Home

G700 Maintenance Manual R3

Contents

1. SEUCH MIC SEUCH PILOT PILOT COPILOT COPILOT EN DX I m Ra aT Re Rare RAD DNK oh 2 74 pe I pua EE 9 E o o Szyna Awioniki s z E jaa x 1 4V PM TIO mie ge JRADIOSTACJA e A S JA COMM E aw TO to S ro rm co S ja lt lt j lt c lt lt I x RA 3 x x c 02 x N O i Lu Ll Rov m x lt lt e D D na ah ra lt s E x E lt lt lt lt gt m N N N I TN CLIE CON SEDES In raj lt 15 N o GA lt lt lt lt lt lt O c x P JEZ SL NE lt L KI x m E Z m E x lt lt lt lt x m gt S S S RG142B U RG 58 2m N amp p SIE x f P Y s 5 o eee Ed lt l EE 9 14 13 6 1218 4 15112 9 1411316 7 1218 4 15112 HITITE LETI TTT Taye T Ld amp gt Gl e 5 gt lt O S O ES E C5 C5 m C E 5 O u OO 15 PIN Connector
2. 18 3 11 GPSMap electrical Gia Grams isti au a tected oken 18 3 12 MAY 2007 18 3 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 3 AT 4LSA 1 1 List of revisions P o Concernin Revision nr Revision description Pages 5 Data 1 2 List of effective pages 7 7 18 3 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 18 AT 4LSA SUPPLEMENT No 3 1 Description The GPS MAP 296 396496 system are portable GPS receiverswith aviation application The GPS main unit is located on right side of the instrument panel Location of device on instrument panel is shown on Fig 1 1 I le r ows opoogoogoo Carb heat Fig 1 1 Location of GPS Map system on instrument panel 1 GPS MAP 496 receiver 2 GPS circuit breaker The GPS connected to its antenna and on open space will establish initial coordinative within period of 5 min if the unit has UTC time date and initial location introduced the process will be significantly reduced to 15 to 45 s The SL 30 transreceiver is operating with use of two antennas standard GPS weather forecasting which is located ahead of cockpit Location of antennas is shown on Fig l 2 MAY 2007 18 3 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 SUPPLEMENT No 3 1 GPS ante
3. 2 fet 20 min min 0 8 in B 4 40 min min 1 6 in Pr RS Figure 16 8 Gradation of layers MAY 2007 16 13 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 16 AERO Sp z o o REPAIRS AT 4LSA 6 Clean cut out with the acetone for degrease 7 Prepare mixture of Epidian 53 resin and Z1 hardener of weight ratio 10 1 and a guantity eguivalent to the mass of the fabric necessary for a repair When using epoxy system of other manufacturer follow appropriate instruction 8 With a brush or a roller apply mixture on chamfering places than in subsequent order apply and impregnate prepared fabric with resin To attain surface the same as repaired the foil depress can be used for example foil clamp 9 After the hardening process at temperature 18 65 F 24 hours for Epidian clean and polish repaired area 16 5 2 Painting repaired composite parts 1 Apply primarily automotive filler polyester 2 Polish surface with emery fabric 100 200 3 Apply a filler with a gun 4 Polish with a waterproof sand paper 360 400 5 Perform painting 6 When the last painting dry up polish it 16 14 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 16 AT 4LSA REPAIRS 16 6 VALUE OF THE TORGUE MOMENTS OF BOLTED JOINTS TABLE OF DRY TORQUE MOMENTS FOR BOLTED JOINTS Location of the joint Moment 2 2 3 Joint of win
4. C 5 2 PADE 5 2 ls SGOT OI s oon cosh a sar ama Oa au 5 3 2 Operations 5 4 2il Starine and mode SEE CUION uuu o OUS 5 5 22 ode chs E as 5 6 3 Transponder disassembly and assembly 5 5 3 Encoding altimeter disassembly and assembly 5 7 4 Antenna disassembly and assembly 5 8 5 Drausponderelectric SYS IN sizes teste esto a ve 3 9 Gy Statie pressure syste sinais RU e aiiin 5 11 7 Transponder configuration 5 11 MAY 2007 18 5 1 AIRPLANE MAINTENANCE MANUAL No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 5 AT 4LSA 1 1 List of revisions bi En Concernin Revision nr Revision description Pages Data 1 2 List of effective pages May 2007 May 2007 May 2007 May 2007 May 2007 May 2007 r FEE 18 5 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z CHAPTER 18 AT 4LSA SUPPLEMENT No 5 1 Description The GTX327 transponder is is located on right side of the instrument panel The unit is associated by AK 350encding altimete
5. ALTTUDE Ct 10 10 mc v ALTITUDE C2 4 4 HECE ALTITUDE C4 7 7 d 12024 ALTITUDE 04 18 18 gene z slon Hit C ezarnyzbidi DO M czrwony biat Hana 15 PIN Connector WYSOKOSCIOMIERZ KODUJCY 550 MAY 2007 18 5 10 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 ROZDZIAL 18 AT 3 R 100 UZUPELNIENIE 22 6 Static pressure system The AK350 Encoder is connected to the aircraft s static pressure system Static pressure system diagram is presented on Fig 8 1 The connection between encoder and the static pressure system is provided with elastic rubber hose of 4 mm internal diameter 5 3 IN b0226003 Fig 6 1 Static pressure system for GTX327 transponder 1 Static pressure system 4 Flight instruments 2 Static pressure line 5 AK 350 altitude encoder 3 Water Trap 7 Transponder configuration Menu is utilized during device installation or after removal of transponder It is highly recommended to take special care in cause of introducing any modifications into transponder s configuration To start transponder menu configuration follow procedure 1 While turning on transponder press and hold FUNC button use ON STBY and ALT buttons 2 Select required page with FUNC and START STOP buttons and press FUNC 3 Highlight selected option at selected page with CRSR button 4 Select desired option using 8 9 keys and introduce new data with keys 0
6. 18 2 3 Z Sy erro ses ed on tese O ao eo tv aa ctio E Opp 18 2 4 Did PO Wer ON a ua 18 2 4 2 2a PCOM MOJE e 18 2 5 2 COM frequen Gy basado O 18 2 6 3 Disassembly and assembly of SL 40 18 2 6 3 1 Disassembly of SL 40 main nennen 18 2 6 3 2 Disassembly and assembly of transmission switch 18 2 6 3 3 Disassembly and assembly of COM antenna 18 2 6 4 COM and Intercom system dia ram 18 2 6 DC OM coni eura u O uuu u u 18 2 8 MAY 2007 18 2 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z o o SUPPLEMENT No 2 AT 4LSA 1 1 List of revisions te TE Concernin Revision nr Revision description Paves 5 Date 1 2 List of effective pages 18 2 6 May 2007 18 2 7 2007 18 2 8 2007 Lo 7 j 7 18 2 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o SECTION 18 AT 4LSA SUPPLEMENT No 2 1 Description The SL 40 COM NAV transreceiver is located on right side of the instrument panel It has full communication capabilities and also enables internal communication between crew members intercom Location of device on instrument panel is shown on Fig 1 1 VO IMA v 4 4
7. If removal of the alternator s V belt pulley is required perform following steps Remove the propeller and shaft extension Remove the bushes from the engine shaft flange Remove the V belt pulley plate and the V belt pulley from the engine shaft Installation 1 Perform steps 3 9 in reverse order 2 Adjust the V belt tension acc Para 3 3 Install the engine cowlings 15 2 3 Alternator operation check With the engine switched off turn on the BATTERY switch the ALTERNATOR FAILURE lamp should light up Start the engine The ALTERNATOR FAILURE lamp should go off Turn off the GENERATOR switch With the maximum RPM on the ground the voltage should amount ca 14 2 14 8 V Turn on a high power electrical receiver The voltage should remain unchanged or decrease slightly Exceeding a load of over 50A with the generator switched off could automatically turn off the ALTERNATOR switch MAY 2007 15 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 15 AERO Sp z o o ELECTRICAL SYSTEM AT 4LSA 15 3 ENGINE ELECTRICAL SYSTEM AND ENGINE MONITORING INSTRUMENTS The Rotax 912ULS engine is eguipped with an integral generator and an electronic pointless dual ignition system operating on the principle of discharging of capacitors Switching on both ignition systems is operated by means of combined ignition switch The ignition system does not require any external s
8. 1 Cockpit Canopy Open it and check for smooth movement Pay special attention to the function of the gas springs Canopy lock Check function Plexiglas canopy Check condition and cleanliness Venting tabs Open and shut again Jettisoning levers Check set position and wire locking Ignition switch Check the key is removed Cockpit interior Remove foreign objects and check cleanliness Luggage compartment Remove foreign objects and check cleanliness port and starboard locker 3 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 3 AT 4LSA SERVICING Seats Check condition and fastening Seat belts Check condition function of fastener and fastening Rudder pedals Check condition range of travel brake levers fastening of the brake cylinders brake lines coupling rods and for leaks Control sticks Check full and free travel Wing flaps Extend to 40 Trim amp balance tab Check the full range of travel and set into TAKE OFF position Levers for power choke Check for smooth travel lack of play and for cabin heating and ventilation excessive friction carburetor heating fuel valve Instrument panel Check legibility and condition of the placards Instruments Check condition and fastening legibility of the scales and their color markings Switches Set to OFF levers down BATTERY switch Set to ON lever up The engine monitoring instruments read O The fue
9. Figure 3 Location of sensors on engine 1 Oil pressure sensor 3 Cylinder head temperature sensor 2 Oil temperature sensor MAY 2007 15 11 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 15 AERO Sp z o o ELECTRICAL SYSTEM AT 4LSA U Engine DK Fuel a KO M Pump MAIN BUS 12 V s bus cB KSZ7 z KSZI gt d 1 88 m KS 2 s KS1Z KS13 s KSI4 KS15 KST8 K317 KS18 KST9 53 Ekran 20AWG Ekran ET q Ta ksa KS4 a R Engine KSR 22AWG El S Figure 4 Engine electrical system and engine monitoring instruments diagram 15 12 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 15 AT 4LSA ELECTRICAL SYSTEM 15 3 1 Engine monitor Oil pressure Oil temperature Oylinder head no 2 temperature Oylinder head no 3 temperature Oylinder no 4 exhaust gas temperature Cylinder no 3 exhaust gas temperature Electrical installation voltage Carburetor inlet air temperature O1 Q D elektronic e After pressing the Memory lnfo button under instrument panel on the left the maximum measured values of all displayed guantities will show PRESS 37M 36 ENGINE J e The ready message shows when the engine has reached the optional temperature after the start u
10. installed equipment O equipment not installed NOTE WEIGHT OF THE INSTALLED EQUIPMENT IS INCLUDED IN THE EMPTY WEIGHT OF THE AIRPLANE MAY 2007 6 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 6 AERO Sp z o o WEIGHTING AND BALANCE AT ALSA PAGE INTENTIONALLY LEFT BLANK 6 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 6 WEIGHTING AND BALANCE Z O CC O O LLI CC ke lt LLI O O lt lt T LLI o N o t o 9 ct lt lt oue dure JO 3uouroui 212 pu 3 8 3uouidinbo sogueuo pue JO p1o523 9 9 o8ed oos yodoy ZUJ M Jod se oue dare ou amp at O NOLLVOIJIGOIN sunivwors SIVA NI HDNVHO Ei Ne SNINQYIOO LSVD ANV IdNIV ALANA AHL HO LNAWOW ANV LHOIHA NDIS TIVO SIHHIALYN IVISIAS 6 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A MAY 2007 CHAPTER 6 AERO Sp z o o WEIGHTING AND BALANCE AT ALSA 6 7 The procedure of recording the data in Form 17 2 1 For each position of the table calculate the weight of pilot and passenger in the following way Subtract from the aeroplane maximum weight 1320 Ib the weight of empty aeroplane fuel and luggage 2 Calculate according item 6 3 of this manual the C G position for the weights received as u
11. I o5 amp o 12 12 12 27 ON TN LIN a sm 13 13 14 15 0 20 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 1 AT 4LSA GENERAL INFORMATION CHAPTER 1 GENERAL INFORMATION 1 1 Basic information on airplane 1 2 1 2 Three view projection of the airplane 1 3 MAY 2007 1 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER1 AERO Sp z o o GENERAL INFORMATION AT 4LSA 1 1 BASIC INFORMATION ON THE AIRPLANE The AT 4LSA is an all metal two seat cantilever low wing airplane It is powered by A four cylinder BOMBARDIER ROTAX model 912SULS flat four piston engine with air cooled cylinders and liquid cooled cylinder heads with dual ignition Take Off Power Rating of 73 5 kW 100 BHP Propeller Setting on the ground clockwise rotation three blades ELPROP 3 1 1P with metal hub and composite blades having outer diameter of 5 68 The tricycle landing gear is of fixed type with nose wheel The main wheels are fitted with hydraulic disc brakes which may be operated from both the LH and RH position The trailing edge wing flaps are manually operated The slab tail is fitted with a trim and trim tab The flight controls are conventional consisting of dual control sticks which operate the ailerons and stabilator and dual pedals which operate the rudder The baggage compartme
12. om ge Figure 11 1 Elevator control system 1 Control stick 5 Intermediate lever 2 Torque tube 6 Lever driving the elevator and outrigger of the mass balance Short push rod 7 Fairing of the rear part of fuselage Rear push rod 8 Partition frame 11 1 1 Removal and installation of the elevator control system Removal 1 Remove the elevator refer to section 9 3 1 2 Using the inspection door in the lower skin of fuselage disconnect the push rods from the intermediate lever and remove the rear push rod Remove the intermediate lever Remove the seats and the middle tunnel refer to sections 13 1 1 and 13 2 1 Remove the short push rod Disconnect the electric wires from the control sticks Remove the trim tab control refer to section 11 5 1 N O O CO Disconnect long push rods and coupling push rod of ailerons actuator refer to section 11 2 1 9 Remove the torque tube together with control sticks 11 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 11 AT 4LSA AIRPLANE CONTROLS Installation 1 Perform steps 1 to 10 in reverse order 2 Lubricate all connections 3 Secure all bolt and nuts 4 For bolted joints torque limits refer to Chapter 16 6 11 1 2 Adjustment of elevator displacement 1 Lock the torque tube and the intermediate lever using 4 mm 0 155 in dia 2 Adjust length of the front push rod 3 Adjust length of the rear push
13. 18 3 13 LO CD OD co s O ZD E ve JN ON d 49 4 5MvzZ 9575 a y KuomJez5 ZdO DMV Q uowasz2 d9 O a 1019 lt NAV IV XR 350 mozoubibwod lt ed 3910A Amozbig X MONG EH N C CIT lt HISTO Z 100 VIVO UGjBiz gt H N3349 Z NI VIVO PRE lt Hana 100 viva A Ke p _ HMOTIBA VIVO VNNJINV AVN 8994 N 8cvI98 1 297 VO TM Z BODY gt gt a NC 1403 851 VOC WNX9 IM Z 890 gt gt Fig 4 1 GPSMap 296 396 496 electrical diagram AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A MAY 2007 CHAPTER 18 AERO Sp z o o SUPPLEMENT No 3 AT 4LSA PAGE INTENTIONALY LEFT BLANK 18 3 14 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o SECTION 18 AT 4LSA SUPPLEMENT No 4 SUPPLEMENT No 4 STALL WARNING ACI T1 J T ASCOT LE VISIONS 18 4 2 E2 pel elle zoo ab ut obe joj 18 4 2 2 DEVICE PO y 18 4 3 3 Stall warning electric installation ee 18 4 5 MAY 2007 18 4 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z SUPPLEMENT No 4 AT 4LSA 1 1 List of revisions na Concernin
14. SON PULL 19 Over the circuit breakers of the particular electric circuits STARTER ENGI NE ENGINE FUEL 12VDC INSTRUMENTS MONI TOR SUPPLY NAV TXPR ARTIF DIR TURN HORI ZON GYRO COORD LANDING TAXI STOBE POSI TI ON INSTR LI GHT LIGHTS LIGHTS LI GHTS LI GHTS MAY 2007 8 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 8 AERO Sp z o o PLACARDS AT ALSA 20 Over enunciator panel warning lights STARER GEN ALTERN FUEL FUEL RESERVE ENGAGED FAILURE FAILURE PUMP ON 2 6 gal 21 Near internal supply plug 12V DC SUPPLY 22 Over of the magnetic compass RPATH 23 Nextto the red lamp signaling the stall STALL WARNING 24 Over instrument light intensity regulator INSTR 25 Over cabin light intensity regulator CABIN 26 Over engine monitor light intensity regulator ENGINE MONITOR 8 6 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 8 AT 4LSA PLACARDS 27 Near parking break handle PARKING BRAKE VALVE CLOSED H OPEN 28 Next to ELT control panel ELT UNIT UNDER RIGHT SEAT 39 On instrument panel THIS AIRCRAFT WAS MANUFACTURED IN ACCORDANCE WITH LIGHT SPORT AIRCRAFT AIRWORTHINESS STANDARDS AND DOES NOT CONFIRM TO STANDARD CATEGORY AIRWORTHINESS REGUIREMENTS FLIGHTS IN KNOWN ICING CONDITIONS PROHIBITED AEROBATIC MANEUVERS INCLUDING SPINS PROHIBITED OTHER LIMITATIONS ACC TO AEROPLANE FLI
15. 2 Put plastic hoses on the bleeding valves and immerse their other ends in a vessel with brake fluid 3 Ensure that the brake fluid container is completely filled with fluid 4 Keep pressing appropriate pedal as long bubbles can be seen in the tank Refill tank if necessary 5 Tighten the bleeding valve 6 Operations 1 5 repeat for each installation 10 14 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 10 AT 4LSA LANDING GEAR 10 3 7 Replacing the brake disc When replacing the brake disc first remove the wheel according to section 10 2 1 CAUTION The brake disk must be replaced when its thickness is less than 3 8 mm 0 15 in itis cracked the surface contains deep pits the run out exceeds 0 1 mm 0 0004 in 10 3 8 Installation method of the brake line terminals 1 Protect the braid of the hose with tape and cut the line to the required length 2 Put the nut of the connector on the line 3 Make a gap between the steel braid 2 and the plastic tube 3 Push in the conical sleeve 1 The sleeve must be in contact with the plastic line with its inner flange MAY 2007 10 15 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 10 AERO Sp z o o LANDING GEAR AT 4LSA 5 Screw the nut on the thread and tighten it CAUTION In case of leaking from the connection the hose must be shortened by cutting off the kneaded part and a new connector must be insta
16. 11E Ground power supply receptacle 11041 11 00500 Firewall LH side option of fuselage z z z oz Stane Emone _ 4Z STARTER IN ACTION signaling 17371250 Instrument panel lamp MAY 2007 15 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A o i gt ot oc LU lt 0 gt LO lt Ep cO Iu O u H 1 uo ODA SSE SS SEITE SS ELD Power supply and engine starter circuit diagram Figure 1 MAY 2007 15 4 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 15 AT 4LSA ELECTRICAL SYSTEM 1 2 3 TX 4 13 9 14 15 5 wd W f iti 4 z a mr 11 D o 12 ua 4 NG 10 H 7 L j aes h m 8 9 i Figure 2 Electrical equipment on firewall 1 Firewall 9 Fastening strip 2 22 starter relay 10 Battery ventilation 1E voltage regulator 11 Electrical bonding 4 Electric harness passage 12 6E battery relay 5 breaker 13 13E fuse 6 11E external supply socket 14 Circuit breaker 3E 8 Battery box 15 Circuit braker 23E MAY 2007 15 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 15 AERO Sp z o o ELECTRICAL SYSTEM AT 4LSA 15 2 Alternator electrical installation The alternators activation circuit is protected by a 5A automatic circuit breaker installed on a bracket on the fire wall The alternator i
17. 18 8 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 CHAPTER 18 AT 4LSA SUPPLEMENT No 9 SUPPLEMENT No 9 Strobe lights TEVISIONS doi eor too a t NA as sss 18 9 2 1 2 NAS OP eLFOCLEVO DODES e 18 9 2 2 DOSE PU OM qood tb cde hands 18 9 3 3 Removal and installation of the strobe light power supply 18 9 4 4 Strobe light removal and Installation 18 9 4 5 Strobe light power supply start up 18 9 5 6 Strobe hehtelec ical uu l tenti ee 18 9 6 MAY 2007 18 9 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 9 AT 4LSA 1 1 List of revisions 1 2 List of effective pages F C j May 2007 May 2007 18 9 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 CHAPTER 18 AT 4LSA SUPPLEMENT No 9 2 Description The strobe lights are installed on the wingtips The strobe light power supply is installed on the cabin floor under the right hand pilot seat The switch STROBE LIGHTS is placed on the right side of the instrument panel Its location is shown on drawing 2 2 2303004 Drawing 2 1 Location of strobe lights 1 Strobe light 2 Strobe light power s
18. 2 Lubricate all joints 3 For bolted joints torque limits refer to Chapter 16 6 11 4 2 Adjustment of wing flap displacement 1 Fix a protractor to the wing flap 2 Set the wing flap control lever to 0 15 40 and check the flap displacement in each position 0 159 2 i 40 5 2 3 The wing flap displacement may be corrected in a small range by extending or shortening the push rod 11 12 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 11 AT 4LSA AIRPLANE CONTROLS 11 5 Trim and balancing tab control The trim tab is controlled trough the torsion movement of the trim control wheel in the cabin The movement is driven through the intersecting axis gear in the trim mechanism on the torsion shaft and further on the screw in the screw gear The rotary movement of the screw is causing the movement of the intermediate lever axle and trough the pushrod is changing the trim tab deflection angle The change of the elevator deflection is causing the deflection of the trim tab according to the elevator deflection and uploading of the control system 12 9 1 11 and M M jel 9 10 6 4 3 UK N Ne sop _ 13 IN Figure 11 8 Trim and balancing tab control Trim and balancing tab Trim and balancing tab lever Pushrods Connectors Intermediate lever Screw gear Torsion shaft conduit Torsion shaft Torsion shaft lock
19. 4 Inspect parking brake valve for general condition and tightness 5 Inspect unions for leaks and proper operation inspect brake linings and disc for wear LANDING GEAR 1 Check tire pressure 2 Inspect nose gear for damage cracks corrosion and play in fixing joints 3 Inspect general condition of fork rubber shocks and nose gear 4 Inspect general condition and steering control and travel Check proper operation of shimmy dumper 5 Lubricate nose wheel fork axle 6 Inspect nose wheel tire for cuts uneven or excessive wear and slippage against to hub 7 nspect nose wheel hub for cracks damage corrosion and condition of bearings 8 Inspect main landing gear for damage cracks corrosion and plays at attaching joints 5 10 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 5 AT 4LSA INSPECTION Nature of Inspection Inspection time hrs LANDING GEAR cont 9 Inspect main wheel tires for cuts uneven or excessive wear and slippage against to hub 10 Inspect main wheel tires hubs for damage cracks corrosion and plays at attaching joints J FINAL STEPS a XIX ed D memet s compartment and cockpit MIMA units displacement 6 Inspect operation of electrical fuel pump and fuel shut off valve ur 8 Inspect oil pressure and temperature x 9 Inspect of operation of carburetor heater and a
20. Fig 1 1 Location of SL 30 system on instrument pane COM NAV SL 30 transceiver MD200 306 VOR LOC GS indicator RADIO COM circuit breaker NAV circuit breaker dup E us The SL 30 transceiver is used to carry on radio correspondence at frequencies between 118 MHz and 139 975 MHz on 760 channels at every 25 kHz The display is shown on Fig 2 1 the active frequency is displayed on left part of liquid crystal display The STBY frequency is preceded with letter s Additionally the unit is equipped with NAV localizer capabilities with 200 channels and LOC GS glide slope receiver The active NAV frequency is displayed on MAY 2007 18 1 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z o o SUPPLEMENT No 1 AT 4LSA right part of liguid crystal display Depending to the used mode right to NAV freguency are displaying additional NAV data The SL 30 transceiver has two antennas a standard COM antenna installed on top of the fuselage and NAV receiving antenna installed at top of fin Antennas location is shown at Fig 1 2 1 c 7 pr ru ed ME Seje pas O _ c Fig 1 2 Location of SL 30 system antennas 1 Standard COM antenna 2 NAV receiving antenna Basic physical specifications Operating temp range 20 to 55 Power supply 10 40V COM radio performance specifications Number of channels 760 Frequency range 118 136 975 Increments 25kHz Transmitter power oW Audio a
21. 10 Slab tail elevator lever 11 Slab tail elevator lever pushrod 12 Outrigger 13 Torsion shaft lock screw e par OY ee MAY 2007 11 13 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 11 AERO Sp z o o AIRPLANE CONTROLS AT 4LSA Figure 11 9 Trim and balancing tab control in the cabin TO Tab position indicator Trim 8 balancing tab control wheel Trim amp balancing tab control drive Console between the seats Torsion shaft Control drive fastening screws Torsion shaft conduit POO eM I 11 5 1 Trim and balancing tab control removing and installation Removing 1 Remove the faring on the end of the fuselage refer to section 11 1 2 Remove the trim pushrods 3 Remove the torsion shaft lock and remove the torsion shaft puling to the back of the fuselage 4 Disconnect the connectors from the intermediate lever 5 Remove the screw gear 6 Remove the slab tail elevator remove the clamping ring with the connectors 7 Remove the seats see sect 13 2 1 and console between the seats refer to section 13 1 1 8 Remove the trim control drive 11 14 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 11 AT 4LSA AIRPLANE CONTROLS Installation 1 Perform steps 1 8 in reverse order 2 Lubricate all joints 3 Check the trim and balancing tab deflection angles 11 5 2 Trim and balan
22. 17 4 2 MAY 2007 AERO Sp z o o CHAPTER 18 AT 4LSA SUPLEMENTS Section 18 SUPPLEMENTS Page Ts oo EI OL A 18 2 18 2 List OF introduced supplemen S oderam peut aaa 18 2 MAY 2007 18 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z SUPLEMENTS AT 4LSA 18 1 Introduction This Section contains relevant supplements needed for safe operation of the aeroplane when eguipped with the supplementary systems installed by the aeroplane manufacturer and specified below This Manual contains supplements which is physically installed on particular aircraft only 18 2 List of introduced supplements i wn mense w nn Pm _ w ann iF w F emm _ j x j 18 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z CHAPTER 18 AT 4LSA SUPPLEMENT No1 SUPPLEMENT No 1 GARMIN SL30 Nav Com System 1 1 East OE revisions iunio eee eo u q 18 1 2 1 2 Last of effective PALES uasa envie enel 18 1 2 Ty Desenptioilu ayu u 18 1 3 k era u i a 18 1 5 2 L Power u NA w uu 18 1 5 2 2 COM MOG occ 18 1 6 3 Disassembly and assembly of SL 30 18 1 8 3 1 Disassembling o
23. 90 110 C 230 266 F 130 C 110 130 C 167 194 F 194 to 230 F 75 90 C 275 F 90 110 C 230 275 F 135 C 110 135 C Oil temperature CHT 1112 to 1560 F 1560 1616 F 1616 1652 F 600 850 C 850 880 C 880 900 C 11 6 30 psi 30 to 72 5 psi 0 8 2 bar 101 5 psi 2 5 bar 72 101 5 psi 7 bar 5 7 bar Exhaust gas temperature Oil pressure 8 3 PLACARDS ON THE FIREWALL 1 On the firewall next to the oil tank OIL 3 6 US gts 2 On the firewall next to the brake fluid container BRAKE FLUID DOT 4 3 On the firewall next to the coolant overflow tank FLUID FOR ALUMINUM COOLERS MAY 2007 8 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 8 PLACARDS AERO Sp 2 o o AT 4LSA PAGE INTENTIONALLY LEFT BLANK MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp 2 o o CHAPTER 9 AT 4LSA AIRPLANE STRUCTURE CHAPTER 9 AIRPLANE STRUCTURE 9 1 Fuselage structure 9 2 9 2 Wing structure 9 4 9 2 1 Removal and installation of wing 9 5 9 2 2 Removal and installation of aileron 9 7 9 2 3 Removal and the installation of wing flap 9 8 9 3 Elevator structure 9 8 9 3 1 Removal and installation of elevator 9 9 9 3 2 Removal and installation of trim amp balancing tab 9 10 9 4 Rudder structure 9 10 9 4 1 Removal and installation of rudder 9 12 MAY 2007 9 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 9 AE
24. Slowly turn the propeller several times by hand and check for abnormal noise excessive drag and proper compression MAY 2007 3 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 3 AERO Sp z 0 0 SERVICING AT 4LSA Continue to turn the propeller until air is pumped into the oil tank which may be recognized by gurgling sounds Check level of oil and replenish if reguired Shut the oil filler cap Check condition and fastening of the air duct cooling the cylinders Check condition and fastening of the ignition cables and proper seat of their connectors on the spark plugs Check condition and fastening of the carburetors and of the drip shields below them Check condition and fastening of the box containing the inlet air filters Check engine mounts condition fastening of the engine mount to the ferrules of the fuselage Check fuel oil coolant and brake systems for leaks Check condition of the rubber hoses Check condition and fastening of the cooler unit and of its air duct Check condition and fastening of the exhaust system Check condition and fastening to the damper of the carburetor and cabin air heater Check condition and fastening of the cabin air mixing box Check condition and fastening of the air ducis Check free movement and full travel of the control cables for throttle choke and carburetor and cabin air heating Check condition and fastening of the equipment installed on
25. The airworthiness of the equipment installed in the airplane is dependent upon its technical condition It means that TBO for the equipment does not exist and the equipment is operated on condition 4 5 RUBBER HOSES The airworthiness of the rubber hoses used in the fuel oil and engine cooling systems is to be determined in accordance with the date of expiry marked on the hose 4 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o AT 4LSA 2 1 5 2 5 3 5 4 Table 5 5 5 5 1 5 5 2 5 5 3 5 5 4 5 5 5 5 5 6 5 5 7 5 5 8 2007 5 INSPECTION Introduction Inspection Reguirements and Periods Preflight Check Special Inspections INSPECTION REPORT A Primary Steps Propeller Group Engine Group Cabin Group Fuselage Group Wing Group Control System Group Brakes Group Landing Gear Group mm oo m Final Steps Test flight program Preparation for test flight Ground test Taxiing Take off Climb Cruise Speed increasing Landing AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 5 INSPECTION 5 2 5 2 5 3 5 3 5 4 5 4 5 4 5 5 5 8 5 8 5 9 5 9 5 10 5 11 5 11 5 12 5 12 5 12 5 12 5 12 5 13 5 13 5 13 5 13 5 1 CHAPTER 5 AERO Sp z 0 0 INSPECTION AT 4LSA 5 1 INTRODUCTION This chapter provides instructions for conducting inspections These inspections are describes in Paragraph 5 2 and 5 3 Repair or replacement
26. 1 1 List of revisions 10 2 1 2 List of effective pages 10 2 2 Description 10 3 3 Instrument panel lightning disassembly 10 3 4 Instrument panel lightning system diagram 10 4 MAY 2007 18 10 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 10 AT 4LSA 1 1 List of revisions T aa Concernin Revision nr Revision description Pa e 5 Date 1 2 List of effective pages Page number Issue date May 2007 May 2007 18 10 4 May 2007 p 18 10 5 May 2007 18 10 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z CHAPTER 18 AT 4LSA SUPPLEMENT No 12 2 Description Instrument panel lightning is turned on with switch 1 located at the instrument panel Brightness is controlled with use of dimmers 2 3 4 located right of circuit breakers Lightening of individual instruments is provided by BEZEL drowns installed between the instruments discs and instrument panel Fig 1 Instrument panel lightghting diming l 2 3 4 Automatic switch Individual instruments lightning dimmer Cockpit lightning dimmer TL lightning dimmer Cockpit lightning bulbs 3 Instrument panel lightning disassembly Disassembly Connection of cables to cockpit lightning bulbs is behind compass To remove cockpit lightning bulbs 1 Disassemble compass 2 Disconnect cables of cockpit
27. 1020 5 Distance of nose landing gear Bench mark 12 to fuselage vertical reference plane 0 40 39 in 0 10mm Displacement of engine from fuselage vertical reference plane measured ay the top of propeller spinner 0 0 59 in 0 15 mm Displacement of engine upward from the fuselage reference measured for the propeller spinner 3 54 0 59 in 90 15 mm Triangulation Distances between bench marks 6G and 1 6G and 2 6G and 4 6G and 5 6G and 10D and 10D Wing span 328 54 0 78 in 8353 20 mm Span of elevator 109 92 0 39 in 2792 10 mm Length 242 32 0 78 in 6255 20 mm Height 90 55 0 78 in 2300 20 mm NAME SIGNATURE 17 3 2 MAY 2007 FORM 174 CONTROL TEST FLIGHT REPORT CALL SIGNS Type AT 4LSA SETA NO ai ae eis Engine Propeller Weight kg Aircraft with equipment Fuel Load ballast poi Fuel PTAC EO NE PRE am Position of the C G OD SCA TASKS AND RANGE OF THE TEST FLIGHT Airfield barometric pressure Engine start time Engine stop time Fuel Carburetor Cylinder Pressure temp head Battery Alternator temp V delete as applicable MAY 2007 17 4 1 FORM 17 4 Engine start time Engine stop time Engine working time tle Landing Cutie i
28. 12 7 5 Removal of the fuel pressure sensor 1 The fuel pressure sensor is located at the branch of the excess fuel returning line and is fixed to the engine mount with bands To remove the sensor have cut the bands and disconnect the sensor from the line 12 7 6 Calibration of the fuel gauge and setting the reserve fuel 1 Level airplane on jacks 2 Remove the canopy and the fuel tank cover 3 Drain all fuel from the fuel tank 4 Switch on the battery 5 Turn both the EMPTY and the FULL knobs clockwise to the end 6 Fill the tank with 0 92 US gal of fuel 7 Turning the EMPTY knob set the fuel gauge to read O 8 Fill the fuel tank completely with fuel 9 Turning the FULL knob set the fuel gauge to read 1 1 1 0 Drain all fuel from the fuel tank and refill the tank again with only 3 56 US gal of fuel 11 Using the ground power supply increase the voltage up to 13 8 to 14 Volt 12 Using the knob of fuel quantity transmitter set the time of switching on the fuel reserve lamp 13 Lower the airplane onto its wheels and reinstall the fuel tank cover and the canopy 12 20 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 12 AT 4LSA POWER PLANT 12 8 OIL SYSTEM The AT 4LSA airplane is powered by the Rotax 912 engine which is fitted with a dry oil sump The oil pump of the engine pumps the oil from the oil tank through the oil cooler The oil tank is located on the firewall Subseque
29. 7 4 MA Y 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 8 AT 4LSA PLACARDS CHAPTER 8 PLACARDS 8 1 External placards 8 2 8 2 Internal placards 8 3 8 3 Placards on firewall 8 9 MAY 2007 8 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 8 PLACARDS 8 1 8 2 AERO Sp 2 o o AT 4LSA EXTERNAL AND INTERNAL PLACARDS NO GRIP On the rudder both sides On upper surfaces of the ailerons and of the trim amp balance tab NO STEP On the upper surface of the wing flaps next to the fuselage FUEL 18 5 US gal UNLEADED MIN RON 95 EN 228 PREMIUM Next to the fuel filler EN 228 PREMIUM PLUS AUTOGAS Min 91 Oct No Alcohol AVGAS 100LL EXTERNAL POWER Fuselage port side next to the power receptacle 12 V DC 36 psi On the port and starboard leg of the main landing gear or on the fairings 30 psi On the leg of the nose landing gear or on the wheel fairing 36 psi AERO Sp z o o AT ALSA Engraved placard made of stainless steel S N fastened to the fuselage underneath of the Ex horizontal tail MADE I N POLAND MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 8 AT 4LSA PLACARDS 8 2 INTERNAL PLACARDS 1 Next to the airspeed indicator one of the followning MAX MANEUVERI NG SPEED Va 90 KTSIAS Or MAX MANEUVERING SPEED 103 MPHIAS Or MAX MANEUVERING SPEED Va 166 h IAS 2 The igni
30. AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 13 AERO Sp z o o CABIN AT 4LSA 13 2 SEATS There are two seats in the cabin The seats form is made of fiberglass epoxy composite The space between the form and the upholstery is made of leather is filled with polyurethane foam and sponge The seat is attached to structure by pressed fit between the sidewall of the cabin and the console between the seats It is supported both the landing gear and spar boxes 13 2 1 Removal and installation of the seats Removal 1 Take the backrest of the seat and pull it upwards positively Do not interchange the seats a Installation 1 Press in the seat in its place Pay attention to the safety belts 13 3 UPHOLSTERY The instrument panel seats consoles are covered with natural leather The sidewalls with pockets for maps are made of a thin fiberglass epoxy composite which is covered with leather The space between the sidewall and the leather lined fiberglass epoxy composite is filled with foam The central tunnel is shielded with upholstery of thin fiberglass epoxy composite The floor of the cabin is covered with anti slipping plastic 13 3 1 Removal and installation of the upholstery Removal of the upholstery is necessary to access to the structure of the airplane 1 The elements of the upholstery of the central console sidewalls are fixed to the structure with screws To remove the element its screws need to be unscrewed 2
31. Installation 1 Perform steps 1 to 4 in reverse order 12 4 2 Replacing the air filters 1 Unscrew the covers from the air filters 2 Loose bands fixing the filters and remove the filters 3 Install new filters CAUTION ORIGINAL K amp N AIR FILTERS MAY BE PERIODICALLY CLEANED USING A CLEANING KIT OF THE SAME BRAND MAY 2007 12 11 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 12 POWER PLANT 12 5 EXHAUST SYSTEM AERO Sp z o o AT 4LSA The exhaust system consists of four exhaust pipes and the muffler To the cylinder heads exhaust pipes are mounted by means of flanges and bolts and to the muffler by means of springs The muffler is fixed to the heater by means of bands All is attached to the engine mount jT y e 2 1 Muffler 2 Front pipes 3 Fastening springs 12 12 In 29 o EY 87 Figure 12 3 Exhaust System 4 Heat exchanger 5 Rear pipes 6 Spring MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 12 AT 4LSA POWER PLANT 12 5 1 Removal and installation of the exhaust system CAUTION Prior to any work with the exhaust system be sure that the engine is cool and the exhaust has cooled down Removal Remove the engine cowling Remove the air inlet tunnel of the radiator refer to section 12 8 Remove the cabin heat exchanger Disconnect the bands fixing the muffler to carburetors air heat exch
32. Revision nr Revision description Pages 5 Data 1 2 List of effective pages May 2007 May 2007 May 2007 18 4 5 May 2007 18 4 4 May 2007 2 s 18 4 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o SECTION 18 AT 4LSA SUPPLEMENT No 4 2 Device description The stall warning unit informs pilot about the low speed of the airplane with a light and horn signal At a speed of 5 10 kts 9 3 18 5 km h lt 5 8 11 5 mph above the stall speed the red warning light on the instrument panel and audible warning signal is activated The stall warning installation consists of Stall warning sensor installed on the leading edge of the left wing audible warning unit installed behind the instrument panel and warning light installed on instrument panel near the airspeed indicator The stall warning sensor electric connector is located under the upholstery of the left side of the cabin The stall warning sensor is fastened to the left wing structure with the blind rivets In the case of removing the sensor the blind rivets should be removed CAUTION The location of the stall warning sensor was settled during the flight tests In the case of exchanging of the stall warning sensor the correction of its location could be necessary Moving of the sensor in the direction of the leading edge is causing the activation of the stall warning at higher speed UMA Figure 1 Inst
33. 12 00 00 Inspect overflow tank for damage and E as a result of overheating distortions and cracks Check fluid level refill as required Inspect filler cock Inspect fixing reliability of gasket under overflow tank Refer to ROTAX engine Maintenance Manual Chapter 12 00 00 Inspect overflow reservoir for damage discrepancies and securing Check fluid level and refill if required Inspect line connecting overflow reservoir for damage leaks and clogging Check that overflow reservoir vent port is unobstructed Refer to ROTAX engine Maintenance Manual Chapter 12 00 00 8 9 Inspect all oil lines for damage leaks lost elasticity as influence of overheating porosity and attachment reliability Check lines arrangement for loops and excessive bends Refer to ROTAX engine Maintenance Manual Chapter 12 00 00 Inspect all fuel lines for damage leaks lost elasticity as influence of overheating porosity and attachment reliability Check lines arrangement for loops and excessive bends Check metal fuel pipes on the engine and connecting link for damage and leaks Refer to ROTAX engine Maintenance Manual Chapter 12 00 00 MAY 2007 5 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 5 AERO Sp z 0 0 INSPECTION AT 4LSA Nature of Inspection Inspection time hrs C ENGINE GROUP cont 10 Inspect electric system wiring for damage wear and fixing reliability Refer to ROTAX engine Maintenance Manua
34. 18 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 12 AT 4LSA POWER PLANT 12 7 2 Removal and installation of the fuel valve Removal 1 Drain all fuel from the system 2 Remove the upholstery lining of the middle tunnel 3 Disconnect the controlling push rod from the valve 4 Disconnect the rubber hose 5 Unscrew the valve from the rigid line Re installation 1 Perform steps 2 to 5 in reverse order 2 For bolted joints torgue limits refer to Chapter 16 6 12 7 3 Removal and installation of the fuel filter Removal 1 Shut the fuel valve 2 Remove the engine cowling 3 Unscrew the fuel lines from the filter 4 Loosen the band fixing the filter to the firewall 5 Remove the filter Installation 1 Perform steps 3 to 5 in reverse order CAUTION WHEN REINSTALLING THE FUEL FILTER OBSERVE THE CORRECT FUEL FLOW WHICH IS MARKED WITH ARROWS OR IN AND OUT INSCRIPTIONS MAY 2007 12 19 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 12 AERO Sp z o o POWER PLANT AT 4LSA 12 7 4 X Removal and installation of the electric fuel pump Removal 1 Shut the fuel valve 2 Remove the engine cowling 3 Disconnect the fuel lines from the electric pump 4 Disconnect the electric line from the pump 5 Unscrew the fuel pump and remove from the firewall Installation 1 Perform steps 3 to 5 in reverse order 2 For bolted joints torque limits refer to Chapter 16 6
35. 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 6 AERO Sp z o o WEIGHTING AND BALANCE AT 4LSA 6 4 AT 4LSA AIRPLANE WEIGHTING 8 BALANCE REPORT SERLATZNO CALLSIGN usn ne Edges of cockpit walls leveled empty airplane with the unusable amount of fuel 0 92 US gal WEIGHING full with oil cooling and brake fluid equipment installed according to the Equipment List REFERNCE PLANE FIREWALL N REFERENCE CENTER OF GRAVITY GROSS WEIGHT TARE WEIGHT NET WEIGHT E Front Right scale sei AIRPLANE EMPTY WEIGHT Qp R Rn Rp Position of the center of gravity R Xsc b 3 Ne EP 51 57 M Qp Xs 6 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 6 AT 4LSA WEIGHTING AND BALANCE 6 5 EQUIPMENT LIST STANDARD EQUIPMENT ADDITIONAL EQUIPMENT Name Name Type Installation Wt 1394T100 7Z Artificial horizon GHO2L 3 RCA 26AK 2 Altimeter RCAISAK 1 Directional Gyro Indicator R C Allen DGO2E 3H Compass Radio transceiver VOR indicator E P GTX327 Engine monitoring instruments sedet AK 350 GPS GPSMAP Vertical speed indicator ENE Lo GPS Do MEM ni as Stall warning system ACT Cabin air intake AT3774000 E HN s i C Wheel fairings AT3 45 000 0 Anti colision strobe WHELEN
36. 9 5 Press CRSR button to confirm settings MAY 2007 18 5 11 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 5 AT 4LSA PAGE LEFT INTENTIONALLY BLANK 18 5 12 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 CHAPTER 18 AT 4LSA SUPPLEMENT No 6 SUPPLEMENT No 6 ELT AK 450 Dist OP TEV ISIONS 18 6 2 1 2 kistof effective uyu u ee lus feline 18 6 2 2 1 Device descriptiOTu s ud ae ne haar davi 18 6 3 UM ciuile et edendo treo onde b de 18 6 4 Do MG ANNI T 18 6 4 3 Battery installation and replacement 18 6 5 Al AUTO COIN SE aa itus caters ts ied ee oa ee tei 18 6 7 5T Periodic maintenance erie 18 6 8 Da TOWEL OULDUL LES 18 6 8 ae orle EI O AN SO O O O O A RR RANE 18 6 9 54 Modulation duty Cy Cle uuu eki e Nie delatae 18 6 9 5 5 Audio e erent 18 6 10 5 0 Power COnDSUTmDLIOLDG c ated a a ete 18 6 10 MAY 2007 18 6 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 6 AT 4LSA 1 1 List of revisions nis Concernin Revision nr Revision description Pages Date 1 2 List of effective pages Page number Issue date Page number Issue date 18 12 1 May 2007 18 12 10
37. 9 Tail navigation light bowl A615 10 Gasket W1283 18 8 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 18 AT 4LSA SUPPLEMENT No 8 11 Gasket 616 12 Gasket A427 A 13 White glass bowl A612 14 Screws fitting light to the wing tip only for A600 lights 4 Instalacja elektryczna wiatel pozycyjnych The navigation lights are attached to main bus with 10A automatic switch S23 which supplies lights Diagram of electrical system of navigation lights is presented at Fig 4 1 DESIGNATION DESCRIPTION TYPE LOCATION A675PR14 520 Left combined light lub AGOOPRI4 A675PG14 S21 Right combined nav light lub A600PG14 Right wing Automatic switch ea NAVIGATION LIGHTS 112 210 101 spl sp2 sp3 sp4 Right wing present in cause of simultaneous installation of strobe and nav lights Lampo zespolona lewo Lompa zespokina prowa szyna 14V E ilk a l l gg 3E E se T s ATS 61 441 0 16AWG SP1 REI SP3 16AWG b 16AWG SPIN els SPIN 16AWG om 18AWG SP2 SP5 Tum b 16AWG SP2N 2 SP5N 16AW Fig 4 1 Navigation lights electrical system diagram MAY 2007 18 8 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z 0 0 SUPPLEMENT No 8 AT 4LSA PAGE INTETNIONAL LEFT BLANK
38. AO IA n ZN EDAN DOGA RADIOSTACJA SL40 P N 430 6040 2xx Fig 5 1 SL 40 transceiver 5 COM configuration Menu is utilized during device installation or after removal of transceiver or NAV indicator It is highly recommended to take special care in cause of introducing any modifications into transponder s configuration Detailed description of additional advanced CMO NAV device and its settings are contained in pilot s manual SL 40 Nav Com Pilots Guide nr 506 0403 01 18 2 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 18 AT 4LSA SUPPLEMENT No 3 SUPPLEMENT No 3 GPSMap 296 396 496 Ja A RA A m A EOR 18 3 2 dite ar eas tO 18 3 2 3DSSCHDOOB je a 18 3 3 De GPS COMMON a y L 18 3 5 PANES ee AR OR t 18 3 7 2 2 Dasic aviation applieatlofis eee eco tede tipa tese dedu te pate lea la 18 3 8 2 9 Dire u iur weed 18 3 9 2 5 Creatior ot lotit va baba bena 18 3 9 2 9 dXd TUO BE DUDCUOPDS er naga RE ROA 18 3 10 3 GPS assembly and disassembly 18 3 10 3 1 GPSMap main unit assembly and disassembly 18 3 11 3 2 Antenna assembly and disassembly
39. Batery installation and replacement The AMERI KING CORP recommends to power the ELT with DURACEL MN1300 batteries alkali only In cause other batteries are used unit will not meet reguirement of TSO C91 and FAR 91 52 Battery must be replaced before its operational limits expire All cells must be replaced at the same time and all must have the same date expiration date It is recommended to replace them once a year in cause unit was transmitting for a period of over one hour FAR 91 52 requires batteries to be replaced Date of expiration must by printed on the cover of Main unit l Using the 3 32 Hex Driver supplied with the ELT remove the 4 Retaining Screws and Split Lock Washers which attach the Battery Case to the ELT Transmitter Assembly See Figure 4 If the ELT contains Batteries loosen the Screws evently a few turns at a time until the Battery contact Spring pressure is relieved 2 Remove Batteries from the Battery Case The six batteries which fit in the bottom of the Battery Case are designed to be a snug fit Make sure the expired Batteries are either discarded or removed from the work area before continuing to step number 3 Examine the Battery contacts any dirt or corrosion should be gently removed using an Electrical Contact Cleaner and a Stiff Brush Do not use Abrasive Cleaners or Materials to clean the contacts The contacts are Nickel and Gold Plated Spring Steel Abrasive Material will remove this plating If the contacts
40. In the event that the strobe light system has been out of service for a period of longer than one year an electrolytic condenser formatting procedure should be performed 1 Disconnect all the strobe lights from the power supply 2 Begin operating the power supply device on a voltage of ca 10 11 V for 10 to 15 minutes 3 Leave the power supply device disconnected for ca 10 minutes than connect all strobe lights CAUTION If the power supply is operated immediately at full voltage after a long period of non use there is a possibility that the condenser will become overheated and damaged MAY 2007 18 9 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o AT 4LSA SUPPLEMENT No 9 5 Strobe light electrical installation The strobe lights are connected to the contact bus through a separate 10 automatic circuit breaker S15 The strobe light electrical installation 1s shown on drawing 6 1 Unit Type Location Automatic circuit breaker STROBE LIGHTS 112 210 101 Instrument panel Strobe light power supply A413 AMDACF Cabin floor Strobe light A625D Left wing Strobe light A625D Right wing contact bus 14V bialy white czarny black czerwony red Drawing 6 1 Strobe light electrical installation 18 9 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z CHAPTER 18 AT 4LSA SUPPLEMENT No 10 SUPPLEMENT No 10 Instrument panel lightning
41. It is recommended to use a platform 14 ft long and of 9 ft width Prepare stands and supports the required amount of ropes strips foam sheet timber and plywood The wings and horizontal stabilizer should be removed before transport according to procedures given in this Manual Prior to any dismantling of the airplane the fuel should be drained and the battery disconnected Protect the push pull rods of elevator and aileron controls from knocking against the structure of fuselage and wings Cover up all openings in the fuselage and wings Recommended sequence for positioning the parts of the airplane on the platform 1 Position the fuselage on the platform Have it moored using the landing gear legs to fasten it to the platform Lock the cockpit canopy and apply a canvas Cover Fix the horizontal stabilizer under the fuselage Secure the wings on each side of the fuselage Figure 2 3 Positioning the dismantled airplane on the platform Sufficient distance should be provided between the various parts to avoid them knocking together or coming into contact during transport All parts must be so fastened so that they will not move during braking of the vehicle If possible the condition of the transported airplane is to be inspected from time to time during the journey Remember that the transporting vehicle must be marked according to the local traffic regulations Tools Required Metric Wrench Set 5 mm to 19 mm Metric Soc
42. May 2007 18 12 6 May 2007 18 12 7 May 2007 18 12 8 May 2007 18 12 9 May 2007 18 12 5 May 2007 __ 18 6 2 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 CHAPTER 18 AT 4LSA SUPPLEMENT No 6 2 1 Device description ELT is used for safety purposes only The device is transmitting at the 121 5 MHz and 243 MHz frequencies System is composed of mobile transmitter which is installed under right seat and telescopic antenna installed in front of communication antenna ELT control is installed on instrument panel Transmitter has it independent power supply unit If removed from aircraft and installation of antenna unit can by used as a mobile device Fig 1 ELT system 1 Transmitter Control panel Antenna mw omm de Communication antenna MAY 2007 18 6 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z 0 0 SUPPLEMENT No 6 AT 4LSA 2 2 ELT Remote unit Fig 2 ELT remote unit 1 Switch ON 2 Control light 3 Switch RESET 2 3 ELT main unit Main switch 1 can be placed in three positions switched ON switched constantly ON and automatically ON ARM Fig 3 ELT main unit 1 Main switch Control light Switch RESET 2 3 4 Antenna jack 5 Microphone jack 6 Control panel jack 18 6 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 CHAPTER 18 AT 4LSA SUPPLEMENT No 6 3
43. OK button appear on a screen Press ENTER A course is plotted you re your location to the selected destination 1 4 Creation of Flight Plan To prepar flight plan follow procedure Press MENU button twice to show Main Menu 2 Highlight Router from vertical list of tabs 3 Highlight first available blank route slot and than press ENTER 4 Press ENTER to find items to add to the router MAY 2007 18 3 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 3 AT 4LSA 5 Selects the identifier facility name or city field and than press ENTER 6 Press ENTER when the point is shown 7 With the on screen OK button highlighted Press ENTER The point is addend to the router 8 When you are finished adding points to your route press QUIT to view the Routes tab again Your new route is highlighted 9 Pres Menu select Active Route and press Enter to start navigating your route 1 5 Additional functions GPSMAP 296 396 496 a part from basic read out of flight plan is offering several additional functions depending on model and software used This can be alarming functions obstacles warnings weather service GPSMap 396 496 and many more Detailed description of GPS operations including initial setting fight plan data intro settings modifications can be found in Owner s Manual Portable Aviation Receiver GPS MAP 496 nr 190 00693 00 18 3 10 MAY 2007 AIRPLANE MAINTENA
44. PINHOLES MAY 2007 16 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 16 AERO Sp z o o REPAIRS AT 4LSA Repair of corroded steel parts 1 Remove corrosion from the corroded area and degrease the area with acetone 2 Prime the prepared area with primer for steel and paint it 16 3 REPAIR OF BOLTED OR SCREWED JOINTS All bolted joints of airplane structure have H7 g6 fit Table 16 1 Maximum play for fitted joints Diameter of the joint Maximum operation play mm in mm 3 6 H7 g6 0 118 0 236 0 00142 Above 6 10 7 96 0 236 0 394 0 044 0 00173 0 394 0 709 0 071 0 00280 sleeves of nose leg Above 0 24 30 H7 g6 fork axis 0 709 1 181 0 060 0 00236 diameter bolt H7 g6 0 012 0 00047 0004 0 00016 BOO 2205 0 012 0 00047 0015 0 00059 0 005 0 00020 Above 6 10 0 236 0 394 Por o 0 021 0 00083 0 007 0 00028 Above 18 30 0 709 1 181 0 0 0 020 0 00079 H7 f7 0 018 0 00071 0 006 0 00024 Above 10 18 0 394 0 709 0 0017 _0 00067 If the play in the joint exceeds the permissible value recommended by the manufacturer of the airplane the repair must be made by replacing the bolt with an oversize first bolt with the diameter increased by 10 2 g6 or oversize second bolt with the diameter increased by 0 5 06 and by reaming the hole increasing it by the same value with tolerance H7 If there is excessive pla
45. Push on the propeller control surfaces wings or fairings The taxiing procedure with engine running 1 Brake Release 2 Control stick fully aft 3 Practice slow taxiing making use of the rudder If the rudder is not effective enough apply the brake in small amounts only in order not to slow the aircraft down more than necessary Avoid braking when the wheels are running into hollow in the ground CAUTION Running the engine at higher power settings than required necessary for taxiing should be limited to minimum 2 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 2 AT 4LSA HANDLING 2 2 NOOR WD 2 3 PARKING Position the airplane facing into the wind Apply chocks to the main wheels Fasten the control sticks with the seat belts Brake the wheels and set parking brake Lock the canopy of the cabin and apply canvas cover if required Set the propeller horizontally The brakes and stick can be locked with use of towing bar that is stowed as described at point 2 6 of this Manual Aircraft Tie Down For aircraft tie down use lugs located at the wing tips nose gear tow bar fittings nose wheel fork and tail skid li 2 4 Face airplane into the wind if possible Put chocks in front of the main wheels Lock the aileron and stabilator controls using front seat belts or control surface blocks Secure tie down ropes to the
46. The right wing tip is equipped with green light The left wing is equipped with red light Additionally both combined lights are equipped with white lights Navigation lights are turned on with NAVIGATION LIGHTS switch placed on rights side of instrument panel If the aircraft is equipped with combines navigation lights and strobe lights it is equipped with combined bulbs A600PRI4 red and A600PG14 green that are integrated with strobe light Those sets are replacing combined lights A675PR14 and A675PG14 respectively Detailed description of strobe lights is in Supplement 24 Strobe lights Rys 2 1 Location of instruments and switches on instrument panel 1 NAVIGATION LIGHTS switch MAY 2007 18 8 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z 0 0 SUPPLEMENT No 8 AT 4LSA 3 Combined navigation lights disassembly Disassembly 1 Screw out screws fitting lamp cover 2 pcs Screw out screws fitting lamp footing to the wing tip 3 pcs Slid out lamp with its electrical cables from the wing tip 239 92 19 Disconnect cables connectors Assembly 1 Execute points 4 in reversed sequence Fig 3 1 Assembly of combined NAV light 1 Assembly plate A605 2 Discharger lamp 3 Bulb 14V W1290 14 4 Green bowl W1284 G or Red bowl W1284 R 5 Cover 6 Pocket A507 7 Screw 6 32 x 5 16 MS51959 27 8 Bulb 14V A508 14
47. and drill the holes in the frame 5 Put the frame on the skin and drill holes for rivets of 23 2 mm in the frame and in the skin 6 Put the frame inside the skin and fix it with retainer 7 Cut a plate matching to the cut out in the skin made of PA7 ta sheet metal of gauge b 8 Mark and drill holes of 23 2 in both the plate and frame 9 Prime all new elements 10 Assemble and rivet the elements using pop rivets of 23 2 mm Skin gauge Plate gauge b Frame gauge a mm mm mm Z 0 4 z 0 4 Z 0 5 Z 0 5 0 6 16 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 16 AT 4LSA REPAIRS MAY 2007 Figure 16 2 Skin Repair between the ribs 1 Frame 5 Pop rivets 2 Plate 6 Structure elements ribs spar 3 Repaired skin shapes 4 Blind rivets 16 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 16 AERO Sp z o o REPAIRS AT 4LSA 16 4 2 Repair of cracked rib flanges frame or stiffening Application all accessible ribs frames and structure shapes repair 1 To prevent enlarging drill hole of 21 5 mm at both ends of the crack and strengthen with an angle bar of matching shape made of duralumin with the flange thicker by 0 2 mm than the damaged element 2 Prime a new element 3 Rivet the flange and rib use Apply
48. brake effectiveness decreases gradually due to changes in temperature and possible leakage For extended parking periods use chocks tie downs or additional protection against movement 10 3 3 Removing and installation of the parking brake Removing 1 Drain the braking fluid from the braking installation 2 Remove the valve lever Remove the central console and the upholstery on the tunnel between the seats 4 Unscrew bracket screws 5 Unscrew screws attaching valve to bracket and remove valve from central console 6 Disconnect lines from the valve 7 Remove the bumper and the valve base 10 12 Installation Install the bumper and the valve base Install the connectors to the brake hoses refer to section 10 3 6 and connect them to the parking brake valve connectors Perform steps 2 5 in reverse order Fill with the braking fluid and vent the braking installation see sect 10 3 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 10 AT 4LSA LANDING GEAR 10 3 4 Removal and installation the brake cylinder see Figure 10 6 Figure 10 6 Installation the brake cylinder 1 Brake cylinder 3 Brake pedal 2 Hoses 4 Attaching bolts Removal 1 Drain all brake fluid from the system using the bleeding valves of the brake calipers CAUTION The brake fluid is caustic and reacts aggressively to most painted surfaces and rubber elements A
49. brake fluid is used See also 3 13 Servicing materials The brake fluid container is located in the engine compartment on the firewall and is visible and accessible after opening the port cover of the upper engine cowling There are two marks on the container marking the lower and the upper level of the brake fluid The transparency of the container allows direct visual inspection of the amount of fluid To replenish the brake fluid unscrew the cap of the container pour in brake fluid until the level reaches the maximum mark and screw the cap on tight Using a funnel will help in this task 3 11 Tire Inflation The tire inflating procedure is straight forward and does not require any explanation WARNING It is prohibited to inflate the tires from a compressed air bottle without an adequate pressure regulator 5 00 4 Nose wheel 36 B 2 5 0 2 bar 5 00 5 8833psi 23 02ba 0 2 bar 1 x 150 15 x 6 00 5 Main wheel 36 3 psi 2 5 0 2 bar 5005 O 00 5 3 18 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 3 AT 4LSA SERVICING 3 12 Lubrication When lubricating only completely dry and clean tools are to be used Prior to any lubrication all dirt old grease and traces of corrosion must be removed from the surfaces which are to be lubricated Lubrication may be made by hand with a grease gun or with an oilier Any excess of lubricant is to be removed with a clean piece of fab
50. cracked rib flanges frame or stiffening 16 8 16 4 3 Repair of trailing edges 16 9 16 4 4 Repair of dented or cracked skin on angle edges 16 9 16 4 5 Replacement of the fuselage structure stiffening 16 10 16 4 6 Loose rivets replacment 16 11 16 5 Repair of composite parts 16 12 16 5 1 Composite cracks or small holes 16 13 16 5 2 Repaired composite parts painting 16 14 16 6 Bolted joints and values of the torque moments 16 15 MAY 2007 16 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 16 AERO Sp z o o REPAIRS AT 4LSA 16 1 GENERAL INFORMATION The information given here applies to the repair of minor damage to the airframe where the replacement of parts is either not necessary or practicable This chapter contains the methods recommended for repair of parts and subassemblies which do not affect the airworthiness It also contains procedures on how to restore the correct status of parts and subassemblies if they have been affected Repairs other than the type mentioned above must be performed in authorized maintenance organizations or by the airplane manufacturer In case of doubt always consult the AERO Service Department see Basic Information Chapter 0 16 1 1 Tools and materials for repair of minor damage TOOLS For repair of minor damage standard commercially available tools may be used MATERIALS Parts of the structure Always use the same materials as originally used on the part to be repaired If the same
51. firewall 9 Airplane structure 9 1 Fuselage structure 9 2 Wing structure 9 2 1 Removal and installation of wing 9 2 2 Removal and installation of aileron 9 2 3 Removal and the installation of wing flap 9 3 Elevator structure 9 3 1 Removal and installation of elevator 9 3 2 Removal and installation of trim amp balancing tab 9 4 Rudder structure 9 4 1 Removal and installation of rudder 0 4 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o AT 4LSA 6 2 6 2 6 3 6 6 6 7 6 9 6 10 7 2 7 3 7 4 8 2 8 3 8 9 9 2 9 4 9 5 9 7 9 8 9 8 9 9 9 10 9 10 9 12 MAY 2007 AERO Sp z o o CHAPTER 0 AT 4LSA BASIC INFORMATION 10 Landing gear 10 1 Nose landing gear 10 2 10 1 1 Removal and installation of nose wheel 10 3 10 1 2 Removal and installation of fork 10 4 10 1 3 Removal and installation of fork axle 10 4 10 1 4 Removal and installation nose leg 10 5 10 2 Main landing gear 10 6 10 2 1 Removal and installation of main wheel 10 7 10 2 2 Removal and installation of main leg 10 8 10 3 Brake system 10 9 10 3 1 Brake fluid replacement 10 11 10 3 2 Removal of brake cylinder 10 11 10 3 3 Brake pads replacing 10 12 10 3 4 Brake system bleeding 10 13 10 3 5 Brake disc replacing 10 14 10 3 6 Installation method of the brake hose unions 10 14 10 3 7 Replacing the brake disc 10 15 10 3 8 Installation method of the brake line terminals 10 15 10 4 Rear skid 10 16 10 4 1 Removal and installation of skid 10 17 10 5 Wheel f
52. go flat for longer periods of time may lead to them becoming permanenily deformed Figure 2 6 Storage of the fuselage with engine and landing gear removed 2 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 3 AT 4LSA SERVICING CHAPTER 3 SERVICING 3 1 Daily pre flight inspection 3 2 3 2 Starting the engine 3 9 3 3 Engine test run 3 11 3 4 Switching off the engine 3 13 3 5 Using the external ground power 3 13 3 6 Daily post flight inspection 3 14 3 7 Refueling 3 14 3 8 Replenishing engine oil 3 15 3 9 Replenishing engine coolant 3 17 3 10 Replenishing brake fluid 3 18 3 11 Inflating the tires 3 18 3 12 Lubrication 3 19 3 13 Servicing materials 3 19 3 14 Cleaning and washing 3 20 3 14 1 Cleaning of outer surfaces of the airplane 3 20 3 14 2 Cleaning the Plexiglas canopy 3 20 3 14 3 Cleaning the cockpit interior 3 21 3 14 4 Removing snow 3 21 3 14 5 Removing ice or hoarfrost 3 21 3 14 6 Cleaning the engine 3 22 3 14 7 Cleaning the propeller 3 22 MAY 2007 3 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 3 AERO Sp z 0 0 SERVICING AT 4LSA 3 1 Daily pre flight inspection This inspection is to be performed commencing at the cockpit and walking in a clock wise direction around the airplane If not specified otherwise all tasks are visual inspections aimed to detect damage and the state of wear During this inspection check also supplementary equipment described in chapter 18
53. instruction for those components found to be unserviceable at inspection may be found in chapter covering applicable aircraft system The tasks specified for the scheduled inspections may only be completed by appropriately licensed mechanics The aim of every inspection is to detect damage deformation cracks corrosion dirt non reliable fastenings excessive play or friction excessive wear missing safety locking leaks leakages of operational fluids improper operation and movement of the airplane assemblies or components 5 2 INSPECTION REQUIREMENTS AND PERIODS Required inspection procedures are listed in Table V 1 Inspection procedure is broken down into ten major group which are Primary Steps Propeller Engine Cabin Fuselage and Empennage Wing Control System Brakes Landing Gear and Final Steps The first column in each group lists the inspection or procedure to be performed The second column is divided onto six columns indicating the required inspection intervals of 25 hour inspection 50 hour inspection 100 hour inspection 200 hour inspection 600 hour inspection and annual inspection Each inspection or operation is required at each of inspection intervals is indicated by a X mark an item is not entirely accessible or must be removed refer to the applicable chapter of this manual for instruction on how to gain access to remove them In addition after the first 25 hours from beginning the use o
54. lugs specified above and attach to the ground anchor Leave sufficient slack on ropes to avoid aircraft damage due to rope contraction caused by moisture Apply the cover to the pitot and static sensors Close the canopy and put on the cover Set the propeller horizontally JACKING Following procedure gives the instructions for proper jacking the airplane 1 2 Locate one of the jacks under the nose landing gear ferrule and other two on each side next to landing gear legs under the maingear carry through box Apply wooden blocks between each jack and airplane structure Raise the jacks until all three wheels are clear of the surface Avoid swaying MAY 2007 2 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 2 AERO Sp z o o HANDLING AT 4LSA 2 5 LEVELING After lifting the airplane should be leveled so that the cabin wall edges are horizontal see Figures 2 1 and 2 2 po LEVEL EDGES OF CABIN WALLS Figure 2 1 Lateral leveling WATER LEVEL EDGE OF d DEED Hn WOODEN BLOCKS Figure 2 2 Longitudinal leveling Leveling of an airplane which is positioned on scales is done by applying pads between the wheels and the scale or by deflating the tires After completing the weighing have the tires properly inflated 2 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 2 AT 4LSA HANDLING 2 6 Tow bar The towing bar is available in two v
55. material is not available a substitute of the same strength properties must be used Parts made of composite None of the composite components are part of the integral strength of the structure Epoxy or polyester resins may be used for repairs The number of layers of fiberglass depends on the thickness of the composite Fiberglass of 100 to 200 g m basic weight should be used 16 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 16 AT 4LSA REPAIRS Primer fillers paints To prime the repaired surfaces primers specially intended for this purpose must be used In areas where the anodic layer has been removed primer for aluminum must be used In cases where the anodic layer has not been affected primer for anodized aluminum must be used The same applies in the case of cadmium plated steel To repair the paint commercial automotive fillers and paints should be used 16 2 CLEANING AND PROTECTING CORRODED SURFACES NOTE BELOW DESCRIBED METHODS SHOULD ONLY BE USED WHERE THE CORROSION ONLY AFFECTS THE SURFACE AND WHERE THERE IS DEFINITELY NO Repair of corroded aluminum surfaces 1 Remove the corrosion from the corroded area using materials which do not leave deep scratches Wash the area with clean water and dry it with compressed air Degrease using acetone Prime the prepared area with primer for aluminum and paint it NOTE CORROSION OF ALUMINUM HAS THE FORM OF WHITE DEPOSITS OR
