDEREA de CONSTRUCT II AERONAUTICE
2200 BRA S 0 v
Casuta Postalia No. 118
ROM A N I A
FLIGHT AND MAINTENANCE MANUAL
IS 28 B2 GLIDER
This manual is applicable for gliders
with serial numbers beginning with 141
and for gliders with serial numbers up
to 140, to which the Modification Kit
No. I,was applied.
Seri~l '10. 117
ROMAINIAN VERSION
APPROVED BY DSA.
WITH NO. 1292.2/23.06.1978
3rd Issue - April 1978

FLIGHT AND MAINTENANCE MANUAL 15-2882
INPORTANT NOTICE
This manual includes instructions on using the 15-2882 glider, on periodic
inspections and maintenance. Information is structured into six chapters
as follows:
Chapter 1 - General
Ghapter 2 - limitations
Chapter 3 - Emergency Procedures
Chapter 4 - Normal Fl ight Procedures
Chapter 5 - Performances
Chapter 6 - Maintenance
Each chapter contains its own detailed table of contents
For ready identification, each page has t\t1O numbers. Thefirst designates
the chapter and the second denotes the page within the chapter.
The pilot nust kn~~ the contents of this manual. Additionally, the
manual must ',~ kept permanently within reach of the pilot during all
flight operations.
REVISING THE MANUAL
Revisions to this manual will be issued by the 0lider 82nufacturer whenever
necessary. Such revisions should, when received, be incorporated in the
manual as directed and the details recorded on the appropriate Revision Record
Card. The new or amended content of revised pages will be indicated by
black vertical lines in the left hand margin, adjacent to the relevent text.
The manual integrity can be checked by means of the mentioned record cards.
Page 61

\
FLIGHT AND MAINTENANCE MANUAL 15-2882
CHAPTER 1.
G ENE R A L
CONTENTS
1.1 Dimensions and Areas
1.1.1. General Dimens ions
1.1.2. Wing
1.1.3. Tails
1.1.4. Landing Gear
1.2 Cockpit Description
1.3 Abbreviations and Definitions
Drawings:
PAGE
Fig 1-1
Fig 1-2 Glider Drawing, 3views
Control Locations in the Front Seat
-==
The 15-2882 is a tandem two-seat gl ider, completely metallic, with T-elevator
and semi-retractable landing gear. It is provided with flaps and air brakes
(spoi1ers)4
1.1. DI MENS IONS and ARE!\S
~
-----_.----j
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.
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FIg. 1-1 Gil6ER DRAWING - Three views

\
1.1.1. GENERAL DIMENSIONS
Span ••••.••..••••••••••.•••.•.•.••••••••••.•••••••
Max imum Leng th .••.•.•...••••...••.•.•..•.••.••...•
Hax imum He i9 h t .
1.1.2 WING
Airfoil a. To 62% of semispan ..•••••••••••••.•••
b. Outer 38~ semi~pan •••.•.•...•.•••.•••
Area: 18.24m2
Dihedral: 2.5 degrees
AIR BRAKE
II
Type: Huter
location: Upper wing surface
AtlERON
Area: 2.56 m2
1.1.3. TAIL SURFACES
17 m
8.45m
1.87m
Wortmann Fx-61-165
Wortmann F -60-126
x
Horizontal: Stabil izer area:
Elevator area: 1.37 m2
1.36 m2 (incl trim tab)
Vertical:
1.1.4. LANDING GEAR
Fin area: 0.68 m2
Rudder area: 0.81 m2
Main, monowheel, semiretractable landing gear
Damping (shock absorber): Oleopneumatic
Wheel size: 500 x 5 (Press =2.5 atm)
Tailwheel : 200 x 50 (Press =2.5 atm)
Wheel Brake: Main wheel only
L.2. COCKPIT DESCRIPTION
The front cockpit is as shown in Fig 1-2
Both tandem seats are covered, by a plexiglass canopy, hinged on the right.
On the left side of the metal canopy frame (in front of each pilot) is the
close-open handle (red).
On the right side, symetrically opposite, is the canopy jettison handle (red).
On the canopy left side, in front of each pilot, is a sliding (clearview) wind~/.
Control Stick and rudder pedals are standard types. The front rudder pedals
are adjustable (fore &aft) by means of a knurled knob on the floor immediately
forward of the stick (rotation to the right brings pedals closer).
Flap control (black handle) and air brake (spoiler) control coupled to the
main wheel brake control (blue handle) are to the left of each seat.

