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.

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-6
Date of issue: 30.01.2008
2.3.5. Control system The airplane is equipped with a classic
dual control system. The elevator and
ailerons are controlled by a control
sticks, connecting rods and arms. The
longitudinal control system stops are
attached to the seats. The lateral control
system steps are located on the control
sticks.
There is the twisting spring controlled by lever next to the
control stick to trim a force in the longitudinal control
system.
The wing flaperons and airbrakes are controlled with
a control lever between a seats. The lever is in a
changing gate and welded to a torsion tube. There are
the levers and rods at both ends of torsion tube to
control the flaperons and airbrakes.
Lever has following positions
1) takeoff position (fixed)
2) landing position (fixed)
3) airbrake position (free movement)
The rudder control system is dual too. The rudder is
controlled by cables attached at the rudder pedals and to
the hinges on the rudder bottom rib. There are the two
turn buckles to adjust the length of the cables.
The rudder control is connected by the rods to the
nose wheel steering arms.

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-7
Date of issue: 30.01.2008
Control lines drawings
Flaperon, airbrakes and rudder control lines
Elevator control line

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-8
Date of issue: 30.01.2008
2.3.6. Landing gear
The airplane is equipped with fixed nose wheel landing gear. The nose wheel is controllable.
The main wheels on both leg are equipped with hydraulic brakes. There is the brake level on
the pilot’s control stick. The main leg are formed from fiberglass springs with foam core. The
main wheels of 400x100 mm size consists of a duralumin alloy rim, bearings and duralumin
brake disc. The brake caliper with the one hydraulic cylinder is floating. There is a brake
fluid hose connected to the brace caliper to the master cylinder on the control stick. The nose
wheel leg is formed from high quality steel tubes welded together. There is a rubber stock
absorber to spring the leg.
The tail wheel steering is connected to the rudder control.

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-9
Date of issue: 30.01.2008
2.3.7. Power plant control
The engine power is controlled by a throttle lever located on the instrument panel, in the
panel center line. There are the two bowden cables led from the throttle lever to the
carburetors.
To start could engine the carburetors are equipped with a chords controlled by a lever
located below the instrument panel. The ignition switches are located on the instrument
panel. Switch on the ignition and the turn key in the in the switch box to start the engine.
2.3.8. Fuel system
The airplane is equipped with two 50 liters ( each ) fuel tanks in both wings.
The fuel tank filler neck is placed on the wing upper surface and equipped with a cap sealed
by a packing “O” ring. A fuel tank bleeding hole is located on the wing tip. A fuel tank
draining valve is located under the wing in the lowest part of the fuel tank. Use the valve to
empty the fuel tank, also.
Fuel is pulled in the fuel tank through the fuel tank outlet coarse screen. Then through the
fuel valve and fine screen to the fuel pump and on he carburetors. Fuel quantity is indicated
by an automotive fuel gauge located on the instrument panel. There is installed a float in
the fuel tank to scan a fuel quantity. The fuel gauge displays the relative quantity of fuel
inside the fuel tank, corresponding fuel quantity liters is shown on the placard “WEIGHT”
in the cockpit.

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-10
Date of issue: 30.01.2008
2.3.9. Electrical system
The electrical system is single-wire type with negative side connected to the chassis. The
power source is a single-phase generator (250 W) with a rectifier and 12 V/14 Ah battery.
Separate appliances have separate switches. The circuits of the particular sections are
guarded individually by fuses. The dual ignition is a separate part of the electrical system.
Each ignition circuit has its own ON/OF switch.
Wiring diagram No.1

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-11
Date of issue: 30.01.2008
Intentionally left blank for optional appliances wiring diagram

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-12
Date of issue: 30.01.2008
2.3.10. Pitot-static system
The pitot tube provides the ram air pressure to the airspeed indicator. The tube is on the fin
tip. Pressure distribution to individual instruments is done through flexible plastic hoses.
Keep the system deck to assure its correct function. If water gets inside the system
disconnect hoses from the instruments and slightly blow into the system.
WARNING!
Do not blow into the system when the instruments are not disconnected - it may cause
instruments damage.

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-13
Date of issue: 30.01.2008
2.3.11. Equipment
Standard equipment
The flight and engine instruments, COMM/NAV instruments, electrical appliances, switches,
switch box, fuses, fuel valve and fuel gauge are on the instrumental panel. Optional
instruments may be installed, also.
The seats are integral part of fuselage. The seats are thin-upholstery by the soft removable
upholstery. The headphones jacks are located aside the seats
Each seat is equipped with a four-part safety belts.
Position lights, anti collision bacon and possible additional equipment optional.
The following optional equipment is installed in the UFM-13 airplane
•Radio
•Intercom

O
OP PE ER RA AT TI IN NG G A AN ND D M MA AI IT TE EN NA AN NC CE E M MA AN NU UA AL L F FO OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E
U
UF FM M – – 1 13 3 L LA AM MB BA AD DA A
Date of Issue: 30. 1. 2008
2-14
2.3.12 Instrument panel
1Heating 10 Vertical speed indicator
2Air speed indicator 11 Altimeter
3TL-engine instrument 12 Throttle
4Compass 13 Magnetos
5Slip ball 14 Switches and fuses
6Fuel tank valve and switch 15 12 V socket
7Main key
8Main fuses
9Fuel indicator
2
1
3
4
5
15
14
8
9
7
6
10
11
13
12

OPERATING AND MAINTENANCE MANUAL FOR ULTRALIGHT AEROPLANE
UFM-13 Lambada
Document No: 2-15
Date of issue: 30.01.2008
2.3.13. Interior & exterior placards
CAUTION:
The owner (aircraft operating agency) of the airplane is responsible for placards readability
during airplane service life.
UFM 13 URBAN – AIR
Empty weight 307 kg
Max. Take-off weight 520 kg
Min. crew weight 65 kg
Max. baggage weight 4 kg
Never exceed speed VNE 200 km/h
Stalling speed Vso 65 km/h
Fuel tank capacity 2 x 50 l
Manufactured: URBAN – AIR s.r.o.
Model: UFM 13
Date of produce: 2008
S/N 105/13
Registration:
Empty weight: 307kg
Max. Take-off weight: 520 kg
Permitted crew weight
25 l in fuel tank 148 kg
50 l in fuel tank 130 kg
75 l in fuel tank 112 kg
full fuel tank 94 kg
half an hour flight 157 kg