56. rod so that the profile of the elevator fits to profile on the fuselage 4 Remove the locking pins from the torque tube and from the intermediate lever 5 Check smoothness of the elevator displacement and the minimal distances between the elements of the system and the nearest elements of the structure ptis N mm 3 dus aree LE lt 8 HE S LITE 4 7 c ov imer CONUS Figure 11 2 Adjustment of elevator displacement 1 Control stick 5 Intermediate lever 2 Torque tube 6 Electric bonding cable 3 Front push rod 7 Holes for locking the system in neutral 4 Rear push rod 8 Push rod coupling the aileron actuator MAY 2007 11 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 11 AERO Sp z o o AIRPLANE CONTROLS AT 4LSA 11 1 3 Mass balancing of the elevator The mass balance of the elevator is a casting made of lead bolted to the outrigger of the elevator actuating lever The mass balance of the elevator must be checked after every painting or paint repair as well as after every repair of the elevator The elevator completely painted and ready to be installed to the airplane with trim tab trim tab push rod and its shielding installed must be balanced on a stand 3 as shown on Figure 11 3 Figure 11 3 Mass balancing of th
57. set to IDLE and the carburetor heating must be set to ON RECOMMENDATION Engine preheating using a ground hot air blower assists engine starting Utilizing of external power sources as indicated under 3 5 saves battery power 3 10 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 3 AT 4LSA SERVICING 3 3 Engine test run 1 Brake Apply 2 Control stick Fully Aft 3 Indications of engine monitoring Check instruments within the green range 4 Engine speed 4000 rpm Set 5 Ignition switch to position 1 Set 6 Engine speed Read indicated value 7 Ignition switch to position 2 Set 8 Engine speed Read the indicated value 9 Throttle lever into full open position Set 10 Maximum engine speed Read the indicated value 11 Engine speed at IDLE 1400 Check 1600 rpm NOTE The engine speed drop with only one ignition unit must not exceed 300 rpm The maximum engine speed difference between position 1 and position 2 must not exceed 120 rpm The maximum engine speed on the ground depends on the propeller and is about 5300 rpm 12 Carburetor heating OFF RECOMMENDATION Setting the carburetor heating to ON results in a noticeable drop of engine speed MAY 2007 3 11 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 3 AERO Sp z o o SERVICING AT 4LSA 13 Engine Allow to cool at 2000 rpm for a short time only NOTE To avoid boiling
58. slam 20 19 18 17 16 11 Fig 2 1 SL 30 transceiver frond display 1 Power Volume Sguelch knob 2 Photocell 3 Transmit annunciator 4 Active frequency 5 Standby frequency 6 Function annunciators 7 Bering 8 TO FROM indication 9 Graphic CDI 10 Large outer knob 11 Small inner knob 12 ENTER button 13 SELECT button 14 IDENT button 15 TO FROM button 16 OBS mode select button 17 System setting select button 18 NAV mode select button 19 COM mode select button 20 Frequency FLIP FLOP select button 18 1 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 SECTION 18 AT 4LSA SUPPLEMENT No 1 Fig 2 2 MD200 306 encoding altimeter 1 Azimuth face 2 NAV annunciator 3 GPS annunciator 4 Glide slope deviation pointer 3 Back Course annunciator 6 Azimuth knob 7 Azimuth pointer 8 VOR LOC deviation pointer 9 TO FROM annunciator 10 Glide slope OFF flag 11 NAV off flag MAY 2007 18 1 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z o o SUPPLEMENT No 1 AT 4LSA 3 SL 30 transceiver disassembly and assembly 3 1 Disassembly of SL 30 main unit Disassembly 1 Remove screw in front panel to unlock the transceiver 2 Sidle out transceiver from a slot in instrument panel Assembly Execute steps 1 2 in reversed sequence If necessary the slot can be disassemble too by removing canopy and co
59. supports came from 7 Remove the pedals 8 Remove the guiding rollers from the partition frame and the central tunnel 9 Remove the cables and the guiding rollers pulling them forward 10 Remove linkage rollers from spar box Re installation 1 Perform steps 1 to 10 in reverse order 2 For bolted joints torgue limits refer to Chapter 16 6 CAUTION Ensure that the cables do not cross 3 Fill the brake system with brake fluid and MAY 2007 11 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 11 AERO Sp z o o AIRPLANE CONTROLS AT 4LSA 11 3 2 Adjustment of rudder displacement 1 Set the rudder in neutral position 2 Using the connecting links of the cables set the ruder pedals in one line 3 Moving manually the rudder check if the setting of the stops refer to section 9 4 responds to the rudder displacement of 30 2 to the left and to the right CAUTION Displacement angle of the rudder must be measured in the plane perpendicular to the axis of rudder rotation 4 Adjust the stops of the rudder pedals to provide correct rudder displacement 5 Check smoothness of the rudder displacements All elements of the system may only be in contact with the structure through the fastenings stops or guides 6 Regulate the tension of the tension members and linkage cables so that the rudder returns to the neutral position when there is more force acting to the pedals 11 10 MAY 2007 AIRPLANE
60. the Notch Filter as appropriate 1 e 243 notch when measuring 121 5 MHz 3 The ELT should be within 50ppm 6 075 KHz of 121 500 000 Hz 4 Repeat with the 121 5 MHz Notch Filter The ELT frequency should be within 50 ppm 4 12 150 KHz of 243 000 000 Hz NOTE The Amplitude Modulation may be suppressed by connecting a Microphone to the MIC input of the ELT Main Unit with its key pressed in 5 4 Modulation duty cycle 1 Connect the Equipment as shown below ELT AK 450 UNEAR DETECTOR OSCILLOSCOPE 2 Acquire waveform 3 Using the following formula verify that the Modulation Duty Cycle is between 33 and 55 Duty Cycle A B x 100 5 5 Audio modulation MAY 2007 18 6 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z 0 0 SUPPLEMENT No 6 AT 4LSA During the swept tone portions the audio should sound like an ELT Also the Morse code if equipped on the ELT should be checked for clarity and accuracy Perform the transmitter tests by activating the ELT and listening on 121 5 MHz Be suro to follow the procedures as outlined under Paragraph 3 3 Transmitter Functional Test An Amplitude Modulation AM Broadcast Radio Receiver should then be used to determine if energy is being transmitted from the Antenna Hold the AM Broadcast receiver about 6 inches from the ELT either al the unit or from the front panel switch An ELT aural tone should be heard on the AM Broadcast Radio Receiver
61. the actual amount of fuel in the tank in gallons provided the airplane is level i e the edges of the cockpit walls are positioned horizontally If the airplane is refueled from canisters a funnel with a fine filter is to be used When ground refueling systems or vehicles are used the ground conductor is to be connected to the exhaust pipe or to the brake disc NOTE At every refueling it is also recommended to check engine oil level 3 14 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 3 AT 4LSA SERVICING 3 8 Replenishing engine oil A detailed description of the oil system is given under 12 8 Oil system According to the Operational Manual of Aviation Rotax 912 Engines item 10 2 3 Lubrication agents the following oils are to be used Ambient temperature Class of viscosity From 23 F 5 C to 104 F 40 C SAE 20W 50 SAE 20W 40 From 5 F 15 to 104 F 40 SAE 15W 50 SAE 15W 40 From 13 F 25 to 104 F 440 SAE 10W 40 From 22 F 30 C to 104 F 40 SAE 5W 50 SAE 5W 40 Maximum capacity of the oil system is 3 6 US ats NOTE The temperature ranges for similar SAE classes of viscosity are quite similar therefore it is not required to change the oil due to short term variations of temperature Checking the oil level 1 Check the key is removed from the ignition switch 2 Open the starboard cover of the upper engine cowl
62. the excess fuel into the tank is located From the tank the fuel flows to the filter then through a rubber hose to the fuel valve and then through a rigid line passing the firewall to the electrical emergency pump From this pump via the fine filter the fuel flows to the engine driven pump The engine driven pump is connected to the distributor From the distributor two lines lead the fuel to the carburetors while the third one returns excess fuel to the fuel tank Into the returning line a T connector is connected which connects to the fuel pressure sensor At the end of the returning line there is the fuel returning terminal with the calibrating jet which provides correct fuel pressure in the fuel feeding line All hoses of the fuel system located in the engine compartment are protected with fire resisting sleeves 12 16 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o AT 4LSA CHAPTER 12 POWER PLANT Figure 12 6 Fuel system 1 Fuel tank 9 Rigid lines 2 Filler throat with cock and rule 10 Fuel filter 3 Fuel gage 11 Engine fuel pump 4 Fuel valve push rod 12 Fuel distributor 5 Fuel drain valve 13 Flexible hoses 6 Drain and ventilation fittings 14 Fuel pressure sensor 7 Fuel valve 15 Returning fuel fitting with nozzle 8 Fuel pump electrical 16 Over tank cover Figure 12 7 Drai
63. the firewall Check condition and fastening of the cables of the electric system Check condition and fastening of the battery box Check the ferrules of the nose wheel and their fastening to the firewall Check level of brake fluid and replenish it if required Check level of engine coolant and replenish it if required Check the holes in the plug of the overflow tank are clear Check condition and fastening of the sensors for fuel pressure oil pressure oil temperature and cylinder head temperature 3 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 3 AT 4LSA SERVICING Check condition and fastening of the oil tank venting line and the draining lines After completing the inspection of the engine compartment proceed with the engine test run 3 2 Starting the engine WARNING Prior to starting any task with the engine check that the key is removed from the ignition switch 1 Wheel chocks Parking brake Apply to the wheels Cool engine 1 Propeller Turn several times by hand Slowly turn the propeller by hand and check for abnormal noise excessive drag and proper compression 2 Fuel valve Open push forward 3 Choke To be set ON pulled NOTE To lock the pulled choke knob turn it clockwise about 30 4 BATTERY GENERATOR ON up and ALTERNATOR switches 5 FUEL PUMP switch ON up 6 Throttle lever Set to idle or opened by 10 7 The are
64. the forth digit entered Pressing the CLR key modes the cursor back to the previous digit Pressing the CLR key when the cursor is on the first digit of the code or pressing the SCRSR key during code entry removes the cursor and cancels data entry resolving the previous code You may press the CLR key up to five seconds after code 1s complete to turn cursor to the forth digit The numbers 8 and 9 are not used for code entry only for entering a Count Down time contrast and display brightness and data selection in the Configuration Mode Fig 2 2 Code selection Important Codes 1200 the VFR code for any altitude in the US refer to ICAO standards elsewhere 7000 the VFR code commonly used in Europe refer to ICAO standards 7500 hijack code Aircraft 1s subject to unlawful interference 7600 Loss of communication 7700 Emergency 7777 military interceptor operations never squaw this code 0000 military use not enterable WARNING DO NOT ACTIVATE TRANSPONDER WITH SELECTED CODES 0000 7700 7777 7700 IS RESERVED AS A EMERGENCY CODE 18 5 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z CHAPTER 18 AT 4LSA SUPPLEMENT No5 3 Transponder disassembly and assembly Disassembly Tools Required Flat Head Screwdriver 1 Loose transponder by screwing out fitting screw on front panel 2 Sidle out transponder from slot It is possible to disassembly whole NAV
65. the riveting 4 Prime and paint the area as required MAY 2007 16 11 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 16 AERO Sp z o o REPAIRS AT 4LSA 16 5 Repairs of composite parts Application minor repairs of composite parts and painting Moulds are not necessary Figure 16 7 Main composite parts of the fuselage 1 Lower engine cowling 8 Rudder tip 2 Spinner 9 Flap control housing 3 Upper engine cowling 10 Fuselage main leg fairing 4 Over tank cover 11 Wheel fairings 5 Canopy frame 12 Wing fuselage fairing 6 Canopy fuselage fairing 13 Wing tips 7 Vertical fin fuselage fairing 14 Slab tail tips 16 12 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o AT 4LSA CHAPTER 16 REPAIRS 16 5 1 1 2 3 Composite cracks hard spots or small holes Localize a position of a damage apply pressing tapping of bending Remove painting Determine a shape of the edge of the cut out for glass fiber composite minimum 20 mm 0 8 in for carbon Kevlar carbon fiber composite 40 mm 1 6 in 4 Carry out the cut out using a file a chisel or emery fabric of grade 40 to 80 5 Choose fabrics as used in manufacturing process Number of layers should be calculated in such a way that the thickness of a patch will be the same as thickness of repaired part Remember about gradation of layers In case when Kevlar carbon fabric is used the face layers should be fiber glass
66. with acid 1 Fill the battery with battery acid with a specific gravity of 1 285 until the separator plates are covered 2 Tilt the battery carefully to release air bubbles in the acid In case when necessary replenish acid 3 Leave the battery for an hour 4 Check the acid level and close the caps and clean the battery 5 Charge the battery for approximately 18 to 24 hours up to moment when specific electrolyte density and voltage will be stabilized The temperature of the acid should be between 60 F to 110 F When the battery is fully charged the acid should have electrolyte density of minimum 1 275 Charging during operation Charge the battery with the current of 3 A In case bubbles when appear reduce current value to 1 5 A When the battery is fully charged the level of the acid should reach a slot or a sleeve of a cap A battery filled with acid and not utilized must be charge every 3 months MAY 2007 15 25 AIRPLANE MAINTENANCE MANUAL CHAPTER 15 AERO Sp z o o ELECTRICAL SYSTEM AT 4LSA PAGE INTENIONALLY LEFT BLANK 15 26 MAY 2007 AIRPLANE MAINTENANCE MANUAL AERO Sp z o o CHAPTER 16 AT ALSA REPAIRS CHAPTER 16 REPAIRS 16 1 General information 16 2 16 1 1 Tools and materials for repair of minor damages 16 2 16 2 Cleaning and protection of corroded surfaces 16 3 16 3 Repair of bolted or screwed joints 16 4 16 4 Airplane structure panel repairs 16 5 16 4 1 Skin repair between the ribs 16 6 16 4 2 Repair of
67. 0 17 10 5 Wheel fairings 10 17 MAY 2007 10 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 10 AERO Sp z o o LANDING GEAR AT 4LSA 10 1 NOSE LANDING GEAR see Figure 10 1 The nose landing gear consists of four main elements the steel leg 1 the rocker 16 the wheel 5 and the shock absorber 7 The steel made leg is attached to the fuselage structure in two points The shock absorption of the nose wheel goes via the rocker and the shock absorber the last consisting of rubber discs Additionally leg shock absorber rubber discs 8 of the same kind absorb the shocks at the point where the leg is fixed to the fuselage structure To reduce vibration of the nose wheel a shimmy damper 6 is installed The rocker 16 consists of steel fork axle 2 steel shock absorber lever 14 and of the wheel fork 3 made of duralumin i ef N a 1 59 S E S JS V u Figure 10 1 Nose landing gear 1 Nose leg 10 Wheel hub 2 Wheel fork axle 11 Rear leg attachment bolt 3 Wheel fork 12 Tunnel wall 4 Shock absorber rod 13 Front leg attachment bolt 5 Wheel 14 Shock absorber lever 6 Shimmy damper 15 Shock absorber rod bolt 7 Wheel shock absorber 16 Rocker bolt 8 Leg shock absorber 9 Fork turn limiter 10 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 10 AT 4LSA LANDING GEAR 10 1 1 R
68. 046 Ekran Lm RAE 222405 skr Ras a 224WG skr RA nis mm 208 Ekran E BALD RA RA12 228 RAMA nuum kp HIKE XX E ANTENNA P RAIZ 224 M ts RAIK H xl BNC SQ WD 04 gt BNE wu 0 serta PS ARR Pik 80 O0ZON MINZVASM 10714 Honas T 10718 DIN 1971903 HONMAS eva 101900 x 2 M 18 1 11 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z o o SUPPLEMENT No 1 AT 4LSA 5 COM configuration Menu is utilized during device installation or after removal of transceiver or NAV indicator It is highly recommended to take special care in case of introducing any modifications into transponder s configuration To activate configuration mode keep pressed in SYS and FLIP FLOP buttons while switching on the device After removal of transceiver or NAV indicator it is necessary to calibrate OBS system Detailed description of additional advanced CMO NAV device and its settings are contained in pilot s manual SL 30 Nav Com Pilots Guide nr 506 0403 01 18 1 12 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 SECTION 18 AT 4LSA SUPPLEMENT No 2 SUPPLEMENT No 2 Radio transceiver GARMIN SL40 P le T m T Umm 18 2 2 1 2 DdstoteHeci ve PADE issu tee bool 18 2 2 L DOSE DUO oot dei Ee bet dete oa
69. 11 AIRPLANE CONTROLS 11 1 Elevator control system 11 2 11 1 1 Removal and installation of elevator control system 11 2 11 1 2 Adjustment of elevator deflection 11 3 11 1 3 Mass balancing of elevator 11 4 11 2 Aileron control system 11 5 11 2 1 Removal and installation of aileron control system 11 6 11 2 2 Adjustment of aileron deflection 11 6 11 2 3 Mass balancing of aileron 11 7 11 3 Rudder control system 11 8 11 3 1 Removal and installation of rudder control system 11 9 11 3 2 Adjustment of rudder deflection 11 10 11 4 Wing flap control system 11 11 11 4 1 Removal and installation of wing flap control system 11 12 11 4 2 Adjustment of wing flap deflection 11 12 11 5 Trim amp balancing tab control 11 13 11 5 1 Trim and balancing tab control removing and 11 14 installation 11 5 2 Trim and balancing tab deflection angles adjustment 11 15 Tools Required Metric Wrenches 5mm to 19 mm Metric Socket set 5 mm to 19 mm Screwdriver Plain 8 Philips Wire Lock Pliers amp locking wire Cotter Pins MAY 2007 11 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 11 AERO Sp z o o AIRPLANE CONTROLS AT 4LSA 11 1 ELEVATOR CONTROL SYSTEM The slab tail elevator is fastened to the fuselage structure by means of two bolts The system of push rods and the intermediate lever connect the elevator to the control stick Displacement of the slab tail elevator 412 1 trailing edge up 10 1 trailing edge down 1 DX
70. 2 10 12 4 1 Removal and installation of air filter box 12 11 12 4 2 Air filters replacing 12 11 12 5 Exhaust system 12 12 12 5 1 Removal and installation of exhaust system 12 13 12 6 Engine mount 12 14 12 6 1 Removal and installation of engine mount 12 15 12 7 Fuel system 12 16 12 7 1 Removal and installation of fuel tank 12 18 12 7 2 Removal and installation of fuel valve 12 19 12 7 3 Removal and installation of fuel filter 12 19 12 7 4 Removal and installation of electric fuel pump 12 20 12 7 5 Removal of fuel sensor 12 20 12 7 6 Calibration of fuel gauge and setting fuel reserve indicator 12 20 12 8 Oil system 12 21 12 8 1 Operation of oil cooler shutter 12 22 12 8 2 Oil change 12 23 12 9 Cooling system 12 25 12 9 1 Replenishment of the engine coolant 12 26 12 10 Engine controls 12 27 12 10 1 Throttle push rods disassembly and assembly 12 28 MAY 2007 0 7 CHAPTER 0 BASIC INFORMATION 13 Cabin 13 1 Instrument panel 13 1 1 Removal and installation of instrument panel 13 2 Seats 13 2 1 Removal and installation of seats 13 3 Upholstery 13 3 1 Removal and installation of upholstery 13 4 Safety belts 13 4 1 Removal and installation of safety belts 13 5 Luggage compartment 13 6 Canopy 13 6 1 Removal and installation of canopy 13 7 Cabin ventilation and heating system 13 7 1 Removal and installation of cabin ventilation and heating system 13 8 Cabin air intake 13 8 1 Removing and installation of the cabin air inlet elements 14 Static an
71. 3 Calculation of the centre of gravity position 6 3 6 4 AT ALSA airplane weight amp balance report 6 6 6 5 Equipment list 6 7 6 6 Weight and moment recording 6 9 6 7 Procedure for recording data in Form 17 2 6 10 MAY 2007 6 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 6 AERO Sp z o o WEIGHTING AND BALANCE AT ALSA 6 1 INTRODUCTION The airplane is delivered with an actual AT 4LSA Airplane Weight Report and Equipment List The weight and centre of gravity CG position of the empty airplane must be updated in the following cases at least After modification for which calculation of the weight and the change of the CG position of the empty airplane without weighting is not possible After repair of the airplane which affects the weight or CG position After repainting the outer surface of the airplane In case that weight CG and arm the distance from the wing leading edge of the new equipment are known the new weight and CG position of the empty airplane may be calculated as shown under item 6 3 of this chapter Regardless of the method used to determine the weight and CG position of the empty airplane by weighing or calculating it is required to fulfill the requirements of this chapter 6 2 WEIGHING PROCEDURE Provide three certified scales of capacity 400 Ib each Prepare copy Form 17 1 and 17 2 per Chapter 17 of this manual Enter into the Equipment List Form 17 1 the equipment installed in airp
72. 6018 Ib ft 1 Ib ft 62 43 g cm Force units 1 N 0 224809 Ibf 1 Ibf 4 4482 N Pressure units 1 Pa 1 1 bar lt 100 000 Pa 1000 hPa 1 bn in psi 0 0689 bar 1 bar 14 5037 Ibf in psi MAY 2007 CHAPTER 0 INSPECTION Power units 1 kW 1 341 hp 1 hp 0 7457 kW 1 kW 1 3596 PS 1 PS 0 7355 kW Temperature units 273 15 F 32 1 8 F x1 8 32 Speed units 1 m s z 3 6 km h 1 ft min 0 3048 m min 18 288 m s 1 m s 0 0555 ft min 1 kts 1 8532 km h 1 km h z 0 53996 kts 1 mph 1 6093 km h 1 km h 0 62139 mph Fuel consumption units 1 g kWh 0 001644 Ib BPH 1 ID BPH 608 277 g kWh Moment units 1 kGm 9 80665 Nm 1 Nm z 0 737 ft Ib lt 8 848 in Ib 1 ft lb 1 356 Nm 1 Ib 0 113 Nm AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 0 AERO Sp z 0 0 INSPECTION AT 4LSA 0 5 REVISIONS Revisions to this manual and supplements will be covered by revisions and editions published by the manufacturer Revised pages cancel and replace the respective pages of the manual For easy identification new or revised text is indicated by black vertical line and marked with subseguent revision Next to the date of issue the number of the revision is placed 0 16 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 0 AT 4LSA INSPECTION 0 6 LIST OF REVISIONS MAY 2007 0 17 AIRPLANE MAINTENANCE MAN
73. 7 Tighten the fastening bolts in two phases in a cross alternate sequence according to the figure 2 first tighten with an initial moment of 1242 Nm 16 3 2 7 ft Ib 1 6 and then with a final moment 2042 Nm 27 1 2 7 ft Ib 7 12 MAY 2007 12 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 12 AERO Sp z o o POWER PLANT AT 4LSA Figure 12 2 Propeller fixing bolts and screw tightening sequence 8 Check and correct if necessary the torque moment of the propeller blade fixing screws 1041 Nm 13 6 1 4 ft lb A F 9 Check that the appropriate surfaces of the shaft flange or its extension fit tighily against the prop hub CAUTION Any play between the shaft flange or its extension and the prop hub surfaces is not acceptable 10 Check the blade linear tracking alignment according to Para 4 If the difference in tracking alignment is greater than the acceptable value reinstall the prop turning it by 120 and if necessary another 120 If none of these settings result in the correct tracking alignment remove the propeller and send it to the manufacturer 12 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 12 AT 4LSA POWER PLANT 11 After tightening all of the screws and bolts check that the minimum clearance between the hub halves is 0 05 mm 0 002 in CAUTION If the clearance between the hub halves is less than 0 05 mm remove the propeller and return it to
74. 7 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 SECTION 18 AT 4LSA SUPPLEMENT No 7 2 Description The light installation consists of a landing and taxiing light Lights are instaled on lower engine cowling under propeller The lights are activated by two switches placed on the instrument panel as on Figure 1 I Figure 1 Location of taxiing and landing lights 1 Landing light 2 Taxiing light E Dor DOO Tno 15555055504 Lol Figure 2 Location of switches on the instrument panel 1 LANDING LIGHT switch 2 TAXIING LIGHT switch MAY 2007 18 7 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z o o SUPPLEMENT No 7 AT 4LSA 3 Removal and installation of the landing and taxiing light Disassembly 1 Remove lower engine cowling panel 2 Disconnect electric cables connectors 3 Take out lights Assembly Execute points 1 3 in reversed sequence 2 Position lights manipulating with its cover 4 Taxiing and landing lights electrical installation The taxiing and landing lights are connected to the contact bus through separate 10A automatic circuit breakers S10 and S 12 An e3 connector is included to enable easy removal of the wing The taxiing and landing lights electrical installation is shown on Figure 4
75. 8 Paint the repaired area as reguired MAY 2007 16 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 16 AT 4LSA REPAIRS 1 6 in 00 06 in Figure 16 4 Repair on angled edges 16 4 5 Replacement of the fuselage structure stiffening Application repair of fuselage sidewall and the floor 1 Remove the rivets fixing the stiffening and remove the stiffening 2 Manufacture a stiffening of the required length 1 of PA7 ta sheet metal of gauge 0 6 mm In case of repair of angle bar choose a suitable profile 10 0 4 in SS amp U 20 0 8 in Lo Figure 16 5 Stiffening 16 10 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 16 AT 4LSA REPAIRS 3 Prime the stiffening 4 Flatten the skin 5 Drill holes in the stiffening according to the holes in the skin 6 Rivet the stiffening to the skin using rivets of 23 2 mm T Paint as required NOTE THE TOP OF THE FUSELAGE MAY BE REMOVED TO GAIN ACCESS TO THE DAMAGED PLACES FOR THIS PURPOSE RIVETS MARKED IN THE FIGURE SHOULD BE REMOVED AFTER COMPLETING THE REPAIR THE TOP MUST BE RE RIVETED USING RIVETS OF A GREATER SIZE Figure 16 6 Removal of the upper skin of the fuselage 1 Upper skin 2 Rivets 16 4 6 Loose rivets replacing 1 Remove the loose rivet 2 Measure the hole and enlarge it to get the diameter of the repair rivet 3 Perform
76. A CHAPTER 12 AERO Sp z o o POWER PLANT AT 4LSA 12 9 1 Replacing the engine coolant 1 Open the overflow reservoir cap 2 Remove the screw sealing washer from the bottom of the water pump and disconnect lower hose of the cooler Drain the coolant 3 Drain coolant from the overflow tank Treat coolant according to local regulation 4 Re attach the cooler hose and water pump screw and sealing washer Screw with a torque of 10 Nm 13 6 ft Ib 5 Fill the cooling system and close the cap 6 Replenish coolant in the overflow tank RECOMMENDATION Warm up the engine and let it cool a little before checking the coolant level WARNING NEVER OPEN THE RESERVOIR CAP WHEN THE ENGINE IS HOT FOR SAFETY REASON PLACE A FABRIC CLOTH OVER THE CAP AND OPEN CAREFULLY OPENING THE CAP QUICKLY MAY CAUSE THE HOT COOLANT TO SPILL OUT AND COULD CAUSE SERIOUS INJURY 12 26 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 12 AT 4LSA POWER PLANT 12 10 ENGINE CONTROLS The engine is controlled by a push rods system levers and Bowden cables which drive the carburetor throttles The push rods with knobs at their ends pass through the instrument panel fuel tank and firewall The RH throttle push rod has installed a brake which enables to stop it in either position After passing the firewall the movement of the rod is transmitted to cables by means of the torque tube The Bowden cables control the thrott
77. AERO Sp z o o CHAPTER 0 AT 4LSA BASIC INFORMATION TABLE OF CONTENTS CHAPTER SUBJECT PAGE 0 Basic information 0 1 Introduction 0 12 0 2 Safety information 0 13 0 3 Documents delivered with airplane 0 14 0 4 Conversion chart 0 15 0 5 Introduction of revisions 0 16 0 6 Log of revisions 0 17 0 7 List of effective pages 0 18 1 General information 1 1 Basic information on airplane 1 2 1 2 Three view projection of the airplane 1 3 2 Handling 2 1 Towing and taxiing 2 2 2 2 Parking 2 3 2 3 Mooring 2 3 2 4 Jacking 2 3 2 5 Leveling 2 4 2 6 Towing bar 2 5 2 7 Airplane disassembling and assembling 2 5 2 8 Dismantled airplane transporting 2 6 2 9 Dismantled airplane storage 2 7 MAY 2007 0 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 0 BASIC INFORMATION 3 Servicing 3 1 Daily pre flight inspection 0 2 3 2 3 3 3 4 3 5 3 6 3 7 3 8 3 9 3 10 3 11 3 12 3 13 3 14 4 1 4 2 4 3 4 4 4 5 3 14 1 3 14 2 3 14 3 3 14 4 3 14 5 3 14 6 3 14 7 Engine starting Engine test run Engine switching off Ground power supply Daily post flight inspection Refueling Engine oil replenishing Engine coolant replenishing Brake fluid replenishing Tires Inflation Lubrication Consumable materials Airplane cleaning and care Outer surface cleaning Plexiglas canopy cleaning Cockpit interior cleaning Snow removing Ice or hoarfrost removing Engine care Propeller care Airworthiness Limitations Airframe Engine Propell
78. ALLAN Fig 1 1 Location of SL 40 system on instrument pane 1 SL 40 COM NAV transceiver 2 RADIO COM circuit breaker The SL 40 transceiver has a standard COM antenna installed on top of the fuselage Antennas location is shown at Fig 1 2 Fig 1 2 Location of SL 40 system antennas Standard COM antenna MAY 2007 18 2 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z o o SUPPLEMENT No 2 AT 4LSA The SL 30 transceiver is used to carry on radio correspondence at frequencies between 118 MHz and 139 975 MHz on 760 channels at every 25 kHz The display is shown on Fig 2 1 the active frequency is displayed on left part of liquid crystal display The STBY frequency is preceded with letter s Basic physical specifications Operating temp range 20 to 455 Power supply 10 40V COM radio performance specifications Number of channels 760 Freguency range 118 136 975 Increments 25kHz Transmitter power oW Audio amplifier power 12W Intercom function 2 System operation 2 1 Power ON To turn on SL 30 turn on battery switch and rotate Power ON OFF Volume knob right clockwise from OFF position The transceiver should come on into standard initiation mode and within 15 seconds the liquid crystal display should project recently used COM and NAV as well stand by frequencies and depending from working mode NAV data When SL 30 is ON pull the knob out to disable au
79. ANUAL Doc No ATT4 02A CHAPTER 15 AERO Sp z o o ELECTRICAL SYSTEM AT 4LSA 15 2 1 V belt tension adjustment Check the V belt tension according to Figure 2 The V belt tension check should be performed during the daily pre flight inspection 50 N 11 10 Figure 5 V belt tension check Should the V belt tension reguire adjustment perform following steps marks to Figure 3 1 Loosen the belt stretcher screw M10 6 2 Loosen the two alternator mount screws M8 4 5 3 Lift the alternator to increase the V belt tension and tighten the screw M10 4 Tighten screws M8 The tightening moment of the M8 screws is 22 Nm 195 Ib in and screws M10 is 35 Nm 310 Ib in Figure 6 V belt tension adjustment 1 V belt 5 Alternator mount lower M8 crew 2 V belt stretcher 6 Belt stretcher M10 screw 3 Alternator 7 Alternator mount 4 Alternator mount upper M8 screw 15 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 15 AT 4LSA ELECTRICAL SYSTEM 15 2 2 Alternator removal and installation Removal 1 Remove the engine cowlings see Chapter 12 3 Assure that the battery and external power supply are disconnected Disconnect the alternator power terminal clamp Disconnect the control cable connector Unscrew the v belt stretcher screw and alternator mount screws Remove the v belt Remove the alternator If necessary remove the alternator mount SO Mme oe OI C cbe
80. AT 4LSA SUPPLEMENT No 3 1 Press and hold Power button CAUTION It is prohibited to start engine with GPSMap system ON 2 Read caution remarks displayed on screen WARNING For VFR use only os an aid to prudent navigation All information is presented for reference only You assume total responsibility and risk associated with using this device Terroin and obstacle data are provided only as an aid to situational awareness Americos Avioton Dota Cycle 0509 01 2005 lo 29 Sep 2005 Jeppesen Sonderson Inc Anericos Terrain Database 2 02 Garmin Lid or ts subsidiaries US Obstacle Database 2 00 Fig 2 3 Caution remarks displayed by GPS CAUTION GPSMap system can be used In VFR operations only All information displayed on the screen are supportive ones and mustn t be used as a main source of navigation data Satellite search status can be monitored on the screen as shown on Fig 2 4 e 3D GPS Location ho Flights E 1 57 01030509 14 15 18 1921 22 25 30 Route N 1 B N 3851 395 id gt 094 47 948 Points O3 AUG 05 10 40 298 Differential Accuracy Track None 14 Fig 2 4 Satelite seach status screen Search for satellites takes place in three phases e Lack of satellites posts satellites have not been located e White satellites posts satellite has been located but its data are still gathered e Greek satellites posts all necessary data hale been collecte
81. BY ON or ALT buttons transponder will be powered on and last active identification code will be displaid STBY selects the standby mode When in standby mode the transpnder will not replay to any interrogation ON Selects Mode A In this mode the transponder replies to identification and altitude interrogations as indicated by the Reply Symbol I8 Replies do not include altitude information ALT Selects Mode A of Mode C In ALT mode transponder replies to identification and altitude interrogations as indicated by the Reply Symbol Bl replies to altitude interrogations include the standard pressure altitude received from an external altitude source which is not adjusted for barometric pressure The ALT mode may be selected in aircraft not equipped with optional altitude encoder however the replay signal will not include altitude information NOTE ANY SELECTION OF ON OR ALT MODE MAKES SYSTEM FULLY OPERATIONAL AND SYSTEM BECOMES AN ACTIVE ELEMENT OF RADAR CONTROLED AIRSPACE SYSTEM ALSO TRANSPONDER IS RESPONDS TO INTERROGATIONS RECEIVED FROM OTHER AIRCRAFTEQUIPPED WITH TCAS MAY 2007 18 5 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 5 AT 4LSA 2 2 Code selection Code selection 1s done with eight keys see Fig 2 1 providing 4096 active identification codes Pushing one of keys 0 7 begins the code selection sequence The new code 1 not activated until
