OPERATION AND INSTALLATION MANUAL
Contents
1. E 18 amp g B di 5 s fe gt 8 ex 5 3 2 E zlo t i c 2 m A 8 ka AN 1 m 2 i BS 5 sle KI 55 ng SUT md 2 5 ilc e TA ta 2 gt SE o jst 8 w 8 su ki l E F 2 5 2 g5 i E COS In E amp i 8 Q DS2. lt C E LU TE e Ww E 205 e 9007 1016 m ux E A gt D z CN CN r KN LU D aie Page 11 8 61 10 66 DRAWINGS g 2010 05 19 OPERATION AND INSTALLATION MANUAL 11 9 AV 844 1 D C F EN 1366 gt co 541 UD 206 500 91019 61 10 66 DRAWINGS Page 11 9 2010 05 19 Avia Propeller Ltd since 1919 Highly experienced engineering and manufacturing company Our specialization is in research and development manufacturing repairs overhauls service and sales of aircraft all metal in flight pitch changeable propellers and their parts Our R amp D team has long term experiences with aircraft propeller design One of the latest R amp D targets is to enlarge the new propeller AV product line lighter aluminium hub and blades Operations department is using up to date machinerv incl CNC devices accompanied with traditional craftsmanship of staff m
3. TON avs soot 59 021 HE 5 5 rr a leo amp lt gt 55 Ts m Dem Acc mee x m s gt Pan den md 5 a m uj e T d 5 p CN HE 61 10 66 DRAWINGS Page 11 5 2010 05 19 OPERATION AND INSTALLATION MANUAL 11 6 842 1 1366 o o a 5 2 KINE S gt a co X P V D 3 HE 52 K 8 5 lt SO HE ME S G 2 LI lt gt ax A acids 5 EO 5 5 o HE 5 3 x 8 8 CN 5 E o COSd V GOOF 91018 JVS ET 9 0 5909 a gt lt al N NN N al IN NI E if I 00 M S 9 0 5 m NI 8 3 be no tal 5 5 E eq l lt lt ea ul ta 61 10 66 DRAWINGS Page 11 6 2
4. 5 5 8 2 3 E og S Njo SE ss He lt N N N N N N N N CN SA gt C X 2 lt lt 4 ar il FI m gt T wo sm 8 3 o c ob H qe Tie EJ IR REN i 5 Ns a 8 Sk NIN i N gt CN SBS xl ser LU EG 61 10 66 DRAWINGS Page 11 2 2010 05 19 OPERATION AND INSTALLATION MANUAL 11 3 AV 803 1 B C AV 803 1 D C EN 1366 C06 div 900791010 TON JYS 503590412 61 10 66 DRAWINGS Page 11 3 2010 05 19 OPERATION AND INSTALLATION MANUAL 11 4 AV 803 1 K C EN 1366 LU ko ND 61 10 66 DRAWINGS Page 11 4 2010 05 19 OPERATION AND INSTALLATION MANUAL 11 5 AV 842 1 B EN 1366
5. 51 4 Re 2727277222222727544722222 hy Zi 2 N N TN EN N N 1 212222 N N N N z ATR bob aunsseud JOUISAOE DAH35 YO OL MO14 1HDIIMHALNNOD 3N 13081N02 35v3u230 OL aunssaud BAWA 391138 DNILVASNAM Wwe pe DNIHAHLV34 W3TIJHOWA HSNd S1N3WD35 puanovn 43431 3 M23H2 AID nye uana mA 0334 3 Suusnrav 911919 03345 147 4 4 2010 05 19 DESIGN AND OPERATION INFORMATION 61 10 66 OPERATION AND INSTALLATION MANUAL EN 1366 5 0 INSTALLATION AND OPERATION INSTRUCTION NOTE TAE 125 engine is installed the CSUM 01 01 must be used for installation and operation of the CSU 5 1 All propellers of these designs are only suitable for installation on flange type engines The code for the flange type can be seen from the model designation see section 3 5 2 A governor with suitable oil pressure direction has to be installed on the engine the control lever being mounted as shown below Figure 5 1 ACCEPTABLE 5 2 1 If applicable install the unfeathering akku to the governor and fix it onto the provided positions 5 2 2 On the TAE engine the CSU is already installed Refer to the CSUM 02 01 5 3 Elect
6. If the blade clamp is not jointed with blade bushing bv special pin clamp is sliding on the blade bushing relate to propellers manufactured up to February 2006 the line on the clamp must coincide with lines on the blade and blade bushing forehead see Figure 5 3 prior to tightening 5 10 Check the blade track Refer to section 6 2 for blade track procedure and limits Turn propeller for safety reasons ignition always opposite the usual direction of rotation 5 11 Install spinner on support plates observe mating marks Torque screws with washers 3 5 Nm 27 44 inlb Check runout of the dome Max 0 08 inch permissible 5 12 Brush block installation The distance between the brush assembly and the slip ring must be 0 8 2 4 mm figure 5 4 Brushes must be splayed at a 2 angle from the perpendicular on the copper rings figure 5 4 The entire face of each brush must contact the copper ring throughout full 360 slip ring rotation figure 5 5 PROP ROTATION NOTE After 2 3 operating hours there should be at least 80 contact between new brushes and slip ring 100 contact after 5 6 hours INCORRECT CORRECT NCORRECT Figure 5 5 5 13 Connect electrical propeller de icing system if required Secure the screws with red paint see slip ring contacts CAUTION Test runs of propellers with installed de icing system are only allowed with mounted s
7. 6120 16 001 R6 FADEC 02 7610 55 001 R1 Table I HIRF Environment ll FIELD STRENGTH V M 100kHz 20 20 500 kHz 20 20 2 MHz 30 30 30 MHz 100 100 70 MHz 10 10 100 MHz 10 10 200 MHz 30 10 400 MHz 10 10 700 MHz 700 40 1 GHz 700 40 2 GHz 1 300 160 4 GHz 3 000 120 6 GHz 3 000 160 8 GHz 400 170 12 GHz 1 230 230 18 GHz 730 190 40 GHz 600 150 4 6 Propeller de icing The propeller mav have electrical or liquid de icing svstems installed The de icers are bonded onto the blades as usual The rest of the electrical svstem is equal to existing components with slip ring and wire harness Page 4 2 61 10 66 DESIGN AND OPERATION INFORMATION 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 4 7 Unfeathering Accumulator Feathering Propeller alwavs have an unfeathering accumulator installed to the governor This enables unfeathering without a running engine An unfeathering accumulator can also be installed to the governor in some aerobatic airplanes to prevent a decrease of RPM at special aerobatic maneuvers This unfeathering accumulator maintains the oil supplv of the propeller for 5 10 sec at short loss of oil supplv bv the engine Figure 4 2 Govemor oil pressure to decrease pitch single engine Figure 4 1 Governor oil pressure to increase pitch single engine Page 4 3 61 10 66 DESIGN AND OPERATION INFORMATION 2010 05 19 EN 1366 OPERATION AND INSTALLATION MANUAL Jojejnuunooe Buuaujeajun
8. 0 50 100 150 200 250 300 Duration of Overspeed In Seconds Figure 6 4 For engine mounted accessories for example governors pumps and propeller control units manufactured by Avia Propeller any overspeed at a severity level and or duration sufficient to require at minimum a search inspection for the propeller will require the accessory to be disassembled and inspected in accordance with the applicable maintenance manual Regardless of the degree of damage make a log book entry to document the overspeed event 6 3 1 Corrective Action The corrective action is based on the severity and the duration of an overspeed or overtorque for a single event Page 6 4 61 10 66 INSPECTIONS 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 6 3 2 No Action Necessarv Where no action is necessarv no maintenance is necessarv other than to verifv that the overspeed was not caused bv a mechanical problem 6 3 3 Overspeed Inspection An overspeed inspection requires the disassembly of the propeller in accordance with the appropriate propeller overhaul manual and performance of the following inspections General Visually inspect for signs of abnormal wear and or damage Evidence of wear and or damage should be further evaluated using the inspection criteria from the appropriate propeller or blade overhaul manual Special attention must be given to blade retention components Hub Visually inspect the blade retention area of the bla
