Urban Air UFM - 13 LAMBADA Operating instructions

Operating and Maitenance Manual for Ultralight Aeroplane
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]

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 1-1
Date of issue: 30.01.2008
1. GENERAL
1.1. Record of Revisions

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 1-2
Date of issue: 30.01.2008
1.2. List of Effective Pages
Note
Latest issue of Maintenance Manual for ultralight airplane UFM 13 Lambada is 18.11.2003.
All pages of this document are effective.

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 1-3
Date of issue: 30.01.2008
1.3. Table of contents
1.GENERAL ...............................................................................1-1
1.1. R ECORD OF R EVISIONS ............................................................................................................................................... 1-1
1.2. L IST OF E FFECTIVE P AGES ......................................................................................................................................... 1-2
1.3. T ABLE OF CONTENTS .................................................................................................................................................. 1-3
2.TECHNICAL DATA..............................................................2-1
2.1. B ASIC TECHNICAL DATA ............................................................................................................................................. 2-1
2.1.1. Basic Dimensions................................................................................................................................................. 2-1
2.1.2. Power plant.......................................................................................................................................................... 2-2
2.2. T HREE VIEW DRAWING ............................................................................................................................................... 2-4
2.3. T ECHNICAL DESCRIPTION OF THE AIRPLANE ............................................................................................................... 2-5
2.3.1. Fuselage............................................................................................................................................................... 2-5
2.3.2. Wing .................................................................................................................................................................... 2-5
2.3.3. Horizontal tail unit ( HTU )................................................................................................................................. 2-5
2.3.4. Vertical tail unit ( VTU )...................................................................................................................................... 2-5
2.3.5. Control system .................................................................................................................................................... 2-6
2.3.6. Landing gear........................................................................................................................................................ 2-8
2.3.7. Power plant control ............................................................................................................................................. 2-9
2.3.8. Fuel system........................................................................................................................................................... 2-9
2.3.9. Electrical system................................................................................................................................................ 2-10
2.3.10. Pittot-static system............................................................................................................................................ 2-12
2.3.11. Equipment.......................................................................................................................................................... 2-13
2.3.12. Instrument panel ................................................................................................................................................ 2-14
2.3.13. Interior & exterior placards .............................................................................................................................. 2-15
3.PERIODICAL INSPECTIONS AND INTERVALS ............3-1
3.1. P RE - FLIGHT INSPECTION ............................................................................................................................................. 3-1
3.2. P ERIODICAL INSPECTION INTERVALS .......................................................................................................................... 3-1
3.2.1. Periodical inspections Sign off sheets.................................................................................................................. 3-1
3.2.2. Periodical inspection after the first 25 hours and every 50 hours..................................................................... 3-2
3.2.3. Periodical inspection after every 100 flight hours............................................................................................... 3-3
4.OPERATION AND MAINTENANCE................................4-1
4.1. O UTLINES ................................................................................................................................................................... 4-1
4.2. W EIGHT AND C ENTER OF GRAVITY POSITION ............................................................................................................. 4-1
4.2.1. Empty weight determination ................................................................................................................................ 4-1
4.2.2. Operating C.G. range calculation ....................................................................................................................... 4-1
4.3. M ECHANISM ADJUSTMENTS ....................................................................................................................................... 4-2
4.3.1. Torque moments................................................................................................................................................... 4-2
4.3.2. Control Surface Deflections................................................................................................................................. 4-3
4.4. P ERMISSIBLE TOLERANCES ( PLAYS ).......................................................................................................................... 4-4
4.5. L UBRICATING C HART ................................................................................................................................................. 4-5
4.5.1. Recommended lubricants.................................................................................................................................... 4-5
4.5.2. Airframe lubrication fundamentals...................................................................................................................... 4-5
4.6. B RAKE FLUID REFILLING , BRAKE SYSTEM BLEEDING , BRAKE PAD CLEARANCE ADJUSTAMENT .................................. 4-6
4.6.1. Brake fluid refilling.............................................................................................................................................. 4-6
4.6.2. Brake system bleeding.......................................................................................................................................... 4-6
4.6.3. Brake pad clearance adjustment.......................................................................................................................... 4-6
4.6.4. Brake pad replacement ........................................................................................................................................ 4-6
4.7. G ROUND HANDLING ................................................................................................................................................... 4-7
4.7.1. Towing the airplane............................................................................................................................................. 4-7
4.7.2. Parking the airplane............................................................................................................................................ 4-7

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 1-4
Date of issue: 30.01.2008
4.7.3. Tieing-down ......................................................................................................................................................... 4-7
4.7.4. Jacking the airplane............................................................................................................................................. 4-7
4.7.5. Road transport..................................................................................................................................................... 4-8
4.8. C LEANING AND CARE ................................................................................................................................................. 4-9
4.8.1. Airplane care outlines.......................................................................................................................................... 4-9
4.8.2. External surfaces cleaning................................................................................................................................... 4-9
4.8.3. Interior cleaning .................................................................................................................................................. 4-9
4.8.4. Cockpit canopy cleaning...................................................................................................................................... 4-9
4.9. A IRPLANE DISASSEMBLY .......................................................................................................................................... 4-10
4.9.1. Wing disassembly............................................................................................................................................... 4-10
4.9.2. Wing assembly ................................................................................................................................................... 4-10
4.9.3. HTU disassembly............................................................................................................................................... 4-10
1. Rematch the safety pin and unscrew the M8 screw ........................................................................................... 4-10
4.9.4. HTU assembly.................................................................................................................................................... 4-10
5.REPAIRS..................................................................................5-1
5.1. D AMAGE CLASSIFICATION .......................................................................................................................................... 5-1
5.2. R UDDER CONTROL CABLES REPLACEMENT ................................................................................................................. 5-1
5.3. F IBREGLASS FAIRING AND COWLINGS REPAIRS ........................................................................................................... 5-1
6.APPENDICES..........................................................................6-1