82. COM set by screwing out screws 2 and sliding out whole unit 1 Transponder 2 Screws 3 Instrument panel Assembly 1 Execute point 1 3 in reversed sequence If necessary the slot can be disassemble too by removing canopy and cover protecting tank than disconnecting electrical cables at the slot s connector The slot 1s attached to supports screwed to instrument panel MAY 2007 18 5 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 5 AT 4LSA 4 Encoding altimeter disassembly and assembly Fig 4 1 AK 350 encoding altimeter 1 Encoding altimeter 4 Instrument panel base 2 Altimeter mount 5 Static pressure hose 3 Screws 6 Electric wires Disassembly 1 Remove canopy see chap 13 6 1 and tank fairing 2 Disconnect electrical encoder s connection 3 Disconnect static pressure hoses 4 Screw out screws and remove encoder Assembly 1 Execute point 1 4 in reversed sequence 6 Demontaz i montaz anteny Disassembly 1 Remove upholstery of central tunnel see chap 13 3 1 2 Disconnect antenna cable from antenna 3 Undo a nut fitting antenna to cockpit s floor and remove antenna Assembly 1 Execute point 3 in reversed sequence 18 5 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 ROZDZIAL 18 AT 3 R 100 UZUPELNIENIE 22 3 GTX 327 transponder electric installation The GTX 327 transponder is c
83. Cleaning and protection of corroded surfaces 16 3 16 3 Repair of bolted or screwed joints 16 4 16 4 Airplane structure panel repairs 16 5 16 4 1 Skin repairing between the ribs 16 6 16 4 2 Repair of cracked ribs flanges frame or stringers 16 8 16 4 3 Repair of trailing edges 16 9 16 4 4 Repair of dented or cracked skin on angle edges 16 9 16 4 5 Replacement of the fuselage structure stringers 16 10 16 4 6 Loose rivets replacment 16 11 MAY 2007 0 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 0 AERO Sp z o o BASIC INFORMATION AT 4LSA 16 5 Repair of composite parts 16 12 16 5 1 Composite cracks or small holes 16 13 16 5 2 Painting repaired composite parts 16 14 16 6 Bolted joints and values of the torque moments 16 15 17 Forms 17 1 Weighing protocol 17 2 Total permissible weight of a pilot and passenger 17 3 Alignment sheet 17 4 Flight test protocol 18 Supplements 18 1 Introduction 18 1 18 2 List of introduced supplements 18 2 0 10 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 0 AT 4LSA INSPECTION CHAPTER 0 BASIC INFORMATION 0 1 Introduction 0 12 0 2 Safety information 0 13 0 3 Documents delivered with airplane 0 14 0 4 Conversion chart 0 15 0 5 Revisions 0 16 0 6 Log of revisions 0 17 0 7 List of effective pages 0 18 MAY 2007 0 11 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 0 AERO Sp z 0 0 INSPECTION AT 4LSA 0 1 INTRODUCTION This manual contains necess
84. ELETED ENGINE AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A MAY 2007 AERO Sp z o o CHAPTER 15 AT 4LSA ELECTRICAL SYSTEM e LOW POWER message will show always when voltage drops under the operation limit This may happen during the engine start up etc In this case wait till the instrument gets back to the normal measuring mode LOW POWER 2 Please Wait ENGINE e lf the automatic internal circuit check found out an error in the instrument or a data integrity defect the SYSTEM ERROR message will show on the display SYSTEM ERROR Q m d gone ENGINE MAY 2007 15 15 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 15 AERO Sp z o o ELECTRICAL SYSTEM AT 4LSA 15 4 FUEL GAUGE ELECTRICAL SYSTEM The fuel gauge electric system is switched to operation after switching on Battery switch The airplane is fitted with one capacitive fuel level sensor installed in the fuel tank The sensor interacts with the fuel quantity indicator installed on the instrument panel fuel quantity sensor In Version 1 moment when fuel reserve light goes on is setting by means of potentiometer which is located in fuel gage casing upper part To facilitate easier access to the potentiometer disassembling of indicator located over the fuel gage is recommended The fuel gage is equipped with additional light signaling activated together with reserve fuel light In Version 2 moment when fuel reserve light goes on is setti
85. ERO Sp z o o CHAPTER 12 AT 4LSA POWER PLANT 12 2 ENGINE Detailed information concerning the engine and the installed accessories and concerning such question as description and operation equipment and special tools diagrams and data tables concerning performances are contained in the Maintenance and Operational Manual of the Rotax 912 engine CAUTION When replacing parts of the engine or its accessories it is mandatory to check all part numbers Usage of unsuitable spare parts may result in serious damage of the engine 12 2 1 Removal and installation of engine Removal Remove the engine cowling Drain oil and coolant from the engine systems Remove the propeller Remove the air inlet tunnel directing air to the cooler Remove the cabin air heater Remove the exhaust system Jo c fF W PN Disconnect the fuel system oil system electric system and all controls and drives from the engine MAY 2007 12 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 12 AERO Sp z o o POWER PLANT AT 4LSA CAUTION IDENTIFY TAG ALL HOSES LINES AND WIRES AS THEY ARE DISCONNECTED AND SEPARATED TO FACILITATE INSTALLATION CAP ALL OPEN FUEL OIL AND VACUUM LINES AND FITTINGS TO PREVENT CONTAMINATION 8 Remove the engine together with the small engine mount 9 Disconnect all rubber hoses between the cylinder heads and the coolant pump 10 Loose the pipes locking nuts of cylinder 1 and 3 on the cove
86. GHT MANUAL MAY 2007 8 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 8 AERO Sp z o o PLACARDS AT ALSA 31 Marking of the airspeed indicator Explanation White sector Range for using of wing flaps displaced to any angle Green sector Range for normal operation Yellow sector Range for limited operation The maneuvers must be performed with great care and in non turbulent weather only Red line Maximum speed for all types of operation AIRSPEED RANGES IAS White sector Green sector Yellow sector Hed line 8 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 8 AT 4LSA PLACARDS 32 Marking of the engine monitoring instruments Markings of the engine monitoring instruments and meaning of their color markings are given in below table Red line or Red line I Green sector Yellow sector Colored marking sector or sector The instrument or the Minimum Range of normal Range of limited measured parameter limit operation operation 1 400 to 0 1400 rpm 5500 5800 7000 m 5 500 rpm rpm 2 2 psi 2 2 to 5 8 psi 5 8 psi Fuel pressure 0 15 bar 0 15 0 40 bar 0 40 bar Table bellow contains engine limitations indicated at the engine controller Maximum limit Minimum Range of normal Range of limited mE Maximum limit limit operation operation The measured parameter 122 194 F 122 194 to 230 50 90 266 F 50 C
87. HAPTER 6 AERO Sp z o o WEIGHTING AND BALANCE AT ALSA 1 the actual value of the empty weight Op and add to it weights of pilot pas senger luggage and fuel the monent arms of engine oil and coolant given in table on page 6 4 may be used The small change of the weight 0 53 US qts 1 Ib between the minimum and maximum amount of these fluids is miniscule and doesn t affect the calculation CAUTION The total weight of the airplane must not be less than 962 Ib and not more than 1320 Ib 2 Take the actual moment of inertia of the empty airplane M from page 6 9 and add to it the static moments of the variable weights mentioned in Para 1 above Mi Qi X Moment of inertia of the variable weights Where Qi weight X arm to be taken from the table below hem Kin Engine coolant 4 61 1 88 Ib US ats 6 4 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 6 AT 4LSA WEIGHTING AND BALANCE 3 Calculate the of the centre of gravity Xsc F m distance from the surface of firewall Q Where Mp gt o Qr CAUTION The value of the received Xsc must not be less than 25 3 in and must not exceed 32 5 in 4 Calculate the C G position in percent of the mean aerodynamic chord of the wing Xsc 100 CAUTION The value of the received Xsc must not be less than 20 0 and must not exceed 34 MAY 2007 6
88. IRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 11 AERO Sp z o o AIRPLANE CONTROLS AT 4LSA 11 2 1 Removal and installation of the aileron control system CAUTION Removal and installation of the long push rod of the aileron control system is possible only when the wings are removed from the fuselage Removal 1 Remove the aileron refer to section 9 2 2 2 Disconnect long push rods from the bell crank lever 3 Turn the bell crank lever and remove short push rod 4 Remove the bell crank lever Installation 1 Perform steps 1 to 4 in reverse order 2 Grease all connections 3 Lock all bolt and nuts 4 For bolted joints torque limits refer to Chapter 16 6 11 2 2 Adjustment of aileron displacement 1 Lock the bell crank levers in wings with a pin of 4 mm 0 155 in dia 2 Adjust the length of the short push rod to set the aileron displacement to 0 3 Adjust the length of the long push rod to set the control sticks into the neutral position The control sticks must be parallel to one another and both equally distanced from the respective sidewall of the cabin If they are not correction must be made by changing the length of the coupling rod 4 Remove the locking pin 5 Check ailerons displacement upward 20 4 2 and downward 15 2 Adjust displacements using stops on the torque tube 6 Check the whole system for free and smooth travel and a clearance between parts of the aileron control sys
89. MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 11 AT 4LSA AIRPLANE CONTROLS 11 4 WING FLAP CONTROL SYSTEM The wing flaps refer to section 9 1 are displaced manually by means of levers system push rods 2 and torgue tube 3 To reduce the control force for wing flap extension an assisting gas cylinder spring 4 has been applied Flap displacement 0 15 2 and 40 5 2 Figure 11 7 Wing flap control system 1 Wing flap control lever 4 Wing flap 2 Push rod 5 Flap actuator lever 3 Torgue tube CAUTION Take care not to change the location of the flap actuator levers on the torgue tube when reinstalling To avoid this make respective markings when disassembling MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A 11 11 CHAPTER 11 AERO Sp z o o AIRPLANE CONTROLS AT 4LSA 11 4 1 Removal and installation of the wing flap control system Removal 1 Remove the wing flaps refer to section 9 2 3 2 Remove the seats refer to section 13 2 1 and the tunnel between seats refer to section 13 1 1 3 Set the wing flap control lever to 0 4 Remove the push rod 5 Remove the wing flap control lever 6 Remove the central lever from the torque tube inspection door in the larger luggage compartment and left or right flap actuator lever 7 Remove the torque tube from fuselage Installation 1 Perform steps 1 to 8 in reverse order
90. NCE MANUAL Doc No ATT4 02A AERO Sp z CHAPTER 18 AT 4LSA SUPPLEMENT No 3 3 GPS ASSEMBLY AND DISASSEMBLY 3 1 GPSMap main unit assembly and disassembly Disassembly 1 Loose BPS lock 2 Take out GPS 3 Disconnect antenna Assembly Execute steps 1 3 in reversed seguence 3 2 Antenna assembly and disassembly Disassembly 1 Remove upper fairings 2 Remove canopy and tank fairing 3 Disconnect GPS antenna s cable from main unit 4 Disassemble antenna Assembly Execute steps 1 4 in reversed sequence MAY 2007 18 3 11 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 3 AT 4LSA 4 GPSMap electrical diagram The GPSMap 296 396 496 systems GP1 are connected to the avionics bus with use of circuit breaker GP3 Electrical diagram is shown on Fig 4 1 Weather antenna GXN 30A In front of cockpit for 396 496 systems only GPS circuit breaker 7274 2 2A Instrument panel GA26C or GP2 GPS antenna In front of cockpit equivalent GPSMAP GPI GS MAP receiver Instrument panel 296 396 4964 The GPSMap units are equipped with internal Lithium batteries which require charging Charging can take place outsider the aircraft with use of separate connection to the line or during operations on bard of aircraft 18 3 12 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 SUPPLEMENT No 3 14V bus GPs ionic Av AERO Sp z o o AT ALSA
91. No ATT4 02A AERO Sp z o o CHAPTER 12 AT 4LSA POWER PLANT 12 6 1 Removal and re installation of the engine mount Depending on need the engine with the small mount or the whole engine mount may be removed Figure 12 5 Shock absorbing bushes of the engine 1 Large mount 5 Sleeve 2 Small mount 6 Rubber inserts 3 Shock absorbing bushes 7 Bolt 4 Cups Removal 1 Remove the engine according to section 12 2 1 of this manual CAUTION IF YOU INTEND TO RE USE THE SAME BUSHINGS MARK EACH ONE AND RE USE EACH ONE IN ITS ORIGINAL POSITION 2 Remove the cotter pins and unscrew the large engine mount nuts Remove bolts Remove large mount Re installation 1 Perform jobs 1 to 2 in reverse order 2 Lubricate all joints 3 For bolted joints torque limits refer to Chapter 16 6 MAY 2007 12 15 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 12 AERO Sp z o o POWER PLANT AT 4LSA 12 7 FUEL SYSTEM The fuel tank of 18 5 US gal capacity is located inside the fuselage between the firewall and the instrument panel It s a structure made of carbon glass composite contains doubled walls A space between the walls is drained and ventilated In the upper central part of the tank the drained filler throat and the capacitive fuel gauge is located A drain valve of the tank is located on the floor beneath the tank There are also drain and venting fittings In the front starboard part of the fuel tank the inlet of
92. ON Position of oil cooler shutter should be set in such a manner that engine oil temperature does not exceed permissible limit 3 1 B A E I SS pse J KA B FEE xj ji 2 hse Nin di Figure 9 Operation of oil cooler shutter flexible connector 1 Oil cooler 2 Oil cooler shutter 3 Flexible connector 4 Setting bolt If necessary is shutter disassembly remove hinge locking wire screw and remove wire During assembly keep attention to install proper return springs of shutter Lubricate hinge axis Regulation of flexible connector control mechanism is done by changing of flexible connector shield length with regulation bolt in such manner that when the shutter control knob is fully pulling out and locked the shutter is fully closed The shutter move should be smooth and without seizures 12 22 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 12 AT 4LSA POWER PLANT 12 8 2 Oil change To perform oil change the following materials are reguired oil 3 6 US gts new seal for the draining plug and the oil filter The oil change must be made with a warm engine The oil temperature should be minimum 50 1 Remove the engine cowling see section 12 3 2 Unlock and unscrew the draining plug of the oil tank 3 Drain oil from the tank 4 Disconnect lines from the oil tank Remove the cover of the oil tank and check its cleanness If necessary
93. ONLY WITH ONE OF THE COWLINGS ATTACHED EITHER UPPER OR LOWER MAY 2007 12 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 12 AERO Sp z o o POWER PLANT AT 4LSA 12 4 ENGINEAIR INTAKE SYSTEM Air to the carburetors enters through the filters box and air filters The cold air flow from inlets in upper engine cowling is regulated by means of switching flap controlled from the cabin by a cable When the switching flap is closed air is sucked from the engine compartment through the heat exchanger on exhaust and air ducts to the air filter box Inside the filter box there is also a outer air temperature sensor Drain holes in the air filter box and carburetors allow any fluids to draint 2 3 1 4 kej 5 9 i 6 8 Figure 12 2 Engine Air Intake System 1 Air inlet 6 Carburetor heat control cable 2 Regulating flap 7 Hot air hose 3 Air filter box 8 Heat exchanger 4 Air filters 9 Carburetors 5 Drain hoses 12 10 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 12 AT 4LSA POWER PLANT 12 4 1 Removal and installation of the air filter box Removal 1 Remove the engine cowlings 2 Disconnect the temperature sensor and the control cable of the Carburetor heating flap 3 Disconnect the air hoses connecting the air filter box with the carburetors and the air heater and the bands fixing the engine control cables 4 Remove the bands fixing the box and take it out
94. Pitot tube 3 Fastening screws 2 Static pressure port 4 Flexible hoses Removal 1 Through the inspection door disconnect lines in left wing 2 Unscrew the screws fastening ports to the wing Installation 1 Perform the steps 1 to 2 in reverse order 2 Check the system for leaks MAY 2007 14 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 14 AT 4LSA STATIC AND PITOT PRESSURE SYSTEM 14 5 CHECKING THE SYSTEM FOR LEAKS 1 Set the altimeter to read 0 zero 2 Generate vacuum in the system so that the altimeter reads 1000 ft 300 m 3 The drop of the altitude within 1 minute must not exceed 100 ft 30 m 4 In the Pitot pressure line generates pressure so that airspeed indicator reads 110 kts 200 km h 5 The drop of the airspeed within 1 minute must not exceed 11 kts 20 km h 14 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 15 AT 4LSA ELECTRICAL SYSTEM CHAPTER 15 ELECTRICAL SYSTEM 15 1 Electric power and starter circuit 15 2 15 2 Alternator electrical installation 15 6 15 2 1 V belt tension adjustment 15 8 15 2 2 Alternator removal and installation 15 9 15 2 3 Alternator operation check 15 9 15 3 Engine electrical system and engine monitoring instruments 15 10 15 3 1 Engine Monitor 15 13 15 4 Electrical system of fuel gauge 15 16 15 5 Gyro instruments electrical system 15 17 15 6 Avionics electrical system 15 18 15 7 Hour Meter 15 19 15 7 1 Removing and
95. Pos ses EH EHE TITIO ao t Fuel Carburetor Cylinder Flight Flight speed Pressure temp head Altitude H m f Pop 500 Climb 1000 500 4 j JP j de Level 500 4800 flight 500 5200 100 Po m o po m je 1 PEN 200 V indicated stall speed IAS Flight Vs stall warning system activation speed if installed Altitude MES ane a ia nena Ile throttle flaps retracted m ft A O A Na idled throttle flaps 40 delete as applicable AIRPLANE CHARACTRISICS duod Su duos oes deae J LAL speed DE NAV dot nde babe ane oo ala ee tempi i sau vb Add bue Ded ds 3 Daldtice Bilitiy nese tob SIDE e TE O OH ESSE rid sasana EQUIPMENT CHECK 1 Airplane controls 6 Avionics and instruments 2 ENE ME COMMONS ie ei T RACIOSIFANSCEIVER oe 3 Carburetor heating 8 Undercarriage and wheel brakes 4 Engine instruments 9 Ventilation and cabin heating 5 Electric installation PILOT S OPINION Visti A mes DD EU S die Troubleshooting confirmation E Performed by Controlled by
96. RO Sp z o o AIRPLANE STRUCTURE AT 4LSA 9 1 FUSELAGE STRUCTURE The cross section of the fuselage is rectangular with a round top All metal riveted structure consists of stringers stiffen the skin sheets Frame 2 is made of stainless steel and forms the firewall which divides the cabin from the engine compartment Fittings 10 located on firewall attach the engine mount and the nose landing gear to the firewall Two lateral boxes are arranged in the lower part of the fuselage One is to accommodate the wing spar 7 which passes through the fuselage and the other to fix the main landing gear 8 At the rear of cockpit there is the luggage compartment frame and the partition frame 9 which form two chambers luggage compartment In the rear the spar of the fin with fittings to connect the elevator 12 and the rudder 13 completes the fuselage structure From the topside the structure is closed with an upper metal skin 4 and with laminated fiberglass fairings 3 and 5 The fin structure consists of skin spar two stringers four ribs and some vertical or horizontal half ribs to fix the fin to the fuselage The fuselage is fitted with inspection holes 14 to enable the maintenance and inspection of the control systems landing gear electrical and radio systems and the fuselage from inside 7 3 459 13 14 SA T 3 D 2 4 z A y d o 8 119 N14 1 M4 Figure 9 1 Fuselage structure 1 Fuselage structure 8 Landin
97. RUCTURE Figure 9 6 Elevator structure 1 Slab tail 4 Fittings 2 Trim 8 balancing tab 5 Hinges 3 Elevator control lever with outrigger 6 Tips 9 3 1 Removal and installation of the elevator Removal 1 Remove the fuselage rear fairing 2 Disconnect tab push rods as per chap 11 5 1 3 Disconnect connecting links from intermediate lever 4 Unlock and unscrew the nuts of the bolts fixing the slab tail to the fuselage While supporting the slab tail remove the bolts 5 Move the slab tail backwards Installation 1 Perform steps 1 to 6 in reverse order 2 Lubricate all joints 3 For bolted joints torque limits refer to Chapter 16 6 Tools Required Metric Wrenches 5mm to 19 mm Metric Socket set 5 mm 19 mm Screwdriver Plain amp Philips Wire Lock Pliers locking wire amp 2 split pins MAY 2007 9 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 9 AERO Sp z o o AIRPLANE STRUCTURE AT 4LSA 9 3 2 Removal and installation of the trim amp balancing tab 1 2 3 4 t FEET Qu iR o ali DICEN A AMINO pup i 4 az s LI LII S Figure 9 7 Trim 8 balancing tab hinge wire locks 1 Slab tail rear small spar 3 Hinge wire 2 Tab hinge 4 Wire lock Removal 1 Remove the elevator control system fairing 2 Disconnect the push rod of the trim amp balancing tab from
98. S AT 4LSA 1 Forms list 17 1 Weight report 17 2 Weight and loading 17 3 Aeroplane alignment sheet 17 4 Control test flight report 2 LIST OF EFFECTIVE PAGES ISSUE DATE 17 12 May 2007 17 2 1 2007 17 2 2 2007 173 1 May 2007 1713 2 2007 1744 May 2007 174 2 2007 17 2 2007 FORM 17 1 AT 4LSA AIRPLANE WEIGHTING amp BALANCE REPORT Edges of cockpit walls leveled CONDITIONS OF empty airplane with the unusable amount of fuel 0 92 US gal full with oil cooling and brake fluid equipment installed according to the Equipment List REFERNCE PLANE FIREWALL dc REFERENCE LINE CENTER OF RLRP GRAVITY RN b a PE M GROSS WEIGHT Ib Ib Front scale Rx pU Right scale Rp AIRPLANE EMPTY WEIGHT Op lt R Position of the center of gravity Xsc b gt 12 P 100 51 57 Mp lt Qp Xs MAY 2007 17 1 FORM 17 1 EGUIPMENT LIST STANDARD EOUIPMENT ADDITIONAL EOUIPMENT Name Name Installation 1394T100 7Z TE GHO2L 3 Artificial h Rm iticial horizon RCA 26AK2 JE RCAISAKI Directional Gyro Indicator R C Allen DG02E 3H Vertical speed indicator Compass Radio transceiver VOR indicator GTX 327 GPS GPSMAP T delec sleni o Engineruncounter Stall warning system ACI TI Extinguisher AT 75 000 0 Wheel fairings AT3 45 000 0 Parking br
99. Sidewalls of the fuselage under the instrument panel are covered with upholstery and riveted with blind rivets In case when necessary perform de riveting 3 To remove a floor cloth at first covers of the linkage must be removed refer to section 11 3 1 then both parts of the floor cloth with a gluing strip can be removed When reinstalling apply new double sided adhesive tape 13 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 13 AT 4LSA CABIN 13 4 SAFETY BELTS Three point safety belts are fitted with a latch of automotive type being very simple to use The length of the waist belt and of the harness is adjustable and the harness may be quickly disconnected The waist belt and the latch are bolted to the steel made ferules at the landing gear box The harness is bolted to the ferule on the luggage compartment frame and located on the stud on the waist belt Figure 13 7 Safety belts 1 Rear cabin bulkhead 3 Waist straps 2 Shoulder straps MAY 2007 13 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 13 AERO Sp z o o CABIN AT 4LSA ii 13 4 1 Removal and installation of the safety belts Removal 1 Remove the seats refer to section 13 2 1 2 Unlock the bolts fastening the waist belt and the latch 3 Through the inspection door in the luggage compartment frame unscrew the bolts of the harness iii Installation 1 Perform steps 1 to 3 in reverse order 2 For bolted jo
100. TAX engine Maintenance Manual Chapter 12 00 00 Check engine system controls for attachment and damage 24 Inspect carburetors Remove disassemble clean carburetors and check all parts and nozzles too test them for float needle valve leakage Assemble again and install carburetors Refer to to ROTAX engine Maintenance Manual Chapter 13 advanced maintenance MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 5 AT 4LSA INSPECTION Nature of Inspection Inspection time hrs C ENGINE GROUP cont 25 On engines with alternator outside the engine check fixing and belt tension check for damage wear and its general condition Refer to ROTAX engine Maintenance Manual Chapter 12 00 00 26 Remove all spark plugs clean and check sparking plug heat factor Clean and check gap adjust as reguired Refer to ROTAX engine Maintenance Manual Chapter 12 00 00 27 Replace spark plugs Refer to ROTAX engine Maintenance Manual Chapter 12 00 00 28 Inspect reliability of spark plug cup attachment Minimum tensile force 30N 29 Check compression ratio with difference suction measurement method Refer to ROTAX engine Maintenance Manual Chapter 12 00 00 30 Inspect exhaust pipes and silencer for securing cracks and burnings inspect condition of silencer attaching springs 31 Inspect carburetor air heater for securing and cracks X x x x x 32 Inspect air intake tunnel and
101. TIONS Special inspections supplement the scheduled inspections as outlined in the Inspection Report Table V 1 to include inspection of items which are required to be examine at intervals not compatible with airframe operating time or airframe inspection intervals MAY 2007 5 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 5 AERO Sp z o o INSPECTION AT 4LSA TABLE V I INSPECTION REPORT NOTE All inspections or operations must be performed at each of the inspection intervals as indicated by a cross x AT 3R 100 Airplane Serial number Airplane call sign Total flight time Time from last inspection Kind of inspection ROTAX engine Engine serial number Engine operation time CAUTION Disconnect battery and protect the engine against unintentionally starting before beginning of any maintenance practices Nature of Inspection Inspection time hrs A PRIMARY STEPS 1 Remove any unnecessary items from cockpit inspect aircraft cleanness 2 Remove clean and inspect engine cowlings for securing cracks distortion leaks and burns 3 Remove wing fuselage fuselage main leg fairings rear fuselage fairing and wheel fairings Inspect them for attaching cracks and distortion 4 Inspect canopy for cracks damage proper locking 5 Perform canopy emergency jettison 6 Remove over tank cover Inspect for general condition cracks and chafing 7 Remove seats side upholstery central tunn
102. This is not a measure check thus it does not verify adequacy of the power output The signal may be weak even if it 1s picked up by an Aircraft Receiver located at a considerable distance from the radiating ELT NOTE Ali ELT ON tests should be performed within the first five minutes of the hour 5 6 Power consumption Verify power consumption are 2 Amp maximum 9 0 Vdc Main Switch ON Position 0 Amp 9 0 Vdc Main Switch ARM Position 0 Amp 9 0 Vdc Main Switch OFF Position 18 6 10 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 SECTION 18 AT 4LSA SUPPLEMENT No 7 SUPPLEMENT No 7 Landing and taxing lights SOS a au uum eo Boii tue 18 7 2 1 2 MASE OE effective PADS u ei one ska a eadera 18 7 2 2 DOSE PU Ama tasu had dtes 18 7 3 3 Removal and installation taxing and landing lights 18 7 4 4 Landing and taxiing lights electrical installation 18 7 4 MAY 2007 18 7 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z o o SUPPLEMENT No 7 AT 4LSA 1 1 List of revisions Revision nr nr Revision Revisionnr Revision description Affected Pages Date Affected Pages Dae 1 2 List of effective pages Page number Issue date 18 7 5 May 2007 18 7 6 May 2007 18 7 4 May 2007 pw 18
103. UAL Doc No ATT4 02A CHAPTER 0 INSPECTION 0 7 LIST OF EFFECTIVE PAGES g e 8 TE T E ULE TET SELE IE A 5 E I Lp LUN INE EHE pa Mi IE 2 1 9 LX Low RE NAME IME T INNEN 8 1 LT 1 S 88 0 18 AERO Sp z AT 4LSA CHAPTER PAGE No QJ CO QJ lij y y O N gi o oj N tini g UJ we 3 3 3 4 42 5 NEN c ZE JIM 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 0 AT 4LSA INSPECTION 0 7 LIST OF EFFECTIVE PAGES cont 66 CHAPTER 10 1 5 B go 11 6 E LES I4 NM NN 7 8 MEL ND ma M A o LE HS et NN ND EE MK EN NN NK UN o b NE sasa 11 12 12 12 2007 0 19 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 0 AERO Sp z 0 0 INSPECTION AT 4LSA 1 7 LIST OF EFFECTIVE PAGES cont N til ti to m Oo re 15 15 b m b 5
104. Unit Type engine fairings Automatic circuit breaker SI Landing LED light LED 12VDC 7A Automatic circuit breaker 13 Taxiing LED light LED 12VDC lower engine fairing 18 7 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 SECTION 18 AT 4LSA SUPPLEMENT No 7 12V BUS ZA za O 15 R Y Fi 16 RKI Taxiing and landing lights electrical installation Figure 4 MAY 2007 18 7 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z o o SUPPLEMENT No 7 AT 4LSA PAGE INTENIONALY LEFT BLANK 18 7 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 AT 4LSA 1 1 List of revisions 1 2 List of effective pages 2 Description 3 Combined navigation lights disassembly 4 Combined navigation lights system diagram MAY 2007 CHAPTER 18 SUPPLEMENT No 8 SUPPLEMENT No 8 Position lights AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A 18 8 1 CHAPTER 18 AERO Sp z 0 0 SUPPLEMENT No 8 AT 4LSA 1 1 List of revisions bi En Concernin Revision nr Revision description Pages Data 1 2 List of effective pages May 2007 May 2007 May 2007 18 9 5 May 2007 18 9 4 May 2007 2 s 18 8 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 18 AT 4LSA SUPPLEMENT No 8 2 Description Combined navigation lights are installed at the wing tips
105. a limited alignment check may be performed in a range which allows checking the position of the benchmarks or angles of displacement of the replaced element Alignment is to be performed hangar without air movement Whilst performing the alignment the cockpit must not be occupied and no load may be applied to the airplane in anyway For the purpose of alignment the airplane is to be lifted refer to Chapter 2 4 so that the wheels do not touch the ground The benchmarks 6L and 6P are to be set level Longitudinally the airplane is to be leveled by setting level the benchmarks 1 and 2 For leveling a leveling instrument and a rule with scale in millimeters are required The leveling instrument is to be set in the plane of symmetry behind the airplane After setting to the benchmark a rule is to be positioned vertically 7 2 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 7 AT 4LSA ALIGNMENT OF THE AIRPLANE 7 2 DISTRIBUTION OF THE BENCH MARKS a Al I p 13 3L TEE Towing lug 9 8 VE Benchmark MAY 2007 7 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 7 AERO Sp z o o ALIGNMENT OF THE AIRPLANE AT ALSA 7 3 THE ALIGNMENT SHEET The Alignment Sheet Form No 17 3 may be found in Chapter 17 3 of this Manual A copy of that form is to be prepared and the results obtained during the alignment are to be entered into it
106. a next to the propeller Check to be clear of obstacles and people WARNING Never start the engine when obstacles or people are in the area next to the propeller MAY 2007 3 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 3 AERO Sp z 0 0 SERVICING AT 4LSA 8 Brakes Apply 9 Ignition switch Turn the key to START NOTE The starter may be switched on for maximum 10 sec only allow it to cool for 2 minutes at least prior to any further starting attempt Never switch the starter on before the engine has stopped 10 Release the key when the engine starts and allow it to return into position 1 2 BOTH Move the throttle lever forward to achieve smooth engine run at ca 2000 2500 rpm NOTE Check whether oil pressure starts to rise within 10 sec and subsequently always monitor it The engine speed may be increased when the oil pressure is stabilized above 2 bars 30 psi 11 Choke Set to OFF 12 Engine monitoring instruments Check indication 13 Electric power consumers Switch on if any required 14 Procedure with engine warm up maintaining about 2000 rpm for 2 minutes and subsequently 2500 rpm until oil reaches 50 122 F Hot engine Carry out tasks 2 to 14 of the procedure for starting a cool engine Engine starting at low air temperature The procedure for starting the engine at low air temperature is the same as for a cool engine but the throttle lever must be
107. airings 10 17 MAY 2007 0 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 0 AERO Sp z o o BASIC INFORMATION AT 4LSA 11 Airplane controls 11 1 Elevator control system 11 2 11 1 1 Removal and installation of elevator control system 11 2 11 1 2 Adjustment of elevator deflection 11 3 11 1 3 Mass balancing of elevator 11 4 11 2 Aileron control system 11 5 11 2 1 Removal and installation of aileron control system 11 6 11 2 2 Adjustment of aileron deflection 11 6 11 2 3 Mass balancing of aileron 11 7 11 3 Rudder control system 11 8 11 3 1 Removal and installation of rudder control system 11 9 11 3 2 Adjustment of rudder deflection 11 10 11 4 Wing flap control system 11 11 11 4 1 Removal and installation of wing flap control system 11 12 11 4 2 Adjustment of wing flap deflection 11 12 11 5 Trim amp balancing tab control 11 13 11 5 1 Trim and balancing tab control removing and 11 14 installation 11 5 2 Trim and balancing tab deflection angles adjustment 11 15 0 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 CHAPTER 0 AT 4LSA BASIC INFORMATION 12 Power plant 12 1 Propeller 12 1 1 Removal and installation of propeller 12 3 12 1 2 Blade linear tracking alignment check 12 5 12 1 3 Checking and adjustment of the blade angle of incidence 12 6 12 2 Engine 12 2 1 Removal and installation of engine 12 7 12 3 Engine cowlings 12 9 12 4 Engine air intake system 1
108. ake AT3 47 100 0 AT3 61 390 0 Strobe lights AT3 61 400 0 Position lights mmm SS NN SS p Cabinairintake AT3774000 po as je p NN and NNI installed equipment O equipment not installed 17 2 MAY 2007 MAY 2007 FORM 17 2 17 1 1 AERO Sp z o o SECTION 6 AT 4LSA WEIGHT AND BALANCE OPTIONAL EGUIPMENT Type of eguipment Model Installed Equipment installed o Equipment not installed MAY 2007 Page 6 11 AIRPLANE FLIGHT MANUAL Doc No ATL4 02A 17 1 2 FORM 17 2 MAY 2007 SECTION 6 AERO Sp z o o WEIGHT AND BALANCE AT 4LSA 6 5 Usable weight Baggage 22 33 44 55 66 Fuel E db Ib Ib Ib Ib Ib 3 US gal we _ foe PO GO O 36 Ib DUI tt j 54 Ib foe ft POG O 72 lb ow 90 Ib 18 5 US gal wwe tlt tt Completed by SISU AUCs viens as Ce The table above contains total weight of pilot and passenger against fuel and baggage weights Application of data contained in the table prohibits from exciding of allowed maximum weight and center of gravity limits Any change in airplane empty weight requires new creation of above table as per procedure given at AT 4LSA Airplane Maintenance Manual Page 6 12 MAY 2007 AIRPLANE FLIGHT MANUAL Doc No ATL4 02A FORM 17 3 AT 4LSA AEROPLANE ALIGNMENT SHEET for bench mark location refer to Chapter 7 item 7 2 SERIAL No CALL SIGN No Measured values P starb