9. 1 Contact manufacturer 2 Contact manufacturer 3 Replace repair instrument Page 8 2 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 8 6 Rpm increase during normal operation without change of propeller lever position Cause 1 Oil leakage or hot oil 2 Worn oil transfer system causes a decrease in blade angle of attack 3 Internal leakage in the propeller 4 Governor drive failure or broken relief valve spring Remedv 1 Check for oil leaks replace gaskets decrease oil temperature with higher airspeeds 2 If the system works with cold oil and fails at high oil temperature this will indicate high leakage in the oil transfer system on the propeller shaft Repair engine 3 Contact manufacturer 4 Check governor drive and governor on the test bench Attention If sudden oil leakage occurs move power lever back until the rpm will decrease In this condition the propeller goes back to the low pitch stop automatically and no oil pressure is needed Adjust the propeller control for take off position Apply power again no more than required to remain about 100 rpm below take off rpm Note that the propeller rpm should be always lower than adjusted with the propeller control This will hold the governor in underspeed condition and no oil pressure will be transferred from the governor to the propeller 8 7 Rpm decrease during normal operation without change of propeller lever position Cause 1 Speeder spring in the governor brok
10. The rpm can be changed at all power and rpm settings and must be held constant automaticallv within the entire flight envelope If oil pressure is lost and high speeds are used overspeed is possible none counterweighted propellers and throttle must be retarded immediatelv to correct the situation High pitch is set to such a value that in case the oil return line is blocked or for propellers with counterweights installed if the oil pressure fails it should be possible to continue flight with reduced power Go around would be from limited to impossible NOTE Move power lever and rpm lever always slowly to avoid overspeed Page 5 4 61 10 66 INSTALLATION AND OPERATION INSTRUCTION 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 5 21 Pre flight check The propeller should be cvcled at least twice to spill oil before everv flight In cruise flight an infinite number of power and rpm settings are possible because there is no restriction between the stops Rpm restrictions from the engine or propeller manufacturer must be observed and the tachometer must be marked TAE 125 engine is installed the pre flight check must be performed according to the CSUM 02 01 If necessary use the warm air to remove ice from the spinnerdome Spinnerdome surface can be heated to max 85 C for metal spinnerdome max 60 C for composite spinnerdome 5 22 Feathering With the AV C F feathering is achieved with propeller lever pulled to f
11. airspeed and power Usuallv this is called a constant speed propeller Mechanical stops for low pitch and high pitch limit the pitch change travel In case of the oil pressure of the governor to be lost the blades return automaticallv to low pitch or if counterweights are installed to high pitch enabling the pilot to continue the flight The oil pressure is single acting 2 3 0 Feathering position of the blades is possible as an option With the propellers with counterweights oil pressure to decrease pitch is used Feathering is reached with propeller control being pulled to feathering Additionallv there could be a safetv svstem integrated in the propeller to avoid unintended feathering with the engine running at high rpm 2 4 Parts ordering Use the appropriate propeller drawing see section Drawings if any propeller part is need to order due to its damage or loss See the item of the part you reguested Contact propeller manufacturer to original part information and or delivery NOTE Not all propeller parts can be replaced in the field Only outside mounted parts as the flange o ring and the connecting hardware screws nuts cables etc can be replaced in the field Contact propeller manufacturer for more information 10 Page 2 2 61 10 66 GENERAL 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 3 0 3 1 61 10 66 MODEL DESIGNATION Hub designation AV 844 1 E C 1 2 10 11 3 4 5 6 7 8 9
12. mounting number on the blade shank face behind the serial number or the blade set number correspond with number stamped on the hub arm Incorrect installation of the blades can cause the unbalance of the propeller and incorrect blade angles It can lead to abnormal vibration and the engine can be damaged CAUTION O ring prevents moisture to get into the blade bushing thread If the o ring will not to be installed the blade shank can be affected by corrosion Use only original o rings delivered by manufacturer CLAMPING AREA O NOT LUBRICATE lade root area to be slichtl lubricated Position line U r n Figure 5 2 Lubricate the thread and centre diameter in the end of the blade shank slightiv with grease CAUTION DO NOT APPLY ANY GREASE TO THE SURFACE WHERE THE BLADE IS CLAMPED IN THE BUSHING CYLINDRICAL PORTION BETWEEN THE THREAD AND BLADE AIRFOIL SEE FIGURE 5 2 THIS SURFACE MUST BE ABSOLUTELY DRY AND FREE FROM ANY GREASE AFTER BLADE IS INSTALLED IN THE BUSHING Page 5 2 61 10 66 INSTALLATION AND OPERATION INSTRUCTION 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 Screw the blade fullv into the bushing and move it back into the right position The position line on the blade shank must coincide with line on the blade bushing forehead Figure 5 3 Slightiv lubricate the thread of the clamp bolt with graphite grease and tighten with torque 65 70 Nm 48 52 ftlb Secure the nut bv cotter pin CAUTION
13. speed Remedy Increase governor rpm unscrewing the stop screw One turn on the screw will change rpm by approx 25 rpm Important The control must be long enough to have the necessary way in order to contact the stop Secure screw with safety wire 8 1 2 Rpm in flight too high If the static rpm is within the limits only the governor allows overspeed Adjust rpm to the desired value in flight an turn the stop screw in after landing until it touches the governor lever Important Do not change position of the rpm control during final approach Secure screw with safety wire 8 2 Blade shake 8 2 1 Fore and aft movement Cause Blade bearing loose Remedy If more than 3 mm return propeller to the factory or any approved repair station to correct the pre load of the blade retention bearing 61 10 66 TROUBLESHOOTING Fages 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 8 2 1 1 SMA Application Cause Blade bearing loose Remedv No blade shake is allowed In case of blade shake return propeller to the factorv or anv approved repair station to correct the pre load of the blade retention bearing 8 2 2 Blade angle plav 8 3 8 4 8 5 61 10 66 TROUBLESHOOTING Cause Blade bearing loose bv seating and or increased plav bv wear in the pitch change mechanism pitch change pin pitch change block Remedy If more than 2 return propeller to the factory or any approved repair station Sluggish rpm chan