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The flap has five settings: 0
---- +1
+2
+3
-1
00 deflection
+50
+100
+150
-50 (upward deflection)
Tri~ tab control is located on the left side, forward of the spoiler control.
Landing Gear Retraction control is on the right of both seats (forward =up).
Tow Release control (yellow T-handle) is located on the left side of the front
instrument panel, and on the left wall of the rear cockpit.
Ventillator control is on the upper central portion fa the front instrument panel.
Ballast Box is located on the floor just forward of the front Stick.
1.3 ABBREVIATIONS AND DEFINITIONS
OSTIV - Organization Scientifique et Technique Internationale du Vol aVoile
FAA - Federal Aviation Administration
IAS - Indicated Air Speed =Airspeed indicator reading with instrument
correction, but without correction of errors
from the speed measuring system.
CAS - Calibrated Air Speed =IAS +correction of static source system errors.
n - Load factor. Total lift referred to the glider weight.
CMA =HAC - Mean aerodynamic chord

CHAPTER 2
LIMITATIONS
Contents: Page
Certification
Speed Limitations
Airspeed Indicator markings
Load factors and limit weights
Maximum Weights
Balance
Permissible Maneuvers
Special Instructions
Placards
2.1.
2.2.
2.3.
2.4.
2.5.
2.6.
2.7.
2.8.
\ 2.9. 2.9.1.
2.9.2.
2.9.3.
2.9.4.
Limitations placard
Aerobatic Maneuvers Speed Placard
Warning placard for maximum luggage weight.
Control Identification Placards
2.9.4.1.
2.9.4.2.
2.9.4.3.
2.9.4.4.
2.9.4.5.
2.9.4.6.
2.9.4.7.
2.9.4.8.
2.9.4.9.
Spoiler and Wheel Brake control
Flap control
Trim Tab control
Landing Gear Retraction control
Canopy Opening and Canopy Jettison
Tow Release control
Front Air Scoop control
Main Wing Junction Lock - direction
Miscellaneous other markings.
2.1. CERTIFICATION
The glider is certified
versions: dual control
solo control
FAA
2.2. SPEED LIMITATIONS
in accordance with OSTIV 1971 regulations, in the following
utility category
aerobatic category (with weight limitations)
additional requirements
Never exceed speed -
V-
124 kts
Max speed at 15 m/s gust strength
-
Vne -
89 kts
-
Max rough air speed
b
Max aerotow speed -
Vt -
75 kts
Max winch-launch speed
-
Vw -
67 kts
Max speed, gear down
-
V-
124 kts
Max speed with 150 flap
-
VIe -
70 lts
Max speed with spoilers extended
-
/0-
124 kts
ab
Max maneuvering speed -
V-
89 kts
a
2.3 AIRSPEED INDICATOR MARKINGS
RED radial line at
YELLOW arc (caution range)
GREEN arc (normal operating range)
WHITE arc (flap operating range)
124 kts
- 89-124 kts
- 38-89 kts
- 35-70 k~s

2.4. LOAD FACTORS AT liMIT WEIGHTS
At all-up weight of 1301 lbs (max Gross) .
At all-up weight of 1146 lbs (max aerobatic weight) ..
2.5. MAXIMUM WEIGHTS
+5.3 g,
+6.5 g, -2.65 9
-4 g
Maximum gross weight (max all-up) (dual) ...
Maximum aerobatic weight (solo) .•..•...
Maximum weight in luggage compartment (without
exceeding max gross)
1301 lbs
1146 lbs
44 Ibs (incl 02 tanks
NOTE: The pilot-in-command is responsible for correct
loading of the glider
2.6. BALANCE (Manufacturer's CG limits)
Forward CG Limit =22% MAC
Aft CG limit =47% MAC
=9.787" from datum
=20.9111 from datum
WARNING Solo flight from front seat ~
In case of light pilots~ to keep the glider within CG limits, useadditional
lead ballast in the tray provided on the front seat floor forward of stick.
Ballast is required for solo flight when the pilot weight (incl parachute)
is less than 183 lbs.
Ballast weight(s) shall be added depending on Pilot weight, (incl.chute)~
as shown in Table 2.1
'Pi16t's weight +
+parachute
TABLE 2. I
Ballast ',wei£ht Ba.llast locat,io.n
21 c •
]"~ 11) 11 ,
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2.7. PERMITTED MANEUVERS
~ the following aerobatic maneuvers are permitted: Spin
loop
Stal1-turn(wingover)
Ro 11
2.8. SPECIAL INSTRUCTIONS
For winch launch or aerotow, the t~~ing cable (rope) shall contain
a weak-link of 1102 lbs strength (or less).
7

2.9. PLACARDS - The glider is provided with the foll~~ing placards.
2.9.1. LIMITATIONS PLACARD (painted in red)
ll' 'l-'-'-I"'~I"" I'i '/1 1,/t ., lI
1/\/1 jh1LUl'~:)' .. l\m 111<no.lS mon I
. i ,I
,,,)-l{ I2.,--'0 -, -1'? I'J' 0' 7
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,:811G7 891103.
5- .. ~ 1LtO I7:) I871
I I
'\1-127 I Gr-' I78 .
II[-,11T J\ R I
4-.A. I
~ f'IE
'0"
2.9.2. AEROBATIC MANEUVERING SPEED PLACARD (painted in red)
AER08l\TIC8~~~TRYIAIRSP~E_E_D
;, I [I hiJ-.J1ut' cIr ( " f
-" IfJ;)
SPIN I70 I38\ L.3
,.
LOOPING 1-170192j106
TUm! 1170 I 92 1106 I
ST;\LLTURI'1I1SQ! 81 r93-

'fl.
,;\ .(
brake
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+Bctunted
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max. vSdJ- L.U il'J •
M/\~IL1Ur/1 6AGH.e,
lO AD 4!~lb
Ret~bc~~~ alr
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