109. allation of the stall warning on the fuselage 1 Instrument panel 3 Warning light 2 Warning unit MAY 2007 18 4 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z o o SUPPLEMENT No 4 AT 4LSA Figure 2 Location of the stall warning sensor on the wing 1 Stall warning sensor 3 Leading edge skin 2 Electric cables 3 ACI T1Stall warning electric installation The stall warning system is supplied from the electrical system of the airplane and protected by the STARTER fuse Additional protection is given by a 1 0 A fuse inside the warning unit Figure 3 Warning unit Sensor and warning light cable 4 Alarm sounder 2 Circuit breaker 1A 20mm 5 Unit case 3 Electric supply cable 18 4 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o SECTION 18 AT 4LSA SUPPLEMENT No 4 No ACITI Behind he mine panel Stall warning sensor ACI TI leading edge of the left wing SP3 jConmecor left side of the cabin Warning light SP4 17371250 Instrument panel 12V BUS si Figure 4 ACI T1Stall warning electric installation MAY 2007 18 4 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z o o SUPPLEMENT No 4 AT 4LSA PAGE INTENTIONALLY LEFT BLANK 18 4 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z CHAPTER 18 AT 4LSA SUPPLEMENT No 5 SUPPLEMENT No 5 Transponder GARMIN GTX327 Fl SPOL Fe on
110. anasreceiver Press RESET switch on control panel and check whether transmission was interrupted and both control lights are not illuminating 18 6 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 6 AT 4LSA 3 1 Periodic maintenance In addition to the periodic maintenance requirements prescribed in Paragraph 3 4 the following tests must be performed to comply with Engineering and Inspection Manual Part II Chapter III Section 3 12 7 lei NOTE These tests should be performed only within an RF Screen Room or Facility providing shielding of RF Emissions 5 2 Power output test 1 Connect the Equipment as shown below AVERAGE POWER METER Or PEAK READING WATTMETER Or SPECTRUM ANALYZER 2 Connect the RF Output of the ELT to an Average Power Meter or a Peak Reading Wattmeter or a Spectrum Analyzer NOTE If measuring power with an Average Power Meter be sure to add 43 dBm to the average measurements to obtain Peak Power 50 Sguare Wave Modulation 3 The minimum power allowed on 121 5 MHz is 20 5 dBm or H2mW and on 243 0 MHz is 19 5 dBm lor 89 mWJ 5 3 Frequency test 18 6 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z CHAPTER 18 AT 4LSA SUPPLEMENT No 6 The ELT transmitter freguency may be measured as follows 1 Connect the Frequency Counter as shown below FREOUENCY ELT AK 4S0 NOTCH FILTER COUNTER 2 Select
111. and excessive plays 5 8 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A MAY 2007 AERO Sp z o o CHAPTER 5 AT 4LSA INSPECTION Nature of Inspection Inspection time hrs e e r N E FUSELAGE AND EMPENNAGE GROUP cont 16 Inspect general condition and fixing of elevator unit outrigger 17 Inspect trim and balancing flap for damage and proper mounting 18 Inspect general condition and fixing of antennas and electric wiring 19 Inspect lighting lamps anti collision and navigation lights for attachment and operation 20 Lubricate ball bearings of elevator unit attachment and rudder and trim and balancing flap hinge F WING GROUP 1 Inspect wing attachment joints for damage cracks and loose attachment 2 Check bolted joints torque between wing spars and fuselage 3 Inspect structure of wing tips ailerons and flaps externally for general condition damage and proper attachment Inspect structure of wing tips ailerons and flaps internally through all access doors and accessible openings for damage cracks and corrosion Check aileron and flap hinges for plays and attaching Inspect general condition and fixing of aileron balancing weight Lubricate aileron and flap hinges Inspect pressure port for attachment and cleanness Check Pitot and static pressure systems hoses and electric system inside wing for general condition and fixing G CONTROL SYSTEMS 2 Insp
112. and condition Check condition of the rubber elements Check condition and fastening Check condition and fastening Check if the towing rod is removed 3 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 3 AERO Sp z 0 0 SERVICING AT 4LSA 6 Main landing gear Tires Visually check tire pressure and condition Brake disc Check condition Brake caliper Check condition and wear of the brake pads Brake line Check condition and fastening to the leg Leg Check condition of the leg and connection with the fuselage Wheel fairing Check condition and fastening 7 Starboard wing Wing structure Check condition of the upper and lower skin Wing tip Check condition and fastening Position light optional item Check condition and fastening Strobe Light optional Check condition and fastening Aileron Check condition of structure play in the hinges and control system Inspection hole lower wing Open it check the aileron control system and surface condition shut the inspection hole Wing flap Check condition of structure play in the hinges and control system Wing fuselage fairing Check condition and fastening 8 Fuselage rear part starboard Fuselage structure Check condition and cleanliness Inspection holes lower Open it check the control system shut the fuselage surface inspection holes 9 Tail unit Vertical stabilizer Check condition and cleanliness Rudder Check conditi
113. anger Disconnect the fastening springs Unscrew the bolts fastening the pipes to the cylinder heads Using a rubber hammer loose the connections pipes muffler Remove the muffler O O O O FW DPD Remove the exhaust pipes Installation 1 Perform steps 1 to 9 in reverse order 2 For bolted joints torque limits refer to Chapter 16 6 CAUTION WHEN REINSTALLING THE EXHAUST SYSTEM SEAL THE CONNECTIONS BETWEEN THE EXHAUST PIPES AND THE MUFFLER WITH LOCTITE SEALANT AND WRAP THE SPRINGS WITH SECURING WIRE AND FILL WITH HIGH TEMPERATURE PROOF ORGANO SILICONE POLYMERS MAY 2007 12 13 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 12 POWER PLANT 12 6 ENGINE MOUNT AERO Sp z o o AT 4LSA The engine is attached to fuselage structure through two part engine mount welded with alloy steel pipes The large mount and the small mount are jointed through the rubber shock absorbing bushes The large mount is attached to in four points to the firewall by means of bolts The small mount with the carburetor heat exchanger is attached directly to the engine 1 Large engine mount 2 Small engine mount 3 Shock absorbing bushes 12 14 Figure 12 4 Engine Mount 4 Engine attaching bolts 5 Heat exchanger 6 Firewall MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc
114. appear to be badly corroded they must be replaced 3 Record the Battery replacement date of the new cells being installed using one of the adhesive labels provided with the ELT The Battery replacement date is found on each Duracell MN 1300 cell See Figure 4 It reads as follows Best if installed by Date The Date indicated is the date by which the Batteries must be replaced Ali cells must have the same date Install the new Batteries as indicated by the Battery installation placards which are affixed to the inside of the Battery Case 4 After installation a voltage and polarity check must be performed to insure that the batteries have been installed correctly See Figure 4 MAY 2007 18 6 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 6 AT 4LSA 5 After performing the above voltage check install the Battery Case to the Transmitter Assembly making sure that all three UP Arrow markings located on the Battery Case the Battery Separator and the Transmitter Assembly are in the same direction Ensure that the O Ring seal is in place See Figure 4 6 Place the Transmitter Assembly face down on a bench Press down on the Battery Case to compress the Battery Contact Springs Replace the four Battery Retaining Screws and Lock Washers and evenly tighten until the Battery Case is pulled fiat against the Transmitter Assembly If the O Ring appears to be pinched between the Case and the Trans
115. ariants fixed or foldaway Both variants are attached to the attachment points at the front wheel axel To fold the foldaway towing bar remove pin fixing towing bar handle slide handle to compress tow bar The foldaway tow bar attaches to the rear cockpit bulkhead for transport via 3 attachments To lock stick and brake pedals with foldaway tow bar attach tow bar arms to the pedals remove pin and use it to attach movable arm to the stick extend towing bar until stick and pedals are locked To unlock release the catch Locking of stick and pedals with use of foldaway towing bar 1 Foldaway tow bar arms 2 Pin 3 Catch 2 7 AIRPLANE ASSEMBLING AND DISASSEMBLING Disassembling 1 Disassemble wings as per chapter 9 point 2 1 2 Disassemble elevator as per chapter 9 point 3 1 3 When required disassemble propeller as per chap 12 point 1 1 and rudder as per chap 9 point 4 1 main undercarriage as per chap 10 point 2 and front undercarriage as per chap 10 point 1 Assembling Execute points 1 3 as per relevant procedures in reversed sequence MAY 2007 2 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 2 AERO Sp z o o HANDLING AT 4LSA 2 8 TRANSPORT OF DISMANTLED AIRPLANE This chapter contains guidelines on how to prepare the dismantled airplane for transport Prior to choosing the transport vehicle refer to the overall dimensions given in chapter 1 2 View of the airplane three projections
116. ary data for assuring continuous airworthiness of the airplane indicating when and how a maintenance should be performed how to detect malfunctions and remedy them how to replace assembles or parts in the frame of tasks defined by the manufacturer as normal maintenance tasks All information contained in this manual is based on the data and experience In usual circumstances this information is adequate and sufficient for persons which possess professional aviation knowledge aviation experience and have professional aviation maintenance qualification All information contained in this manual and in other manuals delivered with the airplane is useful and necessary during self training On the procedures for this aircraft However it cannot be considered a substitute of theoretical and practical training in aviation engineering and maintenance The information and components system descriptions contained in this Manual are correct at the time of publication AERO however maintains a policy of continuous improvement of its products without imposing upon itself any obligation to install them on its products previously manufactured AERO reserves the right at any time to discontinue or change specifications designs features models or equipment without incurring obligation WARNING Never fly the aircraft equipped with engine at locations airspeeds altitudes or other circumstances from which a successful no power landing cannot be made a
117. bility of the airplane Check stall speed and minimum speed when the throttle is set in low speed position with flaps in retracted and extended positions Check trim tab efficiency Perform maneuvers according to section 2 8 Approved maneuvers of the Flight Manual Maintaining Vee speed check flaps Note in the Form 17 4 indications of the engine instruments and airspeeds when engine speeds are set Check radio transceiver navigation equipment 5 5 7 Speed increasing Perform a glide flight with engine at idle and flaps retracted Evaluate the engine run Record indications of the engine instruments in the Form 17 4 5 5 8 Landing Perform landing according to section 4 5 13 Landing of the Flight Manual evaluate the airplane during landing Defects stated during test flight should be recorded in Form 17 4 Defects should be checked in maintain manual Defects alerting should be noted in Form 17 4 After the Test Flight Form should be completed and signed A flight ended with satisfactory result empowers the pilot to state that airplane can be realeased to service MAY 2007 5 13 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 5 AERO Sp z 0 0 INSPECTION AT 4LSA PAGE INTENTIONALLY LEFT BLANK 5 14 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 6 AT ALSA WEIGHTING AND BALANCE CHAPTER 6 WEIGHT AND BALANCE 6 1 Introduction 6 2 6 2 Weighing procedure 6 2 6
118. bles pass through the elements of fuselage structure under covers 11 and are supported by rollers 9 Figure 11 7 Rudder control system 1 Support 8 Linkage rollers 2 Stops 9 Guide rollers 3 Tension spring 10 Rudder cables 4 Pedals 11 Cable covers 5 Connecting link 12 Cable bolts 6 Linkage cable 13 Rudder 7 Covers of the linkage cables 14 Cable adjusting nuts 11 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 11 AT 4LSA AIRPLANE CONTROLS 11 3 1 Removal and installation of the rudder control system Removal 1 Remove the engine cowling refer to section 12 3 cockpit canopy refer to section 13 6 1 fuel tank cover refer to section 12 7 the upholstery of the central tunnel refer to section 13 3 1 the fuel tank refer to section 12 7 1 and covers of the linkage rollers Remove the rudder refer to section 9 4 1 Disconnect the springs tensioning the rudder cables Disconnect the rudder cables and linkage cables from the rudder pedals W N Drain the brake fluid from the brake system and disconnect the feeding lines and pressure lines of the brake cylinders refer to section 10 3 6 Unscrew the support 1 fixing the controls to the structure CAUTION Remember install the supports to the same place When removing mark the pairs and front side of the support and the place where the
119. breaker 37 POSITION LIGHTS automatic circuit 52 GPS circuit breaker breaker 38 TAXING LIGHTS automatic circuit breaker 53 ARTIFICAL HORIZON circuit breaker 39 LANDING LIGHTS automatic circuit breaker 54 DIR GYRO circuit breaker 40 INSTR LIGHTS automatic circuit breaker 55 INSTR light dimmer 41 TURN COORD circuit breaker 56 CABIN light dimmer 42 COMM circuit breaker 5 ENGINE MONITOR light dimmer 43 STARTER circuit breaker 44 ENGINE INSTRUMENTS circuit breaker 13 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 13 AT 4LSA CABIN Figure 13 3 central console 58 Choke 59 Carburetor preheating knobs 60 OIL HEATING leaver 61 CABIN HEAT leaver 62 CABIN VENT leaver 63 Ignition switch 64 Parking brake lever 64 MAY 2007 13 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 13 AERO Sp z o o CABIN AT 4LSA Figure 13 5 LH side of the center console Figure 13 6 Panel between seats 9 Flaps control lever 67 Microphone sockets 65 Trim wheel 68 Headphone sockets 66 Seats 69 Fuel shut off valve 13 1 1 Disassembly and assembly of the instrument panel Disassembly 1 Remove the canopy and fuel over tank cover 2 Disconnect the throttle control rod from the torsion tube and remove them from the instrument panel Remove the screws which secure the base of the instrument panel to the fuselage structure Disconnect all electric w
120. broker Detailed description of avionics instruments is in charter 18 Supplements of this Manual MAIN BUS 12V 15A AVIONIC MASTER RADIO GPS TRANSPONDER Figure 8 Avionics electrical system 15 18 MAY 2007 AIRPLANE MAINTENANCE MANUAL AERO Sp z o o CHAPTER 15 AT 4LSA ELECTRICAL SYSTEM 15 7 HOUR METER optional The HOUR METER records the total engine time The decimal counter counts with the accuracy of 1 10 of an hour The hour meter is activated with a pressure switch connected to the oil system of the engine The switch activates the hour meter when the oil pressure rises above 0 03 Mpa 15 7 1 Removing and installation of the hour meter pressure sensor Removing 1 Remove the upper and the lower engine cowling refer to section 12 3 2 Remove the heat exchanger air inlet refer to section 13 7 3 Disconnect the sensor electric cables 4 Unscrew the sensor from the connector in the oil pump cover 5 If necessary unscrew the connector Installation 1 Perform steps 1 5 in reverse order Figure 2 The pressure sensor location on the engine 1 Pressure sensor MAY 2007 15 19 AIRPLANE MAINTENANCE MANUAL CHAPTER 15 AERO Sp z o o ELECTRICAL SYSTEM AT 4LSA 15 7 2 Hour meter electric installation The hour meter MT1 is supplied from the airplanes electric installation trough the pressure sensor MT2 No Pressure sensor HOBBS M4006 4 Hour meter Hobbs Instrument
121. cator 8 Pitot tube 4 Pitot pressure line 9 Static pressure port 5 Static pressure line 14 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 14 AERO Sp z o o STATIC AND PITOT PRESSURE SYSTEM AT 4LSA Figure 14 2 View of pressure lines behind the instrument panel 1 Instrument panel 4 Static pressure line 2 Sidewall 5 Pitot pressure line 3 Flexible hoses of instruments 14 2 DRAINING OF SEDIMENT FROM THE SYSTEM To drain the water sediment from the system have unscrewed the caps from the sediment traps After drainage screw caps and check the system for leaks MAY 2007 14 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 14 AT 4LSA STATIC AND PITOT PRESSURE SYSTEM 14 3 PRESSURE SYSTEM LINES CONNECTIONS IN WING AND FUSELAGE Figure 14 3 Pressure system lines connections between wing and fuselage 1 Pressure lines in the fuselage 4 Water sediment traps 2 Pressure lines in the wing 5 Trap caps 3 Root rib connector of left wing To get an access to connections in the fuselage and the wing remove L H sidewall panel refer to section 13 3 1 To disconnect pressure lines system unscrew fitting screws and disconnect lines 14 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 14 AERO Sp z o o STATIC AND PITOT PRESSURE SYSTEM AT 4LSA 14 4 REMOVAL AND INSTALLATION OF THE PRESSURE SYSTEM PORTS Ep up Figure 14 4 Pressure ports assembly 1
122. cing tab deflection angles adjustment 1 Lock the slab tail control mechanism in the neutral position refer to section 11 1 3 2 Set the trim control wheel to the nose down position 3 Set the screw gear in extremely rear position 4 Adjusting the length of the pushrods set the trim and balancing tab in the 7 5 1 position trailing edge up 5 Unlock the slab tail control mechanism and check the elevator and trim for fee travel in the whole range of angles Check the deflection angles of the trim and balancing tab Slab tail elevator and trim and balancing tab deflection angles related from the level Slab tail elevator deflection Trim and balancing tab Trim and balancing tab angle deflection angle position 12 7 35 3 7 0 Tob Mia Nose down 10 s 11 3 12 2 20 3 7 trailing edge down 7 trailing edge up MAY 2007 11 15 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 11 AERO Sp z o o AIRPLANE CONTROLS AT 4LSA PAGE INTENTIONALLY LEFT BLANK 11 16 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A 12 1 12 1 1 12 1 2 12 1 3 12 2 12 2 1 12 3 12 4 12 4 1 12 4 2 12 5 12 5 1 12 6 12 6 1 12 7 12 7 1 12 7 2 12 7 3 12 7 4 12 7 5 12 7 6 12 8 12 8 1 12 8 2 12 9 12 9 1 12 10 12 10 1 MAY 2007 CHAPTER 12 POWER PLANT Propeller Removal and installation of propeller Blade linear tracking alignment check Checking an
123. clean it according to Maintenance Manual section 5 2 12 00 00 of Rotax 912 engine Disconnect lower line from oil cooler 6 Drain oil from the cooler 7 Unscrew the oil filter Checked it according to Maintenance Manual section 5 2 12 00 00 of Rotax 912 engine 8 When contaminations are found in the oil system it is necessary to rinse oil cooler using agents according to Maintenance Manual section 5 2 12 00 00 of Rotax 912 engine 9 Lubricate the seal of the new oil filter with oil and screw the filter onto the engine by hand 10 Screw the draining plug into the tank again but use a new seal Lock the plug with wire 11 Connect the lower line to the oil cooler and return line to the oil tank 12 Fill the tank with about 2 11 US qts oil 13 Remove spark plugs 14 Trough the suction line of the oil tank fill cooler with oil using the funnel of an oil gun Turn slowly the propeller until oil is sucked in by the engine pump 15 Connect the line to the tank and reinstall spark plugs MAY 2007 12 23 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 12 AERO Sp z o o POWER PLANT AT 4LSA 16 Start the engine Oil pressure must rise up to 30 psi 2 bar per 10 sec If oil pressure reached required value observe for a while at low engine speed and then turn it off CAUTION If oil pressure did not reach required value turn off the engine and repeat the bleeding of the line connecting the oil tank with
124. coolant in the cylinder heads after a full Power engine run up engine cooling at 2000 rpm is reguired for a short time 14 Smooth increase and reduction of Check engine speed RECOMMENDATION Move the throttle lever smoothly so that the full range of travel is reached within 3 seconds NOTE After returning the throttle lever to IDLE allow about 3 seconds for the engine speed to stabilize before you increase the speed again 3 12 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 3 AT 4LSA SERVICING 3 4 Switching off the engine 1 Radio eguipment OFF 2 Electric equipment OFF 3 Throttle lever To be set to IDLE 4 Ignition switch Set key to OFF After the engine stops 5 BATTERY and GENERATOR OFF down switches 6 Fuel valve OFF Pull 3 5 Using the external ground power The electrical system of the airplane is capable of utilizing external power sources ground power The external power receptacle of 11041 type is installed on the port side of the airplane in the area of the lower engine cowling next to the firewall The cable to connect the external power has been delivered with the airplane and its polarity is marked Its male connector is to be plugged into the receptacle of the airplane and the free ends are to be connected to the external battery with the crocodile terminals The correct of the polarity of the connection must be strictly observed Th
125. coolers for condition and attachment and oil cooler flap for general condition and operation 33 Inspect cabin heater for attachment and leak tightness 34 Inspect heated air cabin mixer for general condition attachment and leak tightness 35 Inspect cabin and carburetors heating hoses for securing chafing 36 Inspect filters box for general condition and attachment Check operation of carburetor heating flap 37 Inspect electric fuel pump for securing and leak tightness x xx x x x 38 Clean electric fuel pump filter and fuel tank filter Px x x x x 39 Replace fuel filter on firewall 40 Inspect rigid fuel lines on firewall for securing leakage and cracks 41 Inspect drain lines for general condition and fixing 42 Inspect carburetor heating control mechanism for displacement range and securing 43 Inspect equipment attached to firewall for general condition and securing MAY 2007 5 7 AIRPLANE MAINTENANCE MANUAL Doc No A TT4 02A CHAPTER 5 INSPECTION AERO Sp z 0 0 AT 4LSA Nature of Inspection Inspection time hrs C ENGINE GROUP cont 44 Check battery electrolyte level and condition of battery clamping elements 45 Inspect firewall engine mount joints and nose gear joints for cracks damage and tightness condition 46 Inspect general condition and securing of brake lines and fluid level in brake reservoir refill as required 47 Perform mechanical and pneumatic carbure
126. d MAY 2007 18 3 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z 0 0 SUPPLEMENT No 3 AT 4LSA A part from geographical data reports can appear on the screen see GPSMap user s manual After establishing position GPS can be used as a supporting navigation device To switch off GPD press and hold Power button 1 2 Basic aviation applications GPS Map receiver is offering three main modes aviation naval and automotive Change of mode is possible with use of PAGE and QUIT buttons Each of those modes has its own menu In Aviation Mode five submodes are available as follows Terrain Page Panel page Active Route Page 345 015 1034 00 00 1034741 390 10 12211 Position Data Page 10 18 50 0000 00 00 05 6525 TAN From Johnson Co Executive 18 3 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 18 AT 4LSA SUPPLEMENT No 3 1 3 Direct To function Direct To function is initiated with 3 button If pressed Direct To page will be opened Select the airport navid or defined waypoint you want to fly to To activate airport of David follow the procedure 1 Open Direct To page with o button and with ROCKKER select following window 2 Select type of ID airport nawid waypoint etc 3 Select particular ID airport David waypoint town etc and confirm it with ENTER 4 Press ENTER when selected point is highlighted 5 When yellow
127. d Pitot pressure system 14 1 Static and Pitot system diagram 14 2 Draining of sediment from static and Pitot system 14 3 Static and Pitot system connection in fuselage and in wing 14 4 Removal and installation of static sensors 14 5 Checking of static and Pitot system for leaks 0 8 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o AT 4LSA 13 2 13 6 13 8 13 8 13 8 13 8 13 9 13 10 13 10 13 11 13 12 13 13 13 14 13 15 13 15 14 2 14 3 14 4 14 5 14 6 MAY 2007 AERO Sp z o o CHAPTER 0 AT 4LSA BASIC INFORMATION 15 Electrical system 15 1 Electric power and starter circuit 15 2 15 2 Alternator electrical installation 15 6 15 2 1 V belt tension adjustment 15 8 it eee 15 9 15 2 3 15 9 15 3 Engine electrical system and engine 15 10 monitoring instruments 15 3 1 Engine Monitor 15 13 15 4 Electrical system of fuel gauge 15 16 15 5 Gyro instruments electrical system 15 17 15 6 Avionics electrical system 15 18 15 7 Hour Meter 15 19 15 7 1 Removing and installation of the hour meter 15 19 15 7 2 pressure sensor 15 20 Hour meter electric installation 15 8 Anti collision light electrical system 15 21 15 8 1 Removal and installation of anti collision light 15 22 15 9 Lighter electrical system 15 23 15 10 Battery 15 24 15 10 1 Removal and installation of battery 15 24 15 10 2 Battery charging 15 25 16 Repairs 16 1 General information 16 2 16 1 1 Tools and materials for repair of minor damages 16 2 16 2
128. d adjustment of the blade angle of incidence Engine Removal and installation of engine Engine cowlings Engine air intake system Removal and installation of air filter box Air filters replacing Exhaust system Removal and installation of exhaust system Engine mount Removal and installation of engine mount Fuel system Removal and installation of fuel tank Removal and installation of fuel valve Removal and installation of fuel filter Removal and installation of electric fuel pump Removal of fuel sensor Calibration of fuel gauge and setting fuel reserve indicator Cil system Operation of oil cooler shutter Oil change Cooling system Replenishment of the engine coolant Engine controls Throttle push rods disassembly and assembly AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A 12 3 12 5 12 6 12 7 12 9 12 10 12 11 12 11 12 12 12 13 12 14 12 15 12 16 12 18 12 19 12 19 12 20 12 20 12 20 12 21 12 22 12 23 12 25 12 26 12 27 12 28 12 1 12 1 Description ELPROP 3 1 1P propeller is a three blade ground adjustable propeller with blades manufactured from carbon fiber and a hub consisting of two aluminum parts The blades are fixed to the hub with a self locking mechanism The propeller is equipped with a composite spinner fixed to the prop with an aluminum spinner disc The propeller is installed on the engine with a shaft extension Detailed information on the ELPROP propeller characteristics limitations installation ma
129. e elevator 1 Additional balancing weights 3 Balancing stand 2 Locking screw CAUTION Mass balancing must be carried out indoors in a draught free area with no air movement 1 Position the elevator in the stand 3 2 Add or remove weight from the outrigger until the chord of the elevator brought to a horizontal position 3 Additional balancing weights 1 should be put to the upper side of the outrigger and secured with a locking screw 2 To remove a surplus weight the casting should be drilled or filed 11 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 11 AT 4LSA AIRPLANE CONTROLS 11 2 AILERON CONTROL SYSTEM The ailerons are attached to the structure by means of hinges The ailerons are moved by the control system consisting of push rods intermediate levers and the control sticks in the cockpit The coupling rod connects the control sticks The ailerons displace differentially i e 20 2 upward and 15 2 downward Figure 11 4 The aileron control system inside the wing 1 Long push rod 4 Aileron 2 Bell crank lever 5 Electric bonding cable 3 Short push rod Wing spar Figure 11 5 The aileron control system inside the fuselage 1 Torque tube 6 Electric bonding cable 2 Stops 7 Control stick Lever 3 Long push rod 8 Coupling rod 4 Push rod bellows Cabin side wall 5 Mounting of the torque tube I Floor MAY 2007 11 5 A
130. e preformed by an authorized person or organization qualified and approved by local airworthiness authority To eliminate possible injury or damage ensure any loose equipment or tools are properly secured before flight When in storage protect the aircraft and fuel system from contamination and exposure Certain operating locations altitudes and conditions present greater risk than others The engine may require carburetor recalibration or humidity or dust sand preventative equipment or additional maintenance may be required Never operate the engine and gearbox without sufficient quantities of lubricating oil Drawings placed in this manual are representative only to assist in general understanding They are not suitable for manufacture of parts or sub assemblies In case of doubts concerning manuals delivered with the airplane or problems with maintenance of the airplane please contact the manufacturer AERO Sp z O O 03 942 WARSZAWA ul Wal Miedzeszynski 844 POLAND tel 48 22 616 20 87 fax 48 22 617 85 28 E Mail info at 3 com MAY 2007 0 13 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 0 AERO Sp z 0 0 INSPECTION AT 4LSA 0 2 SAFETY INFORMATION To emphasize particular information in this manual below mentioned expressions are used WARNING means that if the warnings concerned are not followed this will lead to serious injuries or death CAUTION means that if the precautions concerned are not fo
131. e voltage of the external source must be 12 to 14 Volts The engine starting procedure using an external power source is the same as standard starting procedure After completing engine start Disconnect the external power cable From the receptacle NOTE Connection of the wrong polarity may result in damage to the airplane s electric system MAY 2007 3 13 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 3 AERO Sp z 0 0 SERVICING AT 4LSA 3 6 Daily post flight inspection 1 Receive the pilot s report on airplane operation 2 Perform inspection of the structure as under 3 1 Daily pre flight inspection items 2to 10 3 Check for leaks of fuel oil and coolant 4 Prepare the airplane as required for the location and period of parking 5 Make respective entries in the Airplane and Engine Log Books concerning the completed flights 3 7 Refueling A detailed description of the fuel system is given under 12 7 Fuel system The total capacity of the system is 19 42 US gal MOGAS ASTM D4814 or AVGAS 100LL ASTM D910 may be used However it should be observed that when AVGAS 100LL is used more frequent oil changes i e every 25 hours is required Refer to the Rotax 912 Series Engine Operating Manual for limitations and recommendations relating to fuel grades used The fuel filler is on the upper side of the fuselage between the firewall and the cockpit canopy The filler cap contains a gauge stick which shows
132. ect pedals and their slide bearings for general condition and attachment Inspect rudder control cables and pedal stays for chafing bends and corrosion Check cables tension and general condition of pulleys 4 Inspect general condition and operation of elevator control system 5 Inspect control pushrods together with torque pipe for general condition and smoothness and range of deflection 6 Inspect general condition and fixing of elevator intermediate lever 7 Inspect general condition and operation of aileron control system 8 Inspect aileron intermediate levers for general condition and attachment 9 Inspect general condition and operation of trim control mechanism MAY 2007 3 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 5 AERO Sp z 0 0 INSPECTION AT 4LSA Nature of Inspection Inspection time hrs G CONTROL SYSTEMS cont Inspect flap control mechanism for general condition and smoothness and range of deflection Inspect flap torque pipe and their slide bearings for general condition and attachment Inspect general condition of flap drive seats and their attaching to flaps Inspect all push rods of control system for general condition chafing and loose ends Inspect general condition of bonding at all control systems Lubricate push rods and cables flap drive seat trim control system 3 Inspect brake hoses for general condition chafing and leaks
133. efer to Ch 14 3 Put 9 8 mm 0 385 in dia rod into the service hole 2 of the spar box Unscrew the nuts from the main spar bolts Slightly lift up the wing tip to loosen the bolts and remove the bolts Remove the bolt from the rear spar Move the wing outside the fuselage Figure 9 4 Wing installation 1 Main wing spar 4 Main bolts 2 Service hole 5 Rear bolt 3 Rear wing spar 6 Wing fuselage fairing MAY 2007 9 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 9 AERO Sp z o o AIRPLANE STRUCTURE AT 4LSA CAUTION When removing the wing slight swinging of the wing is allowed but the natural wing dihedral relative to the fuselage must be maintained especially when only the last bolt is in its hole Extensive motion may damage the wing spar box Installation 1 2 9 10 11 12 Set the wing flap control lever in cockpit to 40 Put in the main wing spar into the wing spar box and the rear one into its fuselage fitting Put in the wing flap control system into its fitting Put a 9 8 mm 0 385 in dia rod into the service hole 2 of the wing spar box Fix the rear spar temporarily with a 5 mm 0 197 in dia pin Lubricate the spar bolts with grease Screw a guide pin of 10 dia M8 onto the bolt of the spar and drive it into the hole of the wing spar box fitting Screw off the guide pin and repeat this operation with all the remain bolts Remove the pin from the rear spar hole
134. el upholstery and console between seats Inspect for general condition 8 Drain fuel sample and inspect for presence of water 9 Drain fuel tanks B PROPELLER GROUP 1 Remove and inspect spinner for distortion and cracks 2 Inspect visible part of propeller blades area for distortion and cracks specially blades leading edge and handle 3 Inspect visible part of propeller head propeller mounting screws and head mounting bolts for general condition 5 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o AT 4LSA CHAPTER 5 INSPECTION TABLE V I INSPECTION REPORT Nature of Inspection B PROPELLER GROUP cont 4 Checktorque of screws and bolts 5 Inspect that clearance between head halves at least 0 05 m 0 020 exist Inspection time hrs Ammual C ENGINE GROUP 2 3 4 7 Perform visual engine inspection for damage and abnormality specially of air intake tunnel delivered air to cool the cylinders condition of cylinder ribs for clogging cracks and overheating Inspect oil temperature and pressure senders head temperature transmitter exhaust gas temperature EGT sensor and fuel pressure sensor for securing and condition Check fixing of electric wiring Inspect cooling system hoses for damage leaks lost elasticity porosity and attachment reliability Check hose routes for loops and excessive bends refer to ROTAX engine Maintenance Manual