14. this manual up dating according to issued changes Implementation of changes it s necessary to write in list of changes Latest revision of this manual as well as Service Bulletins Service Letters and Service Advisories associated with propellers in this manual are freely disposable at www aviapropeller com NOTICE Illustrations pictures and drawings in this manual are only by example for displayed object and it s not to be regarded as binding on any propeller type or her section GUARANTEE Guarantee conditions for each one propeller are determinated in contract of purchase THANK YOU FOR CHOOSING AVIA PROPELLER PRODUCT Properly maintained it will give you many years of reliable service OPERATION AND INSTALLATION MANUAL Table of content 10 11 61 10 66 AIRWORTHINESS LIMITATION GENERAL MODEL DESIGNATION DESIGN AND OPERATION INFORMATION INSTALLATION AND OPERATION INSTRUGTION INSPECTIONS MAINTENANGE TROUBLESHOOTING SHIPPING AND STORAGE SPECIAL TOOLS DRAWINGS TABLE OF CONTENT Page 1 1 2 1 3 1 4 1 5 1 6 1 7 1 8 1 9 1 10 1 EN 1366 Page l 1 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 This page is intentionallv blank Page l 2 61 10 66 TABLE OF CONTENT 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 LIST OF REVISIONS Revision New page 2010 05 19 all Mav 19 2010 2010 06 01 Il 1 IIl 1 2 1 6 1 June 1 2010 Page Il 1 61 10 66 LIST OF REVISIONS 2010 0
15. 010 05 19 91 SI Yl l A LL 0l 9 S 1366 PBAW JINLUA 500270 s 915 331134039 unjog AR wW TON XALVWAJA JDOWOd LILSIFOd UWNPE 05 LN3NON IDYAOHVLN 77 TA AVAOSITYN 9 Page 11 7 2010 05 19 uug oe WALYBO WNO6 SB L 19 NG 8 INIWOM IDYAOHYLN fyc 31201 DONOA LILSIFOd m 5 DRAWINGS OPERATION AND INSTALLATION MANUAL 11 7 AV 843 1 61 10 66 OPERATION AND INSTALLATION MANUAL 11 8 AV 844 1 D EN 1366
16. 10 11 Avia Propeller manufacturer automatic propeller variable pitch propeller ground adjustable propeller fixed pitch propeller lt gt Blade root type Number of blades Number of variant of the propeller model Code letter for flange tvpe A Motorglider engines 7 16 20 UNF bolts circle dia 80 mm AS 127 D SAE No 2 mod 1 2 20 UNF bolts SAE No 2 mod 7 16 20UNF bolts ARP 502 1 2 20UNF bolts ARP 880 9 16 18UNF bolts SAE No 1 3 8 24UNF bolts Walter LOM flange M10 bolts PW 115 9 16 18UNF bolts M14 flange AIQmnmoou Code letter for counterweights blank no or small counterweights for pitch change forces to decrease pitch C counterweights for pitch change forces to increase pitch Code letter for feather provision blank no feather position possible F feather position installed Only applicable for reversible propellers Only applicable for reversible propellers Code letter for design changes small letter for changes which do not affect interchangeability capital letter for changes which restrict or exclude interchangeability Page 3 1 MODEL DESIGNATION 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 3 2 Blades designation 245 407 1 2 3 4 5 1 Code letter for position of pitch change pin blank pitch change pin position for pitch change forces to decrease pitch C pitch change pin position for pitch change forces to increase pitch CF pitch change pin posit
17. 10 66 SHIPPING AND STORAGE 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 10 0 SPECIAL TOOLS Torque wrench with range 55 150Nm 40 110 ftlb Including all propeller models See section Installation for torques needed to specific propeller installation Insert tools for torque wrench 19mm or 3 4inch B and flange blade clamp only models with threaded blades 16mm or 5 8inch flange 22mm or 7 8inch flange Above mentioned tools are possible to be delivered based on special order Page 10 1 61 10 66 SPECIAL TOOLS 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 11 0 DRAWINGS 11 1 AV 723 1 C lt a u 2 o o I 8 ric fa fa bj 3 5 2 Z 5 5 3 3 a a e m E 3 8 2 si 2 Dp 7 e 8 z o N o o m lt m w u gt 11 1 61 10 66 RORIS 2010 05 19 11 2 AV 723 1 C F OPERATION AND INSTALLATION MANUAL EN 1366
18. 6 01 OPERATION AND INSTALLATION MANUAL EN 1366 This page is intentionallv blank Page Il 2 61 10 66 LIST OF REVISIONS 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 LIST OF EFFECTIVE PAGES Page Date of issue Page Date of issue 1 2010 05 19 11 1 2010 05 19 l 2 2010 05 19 11 2 2010 05 19 Il 1 2010 06 01 11 3 2010 05 19 Il 2 2010 05 19 11 4 2010 05 19 2010 06 01 11 5 2010 05 19 Ill 2 2010 05 19 11 6 2010 05 19 1 1 2010 05 19 11 7 2010 05 19 1 2 2010 05 19 11 8 2010 05 19 24 2010 06 01 11 9 2010 05 19 2 2 2010 05 19 3 1 2010 05 19 3 2 2010 05 19 4 1 2010 05 19 4 2 2010 05 19 4 3 2010 05 19 4 4 2010 05 19 5 1 2010 05 19 5 2 2010 05 19 5 3 2010 05 19 5 4 2010 05 19 5 5 2010 05 19 6 1 2010 06 01 6 2 2010 05 19 6 3 2010 05 19 6 4 2010 05 19 6 5 2010 05 19 7 1 2010 05 19 7 2 2010 05 19 8 1 2010 05 19 8 2 2010 05 19 8 3 2010 05 19 8 4 2010 05 19 9 1 2010 05 19 10 1 2010 05 19 61 10 66 LIST OF EFFECTIVE PAGES 11 1 2010 06 01 OPERATION AND INSTALLATION MANUAL EN 1366 This page is intentionallv blank Page Ill 2 61 10 66 LIST OF EFFECTIVE PAGES 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 1 0 AIRWORTHINESS LIMITATION 1 1 TBO limits and total service life For TBO limits and total service life refer to Service bulletin No 1 latest revision of Avia Propeller All valid bulletins are freely disposable at www aviapropeller com 1 2 Life limited p
19. AA WA AVIA PROPELLER OPERATION AND INSTALLATION MANUAL HYDRAULICALLY CONTROLLED VARIABLE PITCH PROPELLER CONSTANT SPEED AV 842 AV 844 AV 843 AV 803 AV 723 Document number EN 1366 ATA 61 10 66 Avia Propeller s r o Beranovych 65 666 199 00 Praha 9 Let any CZECH REPUBLIC Tel 420 29633651 1 Issue 3 Fax 420 296336519 May 19 2010 sales Qaviapropeller cz Revision June 1 2010 www aviapropeller com ATTENTION FOR OWNERS USERS AND SERVICE STAFF This installation and operation manual contains descriptions technical specifications and instructions for operation and maintenance of AV propeller tvpe series All activities associated with propellers operation and maintenance must be practises according to this manual Activities which be exceeden scope of this manual shall be practises only by manufacturer or authorized service centre CAUTION All activities contains in this manual shall be practises only by persons with commensurating qualification l Breach of the operating instructions and procedures in this manual exceeding of rated operational terms or performance limits can cause incorrect propeller function Manufacturer or authorized service centre doesn t bear anv responsibilitv for damages incurred non performance instructions or procedures stated in this manual l SERVICE BULLETINS SERVICE INSTRUCTIONS SERVICE LETTERS Product user is responsible for
