Urban Air UFM - 13 LAMBADA Technical specifications

Operations and Flight Manual
UFM – 13 LAMBADA
Serial No. 105/13
Date of Issue: 30/01/2008
Urban Air s.r.o., T.G.Masaryka 897, 562 01 Ústí nad Orlicí, Czech Republic,
Tel./fax: [phone], E-mail: [e-mail]

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0. Table of Contents
0. Table of Contents...................................................................0-11
1. General......................................................................................1-0
2. Limitations................................................................................2-0
3. Emegency procedures...........................................................3-0
4. Normal procedures..................................................................4-0
5. Performance.............................................................................5-0
6. Weight and Balance.................................................................6-0
7. Aeroplane and Systems Description .....................................7-3
8. Aeroplane handling, servicing and maintenance...............8-13
9. Supplements.............................................................................9-0

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Section 1
1. General
1.1 Introduction..................................................................................1-1
1.2 Certification basis........................................................................1-1
1.3 Warnings, cautions and notes.....................................................1-3
1.4 Descriptive data...........................................................................1-4
1.5 Three-view drawing.....................................................................1-7

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1.1 Introduction
This Flight Manual provides information useful for the safe and effi-
cient operation of UFM - 13 ultralight aeroplane.
It also contains supplemental data supplied by the aeroplane
manufacturer.
1.2 Certification basis
This type of aeroplane has been designed in compliance with
„Požadavky na letovou způsobilost Sportovních létajících zařízení
Ultralehké letouny řízené aerodynamicky UL-2 část I (Ultralight Airwor-
thiness Requirements UL-2, part I)“, that is the valid Certification basis for
the ULTRALIGHT category aeroplanes approved by the Czech Amateur
Light Aircraft Association (www.laacr.cz ).

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1.3 Warnings, cautions and notes
The following definitions apply to warnings, cautions and notes in
the flight manual.
Warning
Means that the non-observation of the corresponding proce-
dure leads to an immediate or important degradation of the flight
safety.
Caution
Means that the non-observation of the corresponding proce-
dure leads to a minor or to a more or less long term degradation of the
flight safety.
Note
Draws the attention of any special item not directly related to
safety but which is important or unusual.

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1.4 Descriptive data
1.4.1 Aeroplane description
UFM - 13 ultralight aeroplane is intended for recreational and
cross-country flying. It is not approved for aerobatic operation.
UFM - 13 is
a single engine, all-
fibreglass aeroplane
with two side-by-
side seats. The
aeroplane is
equipped with fixed
two main wheel
undercarriage with a
steer able tail wheel.
The fuselage is a
fibreglass shell with
fibreglass seats
integrated. Safety
belts are attached to
the seats and to a
shelf intended for
putting off lightweight objects (headphones, maps, etc.).
The wing is a monospar construction with a sandwich skin com-
posed of two layers of fibreglass and special foam. Control surfaces and
empennage is of the same construction.
The aeroplane is controlled by dual push-pull control system, only
rudder drive is controlled by cable. The ailerons and elevator are controlled
by the control stick located between the pilot's legs (co-pilot's). The rudder
is controlled by the rudder pedals, flaps are operated by a control lever
located between the pilots on the fuselage main spar.

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1.4.2 Basic Technical data
Wing
Span/span with wing extension ........................ 12.94/14.95m
Area/area with wing extension.......................... 12.16/12.87m
2
MAC.................................................................... 0.987m
Loading/loading area with wing extension....... 37/34.9kg/m
2
Flaperon
area..................................................................... 0.82 m
2
Fuselage
length .................................................................. 6.6 m
width.................................................................... 1.08 m
height .................................................................. 1.95 m
Horizontal tail unit
span .................................................................... 2.5 m
area..................................................................... 1.3 m
2
elevator area....................................................... 0.45 m
2

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Vertical tail unit
height .................................................................. 1.2 m
area..................................................................... 1.1 m
2
rudder area ......................................................... 0.44 m
2
Landing gear
wheel track.......................................................... 1.54 m
wheel base.......................................................... 4.16 m
main wheel diameter........................................... 0.4 m
tail wheel diameter.............................................. 0.2 m