135. emoval and installation the nose wheel see Figure 10 2 Removal Lift the nose of the airplane Unlock and unscrew the wheel axle nut Remove the wheel axle 4 Move off the wheel from the fork Deflate the tube Unscrew and separate the halves of the wheel hub Note the duralumin distance sleeve of the hub bearings 2 O G W N Installation 1 Perform steps 2 to 6 in reverse order 2 Lubricate all joints 3 Inflate the wheel with compressed air 4 For bolted joints torque limits refer to Chapter 16 6 1 lt SKIN ZI L Figure 10 2 Cross section of the nose wheel hub 1 Half of the wheel hub 5 Wheel fork 2 Distance sleeve of the hub bearings 6 Nutlock 3 Distance sleeve 7 Axle lock 4 Wheel axle MAY 2007 10 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 10 AERO Sp z o o LANDING GEAR AT 4LSA 10 1 2 Removal and installation the fork Removal 1 Lift the nose of the airplane 2 Unlock and unscrew the shimmy damper nut 3 Unlock and unscrew the castellated nut of the fork axle 4 Move off the fork from the axle Installation 1 Perform steps 2 to 4 in reverse order 2 Lubricate all joints 3 For bolted joints torque limits refer to Chapter 16 6 10 1 3 Removal and installation the fork axle Removal 1 Lift the nose of the airplane 2 Remove the fork as per section 10 1 2 3 Unlock a
136. ent panel and central console 1 Left throttle lever 7 Radio transceiver 2 Engine monitor 8 Transponder 3 Trim tab setting indicator 9 Flaps control lever 4 Air inlets 10 12 DC supply 5 Magnetic compass 11 Push to talk buttons 6 GPS 12 Control sticks 13 Air inlet cable MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o AT 4LSA CHAPTER 13 CABIN Figure 13 2 1 Right part of the instrument panel 14 Stall warning light 15 Artificial Horizon 16 Airspeed indicator 17 Turn coordinator 18 VOR with G S indicator 19 Altimeter 20 Directional Gyro 21 Vertical speed indicator MAY 2007 22 RPM indicator 23 Fuel pressure indicator 24 Fuel level indicator 25 FUEL RESERVE light 26 FUEL PUMP ON light 27 ALTERN FAILURE light 28 GEN FAILURE light 29 Starter Engaged Light 13 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 13 AERO Sp z o o CABIN AT 4LSA Figure 13 2 2 Left part of the instrument panel 30 BTTERY automatic circuit breaker 45 ELT control panel 31 GENERTAOR automatic circuit breaker 46 Hours meter 32 ALTERNATOR automatic circuit breaker 47 ENGINE MONITOR circuit breaker 33 FUEL PUMP automatic circuit breaker 48 FUEL circuit breaker 34 AVIONICS MASTER automatic circuit 49 12 DC SUPPLY circuit breaker breaker 35 GYRO INSTR automatic circuit breaker 50 NAV circuit breaker 36 STROBR LIGHTS automatic circuit breaker 51 TRANSP circuit
137. er Equipment Rubber hoses AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o AT 4LSA 3 2 3 9 3 11 3 14 3 14 3 15 3 15 3 16 3 18 3 20 3 20 3 21 3 21 3 22 3 22 3 23 3 23 3 24 3 24 3 25 3 25 4 2 4 2 4 2 4 2 MAY 2007 AERO Sp z o o CHAPTER 0 AT 4LSA BASIC INFORMATION 5 Inspection 5 1 Introduction 5 2 5 2 Inspection reguirements and periods 5 2 5 3 Preflight check 5 3 5 4 Special inspections 5 3 Table V I INSPECTION REPORT 5 4 A Primary steps 5 4 B Propeller group 5 4 C Engine group 5 5 D Cabin group 5 8 E Fuselage group 5 8 F Wing group 5 9 G Control system group 5 9 H Brakes group 5 10 l Landing gear group 5 11 J Final steps 5 11 5 5 Test flight program 5 12 5 5 1 Preparation for test flight 5 12 5 5 2 Ground test 5 12 5 5 3 Taxiing 5 12 5 5 4 Take off 5 12 5 5 5 Climb 5 13 5 5 6 Cruise 5 13 5 5 7 Speed increasing 5 13 5 5 8 Landing 5 13 MAY 2007 0 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 0 BASIC INFORMATION 6 Weighting and Balance 6 1 Introduction 6 2 Weighing procedure 6 3 Calculation of the centre of gravity position 6 4 AT 4LSA airplane weighting amp balance report 6 5 Equipment list 6 6 Weight and moment recording 6 7 The procedure of recording the data in Form 17 2 7 Alignment of the airplane 7 1 Positioning for alignment 7 2 Bench marks location 7 3 Alignment sheet 8 Placards 8 1 External placards 8 2 Internal placards 8 3 Placards on
138. f SL 30 main unit 18 1 8 3 2 Disassembly and assembly of transmission switch 18 1 8 3 3 Disassembly and assembly of MD200 306 indicator 18 1 8 3 4 Disassembly and assembly of COM antenna 18 1 9 3 5 Disassembly and assembly NA V antenna 18 1 9 4 COM and Intercom diagram 18 1 10 9 COM COMPMB UA TION ec 18 1 12 1 1 List of revisions T ee Concernin Revision nr Revision description Pages 5 Date MAY 2007 18 1 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z SUPPLEMENT No 1 AT 4LSA 1 2 List of effective pages 18 1 8 May 2007 18 1 13 May 2007 18 1 14 2007 18 1 2 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 SECTION 18 AT 4LSA SUPPLEMENT No 1 1 Description The SL 30 COM NAV transreceiver is located on right side of the instrument panel It has full communication capabilities and also enables internal communication between crew members intercom It is also working with MD200 306 VOR LOC GS indicator Location of device on instrument panel is shown on Fig 1 1 2 Airspeed heit horn Atimeter
139. f a new airplane engine or an overhauled engine a special inspection is due and its scope differs from the scope of the above mentioned inspections In the practice of these inspections the accommodation of elements which are under stress or exposed to variable temperatures is considered NOTE In addition to inspection intervals required in Table V 1 a preflight check must be performed as described in Paragraph 5 4 The performance of the inspections is to be recorded in the respective Log Book airframe and engine 5 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 5 AT 4LSA INSPECTION If more convenient for the operating schedule the inspections may be carried out earlier that after the nominal time e g not to interrupt a planned operational cycle ouch an earlier performed inspection is valid for the nominal number of hours plus the permissible 1096 tolerance For example if the 100 hour inspection has been performed at 92 flight hours it is valid for 100 10 96 i e 110 hours Thus the next 100 hour inspection is due at 92 110 202 flight hours 5 3 PREFLIGHT INSPECTION The airplane must be given a through preflight and walk around check The pilot and or mechanic must include the preflight check as a normal procedure necessary for safe operation of the aircraft Refer to the Flight Manual or section 3 2 of this manual for listening of items that must be checked 5 4 SPECIAL INSPEC
140. fter sudden engine stoppage Whether you are qualified pilot or a novice complete knowledge of he aircraft its controls and operation is required before any flight Flying any type of aircraft involves a certain amount of risk The Pilot assumes this risk and prepares before each flight taking into account aircraft condition meteorological and other conditions A recognized training program and continued education for piloting an aircraft is absolutely necessary for all aircraft pilots Make sure you also obtain as much information as possible about your aircraft its maintenance and operation from all available sources Before flight ensure that all aircraft controls are operative Make sure all controls can be easily reached in case of emergency Unless in a run up area never run the engine with the propeller turning while on the ground Do not operate engines if bystanders are close In the interest of safety the aircraft must be not left unattended while the engine is running 0 12 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 0 AT 4LSA INSPECTION Keep an aircraft log and respect engine and aircraft maintenance schedules Keep the engine in top operating condition at all times Do not operate any aircraft which is not properly maintained or has engine operating irregularities which have not been corrected opecial tools and equipment may be required engine servicing Servicing should only b
141. g gear well 2 Firewall 9 Partition frame 3 Laminated canopy fuselage fairing 10 Engine mount and nose gear fittings 4 Upper skin 11 Wing rear fitting 5 Laminated fin fuselage fairing 12 Elevator fitting 6 Fin 13 Fin fitting 7 Wing spar box 14 Inspection door 9 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o AT 4LSA 1 Engine upper fitting 2 Angles 3 Engine lower fitting 4 Nose gear fitting 5 Firewall 6 Canopy rotational joint MAY 2007 CHAPTER 9 AIRPLANE STRUCTURE Figure 9 2 Fuselage fittings 7 Canopy gas spring fitting 8 Wing rear fitting angle 9 Flap torque tube block 10 Elevator fitting 11 Rear skid angle 12 Inspection door 9 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 9 AERO Sp z o o AIRPLANE STRUCTURE AT 4LSA 9 2 WING STRUCTURE The cantilever wings of rectangular form are fitted with composite wing tips The skeleton of each wing consists of the main spar 7 the rear spar 8 and nine ribs each rib divided in two parts at the main spar The whole structure is riveted to the skin At the inboard end of the wing between ribs no 1 and no 2 the skin is reinforced with a walkway floor mat 9 and additionally supported with a half rib The wing is connected to the fuselage by means of eight bolts at the flanges of the main spar and one bolt in the rear spar fitting The all metal aileron 2 is mass balanced a
142. g spars with the fuselage M8 1 5 Joint of the parts of engine mount M10 2 3 3 1 3 4 NOTE WHEN TIGHTENING NUTS WITH SPLIT PIN LOCKING APPLY THE MINIMUM TORQUE AND THEN UTILIZE THE MAXIMUM PERMISSIBLE TORQUE TO MATCH THE HOLES FOR THE SPLIT PIN IN THE BOLT AND NUT AS REQUIRED When tightening nuts or screws for which torque moments have not been established apply the following rule Diameter of the thread M5 0 3 0 5 Nm 0 4 0 7 ft ib M6 0 6 0 75 Nm 0 8 1 ft ib M8 1 6 2 Nm 2 2 2 7 ft ib M10 2 3 2 7 Nm 3 1 3 7 ft ib Where it is possible always use a torque wrench and in places difficult to access use common spanner and provide a reliable joint NOTE It is not permissible to reinstall used split pins or locking washers Self locking nuts can be reinstalled Check them carefully before use for proper shape of locking part If necessary replace with new one NOTE Self locking nuts after tightening must be covered with a red paint together with the end of a thread This action allow to detect loose joints MAY 2007 16 15 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 16 AERO Sp z o o REPAIRS AT 4LSA PAGE INTENTIONALY LEFT BLANK 16 16 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z CHPTER 17 AT 4LSA FORMS CHAPTER 17 FORMS 1 Forms list 17 2 2 List of effectives pages 17 2 MAY 2007 17 1 CHAPTER 17 AERO Sp z o o FORM
143. he mixing box to firewall and remove the mixing box Remove two bands fixing the air heater to the silencer and remove the air heater Unscrew central console and tilt it Disconnect air flow control cables iv Installation Perform steps 1 to 7 in reverse order For bolted joints torque limits refer to Chapter 16 6 13 14 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 13 AT 4LSA CABIN 13 8 Cabin air intake option The cabin air intake for ventilation of the canopy and upper part of the cockpit is located in the tank cover Water from the air intake is drain trough the train line Air flow can be adjusted with the pull knob The knob when pulled out fully opens intake The air is supplied to the cabin through the row of holes located above the instrument panel and four inlets The rate of flow can be adjusted by turning the diaphragm and the direction of the air flow by turning the inlet To achieve the maximum air flow on the canopy glass close all four inlets 1 Tank cover 5 Air inlet 2 Air intake 6 Canopy air inlets 3 Control flap 7 Air intake drain line 4 Pull knob 8 Drain outlet 9 Diaphragm 13 8 1 Removing and installation of the cabin air inlet elements All elements of the canopy air inlets and upper cabin ventilation are integrated in the fuel tank cower and are to be removed with the cover Only the vent eyelets are pressed in to the sleeves bonded to the f
144. iddle console and is connected to bar bus through ZP1 circuit breaker No DESCRIPTION DESIGNATION LOCATION LIGHTER circuit breaker 7274 2 7 Instrument panel Lighter socket 57 607 002 Middle console 12V BUS 18 18 Figure 9 Lighter socket electric system 15 23 MAY 2007 AIRPLANE MAINTENANCE MANUAL CHAPTER 15 AERO Sp z o o ELECTRICAL SYSTEM AT 4LSA 15 10 BATTERY The airplane is fitted in G 25 load battery made by GILL Company The battery consists of dry charged plates of high activity If required it may be used instantly after filling the battery with acid without any charging It is a 12 V 18 Ah battery The battery is placed in a box in front of the firewall on port side An access to the battery box is possible after cowling removal The battery box is ventilated with air from the inlet tunnel of coolers 15 10 1 REMOVAL AND INSTALLATION OF BATTERY Removal 1 Have removed the engine cowlings see ch 12 3 2 Remove the safety pin and open the buckle of the band fastening the battery box 3 Remove the cover of the battery box 4 Disconnect from the battery and secure the minus cable Than disconnect the plus cable 5 Remove the battery together with the battery box Installation Perform steps 1 to 5 in reverse order 15 24 MAY 2007 AIRPLANE MAINTENANCE MANUAL AERO Sp z o o CHAPTER 15 AT 4LSA ELECTRICAL SYSTEM 15 10 2 BATTERY CHARGING Filling
145. inders and brake calipers is made as replacement of worn parts or complete unit 10 10 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 10 AT 4LSA LANDING GEAR 10 3 1 Brake fluid replenishment 1 Drain brake fluid from the system using bleeding valves on the brake calipers Follow local regulations about the fluid discarding 2 Fill system with fresh brake fluid 3 Bleed the brake system refer to section 10 3 4 CAUTION Fill the brake system with the DOT 4 fluid The brake fluid shall be replaced every two years 10 3 2 Parking brake valve The parking brake valve in installed in the high pressure brake line between the T distributors and calipers In order to apply the parking brake depress the levers on the rudder pedals and then turn the parking brake lever to the on position This action is causing the remaining of high pressure in the brake calipers The parking valve is installed in the tunnel between seats The brake system with parking valve schematic is to find in section 10 3 2 4 3 2 SZ WN F Figure 10 6 The parking brake valve in off position MAY 2007 10 11 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 10 AERO Sp z o o LANDING GEAR AT 4LSA o a Ra ME Bracket Pressure lines main cylinder Pressure lines to clamps Parking brake valve lever Screws attaching valve to bracket Bracket screws WARNING Parking
146. ing 3 Unscrew the oil filler cap 4 Slowly turn the propeller by hand several times to pump the oil from the engine into the tank The above task is completed when air is pumped into the oil tank which may be recognized by gurgling sounds 5 Remove the gauge stick clean oil from it immerse it in the tank and read the level MAY 2007 3 15 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 3 AERO Sp z 0 0 SERVICING AT 4LSA The level of oil in the engine should be between the Min and Max marks of the stick The difference between the minimum and maximum is 0 78 US gts 1 Oil filler cap 2 Max oil level 3 Min Oil level 4 Oil tank A Excess of oil above the Max mark will cause venting of the oil though the venting pipe WARNING It is prohibited to allow the airplane to takeoff with the minimum amount of oil lower mark The amount of oil over the lower mark must correspond to the planned flight time The approximate oil consumption is about 0 11 US gts per hour 3 16 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 3 AT 4LSA SERVICING Replenishing the oil level 1 Check oil level as indicated above 2 Add the reguired amount of oil 3 Put in the gauge stick 4 Screw the filler cap up tight 5 Shut the cover of the upper engine cowling NOTE A commercial name of the suggested oil Is given in the placard located on the firewall next to
147. initiate entry and to confirm them and to mark waypoint is pressed and held 4 MENU WX button is used to view Options Menu for current page If pressed twice will display Main Manu If pressed and held will turn weather Map Page off and on MAY 2007 18 3 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No AT 4LSA 1 1 button is used to turn unit on and off by pressing and holding it If pressed and released will adjust backlight and external speaker volume IN OUT buttons are used to zoom in and to zoom out the Map Page e ROCKER button is used to select Menu options enter data or move the pointer on the Map Page left Wright up down NRST FIND button is used to show nearest airport navids points of communication and also airspace boundaries in Av Mode When pressed multiple Times in Aviation Mode Find Menu will appear DIRECT TO button is used to start Go To using airports navids recently used waypoints or created waypoints If pressed and held will display additional information for current destination such communication frequency runway data etc Starting Before first start GPS Map must find satellites and define its position Before running GPS it is recommended to check whether antenna 1s connected to the GPS and than 18 3 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z CHAPTER 18
148. installation of the hour meter pressure sensor 15 19 15 7 2 Hour meter electric installation 15 20 15 8 Anti collision light electrical system 15 21 15 8 1 Removal and installation of anti collision light 15 22 15 9 Lighter electrical system 15 23 15 10 Battery 15 24 15 10 1 Removal and installation of battery 15 24 15 10 2 Battery charging 15 25 MAY 2007 15 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 15 AERO Sp z o o ELECTRICAL SYSTEM AT 4LSA 15 1 ELECTRIC POWER AND STARTER CIRCUIT The airplane is fitted with DC system of 12 V rated voltage It is a single conduit system with the minus pole connected to the airplane structure The power source is integral generator with 20 A rated output The rectifier voltage regulator facilitates correct operation of the generator Supply circuit is protected by the fuse 13E Disconnection of the generator from the system is signalized by illuminated red warning lamp 2E Generator failure on the instrument panel The electric power system includes the G 25 acid battery of 18 Ah nominal capacity which provides engine starting emergency power supply in the case of generator failure Voltage at the electrical installation is indicated by engine controller The battery is connected to the electric system by circuit breaker 5E and the relay 6E which is activated by Battery switch 9E installed in the central console of the instrument panel Next to the battery sw
149. intenance repairs storage and transportation are included in the ELPROP Propeller Maintenance Manual Figure 12 1 ELPROP propeller assembly 1 Propeller blade 9 Shaft extension fixing screw 2 Propeller hub 10 Bush 3 Propeller spinner 11 Shaft extension 4 Propeller fixing bolt 12 Spinner disc 5 Washer 13 Blade cover 6 Nut 14 Spinner fixing screws 7 Spring washer 15 ROTAX engine shaft 8 Special washer MAY 2007 12 2 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 12 AT 4LSA POWER PLANT 12 1 1 Removal and installation of the ELPROP Propeller 2 3 Removal CAUTION Before removing the propeller mark the mutual position of the propeller and spinner in relation to the shaft extension Unscrew the fixings screws and remove the spinner and blade covers Remove the wire locking and unscrew the prop fixing bolts Remove the propeller and the spinner disc If necessary remove the shaft extension marking its position in relation to the engine shaft Installation Clean the propeller Check the technical condition of the prop Install the shaft extension aligned with the marks made during removal secure with locking wire 4 5 6 Install the spinner disc aligned with the marks made during removal Install the propeller aligned with the marks made during removal Put the assembly bolts together with flat washers
150. ints torque limits refer to Chapter 16 6 13 5 LUGGAGE COMPARTMENTS There are two luggage compartments in the cabin both with covers with locks and hinges In the right luggage compartment the fire extinguisher is fixed In the bottom of the left compartment an inspection door with cover is installed to enable access to the wing flap actuator Figure 13 8 Luggage compartment 1 Luggage compartment covers 3 Right compartment 2 Fire extinguisher 4 Left compartment 13 10 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 13 AT 4LSA CABIN 13 6 CANOPY The frame of the canopy is made of fiberglass carbon epoxy composite The Plexiglas panels are adhesive to the frame The canopy consists of one piece and opens upwards turning around the axis located in front of it Two gas springs aid the opening of the canopy and hold it in opened position When closed the canopy is locked by a system of levers and push rods separate for each side The canopy is fitted with a jettisoning system which lever is safety with locking wire against unintentionally use Two slide flaps enable additional venting of the cabin As an option additionally the canopy blocking with lock installed in canopy fuselage shield 4 B B C C 1 2 vus D D 3 2 EP a A 4 T 3 1 xs C IB 8 11 ES 1 j 15 4 12 11 10 i KO pc Ja SE Y E E iili a e 2 _ Figure 13 9 mechan
151. ir temperature indicator MEER El isl _ ELE 8 1 2 Inspect operation of ignition switch 13 Inspect operation no plays and range and operation smoothness of engine controls throttle and choke 14 Check operation of flight electronic equipment and engine monitoring system instruments 15 Inspect general inspection and operation of optional equipment installed in the airplane ir IU 17 Inspect operational notes placards and instrument color marking for complexity and readability K GENERAL 1 The airplane conforms to FAA specifications x xw xw x x x 2 All latest Airworthiness Directives complied with 3 All latest manufacturers Service Letters and Bulletins complied with for the airplane engine and equipment 4 Check for proper Flight Manual 5 The airplane papers are in proper order NOTES Inspection after first 25 h Inspection of propeller transmission after 400 flight hour MAY 2007 5 11 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 5 AERO Sp z 0 0 INSPECTION AT 4LSA 5 5 TEST FLIGHT PROGRAM Test flight should be performed to renew Certificate of Airworthiness or after inspection when test in flight is needed Test flight performed according to the procedure and finished with the Protocol on Test Flight Form 17 4 Chapter 17 of this manual allows comparing date of the previous test Form 17 4 should be retained as airplane s documents Because of weather cond
152. ires and pressure lines from instruments and switches located on instrument panel Remove complete instrument panel Assembly 1 Carry out steps 1 5 in reverse order The instruments are fastened with screws from the front side or with holders from the rear side All instruments and switches may be removed from the instrument panel without removal of the instrument panel Loose the screws fastening the panel to fuselage structure and tilt the panel backward 13 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 13 AT 4LSA CABIN Disassembly of the central console Unscrew screws fastening the central console to the fuselage structure Remove upholstery of the central tunnel Disconnect all electric wires from switches and the lighter socket Remove a knob of the fuel valve control Remove the upper part of the central console O G W N Disconnect all control cables and take them out together with the lower part of the central console Assembly of the central console 1 Carry out steps 1 5 in reverse order Disassembly the console between seats 1 Remove seats refer to section 13 2 1 2 Unscrew screws fastening a placard near the flaps control lever or remove a flaps control lever knob 3 Set flaps to 40 4 Unscrew remaining screws and remove the console Assembly the console between seats 1 Carry out steps 1 4 in reverse order MAY 2007 13 7
153. isms 1 9 Jettison locking bolt 2 Fresh air small window 10 Conical pins of the canopy 3 Over tank cover 11 Spring yokes 4 Additional lock 12 Gas springs 5 Fuselage rim composite angle 13 Canopy locking lever 6 Canopy roller 14 Canopy jettison lever 7 Canopy hinge fitting 15 Gas spring fitting 8 Canopy structure MAY 2007 13 11 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 13 AERO Sp z o o CABIN AT 4LSA 1 13 6 1 Removal and re installation of the canopy Removal 1 Remove the locking wire from the jettisoning levers 2 Open the little windows and close the canopy but do not lock it 3 Pull the jettisoning levers backwards The gas springs should drop down from their fastenings in the canopy and extends If they did not drop down move them by hand 4 Lift the canopy and store in a safe place CAUTION PLEXIGLAS IS NOT RESISTANT TO SCRATCHING OR IMPACT AVOID INTENSIVE PRESSING ON THE CANOPY PLEXIGLAS Installation 1 Be sure that the canopy jettisoning lever is pulled backwards 2 Place the canopy on the fittings in fuselage and put it in position enabling allowing installation of the extended gas springs 3 Set the gas springs together with the locking yokes on the conical pins of the canopy 4 Move the jettisoning lever forward simultaneously pushing the locking wire into the hole of the conical pin 5 Check that the canopy opens and close smoothly Lock the jettisoning leve
154. itch there is the circuit breaker of the generator field circuit E Optional ground service plug receptacle which can be used to supply electrical power on ground while engine is not running can be installed It is to be located in front of firewall and accusable from port side of aircraft Main bus is protected by circuit breaker SE The alternator is an additional source of on board electrical power The installation of the alternator is necessary when the engine generator power is not sufficient to supply the additional electrical power demand resulting from increased optional equipment installed on the airplane 15 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 15 AT 4LSA ELECTRICAL SYSTEM The engine starting system consists of starter 3Z relay 2Z and the combined ignition switch 1 Z The ignition switch is located on the central console and may be set into five positions OFF Ignition switched OFF 2 x First ignition circuit ON ve Second ignition circuit ON 1 2 Both ignition circuits switched ON STARTING Engine starting with both ignition circuits switched ON The relay is supplied from the main bus trough the Starter circuit breaker Z LIST OF ELECTRICAL EQUIPMENT RELATED TO AIRFRAME No DESCRIPTION DESIGNATION LOCATION gt se s 6E Relay SI ANCOR 70 906 Behind firewall 9E BATTERY switch WG 15K Instrument panel 10E BYP 401 100 Behind the panel
155. itions the test in flight should be performed when minimum cloud base above terrain is 1500 ft horizontal visibility is minimum 4 miles maximum wind velocity 15 kts 5 5 1 Preparation for test flight Study Certificate of Approval Check limitations in Chapter 2 of the Flight Manual of AT 4LSA airplane Calculate the weight and position of the centre of gravity for the test flight according to the Chapter 6 of the Maintenance Manual Based on weather conditions decide flight level appropriate to location Perform pre flight inspection according to Flight Manual section 4 4 2 5 5 2 Ground test Check instruments and electrical system Check radio transceiver and navigation equipment Perform engine test run according to Flight Manual section 4 5 5 and fulfill Form 17 4 Check control systems of airplane and engine 5 5 3 Taxiing Check a behavior of the airplane during the taxiing Evaluate suspension and brakes 5 5 4 Take off Perform take off according to section 4 5 8 Take off of the Flight Manual paying special attention to the behavior during take off run and after lift off 5 12 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 5 AT 4LSA INSPECTION 5 5 5 Climb Perform climb when Throttle is opened to full travel Flaps are retracted Note in the Form 17 1 indications of the engine instruments 5 5 6 Cruise Check stability and controlla
156. ket Set 5 mm to 19 mm Screw Drivers Flat head amp Philips Wire Snips Pliers etc No special tools required 2 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 2 AT 4LSA HANDLING 2 7 STORAGE OF DISMANTLED AIRPLANE The parts of the dismaniled airplane should be stored as shown below Prior to dismantling the airplane the reguired number of stands should be prepared and suitable storage place chosen The surface of the stand which is in contact with the airplane structure is to be faced with felt foam or other suitable material All fitment holes are to be protected against corrosion and the ports of the fuel lines and holes in the structure must be covered to prevent intrusion of rodents birds or insects It is recommended to cover the parts with canvas or other lightweight waterproof material Stands should be positioned along a Rib line look at rivets on skin Lower wing surface Figure 2 4 Storage the wings NOTE To avoid damage it is recommended that the pitot and static sensors are removed Figure 2 5 Storage of the slab tail MAY 2007 2 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 2 AERO Sp z o o HANDLING AT 4LSA When the engine and landing gear is fitted to the fuselage there is no need for any additional shoring with stands The tires should be checked periodically for the correct inflation pressure Allowing the tires to
157. kin Check condition and check for missing screws Check securely fastened 8 check movement MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 AT 4LSA 3 Main landing gear Tires Brake disc Brake caliper Brake line Leg strut Wheel fairing 4 Fuselage front part Fuselage structure Engine cowling Landing and taxing lights optional items Propeller blades Fuel system Fuel system 5 Nose wheel Tire Shock absorber Leg Wheel fairing Towing rod MAY 2007 CHAPTER 3 SERVICING Visually check tire pressure and condition Check condition Check condition and wear of the brake pads Check condition and fastening to the leg strut Check condition of the leg and connection with the fuselage Check condition and securely fastened Check condition and cleanliness Check condition and fastening Check if covers of the inspection holes of the upper part open and close properly Check condition and fastening of lights Check condition of the lamp shield Check condition and cleanliness Drain fuel sediment and check whether it contains water or other contamination Check amount of fuel and refuel if required use the gauge stick attached to the filler cap Drain fuel sediment and check whether it contains water or other contamination Check amount of fuel and refuel if required use the gauge stick attached to the filler cap Visually check tire pressure
158. l Chapter 12 00 00 Inspect rubber shocks and engine attachments for damage as result of overheating distortion and attachment reliability Refer to ROTAX engine Maintenance Manual Chapter 12 00 00 Check bolted joints torque at large small mounts connection Inspect securing and attachments to outer parts of the engine Check condition of safety wire as required replace with new one Check propeller transmission friction moment Refer to ROTAX engine Maintenance Manual Chapter 12 00 00 Inspect propeller transmission repo raste 17 Replace oil 8 For engines operating with AVGAS fuel and or in difficult conditions 18 Flush cooling system Refer to ROTAX engine Maintenance Manual Chapter 12 00 00 19 Check air filters condition Clean filters x x x x 20 Inspect rubber flanges carburetors for damage cracks overheating wear and usability to operation Refer to to ROTAX engine Maintenance Manual Chapter 13 advanced maintenance 21 Inspect float chamber vent Inspect condition of vent lines attachment reliability free flow no loops and bends 22 Lubricate throttle pushrod ends gas torque pipe ball bearings carburetor heating flap hinges engine cowlings oil cooling shutter flaps axis of cabin air heating mixer 23 Check free move of carburetor system control throttle and choke lever Be sure that Bowden cables permit on full range move Refer to RO
159. l gauge indicates the amount of fuel in the tank The signaling lamp GENERATOR FAILURE is illuminated red FUEL PUMP switch Set to ON Make sure signal lamp FUEL PUMP ON lights Listen for the sound of pump operation GYRO INSTR switch Switch ON and check function of Artificial Horizon Turn Coordionator Directional Gyro Indicator MAY 2007 3 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 3 SERVICING ANTI COLLISION STROBE switch optional Engine monitor AERO Sp z o o AT 4LSA Switch ON and check function Indicates the voltage NOTE Battery is serviceable if the voltmeter reads Min 12 Volts Switches Canopy 2 Left wing Wing flap Aileron Inspection hole lower wing surface Wing tip Position light optional item Strobe Light optional Sensors of static and pitot pressure Wing structure Wing fuselage fairing Stall Warning senor 3 4 Switch OFF all switches levers down Close Check condition of structure play in the hinges and control system Check condition of structure play in the hinges and control system Open check aileron control system and condition and fastening of the static and pitot pressure lines Close inspection hole when finished Check condition and securely attached Check condition and securely fastened Check condition and fastening Check fastening and cleanliness of the sensors Check condition of the upper and lower s