20. ade mark thickness Otherwise reinstall the blade according to section Installation and operation instruction in this manual No critical cracks in the blades PU strip proper and existing If not replace within the next 2 hours after last inspection No oil leaks 6 1 1 SMA Application On the SMA application no blade shake is allowed However a blade angle play of 2 is acceptable CAUTION In case of blade shake send the propeller to an authorized service station for re adjustment 6 2 Annual 100 Hours Inspection Note Detailed inspection must be made at 100 hour intervals of operation not to exceed 12 calendar months as follows 1 Remove spinnerdome and check for cracks or damage Check front and rear spinner plates for cracks and fixing 2 Inspect outside condition of the hub and parts for cracks corrosion deterioration Check all safety means to be intact 3 Inspect blade shank and hub for oil and grease leaks 4 Check tightness of flange bolts or nuts with appropriate torque refer to section Installation 5 If de icing exist check de icers and wire harness for condition and fixing Check brushes and slip ring for abnormal wear 6 Use a clean cloth soaked in soap water to properly clean the blades from all dirts Use 10x magnifving glass to inspect the blade surface for cracks with special attention to the leading edge and face side of the blade If crack is detected or suspected or in case of any doubt re
21. anufacturing products of the best qualitv gt Quality department guarantees the highest quality level the goods being delivered to our customers Our quality system fulfilled requirements of the European Aviation Safety Agency EASA 2 Our commercial department co operate with customers from about 50 countries of the world We consider each and everv customer to be of great importance for us Our products and activities All metal aircraft propellers for piston and turboprop engines up to 2000 HP used on regional airline airplanes agricultural general aviation sport and aerobatic airplanes Licensed blade and spinner manufacturing for propellers made world famous U S company Hamilton Standard Ltd for Warbirds like the P 51 Mustang T 6 Texan etc gt High qualitv products certified in the Czech Republic USA and European Asian Australian Central and South American countries Sales and Service Centers the USA Canada Venezuela Germanv FOR MORE INFORMATION VISIT OUR WEBSITE www aviapropeller com
22. arts Life limited parts if defined are mentioned in appropriate Overhaul manual Page 1 1 61 10 66 AIRWORTHINESS LIMITATION 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 This page is intentionallv blank Page 1 2 61 10 66 AIRWORTHINESS LIMITATION 2010 05 19 OPERATION AND INSTALLATION MANUAL 2 0 2 0 1 2 1 GENERAL Statement of purpose This publication provides operation installation and line maintenance information for the Avia Propeller hvdraulicallv variable pitch propellers with single acting svstem without reversing position of the blades Propellers in this manual are designed entirelv for reciprocating engines In addition to the propeller assemblv the propeller governing svstem is addressed in this manual Installation removal operation and trouble shooting data is included in this publication However the airplane manufacturer s manuals should be used in addition to this information All informations procedures inspections and limits stated in this manual are valid to all propeller models listed on the cover of this manual unless specifically noted Definiton of component life and service Overhaul Overhaul is a periodic process and contains the following items disassembly inspection of parts reconditioning of parts reassembly The overhaul interval is based on hours of service operating time or on calendar time At such specified periods the propeller assembly should be comp
23. balance staticallv mount balance weights to forward spinner bulkhead 2 Rebalance dvnamicallv Install balance weights to rear spinner bulkhead 3 Refer to airplane flight manual Check rpm gauge for correct reading Repair or replace if necessarv Propellers with counterweights or feathering Propellers with counterweights on the blade roots use oil pressure to decrease pitch Therefore the information in chapter 8 has to be converted as a result of the changed direction of oil pressure Slow feathering If more than 10 sec are needed for full feathering there is one of the following problems sticking blades or pitch change mechanism control too long or wrong adjusted governor If no discrepancies are found during inspection readjustment of the liftrod checknut is possible Turn out lift rod only in steps of turn If the lift rod is turned too far out early feathering is possible and must be corrected Unfeathering accumulator Cause No function of accumulator Remedy 1 Increase or refill air at the accumulator 2 Repair leaking check valve of the governor Remark The air pressure in the unfeathering accumulator should be 125 psi with the blades in the start lock position low pitch position Page 8 4 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 9 0 SHIPPING AND STORAGE 9 1 For anv shipment of the propeller use original container If this is impossible it will be verv important to fix the propeller at
24. de socket Blades Visually inspect the blade retention radius for evidence of damage or premature wear This requires removal of the bearing races 6 3 4 Overhaul When an overhaul is the corrective action for an overspeed or an overtorque the Propeller must be overhauled in accordance with the appropriate overhaul manual 6 3 5 Scrap When the corrective action requires scrapping the propeller the propeller must be removed from service 61 10 66 INSPECTIONS 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 7 0 MAINTENANCE 7 1 There are no frequent maintenance works required on the hub because all moving parts are inside the hub and not exposed to the environment Blade bearings and pitch change mechanism are filled with special lubricants and there is no need to refill between overhauls A corrosion protection of the hub with thinned engine oil or anticorrosion sprav is recommended 7 2 Repair of spinner parts is not permissible Cracked spinner domes filler plates and backplates are to be replaced bv airworthv parts 7 3 In case of a ground strike with Aluminum blades refer to Blades Overhaul Manual for evaluation 7 4 DVNAMIC BALANCE 7 4 1 Overview 7 4 1 1 Dynamic balance is accomplished by using an accurate means of measuring the amount and location of the dvnamic imbalance After such a undertake the remaining imbalance should be below 0 2 ips 7 4 1 2 Follow the instructions from the equipmen