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-1
Date of issue: 30.01.2008
2. TECHNICAL DATA
2.1. Basic technical data
2.1.1. Basic Dimensions
UFM-13
Wing
span.............................................................. 13 m
area............................................................... 12,16 m
2
MAC ............................................................ 0,987 m
loading ......................................................... 37 kg/m
2
Flaperon
area............................................................... 0,74 m
2
Fuselage
length ........................................................... 6,6 m
with .............................................................. 1,08 m
height ........................................................... 1,95 m
Horizontal Tail Unit (HTU)
span.............................................................. 2,5 m
area............................................................... 1,3 m
2
elevator area................................................. 0,45 m
2
Vertical Tail Unit (VTU)
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 diam./width............................... 0,4 m/0,1 m
tail wheel diam./width................................. 0,2 m/0,06 m

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-2
Date of issue: 30.01.2008
2.1.2. Power plant
Engine
The ROTAX 912 UL is 4-stroke, 4
cylinder, horizontally opposed, spark
ignition machine, one central camshaft –
push – rods – OHV. Liquid cooled
cylinder heats, ram air cooled cylinder.
Dry sump forced lubrication. Dual
breaker less capacitor discharge ignition.
Engine electrical system consist of 10-
poles single –phase generator, ignition,
electric starter, regulator and 12
V battery. The coolant is forced trough
is forced through the radiator by a water
pump, driven from the crankshaft to
cylinder heads. From the top of cylinder
heads the coolant passes on the expansion tank which allows for coolant expansion. The
expansion tank is closed by a pressure cap with excess pressure valve and return valve. When
the temperature vises the coolant creating excess pressure, a relief valve opens and the
coolant flows through a hose to the overflow bottle mounted on the firewall.
The engine is attached to the engine mount attached to the firewall with 4 bolts. The engine
mount is spring – mounted with 4 rubber shock absorber.
Engine Manufacturer……….. Bombardier – Rotax GmbH Gurnskirchen, Austria.
The engine instruments:
•Engine rpm
•Engine hours
•Cylinder head temperature
•Oil temperature
•Oil pressure

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-3
Date of issue: 30.01.2008
Engine Technical Data
Power
Max Take off power……….59.6 kw / 80 hp at 5800 rpm / min max. 5 min
Max. Continuous power……..58 kw / 78 hp at 5500 rpm / min
Cruising power……...………..53 kw / 71 hp at 4800 rpm / min
Idling rpm…………………………1400 rpm / min
Cylinder Heat Temperature
Maximum...........................................................150 °C
Oil Temperature
Minimum .............................................................50 °C
Maximum...........................................................140 °C
Optimum Operating..................................... 90-110 °C
Fuel Pressure
Maximum...........................................................0.4 bar
Minimum .........................................................0.15 bar
Fuel brands
•Automotive premium grade petrol, according to DIN 516000,Ö-NORM C 1103
•EUROSUPER RON 95 unleaded accord. to DIN 51607,Ö-NORM 1100
•AVGAS 100 LL
•the BA 95 NATURAL is recommended for the Czech Republic
Oil brands
Automotive engine oil of registered brand with gear additives, but not aircraft oil API
classification “SF” or “SG”
Fuel consumption
Max. Take off power ......................................22.7 l / h
Cruising power 75 % ...............................16.2 l / hours
Specific. consumption...............................285 g / kWh

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-4
Date of issue: 30.01.2008
2.2. Three view drawing

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-5
Date of issue: 30.01.2008
2.3. Technical description of the airplane
2.3.1. Fuselage
The fuselage is all – fiberglass monocoque construction with integrated seats. Safety belts are
attached to the seats and to a shelf for lightweight objects (headphones, maps, etc.) The
engine is attached to the firewall covered with the fire resistant mat. The removable engine
cowling is attached with 13 CAMLOC screws. The cockpit canopy is made of the Perspex of
3 mm thickness. The canopy may be tilted backwards. Two side sliding windows and the
windshield air window are installed on the canopy to vent the cockpit.
An instrument panel is attached to the cockpit front part. There are installed the flight, engine
instruments, switches, fuses and throttle lever on the instrument panel.
The wing center-section is formed with the two bushings for wing connecting pins.
The hand control system rods are connected by means of the automatic grips installed on the
wings center – section ribs.
The fuselage main spar is located between the seats. The nose wheel and rudder pedals are
attached to the main spar front part.
The main landing gear leg bracket is attached to the fuselage main spar rear part.
The vertical tail unit is of sandwich construction. The horizontal tail unit is attached to the
VTU front part with the two pins and the one screw.
The rudder is controlled by the two cables. The ailerons, flaps and elevator are controlled
through rods. The cockpit heating is done through the two holes located in the firewall
cower part to bring the hot to the cockpit.
2.3.2. Wing
The cantilever wing is a monospar construction with the sandwich skin consist of the two
fiberglass layers and the special foam core. The spar flanges are made from a carbon
fiber. The spar web is the sandwich construction, also. The wing root ribs are stuck between
the spar flanges. The wing pins, bushings, control system nuts and fuel level float bracket are
laminated to the root rib. The 50 liters fuel tank is an integral part of the wing.
2.3.3. Horizontal tail unit ( HTU )
The HTU is of the some construction as the wing, only the spar is made from the fiberglass.
2.3.4. Vertical tail unit ( VTU )
The VTU is of the same construction.