160. lane zx SOUS He Check that the airplane contains unusable fuel 0 92 US gal and the full amounts of engine coolant oil and brake fluid 5 Put the airplane with wheels on three scales and have it leveled as per section 2 5 of Chapter 2 6 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 6 AT ALSA WEIGHTING AND BALANCE It is recommended to arrange the weighing of airplane in hangar without any air movement 6 Close the cockpit canopy 7 Weigh the airplane Enter the results into the AT 4LSA Airplane Weight Report Form 17 1 8 Complete the following entries AT 4LSA Airplane Weight Report Form 17 1 AT 4LSA Airplane Weight Report Form 17 2 as per procedure in point 6 7 Table recording the weights and arms as per page 6 9 of this Chapter and table from Chapter 6 3 of AIRPLANE FLIGHT MANUAL Doc No ATL4 02A 9 Enter the completed Form 17 1 into the airplane files Cancel previous Weight Report 6 3 CALCULATION OF CENTRE OF GRAVITY POSITION Ib Weight kg 1320 600 1069 485 926 420 25 3 27 7 ARM in 32 5 0 643 0 704 m 0 826 20 25 MAC 34 Figure 6 1 Limitations of CG position The diagram above shows the permissible airplane weight in flight depending on the CG position To determine exactly weight and CG position of the airplane the following procedure should be used MAY 2007 6 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A C
161. les There is a choke system installed to start the cold engine The choke lever located at the middle tunnel moves by means of cables the choke levers of the carburetors To protect the carburetors against icing during flight in icing conditions the airplane is fitted with a carburetors heater controlled by means of Bowden cable Figure 12 10 Engine Controls 1 Throttle push rod left 8 Choke control cable 2 Throttle push rod right 9 Carburetor heater cable 3 Limiter 10 Carburetor heater actuating cable 4 Friction brake 11 Carburetor heater regulating flap o Throttle lever 12 Throttle Bowden cable 6 Choke lever 13 Torsion tube 7 Choke Bowden cable 14 Push Rod End MAY 2007 12 27 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 12 AERO Sp z o o POWER PLANT AT 4LSA 12 10 1 Throttle push rods disassembly and assembly Disassembly 1 2 3 4 Remove the canopy of the cockpit see section 13 6 1 and the cover of the tank Remove limiter from right throttle push rod Remove cotter pins fitting push rods to push rod ends Screw out push rods from push rod ends and sidle out push rods Assembly Execute points 1 4 in reversed sequence 12 28 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AT 4LSA 13 1 13 1 1 13 2 13 2 1 13 3 13 3 1 13 4 13 4 1 13 5 13 6 13 6 1 13 7 13 7 1 13 8 13 8 1 MAY 2007 AERO Sp z o o CHAPTER 13 CABIN Instrument panel Removal and insta
162. lightning bulbs 3 Screw out screws and remove bulb Assembly Execute points 1 3 in reversed sequence MAY 2007 18 10 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 10 AT 4LSA 4 Instrument panel lightning system diagram 1000 SW OPI MAIN BUS 12V TL asw 65 LIST OF ELECTRICAL EQUIPMENT No DESCRIPTION LOCATION Monitor Instrument panel OP2 Compass lightning mmm ronem Dimmer Ik 5W Instrument panel Tore pez 18 10 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A
163. llation of instrument panel Seats Removal and installation of seats Upholstery Removal and installation of upholstery Safety belts Removal and installation of safety belts Luggage compartment Canopy Removal and installation of canopy Cabin ventilation and heating system Removal and installation of cabin ventilation and heating system Cabin air intake CHAPTER 13 CABIN 13 2 13 6 13 8 13 8 13 8 13 8 13 9 13 10 13 10 13 11 13 12 13 13 13 14 13 15 Removing and installation of the cabin air inlet elements 13 15 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A 13 1 CHAPTER 13 AERO Sp z o o CABIN 13 1 13 2 AT 4LSA INSTRUMENT PANEL AL flight navigation indicating instruments radio blocks and electric system fuses are located on the instrument panel located in front part of the cabin The flight and navigation instruments are located on the left side of instrument panel in the central part of instrument panel there are engine monitoring instruments and on the right side of instrument panel there are radio blocks and fuses On the instrument pane there are also the carburetor control levers In the central console under the instrument panel there are switches controls of the fuel valve cabin ventilation and heating In the console between seats there is a lighter socket an ashtray flaps control lever a trim control wheel and microphone and earphone sockets 2 5 4 7 1 Figure 13 1 Instrum
164. lled Therefore new aircraft have lines a little longer than required to allow for future repair 10 4 TAIL SKID The rear skid 1 is made of laminated epoxy fiberglass composite It is mounted to the fuselage with two bolts 2 In place where contact with ground is possible a steel made ferrule 3 protects the skid from wear Figure 7 Tail skid 1 Skid 3 Fuselage angle bars 2 Attaching bolts 4 Protective ferrule 10 16 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 10 AT 4LSA LANDING GEAR 10 4 1 Removal and installation of the skid 1 Unscrew nuts of the attaching bolts and remove the bolts 2 To install the skid perform step 1 in reverse order 3 For bolted joints torque limits refer to Chapter 16 6 10 5 WHEEL FAIRINGS The AT 4LSA airplane may be fitted with wheel fairings The fairings are made of Kevlar epoxy composite To attain access to landing gear elements remove the fairings The fairings are fastened to the landing gear by means of screws Figure 8 Wheel fairings 1 Main wheel fairing 3 Front part of the nose wheel fairing 2 Hear part of the nose wheel fairing 4 Fairing of the nose leg MAY 2007 10 17 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 10 AERO Sp z o o LANDING GEAR AT 4LSA PAGE INTENTIONALLY LEFT BLANK 10 18 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 11 AT 4LSA AIRPLANE CONTROLS CHAPTER
165. llowed this will lead to serious damage of the airplane of it s sub assembles NOTE indicates additional information necessary for wording complements or a proper understanding of the manual Only licensed aviation mechanics which where trained on AT 4LSA are authorized to perform maintenance WARNING Before starting maintenance disconnect battery and protect engine against unintentional starting During maintenance tasks when ignition system must be switched on and battery must be connected protect propeller against unintentional hand rotating and keep propeller zone clear All parts should be cleaned checked and installed according to the proper manual When installing assembly check complete The information in this manual and aviation authority requirements should be observed In case of differences between this manual and FAA requirements more restricted rules should apply 0 14 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 AT 4LSA 0 3 CONVERSION CHART Length units 1 mm 0 03937 in 1 in lt 25 4 mm 1 ft 12 in 0 3048 m Area units 1 cm 0 155 sg in in 1 sq in in 6 4516 Volume units 1cm z 0 06102 cu in in 1 cu in in 2 16 3871 cm 1 11 1 dm 0 21997 gal UK 1 gal UK 4 5461 1 dm 0 26417 gal US 1 gal US 3 7854 1 gts US 0 9463 dm Mass units 1 kg 2 2046 Ib 1 Ib 0 45359 kg Density units 1 g cm 0 01
166. lot s connector The slot is attached to supports screwed to instrument panel 3 2 Disassembly and assembly of transmission switch Required tools Flat Head Screwdriver Disassembly 1 Remove fittings from stick 2 Remove seats and disconnect connector of transmission switch cables at the stick s torque tube 3 Screw out two screws fitting the foot of transmission switch 4 Undo nut fitting switch and sidle it out from foot 5 Disconnect electric cables Assembly 1 Execute point 5 in reversed sequence 3 3 Disassembly and assembly of COM antenna Disassembly 1 Disconnect joint in antenna s cable through the service openings in rib of luggage compartment 2 Screw out screws attaching antenna 3 Sidle out antenna from the opening in fuselage Assembly 1 Execute steps 3 in reversed sequence 18 2 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 SECTION 18 AT 4LSA SUPPLEMENT No 2 4 SL 40 COM and Intercom system diagram The SL 40 transceiver RNI is connected to the primary bus via two circuit breakers separated for COM and Connection diagram is given on Fig 5 1 RAT plete pereen pins cover ester Comp _ DEG m eo 329 mi ome _ MAY 2007 18 2 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z o o SUPPLEMENT 2 AT 4LSA
167. mitter back off the Screws slightly and push the O Ring back into place with a thin Screwdriver or a piece of sheet metal 7 Remove any existing Battery replacement date labels from the Battery Case and install the new label you prepared in step 3 above in a readily visible location on the ELT 8 After Battery replacement a Transmitter function test must be performed as described in section 4 of this supplement SIZED MN1300 1 6 VOLTS DURACELL ALKALIME BATTERY TO BE MEASURED BY DVM TO BE MEASUR D BY QVM TO BE MEASURED BY Figure 5 Battery Case 18 6 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z CHAPTER 18 AT 4LSA SUPPLEMENT No 6 4 Funetion test NOTE Functional test can be curried on within first five minutes after every hour only and transmission period cannot exceed 1 5 s MAY 2007 Place main switch in ON position and check whether 121 5 MHz signals are received by communication COM transreceiver and whether control lights are illuminating on control panel and main unit Place main switch in OFF position and check whether control lights are no illuminating and whether signals is not transmitted any more Place main switch in ARM position press switch ON at the control panel Check whether control lights are illuminating and are well visible at the instrument panel from pilot s seat Check whether ELT signal is received by COM tr
168. mplifier power 12W Intercom function 18 1 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o SECTION 18 AT 4LSA SUPPLEMENT No 1 NAV receiver performance specification Frequency range VOR 108 117 95MHz LOC 108 111 95MHz GS 328 60 335 40MHz Increments SOkHz VOR LOC 2 System operation 2 1 Power ON To turn on SL 30 turn on battery switch and rotate Power ON OFF Volume knob right clockwise from OFF position The transceiver should come on into standard initiation mode and within 15 seconds the liquid crystal display should project recently used COM and NAV as well stand by frequencies and depending from working mode NAV data When SL 30 is ON pull the knob out to disable automatic squelch and by rotating the knob right and left select required volume level By pulling the knob in the automatic squelch will be on again CAUTION It is prohibited to start engine with transceiver ON MAY 2007 18 1 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z o o SUPPLEMENT No 1 AT 4LSA 2 2 COM mode The display of SL 30 transceiver and MD200 306 indicator as well their control devices are presented on Fig 2 1 The display in NAV indicator working in tender with transceiver is show on Fig 2 2 4 5 6 8 9 10 3 a 2 S135 0031 199 300 FALL TX eu E O AUD PE m ooo Um
169. n and ventilation fittings 1 Fuel valve drain 5 Tank Vent 2 Cover drain 6 Flexible hoses 3 Filler throat drain 7 Fittings locking screws 4 Cover Vent MAY 2007 12 17 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 12 AERO Sp z o o POWER PLANT AT 4LSA 12 7 1 Removal and installation of the fuel tank Removal 1 Drain all fuel from the system Remove the canopy of the cockpit see section 13 6 1 and the cover of the tank Remove the upholstery of the middle tunnel see section 13 3 1 R W Disconnect from the torque tube the push rods controlling the carburetors and disconnect their terminals Unlock and disconnect the band fastening the tank from the upper side Disconnect the plug of the fuel sensor Unscrew the fuel returning terminal Disconnect the line from the tank to fuel valve O CO N OA Unscrew screws fastening drain fittings and drain valve to the fuselage CAUTION TO FACILITATE INSTALLATION MARK ALL DISCONNECTED LINES WITH SUITABLE TAGS BLANK HOLES OF DISCONNECTED LINES WITH PLUGS 10 Remove the throttle push rods so that they do not pass through the fuel tank 11 Unscrew the screws fastening the instrument panel to the structure and turn back the panel as much as possible 12 Remove the fuel tank together with drain and ventilating fittings Installation 1 Perform steps 2 to 12 in reverse order 2 For bolted joints torque limits refer to Chapter 16 6 12
170. nd hinged along its whole length with a aileron hinge 4 The aileron structure is riveted and consists of skin trailing edge and four ribs The all metal split wing flap 3 is fixed to the wing with three hinges 5 The wing flap structure is similar to that of the aileron includes twelve ribs On the lower side of the wing next to rib no 7 an inspection door 6 gives access to the angular lever of the aileron control system and to the lines of the pitot tube left wing only ud ipe k s Figure 9 3 Wing structure 1 Wing 6 Inspection door 2 Aileron 7 Main spar 3 Wing flap 8 Rear spar 4 Aileron hinge 9 Walkway 5 Wing flap hinges 10 Wing tip 9 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp 2 o o CHAPTER 9 AT 4LSA AIRPLANE STRUCTURE 9 2 1 Removal and installation of wing Removal To remove the wing at least three persons are required 1 o o Remove the wing fuselage fairings and protect the wing flap from downward displacement using self adhesive tape Remove the seats refer to section 13 2 1 Loosen aileron push rods protecting bellows Disconnect the aileron push rods from the from the control stick and disconnect the bonding cables refer to section 11 2 1 Disconnect pitot tube lines r
171. nd unscrew the bolt nut connecting the rod of the shock absorber with the shock absorber lever Remove the bolt 4 Unlock and unscrew the rocker axle nut 5 Remove the axle of the rocker Installation 1 Perform steps 2 to 5 in reverse order 2 Lubricate all joints 3 For bolted joints torque limits refer to Chapter 16 6 10 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 10 AT 4LSA LANDING GEAR 10 1 4 Removal and installation the nose leg Removal 1 Remove the engine cowling refer to section 12 3 and lift the nose of the airplane 2 Remove the laminated lining of the middle tunnel in the cabin refer to section 13 3 1 3 Through the lightening hole in the centre tunnel block the head of the bolt of the rear attachment point of the leg 4 On the underside unscrew the nut of the bolt attaching the leg from the rear 5 Unlock and unscrew the bolt nut of the front attachment 6 Remove the bolt of the front attachment Installation 1 Perform steps 2 to 6 in reverse order 2 Lubricate all joints 3 For bolted joints torque limits refer to Chapter 16 6 MAY 2007 10 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 10 AERO Sp z o o LANDING GEAR AT 4LSA 10 2 MAIN LANDING GEAR see Figure 10 3 The main landing gear of this airplane consists of two flat legs 1 made of spring steel The axle 2 of the wheel with brake discs 5 and the brake calipers are at
172. nder 1 3 If the calculated C G position is within the limits of 20 to 34 of MAC enter the weight of pilot and passenger received under 1 into the table 4 f the calculated C G position is not within the limits of 20 to 34 96 of MAC the weight of pilot and passenger must be reduced by some Ib and item 3 is to be repeated 5 Sign the Form 17 2 6 Cut the Form 17 2 to fit into the size of the pages of the Aeroplane Flight Manual 7 Replace page 6 12 of the Flight Manual of the AT 4LSA Aeroplane Replacement of page 6 12 of the Flight Manual does not require replacing page 0 5 in the List of Effective Pages 6 10 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 CHAPTER 7 AT 4LSA ALIGNMENT OF THE AIRPLANE CHAPTER 7 ALIGNMENT OF THE AIRPLANE 7 1 Positioning for alignment 7 2 7 2 Bench marks location 7 3 7 3 Alignment sheet 7 4 MAY 2007 7 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 7 AERO Sp z o o ALIGNMENT OF THE AIRPLANE AT 4LSA 7 1 POSITIONING FOR ALIGNMENT The alignment of the airplane is performed to confirm correct relative positioning of certain stations of the structure benchmarks Performing the alignment and comparing the results with the results of the previous alignment protocol enables to ascertain whether the structure has been distorted Re alignment is required in the event that the wings fuselage landing gear or engine mount have been replaced Also
173. ng by turning of middle potentiometer which is located inside fuel quantity sensor casing DESCRIPTION DESIGNATION LOCATION 2 FUEL GAUGE circuit breaker 7274 2 2A Instrument panel 2A 7VLL P1 Fuel quantity indicator 2A 7V Instrument panel Fuel level sensor 393 5S 1 5 Fuel level sensor Version 3 395 5S 1B 5LL Fuel tank RESERVE FUEL signaling LED lamp 17371252 Instrument panel Figure 6 Version 1 and 2 fuel gauge electrical system diagram 15 16 MAY 2007 AEROPLANE MAINTENANCE MANUAL AERO Sp z o o CHAPTER 15 AT 4LSA ELECTRICAL SYSTEM 15 5 GYRO INSTRUMENTS ELECTRICAL SYSTEM Gyro instruments are turned on simultaneously with automatic switch EG1 installed on instrument panel They are protected additionally by 2 A circuit breakers MAIN BUS 12V 12V Figure 7 Gyro instruments electrical system No DESCRIPTION DESIGNATION LOCATION Automatic switch 112 210 101 Instrument panel Circuit breaker 7242 2 2A Instrument panel Circuit breaker 7242 2 2A Instrument panel Artificial horizon RCA 26AK 2 Instrument panel Circuit breaker 7242 2 2A Instrument panel Directional gyro DGO2E 3H Instrument panel MAY 2007 15 17 AIRPLANE MAINTENANCE MANUAL CHAPTER 15 AERO Sp z o o ELECTRICAL SYSTEM AT 4LSA 15 6 AVIONICS ELECTRICAL SYSTEM Avionics instruments are turned on simultaneously with automatic switch EA1 installed on instrument panel Each instrument is protected additionally by circuit
174. nna j NN mb ome V E C Z 9 E ae AERO Sp z o o AT 4LSA s Fig 1 2 GPS antennas on aircraft 2 Weather forecasting antenna Basic technical data Working mod Czas uzgadniania Refresh frequency Accuracy Power supply GPS control 12 channel weather forecast GPS MAP 396 496 15s hot start 45s cold start 5 min first initiation New location 1 5 GPS 15 m 49 ft 95 RMS DGPS USCG 3 5m 10 16ft 95 DGPS WAAS lt 3m 10 twith DGPS correct Speed 0 1 kt rechargebla Li ion batery pack time 4 15godz Depending on screen brightness 11 35V aircraft installation GPS front panel is presented on Fig 2 1 18 3 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z CHAPTER 18 AT 4LSA SUPPLEMENT No 3 o ejo Gos M A 686 Y n Ig N x Tr she Eq 4 15 F S 7 Fig 2 1 GPSMap 296 396 496 front panel Fig 2 2 GPS MAP 296 396 496 steering buttons 1 PAGE MODE button is used cycle trough the main pages in seguence and return the display from a submodem page To switch between Aviation Mode Marine Mode and Automotive Mode press and hold button 2 OUIT button is used to cycle trough main pages in reverse seguence to return to previous value in data entry field or to cancel function 3 ENTER MARK button is used to select highlighted option to
175. nstallation is composed of two main cylinders 3 in the pilots ruder pedals which are connected to the clamps 7 with use of elastic pressure resistant lines 5 Brake system liquid tank 1 is located on firewall at the highest point of the system It is supplying each main cylinder independently The left Wheel main cylinder is activated by left pedal and Wright main cylinder is activated by right pedal Variant 2 The hydraulic system is comprised of double independent installations each of which is composed of two main cylinders Cylinders located on right pedals are activating additional clamps Optionally there might be a parking brake valve installed on the aircraft 4 CAUTION The brake system is efficient if it meets the following requirements provides blocking of the wheels on a dry asphalt or concrete surface with full engine power does not brake the wheels when the brake pedals are not pressed MAY 2007 10 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 10 AERO Sp z o o LANDING GEAR AT 4LSA 1 1 VERSION 1 2 VERSION 2 Mons al I B t 1 i i a 4 Tu yt AS 5 po 56 4 TN Figure 10 5 Diagram of the brake system Brake fluid container High pressure brake hoses Feeding lines Bleeding valve Brake cylinders Brake caliper peut m rv oem Parking brake valve optional Brake disc CAUTION Repair of brake cyl
176. nt is located aft of the cockpit and consists of two compartments and a shelf for very light items Aerobatic maneuvers and flights under known icing conditions are prohibited 1 2 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 1 AT 4LSA GENERAL INFORMATION 1 2 THREE VIEW PROJECTIONS OF THE AIRPLANE 20 5 6 25 m MAY 2007 1 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER1 AERO Sp z o o GENERAL INFORMATION AT 4LSA PAGE INTENTIONALLY LEFT BLANK 1 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 2 AT 4LSA HANDLING CHAPTER 2 HANDLING 2 1 Towing and taxiing 2 2 2 2 Parking 2 3 2 3 Tie Down 2 3 2 4 Jacking 2 3 2 5 Leveling 2 4 2 6 Tow bar 2 5 2 7 Airplane assembling and disassembling 2 5 2 8 Transporting Dismantled airplane 2 6 2 9 Storage of Dismantled airplane 2 7 MAY 2007 2 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 2 AERO Sp z o o HANDLING AT 4LSA 2 1 TOWING AND TAXIING On a level surface a single person is able to move the airplane if using the tow bar The tow bar is attached to attachment points at nose wheel axel as per point 2 6 If the ground is not even and there are difficulties in moving the airplane two people can move the aircraft balancing the plane on the main wheels One person keeps the wing tip and the other to control the movement with the tow bar CAUTION Do not
177. ntly the oil is circulated through the lubricating system of the engine while excess oil flows to the bottom of the crankcase The pressure existing in the crankcase blows the excess oil back to the oil tank On the engine are installed electric sensors of oil pressure oil temperature The oil tank oil cooler and the engine are connected with lines all protected with fire resistant sleeves A rule indicating the amount of oil is located in the oil tank Oil radiator and coolant radiator are located under the main mount Normally the airplane is fitted with an oil cooler shutter 8 set on the ground Mounting in the airplane oil cooler shutter operated from cockpit shortens the time when the engine after start up attains proper operation temperatures and permits to effectively accommodate oil cooling intensity to actual operating conditions 2 Figure 8 system 1 Ol tank 5 Oil lines 2 Ol cap 6 Drain plug 3 Oil cooler 7 Drainage fitting 4 Oil filter 8 Oil cooler shutter MAY 2007 12 21 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 12 AERO Sp z o o POWER PLANT AT 4LSA 12 8 1 Operation of oil cooler shutter optional Shutter adjustment is done by turning the knob counter clockwise and pulling it out from the instrument panel Locking in a selected position turn clockwise In case of operation flexible connector disconnection the shutter will be automatically open using return springs CAUTI
178. oard L port Wing setting angle H8 H9 0 0 24 in 0 6 mm H6 H7 0 0 24 in 0 6 mm 2 Wing twist H8 H9 H6 H7 0 0 24 in 0 6 mm Wing dihedral H6 H8 6 1 0 24 in 155 6 mm Twist of elevator HIOL H11L H10P H11P 0 0 39 in 0 10mm Deviation of the elevator from the horizontal plane H10P H10L 0 40 59 in 0 15 mm 11 Displacement of aileron Up 20 2 Down 15 2 Displacement of wing flap TAKEOFF 15 1 LANDING 40 Displacement of slab tail elevator Trailing edge up IZ x Trailing edge down 10 1 Displacement of trim tab Elevator trailing edge down trim tab down 26 3 Elevator trailing edge up trim tab up 35 3 Distance of bench marks 8 and 9 from fuselage reference axis Bench mark 8 27 16 0 39 in 690x10mm Bench mark 9 27 16 0 39 in 690 10mm 12 Distance from aileron to wing tip gap 0 39 0 12 in 10 3 mm 13 17 3 1 Distance of aileron from the upper wing part over the wing flap gap 0 39 0 12 in 10 3 mm 10 Displacement of rudder to port side to starboard 30 2 MAY 2007 No 14 15 16 17 18 19 20 21 22 23 24 FORM 17 3 Measured values P starboard L port 13P 13L lt 0 331 in 0 48 mm Distance of 13P or 13L from 12 13P from 12 13L from 12 lt 0 0 39 in 10mm Distance from 13P or 13L to fuselage vertical reference plane 40 16 0 19
179. on of the structure play in the hinges and control system Anti collision strobe optional Check condition and fastening Navigation light optional item Check condition and fastening 3 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 3 AT 4LSA SERVICING Elevator slab tail Check condition of the structure play in the hinges and control system Trim amp balancing tab Check condition of the structure play in the hinges and control mechanism Fairing of the elevator control Check condition and fastening to the elevator structure 10 Fuselage rear part port Fuselage structure Check condition and cleanliness Inspection holes Next to the Open it check the control systems of elevator and elevator trim amp balancing tab shut the inspection hole Skid Check condition and fastening Antenna Check condition cleanliness and fastening 11 Inspection of the engine compartment After completing the inspections specified above and rectifying any faults found wing flaps should be retracted 09 the inspection of the engine compartment should be carried out WARNING Prior to removing the engine cowling check that the key is removed from the ignition switch Remove the upper and the lower engine cowling Check the cowling inside for damage traces of leaks partial burns originating from leaks in the exhaust system Check condition of air intakes Open the oil filler cap
180. onnected to main bus with circuit breaker RT4 Encoding altimeter is powered via transponder Additionally a light is supplied via R12 fuse GTX327 transponder electric diagram is shown on Fig 7 1 7274 2 3A Instrument panel circuit breaker KA 60 or CI 105 or 11 Encoder AK 350 Behind instrument panel right side MAY 2007 18 5 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 18 AT 4LSA SUPPLEMENT No 5 Fig 5 1 GTX327 transpondera diagram M m OJ a 5 E T SZynd RT Z Awioniki 5 14V zt 330 00198 00 2 XL osw A TRANSPONDER PRZYRZAD p gt sag er 990 00184 25 RI RTA Ter 21 21 te RS 232 UT 20 20 RS 232 IN 1 19 19 R 232N 2 2 2 ARBORNE SENSE 22 22 EXTERNAL SUPPRESSION 17117 sea EXTERNAL STANDBY 18 18 EXTERNAL IDENT 8 8 oo AIRCRAFT GROUND 1313 RUN 20AWG g AIRCRAFT GROUND 258 M LIGHT DIMMER 28VDC 23 23 AT4 85 151 0 T Cl DIMMER 414 5v00 24 24 S 2DAWO ESO 4 gt lt 21 33 ARCRAFT POWER 1515 12 C SWTUED POWER OUTPUT RTS 22AWG Czerwon F8T8 DCPOMRN ac AMONICS MASTER ON 1 1 15 15 DC GROUND og it 6 6 STROBE DC GROUND C ALTITUE A1 3 3 AE AUD A2 5 5 33a ALTITUDE 66 pe ALTITUDE B 9 9 55 ALTITUDE 82 11 11 Nh ALTITUDE B4 12 12
181. or bolted joints torque limits refer to Chapter 16 6 6 C z VP PO e OAS d LB ni a f i WES S cl Ze 9 727 _ Figure 10 4 Brake caliper 1 Brake hose 4 Brake disc 2 Brake caliper 5 Outrigger 3 Main leg 6 caliper for version 2 only MAY 2007 10 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 10 AERO Sp z o o LANDING GEAR AT 4LSA 10 2 2 Removal and installation the main leg Removal 1 Remove the seats refer to section 13 2 1 and open the inspection doors in the landing gear box 2 Unscrew the leg fairing 10 and the inspection doors 9 from the lower side of the fuselage 3 Lift the airplane with jacks by at least 20 cm 8 in 4 Loosen all bolts fixing the leg attaching angle bars to the landing gear box 5 Unscrew nuts of the four bolts fixing the leg with the angle bars Knock out the bolts 6 Disassemble the brake caliper refer to section 10 2 1 disconnect the brake line from the leg 7 Vigorously jerk the leg to remove it from the fuselage Installation 1 Perform steps 2 to 7 in reverse order 2 For bolted joints torque limits refer to Chapter 16 6 10 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 10 AT 4LSA LANDING GEAR 10 3 BRAKE SYSTEM see Figure 10 5 Variant 1 The hydraulic system is comprised of single installation that independenily activates clamps on right and or left main wheels The i
182. ording the instructions contained in the Maintenance Manual of the Rotax 912 series Aero Engines 3 14 7 Propeller Cleaning Cleaning of the propeller is to be performed in the same manner as that of the painted surfaces but with great care 3 22 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 3 AT 4LSA SERVICING THIS PAGE IS LEFT INTENTIONALLY BLANK MAY 2007 3 23 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 4 AT 4LSA AIRWORTHINESS LIMITATIONS CHAPTER 4 AIRWORTHINESS LIMITATIONS 4 1 Airframe 4 2 4 2 Engine 4 2 4 3 Propeller 4 2 4 4 Equipment 4 2 4 5 Rubber hoses 4 2 MAY 2007 4 1 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 4 AERO Sp z 0 0 AIRWORTHINESS LIMITATIONS AT 4LSA 4 1 AIRFRAME The airworthiness of the structure is dependent upon its technical condition It means that TBO for the airframe does not exist and the airframe is operated on condition 4 2 ENGINE The airworthiness of the engine is to be determined according to the Maintenance Manual of Rotax 912 series Aero Engines and according to bulletins issued by the engine manufacturer Currentl engine TBO is 1500 flight hours 4 3 PROPELLER ELPROP propeller The airworthiness of the propeller is to be determined according to the ELPROP Propeller Maintenance Manual Currently TBO for this type of propeller does not exist and the propeller is operated on condition 4 4 EQUIPMENT
183. p This message will show only if the correct start up This message will show only if the correct temperature datum has been set elektronic ENGINE MAY 2007 15 13 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 15 AERO Sp z o o ELECTRICAL SYSTEM AT 4LSA 15 14 The instrument checks the measured values at two levels The first one Warning signalization informs the pilot by blinking on exceeding the limit and the more attention should be paid to the measured values the yellow field If the measured value exceeds the Alarm limit the red field blinking will continue and the OVER message will show After the next turn on of the instrument the SERVICE message will show elektronic ENGINE If the set limit values have been exceeded the SERVICE MESSAGE shows after turning the instrument on This information will disappear after 15 seconds and then the instrument get back to the normal measuring mode By pressing the INFO button the pilot has to find out which measured item has been exceeded and eliminate the possible defect elektronic ENGINE LIMITS STATUS TABLE EGT1 Coldoil Hours 11 Hours 11 59 ENGINE When deleting the SERVICE MESSAGE has been enabled in the instrument via the PC control software the SERVICE MESSAGE can easily be deleted by pressing IINFO button and turning the instrument on at the same time After that the SERVICE DELETED message shows on the display SERVICE D
184. panel 12V Figure 3 Hour meter electric installation 15 20 MAY 2007 AIRPLANE MAINTENANCE MANUAL AERO Sp z o o CHAPTER 15 AT 4LSA ELECTRICAL SYSTEM 15 8 ANTI COLLISION LIGHT ELECTRICAL SYSTEM OPTIONAL The anti collision strobe lamp is mounted at the top of the rudder Switching on is performed by means of ANTI COLL STROBE circuit breaker located in the instrument panel No DESCRIPTION DESIGNATION LOCATION 57 Anti collision strobe lamp P N 01 0770509 02 Rudder 56 ANTI COLL STROBE circuit 112 205 101 Instrument panel breaker 12V BUS Figure 7 Anti collision lamp electrical system MAY 2007 15 21 AIRPLANE MAINTENANCE MANUAL CHAPTER 15 AERO Sp z o o ELECTRICAL SYSTEM AT 4LSA 15 8 1 Removal and installation of the anti collision light Removal 1 Loose the screw and remove the clamp of the lampshade 2 Remove the lampshade 3 Pull out the bulb 4 Unscrew screw fastening the mount to the rudder 5 Pull out the base together with the electric connector and disconnect it Installation 1 Perform steps 1 to 5 in reverse order 2 For bolted joints torque limits refer to Chapter 16 6 Figure 8 Anti collision light 1 Lampshade 4 Bulb 2 Clamp with screw 5 Mount 3 Gasket 15 22 MAY 2007 AIRPLANE MAINTENANCE MANUAL CHAPTER 15 ELECTRICAL SYSTEM AERO Sp z o o AT 4LSA 15 9 LIGHTER ELECTRIC SYSTEM A lighter socket ZP2 is located in the m
185. r Location of instrument on instrument panel is shown on Fig 1 1 Transponder is used to allow aircraft recognition by ATC controllers and can work in A and C modes Ara horizon Atimeter porova ee nj Ignition swich Fig 1 1 Location of instrument on instrument panel 1 GTX 327 transponder 2 Transponder circuit breaker 3 AK 350 encoding altimeter behind the instrument panel b0226001 Fig 2 2 Location of transponder antenna 1 Transponder antenna MAY 2007 18 5 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 5 AT 4LSA Basic technical data Modes A 4096 cods C from 1000 to 62700 feet Freguency 1090 MHz Certified to 50000 feet Power supply min 125W 150W with 1 5dB cable Czu o odbiornika nominalna 74dBm dla 90 odpowiedzi Wilgotno 95 55 16h 85 38 32h Operational temp 20 to 55 2 GTX 327 operations Transponder front panel is presented on Fig 2 1 Fig 2 1 The GTX 327 transponder front panel is presented 18 5 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z CHAPTER 18 AT 4LSA SUPPLEMENT No 5 2 1 Starting and mode selection The GTX 327 transponder is turned on by pressing button ON To turn off unit press OFF button See Fig 2 1 CAUTION DO NOT START ENGINE WITH TRANSPONDER ON OFF is powering off the GTX 327 transponder By pressing ST
186. r of the coolant pump 11 Unscrew the cover from the coolant pump 12 Unscrew the pipes from cylinder 1 and 3 and remove the pump cover 13 Unscrew the set of coils and the cable from the crankshaft position sensor 14 Unlock and unscrew the bolts attaching the engine to the engine mount Remove the bolts and move off the mount carefully Installation 1 Perform steps 3 14 in reverse order 2 Fill the oil and the cooling systems 3 Install the engine cowling 4 For bolted joints torque limits refer to Chapter 16 6 12 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 12 AT 4LSA POWER PLANT 12 3 ENGINE COWLING The engine cowling consists of two parts made of Kevlar composite The lower part is fastened to the fuselage structure with M4 screws It contains the air inlets to the engine cooler oil cooler and cabin venting and heating as well as for the blowing on the oil tank The upper engine cowling is fastened also with screws to the over fuel tank cover and to the lower cowling The upper cowling includes two large inspection doors providing access for the pre flight maintenance of the engine and two air intakes to the carburetors Figure 12 1 Engine Cowling 1 Upper cowling 3 Bracket 2 Lower cowling 4 Inspection door WARNING DURING GROUND ENGINE RUN BOTH ENGINE COWLINGS MUST BE COMPLETELY INSTALLED OR COMPLETELY REMOVED IT IS PROHIBITED TO RUN THE ENGINE