25. design The front spinner support is used to have the balance weights installed if applied Balance weights can be also installed on the spinner bulkhead 4 2 Propeller blades Propeller blades are made from aluminium alloy They are turning in the ball bearings with one or two sets of balls in the propeller hub Connection with the pitch change mechanism is make through plastic pitch change blocks installed on the pins in the blade shanks non threaded blades or on the blade bushings faces threaded blades Propeller blades can be designed with counterweights installed on the blade shank Leading edges of the blades can be protected with polvurethane guards for mechanical damages prevention 4 3 Counterweights Propellers may by equipped with counterweights on the blade shanks or as the part of the hub If governor supplied oil is lost during operation force from counterweights move the blades to high pitch and feather if applied to prevent propeller overspeed Page 4 1 61 10 66 DESIGN AND OPERATION INFORMATION 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 4 4 Spinner The spinnerdome is made from fiber reinforced composite or spinformed aluminum allov The bulkhead is spinformed or truncated aluminium allov If spinnerdome has stiffener no integrated then the front support is installed as part of the hub Filler plates increase the stiffness of the dome on the cutouts for the blades The dome is mounted on the supports bv m
26. e hub is made from forged or milled aluminum alloy with the outer surface shot peened and anodized Propellers with non threaded blades The blade bearings are special designed ball bearings whereas the balls act as split retainers in order to hold the blades in the hub creating an increased safety factor against blade loss The outer bearing race is a one piece part and pressed into the hub while the inner race is split and installed on the blade ferrule or blade root The blade preload is adjusted by the thickness of plastic shims Blade and bearing are held in the hub by a retention ring Propellers with threaded blades The inner bearing race is located on the blade bushing whereas the blade are screwed into the bushing and tightened by the clamp The outer bearing race is a one piece part and pressed into the hub The blade preload is adjusted by the prestressing nut which holds the blade bearing and blade in the hub The pitch change of the blades is obtained with a pin in the blade root or in the blade bushing face A plastic block connects the blade with the piston and the axial movement of the servo piston turns the blades On the front piston the return spring and the sleeve which acts as high low pitch stop are installed Outside the hub are two check nuts with which the low high pitch stop can be adjusted The inner part of the hub is used as the cylinder for the pressure oil This arrangement allows a simple and lightweight
27. e into consideration and must avoid any possibility of interfering with the adjacent airframe deice and engine components In case no spinner is installed mount balance weights in the mounting threads in the hub where normally the spinner bulkhead is mounted 7 4 3 PLACEMENT OF BALANCE WEIGHTS FOR DYNAMIC BALANCE 7 4 3 1 The preferred method of attachment of dynamic balance weights is to add the weights to the rear spinner bulkhead The static balancing weights are installed on the spinner front plate if applicable 7 4 3 2 Subsequent removal of the dynamic balance weights if they exist will return the propeller to its original static balance condition The static balance weights are only allowed to remove exceptionally 7 4 3 3 Use only stainless or plated steel washers as dynamic balance weights on the spinner bulkhead 7 4 3 4 Do not exceed maximum weight per location of 32 g This is approximately equal to eight AN970 style washers 7 4 3 5 Weights are to be installed using aircraft quality 10 32 inch screws of bolts 7 4 3 6 Balance weight screws attached to the spinner bulkheads must protrude through the self locking nuts a minimum of one thread and a maximum of four threads 7 4 3 7 All propellers which have been dynamically balanced must install a decal on blade no 1 This will alert repair station personnel that the existing balance weight configuration may not be correct for static balance 7 4 3 8 Record numbe
28. eans of screws 4 5 Propeller Governor The necessarv servo pressure of the engine oil is reached bv a gear pump in the governor which increases the oil pressure Flyweight and a speeder spring move a pilot valve allowing servo oil flow to and from the piston in the propeller In on speed condition there is no oil flow A speed adjusting lever changes the preload of the speeder spring This results into an engine speed change The following pictures are showing the svstem Please note that the propeller has a single acting svstem where the natural twisting forces of the blades alwavs turn them into low pitch position The governor produces oil pressure to increase pitch Blades having counterweights installed for aerobatic aircraft or twin engine aircraft always turn them into high pitch position and use oil pressure to decrease pitch The relief valve pressure should be set between 270 and 340 psi 4 5 1 Propeller Governor with FADEC For the propellers installed on the TAE engine the propeller control contains the following A gear pump and a magnetic valve allowing servo oil flow to and from the piston in the propeller The maximum governor pressure is between 270 and 340 psi The electronic RPM control is a FADEC system and designed according to DO 1788 Level The FADEC system is tested according to test CAT W and a HIRF test CAT equivalent to critically level hazardous The governor designation is CSU TAE 125 TAE No 02
29. eathering at about 1500 propeller rpm The control must be pulled over a safety stop for unintended feathering Before the engine is restarted in the air move the lever to a low cruise rpm setting in order to avoid overspeed due to windmilling During approach after speed and power is reduced accordingly the propeller lever must be adjusted for take off max rpm in order to have full climb power in case of a missed approach For Motorgliders additionallv refer to the given procedures in the original POH 5 23 Propeller De lcing Check ammeter reading after switching on the electrical propeller de ice system With running propeller no time limit for on is required With non running engine the max switch on time of the de icing system is only 60 sec Otherwise overheating will occur Page 5 5 61 10 66 INSTALLATION AND OPERATION INSTRUCTION 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 6 0 INSPECTIONS 6 1 Dailv Inspection Before each flight inspect the condition of the blades and spinner Manuallv bv hand check the blades for the shake Refer to section Annual 100 Hours Inspection for the blade plav limits if abnormal shake is noticeable or suspected Models with threaded blades only Check correct installation of the blades in the bushings Verifv that the position line on the blade shank coincide with the line on the blade bushing face Maximum tolerance for blade and bushing mark straightness is one half of the bl
30. en or sticking pilot valve 2 Dirt in the fuel system or carburetor 3 Control inoperative Remedy 1 Check governor on the test bench 2 Clean or repair 3 Check free movement and positive stop contact Attention If the cause cannot be found in the fuel system the flight can be continued when throttle setting is reduced avoiding excessive manifold pressure and overheating of the engine The rpm will remain low because the propeller pitch is on the high pitch stop 8 8 Extremely slow pitch change or no pitch change on ground rpm changes with airspeed like a fixed pitch propeller Cause 1 Blocked oil line 2 Sludge deposit in propeller piston 3 Damaged pitch change mechanism 4 Corrosion in the blade bearings Remedy 1 Check engine 2 Clean propeller and crankshaft Concerning 1 and 2 This behavior does not appear at once and gets worse after some time It should be observed at the preflight inspection 3 Contact manufacturer This error may appear suddenly 4 Repair propeller 61 10 66 TROUBLESHOOTING Pagesa 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 8 9 8 10 8 11 8 12 8 13 61 10 66 TROUBLESHOOTING Oil leakage visible outside or hidden inside Cause Damaged gasket Remedv Replace gaskets or repair propeller Rough running engine possibly in limited rpm range only Cause 1 Bad static balance 2 Bad dvnamic balance 3 Operation in restricted rpm range Remedv 1 Re
31. ge Cause 1 Oilis cold 2 Excessive friction Remedy 1 Run the engine until the green arc of the oil temperature is reached 2 Move blades by turning them with hands within the angular play If excessive friction exists the blade retention svstem has to be inspected contact factorv Surging rpm Cause 1 Trapped air in propeller piston 2 Sludge deposit 3 Wrong speeder spring in the governor 4 Wrong pitch stops in the propeller 5 Abrupt movement of propeller or throttle control 6 Wrong carburetor setting 7 Oscillating tachometer Remedy 1 Move propeller control at least twice every time before flying at about 1800 rpm with a drop of about 500 rpm 2 Clean oil tubes in the motor in the propeller piston and eventually in the governor only possible at the manufacturer s 3 Check that the governor part number corresponds to the aircraft data sheet If the rpm does not stabilize after 5 periods this is an indication for a wrong speeder spring contact factory Compare pitch values to those of the data sheet Note static rotational speed Move the controls carefully and slowly Correct as specified in the engine manual Check tachometer and drive NO I A Rpm variations between ascend cruise and descend although having identical propeller setting Up to 50 rpm normal condition If more Cause 1 Excessive friction in the hub 2 Excessive friction in the governor 3 Worn rpm tachometer Remedy
32. ghtness Check all safety means to be intact Check flange bolts or stopnuts for tightness Check front and rear spinner plate for cracks and fixing Inspect blade root and hub for oil and grease leaks Check position of counterweights if applicable Check electric de ice boots and wire harness for con nection and condition Check brushes and slip ring for condition 6 2 2 Check blades for nicks gouges and scratches on blade surface or on the leading or trailing edges of the blade they must be removed before flight Field repair of small nicks and scratches may be performed by qualified personnel in accordance with FAA Advisory Circular 43 13 1A as well as the procedures specified below 6 2 3 Repair of Nicks or Gouges on blades Local repairs may be made using files electrical or air powered equipment Emery cloth scotch brite and crocus cloth are to be used for final finishing Page 6 2 61 10 66 INSPECTIONS OPERATION AND INSTALLATION MANUAL EN 1366 22 depth of nick Looking at 21 2 D x or gouge leading edge Example 1 Example 2 Example 3 WARNING Blades which have been shot peened as indicated bv a peeble grain surface that have damage in the shot peened areas in excess of 0 38 mm 015 in deep on the face or camber or 6 35 mm 0 250 in on the leading or trailing edges must be removed from service and the reworked area shot peened before further flight Shot peening of an aluminum blade m
33. his chapter Page 6 3 61 10 66 INSPECTIONS 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 6 2 4 Repair of bent blades CAUTION Do not attempt to pre straighten a blade prior to deliverv to an approved propeller repair station This will cause the blade to be scrapped by the repair station Repair of a bent blade or blades is considered a major repair This tvpe of repair must be accomplished bv an approved propeller repair station and onlv within approved guidelines Painting after repair Propeller blades are painted with a durable specialized coating that is resistant to abrasion this coating becomes eroded it is necessarv to repaint the blades to provide proper corrosion and erosion protection Painting should be performed bv an authorized propeller repair staion in accordance with Avia Propeller internal specification 6 3 Overspeed Overtorque An overspeed has occurred when the propeller RPM has exceeded the maximum RPM stated in the applicable Aircraft Tvpe Certificate Data Sheet The total time at overspeed for a single event determines the corrective action that must be taken to ensure no damage to the propeller has occurred When a propeller installed on a reciprocating engine has an overspeed event refer to the Reciprocating Engine Overspeed Limits figure 6 4 to determine the corrective action to be taken a ra gt 9 Overhaul 3 5 Overspeed Inspection Nr EN a No Action necessary
34. ion for feather provision pitch change forces to increase pitch 2 Code letter for blade design and installation blank right hand tractor RD right hand pusher L left hand tractor LD left hand pusher 3 propeller diameter in cm 4 Number of blade type contains design configuration and aerodynamic data according to the certified hub blade combinations 5 Code letter for design changes small letter for changes which do not affect interchangeability of blade set capital letter for changes which restrict or exclude interchangeability of blade set 3 3 The complete propeller designation is a combination of both designations for instance AV 844 1 D C C245 407c 3 4 The hub serial No starts with the year of manufacture All records of the propeller are registered in respect to this number 3 5 The propeller for a certain aircraft engine combination is always defined according the hub blade and spinner combination For the actual blade settings depending on the aircraft model the propeller logbook must be considered 61 10 66 MODEL DESIGNATION 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 4 0 DESIGN AND OPERATION INFORMATION The variable pitch propeller consists of the following main groups Hub with blade bearings and pitch change mechanism Propeller blades Counterweights if applied Spinner Propeller Governor Propeller de icing Unfeathering accumulator 4 1 Hub The one piec