187. r with locking wire 13 12 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 13 AT 4LSA CABIN 13 7 CABIN VENTING AND HEATING The cold air blow in to down part of the cabin is done through the air intake common with the air intake to carburetors and is connected by means of the hose to mixing box The mixing box allows to regulate amount and temperature of the air enter the cabin Air to heat the cabin is taken from the air inlet and heated in the air heater located under the silencer and next it is directed to mixing box From mixing box the air enters to outlet The control cables there are on the central console The air outlet is located behind the canopy Figure 13 10 Cabin venting and heating 1 Cold air intake 7 Silencer 2 Air heater Intake 8 Control Bowden cables 3 Air heater 9 Temperature control cable 4 Mixing box 10 Air intake control cable 5 Cabin air inlet 6 Central console MAY 2007 13 13 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 13 AERO Sp z o o CABIN AT 4LSA 13 7 1 Remove and reinstalling of the cabin venting and heating Removal 1 2 3 Mo o0 Remove engine cowling refer to section 12 8 Remove inlet air tunnel to the coolers refer to section 12 8 Remove flexible hoses leading to the mixing box and between the air heater and the air intake Disconnect control cables from the mixing box lever Unscrew bolts attaching t
188. ric The type of lubricant and the points to which it is to be applied are given in the tables below Points to be lubricated Axle of the fork of nose wheel Aeroshell Grease5 Tips of push pull rods and cables Aeroshell Grease5 WD40 Ball bearings of suspension of the slab tail the vertical Aeroshell Greased stabilizer the torgue tube rudder and torgue tube WD40 Hinges of ailerons wing flaps and of trim tab WD40 Wing flap control mechanisms Aeroshell Grease5 Trim tab control system Aeroshell Grease5 3 13 Servicing materials Grease for general application PN 72 C 96134 Aeroshell Grease5 Brake fluid DOT4 SAEJ 1703 FMVSS DOT4 ISO 4925 Grease to tighten screw joints GOST 7171 63 Aeroshell 10 A Shell Aviation Grease S 7108 Engine oil SAE 15W 40 15 50 20W 40 SAE 40 SAE 5W 20 Fuel MOGAS ASTM D4814 AVGAS 100LL ASTM D910 Greasing and preserving aerosols for WD40 hinges and artificial joints MAY 2007 3 19 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 3 AERO Sp z 0 0 SERVICING AT 4LSA For all maintenance of the engine servicing materials specified in the Maintenance Manual of Aviation Rotax 912 Engines Chapter 05 00 00 item 2 5 Servicing materials 3 14 Cleaning and washing Cleanliness is essential for effective operation of the subassemblies of the airplane When cleaning or washing the airplane the following is to be observed 1 When using compressed air safety goggles are to
189. s connected to the contact bus vla a 50A automatic circuit breaker installed on the central console The alternator s electrical installation is shown on Figure 4 20E Automatic circuit breaker 112 250 101 Central console 21 2E Alternator 887251 Gearbox ALTERNATOR KA FAILURE lamp AT3 61 395 0 Instrument 3 Automatic circuit breaker 7274 2 5A 23E sa h V4 DA H d a b Lu E 4 LN Lr s j N IZ 13 JE amp Re lt x ry 2 1 a lax w _ f a i i a ga Q al n 12 BUS 22E es C Figure 3 Alternator electrical installation Dotted lines shows the standard airplane electrical installation 15 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 15 AT 4LSA ELECTRICAL SYSTEM The alternator is installed on the left side of the propeller gearbox and driven by a V belt The V belt pulley is installed on the engine shaft The alternator s speed of rotation is egual to 1 32 of the engine shaft speed The alternator s power output is 600W at 6000 RPM A voltage regulator is integrated into the alternator The alternator installation is shown on drawing figure 4 Figure 4 Alternator installation V belt pulley plate V belt V belt pulley Engine shaft Alternator mount Belt stretcher Alternator Control cable connector Power terminal clamp o Oo INO Lomo ae dra MAY 2007 15 7 AIRPLANE MAINTENANCE M
190. s torque limits refer to Chapter 16 6 Tools Required Metric Wrenches 5mm to 19 mm Metric Socket set 5 mm to 19 mm Screwdriver Plain amp Philips Wire Lock Pliers amp locking wire MAY 2007 9 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 9 AERO Sp z o o AIRPLANE STRUCTURE AT 4LSA 9 2 3 Removal and installation of the wing flap Removal 1 Extend the wing flap to 40 2 Beginning from the inboard side unscrew the hinge wire locks and pull out the wire 3 Lower the outboard end of the flap a little and move outside the flap from its control system Installation 1 Perform steps 1 to 3 in reverse order 2 Lubricate all joints 3 For bolted joints torque limits refer to Chapter 16 6 Tools Reguired Metric Wrenches 5mm to 19 mm Metric Socket set 5 mm to 19 mm Screwdriver Plain amp Philips Wire Lock Pliers amp locking wire 9 3 ELEVATOR STRUCTURE The mass balanced slab tail elevator is of rectangular form Its skeleton 1 consists of two spars and front and rear ribs all riveted to the skin In the central part the elevator control lever integral with the outrigger of the mass balance 3 and the ferrules are bolted to the front spar Along the whole span of the tail at the rear three hinges 5 fix the trim amp balancing tab 2 The tips 6 of the slab tail are made of composite 9 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 9 AT 4LSA AIRPLANE ST
191. sconnect joint in antenna s cable Assembly 1 Execute point 1 4 in reversed sequence MAY 2007 18 1 9 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z o o SUPPLEMENT No 1 AT 4LSA 4 COM and Intercom diagram The SL 30 transceiver RNI is connected to the primary bus via two circuit breakers separated for COM and NAV RN4 Connection diagram is given on Fig 5 1 Transmit button NAV circuit breaker SL 30 18 1 10 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO z o o AT 4LSA SECTION 18 SUPPLEMENT No 1 Fig 5 1 SL30 transceiver with MD200 306 indicator diagram MAY 2007 SS 3H 24 n 162 1005 kp 4M 2005 5 24 162 157 gt z kp 44 20 59 gt AT4 64 051 0 ok ovoja TT E iz ed lt 7 N 25 ed 2 FERE ANGE HANO kpl 7014517 Se RNSN RNIB pi ium AV x 8 t i3 RNi4 224WG skr Eua E c 151 806 228 ure Z Taser lalate preu zea a Rs RNIB 22AWG skr RNIB RLR 3 p m c t Re T g MI M Fs I Q D ge wv BRS y at sis die Z KA 424 2008 XX Xe AT4 64 051 0 Tc L2 RAZ X ma D JIANG akr rat eai w akr RAS ji RAS 2223 skr 2
192. screw a guide pin of 8 dia M6 on the bolt and drive it into the hole of the rear spar fitting Screw the bolt nuts of the main and of the rear spar onto the bolts and torque them accordingly to the table refer to Ch 16 10 Mark the position of each nut relative to its bolt with red paint Connect the aileron push rod to the torque tube reconnect the bonding cable and secure the protective bellow Reconnect the lines to the pitot tube Install the seats Install the wing fuselage fairing For bolted joints torque limits refer to Chapter 16 6 Tools Required Metric Wrenches 5mm to 19 mm Metric Socket set 5 mm to 19 mm Screwdriver Plain amp Philips Wire Lock Pliers amp locking wire MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp 2 o o CHAPTER 9 AT 4LSA AIRPLANE STRUCTURE 9 2 2 Removal and installation of aileron Figure 9 5 Flaps and ailerons hinge wire locks 1 Wing rear spar 4 Flap hinge wire 2 Aileron hinge wire 5 Flap hinge wire lock 3 Aileron hinge wire lock Removal 1 Extend the wing flap to 40 2 Unlock and unscrew the aileron control system bolt nut and remove the bolt refer to section 11 2 3 Unscrew the hinge wire locks and move outside the wire 4 Remove the aileron taking care of the mass balance which is located inside the wing tip Installation 1 Perform steps 2 to 4 in reverse order 2 Lubricate all joints 3 For bolted joint
193. st results can be achieved spraying warmed de icing fluid or using hot air not exceeding 194 F 90 Loose ice should be immediately swept off and the surface dried Do not use tools to scrape chop or knock off the ice They will certainly cause damage to the surface of the airplane If ice occupies the space in front of the control surfaces it is to be removed with use of hot air After completing removal of snow or after de icing the airplane movement of all control surfaces must be checked Before checking the controls in the cockpit check the full travel of all control surfaces manually Check also that the draining holes in the lower surfaces are free MAY 2007 3 21 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 3 AERO Sp z o o SERVICING AT 4LSA In case of snowfall or when circumstances conducive to icing occur the airplane must be completely checked for icing before being flown that its mechanisms and controls are not frozen drain holes are clear brake pads not frozen to the discs or air intakes to the engine not blocked NOTE A high capacity source of warm only air is more effective than a low capacity source of hot air and its use is not as risky in respect of the possibility of overheating the structure Removing ice from the canopy warm air is to be used with special care to avoid crazing cracking or deformation of Plexiglas 3 14 6 Engine Cleaning Cleaning of the engine is to be performed acc
194. tached to the leg The main legs are fastened to the landing gear box 8 of the fuselage by means of angle bars 7 made of duralumin which is integral part of the fuselage The area where a leg is fastened to the fuselage can be screened with a fairing 10 which is screwed to the fuselage with screws Figure 10 3 Main landing gear 1 Main leg 6 Tire with tube 2 Wheel axle 7 Attaching angle bars 3 Wheel hub 8 Landing gear box 4 Distance sleeve 9 Inspection door cover 5 Brake disc 10 Wheel fairing 10 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 10 AT 4LSA LANDING GEAR 10 2 1 Removal and installation the main wheel see Figure 10 4 Removal 1 2 3 Mo oc Lift the airplane with jacks by at least 5 cm 2 in Unscrew the bolts fixing the brake caliper to the outrigger Remove the brake caliper and hang it on the leg to avoid hanging the caliper from the brake line Unlock and unscrew the castellated nut of the wheel axle Remove the wheel from the axle Deflate the tube Unscrew the halves of the hub Remove the brake disc with the distance sleeve disconnect the hub halves Installation 1 2 3 4 Perform steps 2 to 7 in reverse order Note the distance sleeve of the wheel bearings do not omit in when reinstalling the wheel Lubricate all joints Inflate the wheel F
195. tem and the nearest elements of the fuselage min 3 mm 0 12 in 14 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 11 AT 4LSA AIRPLANE CONTROLS 11 2 3 Mass balancing of the aileron The mass balance of the aileron is achieved with the lead weight which is bolted to the outrigger of the aileron The balance must be checked after each painting or paint repair as well as after any repair of the aileron The complete aileron painted and prepared for installation must be balanced in a stand 4 as shown below Figure 11 6 Mass balancing of the aileron 1 Balancing weight 3 Weight of 230 g 0 507 Ibs 2 Thread 4 Balancing stand CAUTION The mass balancing must be checked indoors in a draught free room 1 Locate the aileron in the stand 4 2 Hang weight 3 on thread on the bolt fixing balancing lead so that the thread 2 axis coincides with the bolt axis 3 By adding or removing a weight 1 make that the lower surface of the aileron will be set in horizontal position MAY 2007 11 7 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 11 AERO Sp z o o AIRPLANE CONTROLS AT 4LSA 11 3 RUDDER CONTROL SYSTEM The rudder 14 is suspended on the fin with two bolts refer to Ch 9 4 It is connected with the rudder control pedals 4 by means of a system of cables 10 Springs 3 spanned between the pedals and the firewall provide constant tension of the cables The ca
196. the manufacturer 12 1 2 Blade linear tracking alignment check Remove at least one spark plug from each cylinder head of the engine place the airplane in a level position using jacks Place a dial indicator on the ground in the airplane axis touching the propeller blade approx 10 cm 4 in above the blade tip see drawing 4 1 Check the linear alignment of the blade track The biggest acceptable difference is 2 0 mm 0 075 in S max 2 0 Figure 3 Blade linear tracking alignment check MAY 2007 12 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 12 AERO Sp z o o POWER PLANT AT 4LSA 4 Secure the propeller fixing bolts with locking wire 5 Install the spinner aligned with the marks made during removal 6 Lower the airplane and re install spark plugs 12 1 3 Checking and adjustment of the blade angle of incidence The propeller blade angle of incidence was set during the airplane flight tests to enable optimum performance and safe operation according to the limitations of the AT 4ILSA The blade angle of incidence is 21 5 0 5 The biggest acceptable difference in the blade angle of incidence between blades is 0 2 WARNING Angle of attack of propeller blade should be within 14 26 The method of checking the blade angle of incidence is described in the Chapter 3 of the ELPROP Propeller Maintenance Manual 12 6 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A A
197. the elevator control lever refer to section 11 5 1 3 Unscrew the wires locks and remove the wires from the hinges 4 Remove the trim amp balancing tab Installation 1 Perform steps 1 to 4 in reverse order 2 For bolted joints torque limits refer to Chapter 16 6 9 4 RUDDER STRUCTURE The all metal rudder is partially mass balanced fitted with aerodynamic horn balances and suspended on two hinges Its structure 1 consists of five ribs and the small spar 9 all riveted to the skin At the lower part of the rudder is located rudder control 4 with lower bolt 3 and stop 5 At the upper end the laminated rudder tip with the mass balance 7 inside is located 9 10 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o AT 4LSA Figure 9 8 Rudder structure Upper bolt Lower bolt Rudder control fitting Rudder stop Rudder tip oa mom a MAY 2007 CHAPTER 9 AIRPLANE STRUCTURE Rudder structure 7 Mass balance 8 Rudder control cables 9 Small spar 10 11 Balancing plate Stabilizer stops 9 11 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 9 AERO Sp z o o AIRPLANE STRUCTURE AT 4LSA 9 4 1 Removal and installation of the rudder Removal 1 Remove the split pins and unscrew the bolt nuts connecting the control cables 12 to the rudder control lever 4 Remove the bolts refer to section 11 3 1 2 Remove the split pin and unscrew the lower bolt 3 nut of
198. the oil pump 17 Check the system for leaks fastening of the oil filter check the oil level and replenish if required 18 Reinstall the engine cowling 19 For bolted joints torque limits refer to Chapter 16 6 12 24 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 12 AT 4LSA POWER PLANT 12 3 COOLING SYSTEM The Rotax 912ULS engine is eguipped with a closed pressurized cylinder head cooling system The water pump driven by the camshaft circulates the coolant between the cylinder heads radiator and coolant reservoir The reservoir is closed with a pressure cap which assures constant pressure of the coolant If the coolant temperature rise the cap allows the coolant to flow to the overflow reservoir When a temperature drops coolant is sucked in to the system Hot coolant flows from the overflow reservoir to the cooler and to the pump and cylinders Air inlet tunnel made of composite is installed on the mounts of the cooler Engine cylinders are cooled additional by air Figure 12 9 system 1 Coolant cooler 5 Rigid pipes 2 Overflow reservoir 6 Overflow reservoir 3 Flexible rubber hoses 7 Coolant pump 4 Engine fittings 8 Air inlet tunnel to coolers MAY 2007 12 25 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02
199. the oil tank Always follow engine manufacturers guidelines which may change from time to time 3 9 Replenishing engine coolant A detailed description of the cooling system is given under 12 9 Cooling system According to the Operational Manual of Rotax 912 Series Aero Engines item 10 2 1 waterless coolant EVANS NPG is recommended The coolant overflow tank is located in the engine compartment on the firewall and is visible and accessible after opening the port cover of the upper engine cowling There are two marks on the overflow tank min and max indicating the lower and the upper level of the coolant The transparency of the tank enables direct visual inspection of the level of the coolant To replenish the coolant the filler cap is to be unscrewed the fluid poured in until it reaches the upper mark and the filler cap then screwed up tight There are two venting holes in the filler cup Their cleanliness must be checked frequently NOTE If the venting holes are not clear it may result in damage to the overflow tank and loss of the coolant NOTE The commercial name of the recommended coolant is given in the placard located on the firewall next to the overflow tank MAY 2007 3 17 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 3 AERO Sp z 0 0 SERVICING AT 4LSA 3 10 Replenishing brake fluid A detailed description of the brake system is given under 10 3 Brake system in this manual In the system DOT 4
200. the rudder 3 Remove the rudder lifting it slightly upwards 4 Disconnect the electric wire of the anti collision strobe Installation 1 Lubricate all ball bearings axles and connecting bolts with grease 2 Perform steps 1 to 4 in reverse order 3 Ensure that the rudder control cables are not crossing and are correctly tightened 4 For bolted joints torque limits refer to Chapter 16 6 Tools Required Metric Wrenches 5mm to 19 mm Metric Socket set 5 mm to 19 mm Screwdriver Plain amp Philips Wire Lock Pliers amp locking wire 9 12 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 10 AT 4LSA LANDING GEAR CHAPTER 10 LANDING GEAR 10 1 Nose landing gear 10 2 10 1 1 Removal and installation of nose wheel 10 3 10 1 2 Removal and installation of fork 10 4 10 1 3 Removal and installation of fork axle 10 4 10 1 4 Removal and installation nose leg 10 5 10 2 Main landing gear 10 6 10 2 1 Removal and installation of main wheel 10 7 10 2 2 Removal and installation of main leg 10 8 10 3 Brake system 10 9 10 3 1 Brake fluid replacement 10 11 10 3 2 Removal of brake cylinder 10 11 10 3 3 Brake pads replacing 10 12 10 3 4 Brake system bleeding 10 13 10 3 5 Brake disc replacing 10 14 10 3 6 Installation method of the brake hose unions 10 14 10 3 7 Replacing the brake disc 10 15 10 3 8 Installation method of the brake line terminals 10 15 10 4 Rear skid 10 16 10 4 1 Removal and installation of skid 1
201. the same pitch to both riveted joints 2 6 Figure 16 3 Repair of rib flange 1 Rib frame 4 21 5 holes 2 Skin 5 Crack 3 Angle 6 Rivets 16 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 16 AT 4LSA REPAIRS 16 4 3 Repair of trailing edges Application repair of ailerons wing flaps or control surfaces 1 Remove all rivets along the trailing edge NO Remove the damaged trailing edge Flatten the sheets of the skin A Manufacture a new trailing edge of PA7 ta sheet of gauge 1 2 mm and 12 mm 0 48 in width and prime it 5 Install the trailing edge and rivet it with pop rivets of 23 mm NOTE WHEN RIVETING KEEP THE EDGES STRAIGHT AND THE SURFACES PARALLEL 6 Protect the repaired area with primer and paint it with a suitable color 16 4 4 Repair of dented or cracked skin on angled edges Application repair of the rear part of the fuselage 1 Have manufactured a plate of PA7 ta sheet metal of gauge long enough to connect with the ribs frames or stiffening adjacent to the damaged spot Prime the plate In case of crack drill holes of 21 5 mm at both ends Mark the positions of the rivets and drill the lead holes Straighten the dented edge O O N Remove those rivets in the ribs or frames stiffening which will be used to fix the plate O Drill holes for rivets in the plate and the skin T Rivet the plate to the skin
202. tion switch START Engine starting R L One magneto only switched on BOTH Both magnetos switched on OFF Both magnetos switched off 7 t 3 Next to the switches of Battery Generator and Alternator BATT GEN ALTERN 4 Next to the switches of turn coordinator artificial horizon and directional gyro FUEL AMI ONI CS GYRO PUMP MASTER INSTR 5 Over the fuel shut off valve FUEL SHUT OFF VALVE MAY 2007 8 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 8 AERO Sp z o o PLACARDS AT ALSA 10 11 12 13 8 4 CHOKE O lt e 3 o 27 E Over carburetor preheating knobs CARB HEAT Over oil cooler handle OIL HEATI NG Over cabin vent handle CABI N VENT Over cabin heating handle CABI N HEAT Next to the trim amp balancing tab position indicator NOSE DOWN I DO m HOSE UP Next to the wing flap lever O FLAPS I5 0 Next to the earphone sockets HEADPHONE MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 8 AT 4LSA PLACARDS 14 Next to the microphone sockets MIC 15 On the cover of the port baggage compartment BAGGAGE 44 Ib 16 On the cover of the starboard luggage compartment BAGGAGE 22 Ib FI RE EXTI NGUI SHER INSI DE 17 Next to the levers opening the cockpit canopy LOCK z CANOPY 18 Nextto the cockpit canopy jettisoning levers CANOPY J
203. tomatic squelch and by rotating the knob right and left select required volume level By pulling the knob in the automatic squelch will be on again COMM PULL SOUELCH vot 18 2 4 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o SECTION 18 AT 4LSA SUPPLEMENT No 2 CAUTION Do not start engine with transceiver ON 2 2 SL 40 in COM mode The display of SL 40 transceiver as well its control devices are presented on Fig 2 1 3 4 5 6 7 8 Fig 2 1 SL 40 transceiver frond display 1 Power Volume Squelch knob 2 Photocell 3 Active frequency 4 Transmit annunciator 5 Standby frequency annunciator 6 Standby frequency 7 Large outer knob 8 Small inner knob 9 Frequency FLIP FLOP select button 10 Emergency Channel button 11 Frequency monitor button 12 Recall memory button 13 Store memory button MAY 2007 18 2 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A SECTION 18 AERO Sp z 0 0 SUPPLEMENT No 2 AT 4LSA 3 SL 40 transceiver disassembly and assembly 3 1 Disassembly of SL 40 main unit Disassembly 1 Remove screw in front panel to unlock the transceiver 2 Sidle out transceiver from a slot in instrument panel Assembly 1 Execute steps 1 2 in reversed sequence If necessary the slot can be disassemble too by removing canopy and cover protecting tank than disconnecting electrical cables at the s
204. tors synchronization Refer to ROTAX engine Maintenance Manual Chapter 12 00 00 48 Verify idling speed Refer to ROTAX engine Maintenance Manual Chapter 12 00 00 D CABIN GROUP 1 Inspect compass for damage attachment and operation 2 Checkinlets for general condition and operation and check that inlet drain line is unobstructed at over tank cower Inspect shut off valve for leaks and attachment 3 4 Inspect fuel lines and drain lines for general condition and leak tightness 6 Inspect flight instruments engine monitoring cluster and electronic equipment for damage and fixing 7 Inspect electric wiring in cabin for damage chafing and fixing 8 Drain Pitot and static systems 9 Inspect general condition and leak tightness of Pitot and static systems 10 Inspect safety belts for general condition and attachment 11 Lubricate of canopy locking mechanism and emergency canopy jettison E FUSELAGE AND EMPENNAGE GROUP 5 Inspect electric system switches circuit breakers and fuses gages for general condition damage and fixing 12 Inspect fuselage and empennage structures externally for damage 13 Inspect fuselage and empennage structures internally through all access doors and accessible openings for damage cracks and corrosion 14 Inspect horizontal Inspect nose and main landing gear attaching joints for become loose and damage 15 Inspect stabilizer and rudder attachment for damage
205. trol benzene acetone anti freeze fluid or painting solvents because these materials make the surface of Plexiglass soft and generate a network of fine cracks crazes 3 20 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 3 AT 4LSA SERVICING Agents used in the households for cleaning glass panels may be used provided they do not contain the above specified harmful materials 3 14 3 Cleaning the cockpit interior The seats carpets and upholstery should be cleaned with a vacuum cleaner Water is not to be used for cleaning of cloth covers Commercial cleaning agents for car upholstery are recommended but the indications given by the manufacturer are to be strictly observed 3 14 4 Removing snow When removing snow do not use de icing fluids These fluids diluted with water from snow melt are not resistant against re icing and may produce a kind of icing which is very difficult to remove The best results are achieved when using a soft hair brush brush or broom When removing snow from the wing move it to the wingtip and avoid moving it to the control surfaces or to the trailing edge Snow which is frozen to the structure is to be removed by use of hot air Continue using hot air until the whole surface is completely dry Do not overheat the structure and parts of the airplane The hot air must not be over 194 F 90 3 14 5 Removing ice or hoarfrost When removing ice or hoarfrost the be
206. uel tank cover and could be removed through by pulling firmly on the eyelet MAY 2007 13 15 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 13 AERO Sp z o o CABIN AT 4LSA PAGE INTENTIONALLY LEFT BLANK 13 16 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 14 AERO Sp z o o STATIC AND PITOT PRESSURE SYSTEM 14 1 14 2 14 3 14 4 14 5 MAY 2007 CHAPTER 14 STATIC AND PITOT PRESSURE SYSTEM Static and Pitot system diagram Draining of sediment from static and Pitot system Static and Pitot system connection in fuselage and in wing Removal and installation of static sensors Checking of static and Pitot system for leaks AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AT 4LSA 14 2 14 3 14 4 14 5 14 6 14 1 AERO Sp z o o CHAPTER 14 AT 4LSA STATIC AND PITOT PRESSURE SYSTEM 14 1 STATIC AND PITOT PRESSURE SYSTEM The Pitot and static pressure is taken by ports and delivered to the airspeed indicator altimeter vertical speed indicator and encoder optional The Pitot tube and static pressure ports are installed on the lower surface of the left wing On Pitot and static pressure lines the water sediment traps are installed and are accessible from the fuselage lower side 7 1 2 H N s 3 HL E A 8 Pa Figure 14 1 Pitot and static pressure system diagram 1 Vertical speed indicator 6 Water sediment traps 2 Altimeter 7 Encoder option 3 Airspeed indi
207. upply OOOOO OOOOO OOOOO Aa les O GS C UA We Em CES eee Drawing 2 2 Location of switches on the instrument panel 1 STROBE LIGHT switch MAY 2007 18 9 3 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 18 AERO Sp z o o SUPPLEMENT No 9 AT 4LSA WARNING The strobe light power supply is a high voltage electrical device To avoid electric shock when handling wait a minimum of 10 minutes after disconnecting the strobe light power supply 3 Removal and installation of the strobe light power supply Removal 1 Remove the right pilot seat 2 Disconnect the strobe light power supply connecting cables 3 Unscrew the fixing screws and remove the power supply Installation Perform pts 1 3 in reverse order 4 Strobe light removal and installation Removal Unscrew the strobe light cover fixing screws 2 Pull out the strobe light with the supply cable from wing tip 3 Disconnect the supply cable Installation Perform pts 1 3 in reverse order 18 9 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 CHAPTER 18 AT 4LSA SUPPLEMENT No 9 203005 Drawing 4 1 Strobe light assembly 1 Wing tip 3 Strobe cover 2 Supply cable 6 Fixing plate 3 Strobe light 7 Fixing screws 4 Gasket 5 Strobe light power supply start up
208. upply or any maintenance The engine monitoring instruments are located on the instrument panel The set of those consists of 1 electronic tachometer K17 co operating with the generator 2 fuel pressure indicator K7 3 engine monitor In the AT ALSA airplane fuel system P11 electric emergency fuel pump is installed and switched on with the P10 automatic switch installed in the instrument panel When fuel pump is operated the enunciator FUEL PUMP ON will be illuminating There is possibility to install optional electronic clock M1 supplied by airplane bus through K1 circuit breaker together with engine monitoring instruments 15 10 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 15 AT 4LSA ELECTRICAL SYSTEM LIST OF ELECTRICAL EGUIPMENT RELATED TO ENGINE No DESCRIPTION DESIGNATION LOCATION K17 Tachometer Instrument panel K7 Fuel pressure indicator 2A8 8 TSO Instrument panel K2 EMERGENCY FUEL PUMP circuit 7242 2 3A Instrument panel breaker Circuit breaker 7242 2 3A Instrument panel KS10 TL Memory Info button Under instrumental panel KS Circuit breaker Circuit breaker 7274 72744A 727414 Instrument Instrument panel EIE temperature transmitter ROTAX KS7 Outside air temperature sensor 399OT Instrument panel OAT CHT cylinder 2 CHT cylinder 3 EGT cylinder 3 cylinder 4 Electronic clock Em Instrument panel
209. ver protecting tank than disconnecting electrical cables at the slot s connector The slot is attached to supports screwed to instrument panel 3 2 Disassembly and assembly of transmission switch Disassembly 1 Remove fittings from stick 2 Remove seats and disconnect connector of transmission switch cables at the stick s torque tube 3 Screw out two screws fitting the foot of transmission switch 4 Undo nut fitting switch and sidle it out from foot 5 Disconnect electric cables Assembly 1 Execute point 1 5 in reversed sequence 3 3 Disassembly and assembly of MD200 306 indicator Disassembly Remove canopy see chap 13 6 1 and cover protecting tank 2 Disconnect electrical cables 18 1 8 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z 0 0 SECTION 18 AT 4LSA SUPPLEMENT No 1 3 Screw out screw attaching and remove indicator Assembly 1 Execute point 1 3 in reversed sequence 3 4 Disassembly and assembly of COM antenna Disassembly 1 Disconnect joint in antenna s cable through the service openings in rib of luggage compartment 2 Screw out screws attaching antenna 3 Sidle out antenna from the opening in fuselage Assembly 1 Execute point 1 3 in reversed sequence 3 5 Disassembling and assembling NAV antenna Disassembly 1 Disassemble ruder see chap 9 4 1 2 Screw out screws attaching antenna 3 Sidle out antenna from the opening in fuselage 4 Di
210. void contact between the brake fluid and the airplane structure Elements which might be soaked with brake fluid should be protected with shrink wrap 2 Disconnect the feeding and the pressure lines from the brake cylinder 3 Unscrew bolt nuts fastening the brake cylinder and remove the bolts 4 Remove the brake cylinder The brake cylinder piston rod is not permanently connected with brake cylinder MAY 2007 10 13 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 10 AERO Sp z o o LANDING GEAR AT 4LSA Installation 1 Perform steps 2 to 4 in reverse order 2 Fill the brake system with brake fluid and bleed it refer to 10 3 4 3 For bolted joints torque limits refer to Chapter 16 6 10 3 5 Replacing the brake pads CAUTION The replacement of the brake pad is recommended when the thickness of the friction lining is 2 mm 0 08 in The limit value is 1 5 mm 0 06 in 1 Remove the brake caliper refer to section 10 2 1 2 Remove cotter pins fixing the brake pads and remove the brake pads 3 Install new brake pads and fix with new cotter pins 4 Using a flat screwdriver move the pads to obtain a gap between them wide enough to locate the brake disc between them 5 Install the brake caliper onto the outrigger 10 3 6 Bleeding the brake system CAUTION The brake system must be bleed after all tasks which require unsealing the brake system 1 Loosen the bleeding valve of the brake caliper
211. worn 2 Protect all rubber elements as engine mount bushes tires etc against washing agents and solvents with covers If contamination occurs wash with clean water and dry with a clean towel 3 Washing areas adjacent to electric equipment should be performed with great care The battery must be disconnected 4 Ensure that no water or cleaning fluids enter the pitot or static systems 3 14 1 Cleaning outer surfaces of Aircraft Before commencing the following should be done Apply the cover to the pitot and static pressure sensor Cover all holes e g venting of the tank Flush all fine dirt with clean water and subsequently wash the surface with water with mild soap added Do not use abrasive soaps pungent or basic or detergents To remove spots of grease or oil use a piece of cloth with aliphatic naphtha Surfaces cleaned with naphtha need to be re waxed and polished Use a soft cloth or chamois for polishing High quality automotive waxes or polishing pastes may be used for painted surfaces 3 14 2 Cleaning Plexiglass Canopy Greatest care is required to avoid scratches when cleaning the Plexiglass canopy Never rub Plexiglass dry Rinse the surface with pure water or water with mild soap and subsequently use a clean soft cloth sponge or chamois To remove spots of grease or oil use methyl alcohol or with aliphatic naphtha Rinse with pure water and avoid excessive rubbing of the Plexiglas WARNING Do not use pe
212. y in the joint between a bolt and ball bearing replace both the bolt and the ball bearing If there is excessive play in the joint between a bolt and bronze sleeve the bolt and the sleeve must be replaced The new sleeve must be pressed in and subsequently reamed NOTE REAMING OF BRONZE SLEEVES TO OVERSIZE IS PROHIBITED 16 4 MAY 2007 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A AERO Sp z o o CHAPTER 16 AT 4LSA REPAIRS 16 4 AIRPLANE STRUCTURE PANEL REPAIRS The operator of the airplane may repair himself minor damage to the structure N Vo Figure 16 1 Metal sheet skins gauge 1 Upper part of the fuselage skin 2 Vertical fin skin 3 Rudder skin Z 0 5 mm 4 Rear quarter of the fuselage skin 5 Sidewalls of the fuselage skin Z 0 6 mm 10 Ailerons skin 11 Leading edge of the slab tail skin 12 Trailing surface of the slab tail skin 13 Trim tab skin MAY 2007 16 5 AIRPLANE MAINTENANCE MANUAL Doc No ATT4 02A CHAPTER 16 AERO Sp z o o REPAIRS AT 4LSA 16 4 1 Skin repair between the ribs Application all metal airframe skin repair 1 Cut out the damaged part of skin between the ribs 2 Prepare a frame of 7 sheet metal of gauge a as given in the table 3 The inner and the outer contour of the frame have to be distanced by 14 mm 0 55 in both sides from the contour of the cut out 4 Mark out the outer row of lead holes of 51 6 mm to rivet the frame with the skin

Download Pdf Manuals

Related Search

Related Contents

und Bedienungsanleitung CTC V 22 / 40 Lamda  C50 User Manual  Fedders CH12 User's Manual  カタログPDFダウンロード  User Manual  ToughTech™ Duo Users Manual  + consultotions spécialisées ou des hospitofisotions, nécessitont  Product catalogue  インターネット契約約款  Icom IC-F610 Two-Way Radio User Manual  

Copyright © All rights reserved. Failed to retrieve file