35. letely disassembled and inspected for cracks wear corrosion and other unusual or abnormal conditions As specified certain parts should be refinished and certain other parts should be replaced Overhaul is to be accomplished in accordance with the latest revision of the Overhaul Manual No EN 1367 Repair Repair is correction of minor damage caused during normal operation is done on an irregular basis as required 2 1 2 1 A repair does not include an overhaul 2 1 2 2 Amount degree and extent of damage determines whether or not a propeller can be repaired 2 1 3 without overhaul A blade damage due to a ground strike always requires an overhaul Component Life Component life is expressed in terms of total hours of service TSN Time Since New and in terms of hours of service since overhaul TSO or Time Since Overhaul Both references are necessary in defining the life of the component Occasionally a part may be life limited which means that it must be replaced after a specified period of use Life limited parts are listed in Overhaul Manual No EN 1367 Overhaul returns the component or assembly to zero hours TSO Time Since Overhaul but not to zero hours TT Total Time 61 10 66 GENERAL Page 2 1 2010 06 01 EN 1366 OPERATION AND INSTALLATION MANUAL EN 1366 2 2 0 The pitch change is conducted bv a propeller governor Once an engine rotational speed is selected it will be held constant at variations of
36. move the propeller from service and contact Avia Propeller 3 Check the blade play according to blade play limits see figure 6 1 Radial play pitch change 0 5 degree 1 degree total measured at reference station Blade end play 1 5mm 0 06inch Fore and aft play 1 5mm 0 06inch In and out play 0 8mm 0 032inch Page 6 1 61 10 66 INSPECTIONS 2010 06 01 OPERATION AND INSTALLATION MANUAL EN 1366 NN BLADE END PLAY Figure 6 1 Figure 6 2 8 Check the blade track as follows see figure 6 2 Place a fixed reference point beneath the propeller within 5 mm 0 2 inch of the lowest point of the propeller arc Rotate the propeller manually in the direction of normal rotation until a blade points directly at the paper Mark the position of the blade tip in relation to the paper Repeat this procedure with remaining blades Tracking tolerance is 1 5 mm 0 06 inch 3 mm 0 12 inch total NOTE Abnormal blade track can be caused by dirts between the propeller and engine flange If no foreign matter is detected contact Avia Propeller 6 2 1 1 SMA Application Remove spinner and check for cracks Check blade shake Note Blade shake is not allowed Check blade angle play max 2 If the check shows values above these tolerances contact the service department of Avia Propeller Inspect outside condition of the hub and parts for cracks corrosion deterioration Inspect check nut for low pitch stop for ti
37. pinner because otherwise the de icing wiring will be damaged Before running the engine the ground must be cleaned to avoid stone nicks on propeller blade and the de icers 5 14 Carry out a functional check NOTE Engine and propeller manufacturers recommend not to use high engine speed on ground because it can result in an excessive engine temperature and blade damage Adjust power lever for approx 1700 rpm Pull propeller lever back out until the rom drops by 300 500 Push propeller lever full forward in for take off position and observe rpm increase Page 5 3 61 10 66 INSTALLATION AND OPERATION INSTRUCTION 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 Decrease and increase of engine speed should have about the same time Cvcle three times to bleed air out of the svstem If A TAE 125 engine is installed the functional check of the CSU must be carried out according to the CSUM 02 01 5 15 Adjust power lever at approx 2200 rpm now Pull propeller lever back until rpm drops about 100 rpm When the rpm is stabilized increase manifold pressure by about 3 inhg and observe the governor function rpm must stabilize 5 16 Watch for a clean ground surface to avoid blade damage and advance power lever and propeller lever for take off power and rpm The static rpm must be limited by the propeller and should be 50 100 rpm lower than max rpm See chapter Trouble shooting to check if the propeller or governor limits the r
38. pm If A TAE 125 engine is installed the functional check of the CSU must be carried out according to the CSUM 02 01 5 17 Low and high pitch stops are adjusted during manufacture according to the requirement of the aircraft engine combination Low pitch stop can be adjusted by varying the check nuts High pitch can only be adjusted in a service station For propellers with counterweight it is converselv 5 17 1 Check function of the unfeathering akku at propeller C F For this select app 1400 rpm with the throttle pull propeller lever into feathering position Stop engine with with propeller blades in feathering position Wait a few minutes Push the propeller lever full forward and the propeller blades must move into the start lock do that without a running engine Refer to page 14 5 17 2 CSU TAE 125 Required adjustments are carried out by the manufacturer according to the requirements of the aircraft engine combination 5 18 After the ground runs check for oil leaks blade shake and condition of the de ice svstem 5 19 Perform a test flight 5 20 Operation Propeller and governor are selected as a result of tests The governor must allow constant speed On take off the static rpm should be approx 50 100 rpm lower than max rpm and the propeller must limit this rpm If the governor limits rpm it must be readjusted During the take off run the rpm must increase with airspeed and the governor must limit max rpm
39. r and location of dynamic balance weights and static balance weights if they have been reconfigured in the Propeller Logbook 61 10 66 MAINTENANCE NIME 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 8 0 TROUBLESHOOTING Attention TAE 125 Triebwerk In case of trouble shooting the CSUM 02 01 must be used 8 1 Improper rpm There are means on propeller and governor to adjust pitch and rpm in the field Before the original adjustments are changed please calibrate the tachometer Usually there are only two kinds of problems static rpm is too low and or rpm in flight is too high 8 1 1 Static rpm too low To find out whether the governor or the propeller limit the engine proceed as follows Propeller control to max rpm Power lever to max power Pull propeller control back until rpm drops approx 25 rpm f there is a long way necessary to get the rpm drop the pitch of the propeller will limit the static engine rotational speed Remedy Reduce pitch with the check nuts on the piston guide Turning loose nut by turn will increase rpm by approx 100 rpm This is only applicable for non counter weighted propellers Low pitch of counterweighted or feathering propellers can be changed only by opening of the pitch change mechanism in the factory The checknuts will change coarse pitch only If the rpm drops immediately after a small movement of the lever the governor will limit the static rotational
40. rical propeller deicing may be used optionally Complete Goodrich kits have to be installed according to Manual 30 60 02 Complete McCauley kits have to be installed according to Manual 830415 Observe the limitations during ground operation in order to avoid damage of the de icers overheating 5 4 Clean engine and propeller flange with solvent of gasoline Both surfaces must be dry and clean Remove all surface defects 5 5 Check position of o ring in propeller flange WARNING Use only original o ring delivered by manufacturer 5 6 Depending on spinner design install backplate on crankshaft or on propeller hub 5 7 Install the propeller carefully to the crankshaft Observe the position of the spinner backplate for the blade position If the design does not permit installing the flange bolts after the propeller has been fixed on the crankshaft please observe that the propeller should not be pulled onto the crankshaft with the bolts in order to avoid damage to the hub and to avoid shearing off material causing oil leaks on the o ring Page 5 1 61 10 66 INSTALLATION AND OPERATION INSTRUCTION 2010 05 19 OPERATION AND INSTALLATION MANUAL EN 1366 CAUTION Make sure that complete and true surface contact is established between the propeller hub flange and the engine flange 5 8 Mounting bolts or stop nuts with washers should be tightened crosswise with equal force If flange bolts installed with castle nuts in the hub recesses flange
41. t manufacturers for dvnamic balance 7 4 1 3 If the dynamic imbalance is bigger than 1 2 ips the propeller must be removed and staticallv rebalanced 7 4 2 INSPECTION PROCEDURES PRIOR TO BALANCING 7 4 2 1 Visually inspect the propeller assembly after it has been reinstalled on the aircraft prior to dynamic balancing NOTE The first run up of a new or overhauled propeller assembly may leave grease on the blades and inner surface of the spinner dome This is normal and do not mean that it will be a continuing grease leakage Use a mild solvent to completely remove any grease on the blades or inner surface of the spinner dome 7 4 2 2 Prior to dynamic balance record the number and location of all balance weights from the static balance 7 4 2 3 It is recommended that placement of balance weights on aluminum spinner bulkheads which have not been previously drilled be placed in a radial location 7 4 2 4 The radial location should be outboard of the slip ring and inboard of the bend at which point the bulkhead creates a flange to attach the spinner dome Page 7 1 61 10 66 MAINTENANCE 2010 05 19 OPERATION AND INSTALLATION MANUAL 7 4 2 5 7 4 2 6 7 4 2 7 EN 1366 Drilling holes for use with the AN3 type bolts with self locking nuts is acceptable NOTE Chadwick Helmuth Manual AW 9511 2 The Smooth Propeller specifies several generic bulkhead rework procedures All hole balance weight locations must tak
42. the blades and the hub if necessarv in a manner that avoids damage In case of returning the propeller it is furthermore recommended to return all accessories and parts together with the propeller Thev will also be inspected and not considered to be missing 9 2 f the propeller is stored for a longer period of time preferably use the original container or equivalent one Storage only in a controlled environment temperature 5 F to 95 F rel humidity 10 to 75 Avoid extreme temperature humiditv differences or cycles All metal surfaces should have anti corrosion protection which is easy to remove There is no need to protect the blades because its lacquer is sufficient 9 3 The TBO starts immediately after the initial installation of the propeller to the aircraft and will not be interrupted by removals later on 9 4 f the propeller is stored for longer than 24 months it has to be dismounted before installing to the aircraft and all seals have to be replaced This will bring calendar time TBO back to zero 9 5 Long term storage could require additional preservation All standard anti corrosive preservation oils may be used if they do not affect the seals Only metal parts have to be protected 9 6 If the propeller is stored or transported in corrosive environment such as salt water or fog it is recommendable to cover the visible outside surfaces of the metal parts with a thin film of light engine oil 1n Page 9 1 61
43. tvpe B and or C safetv all mounting bolts with 0 032inch 0 8mm stainless steel wire through the tubular lock pins two bolts per safety after installation on engine Protect the safety wire with delivered protective tube to avoid hub surface damage If the propeller is installed on the engine by using the drilled hexagon flange nuts safety the nuts with 0 032inch 0 8mm stainless steel wire through the holes in the nuts two nuts per safety Torque Flange 1 2 20 UNF bolts 56 63ftlb 75 85 Nm C Flange 7 16 20 UNF bolts 41 44ftlb 55 60 Nm D Flange 1 2 20 UNF stopnuts lt 300 HP 63 66ftlb 85 90 Nm D Flange 1 2 20 UNF stopnuts 2 300 HP 80 85ftlb 110 115 Nm K Flange 9 16 18 UNF stopnuts 100 110 6 135 150 Nm K Flange Vak 18T only 70 81 ftlb 95 110 Nm NOTE Torque values are valid for dry free moving threads only 5 9 If the propeller has threaded blades separated from the hub install them into the hub as follows Before the blades installation check the inner surface of the blade bushings for damage or corrosion and clean it from all dirts Inner surface of the bushing and the blade shank must be clean and dry before blade installation Install the o rings delivered by manufacturer into grooves on the blade shanks if they are not already installed see Figure 5 2 CAUTION It is important to install the blades into the hub in prescribed sequence Prior to mounting verify that the blade
44. ust be accomplished bv an FAA approved repair facilitv in accordance with Avia Propeller Overhaul Manual for metal blades WARNING Rework which involves cold working the metal resulting in concealment of a damaged area is not acceptable A stress concentration mav exist which can result in a blade failure Repairs to the leading or trailing edge are to be accomplished bv removing material from the bottom of the damaged area Remove material from this point out to both sides of the damage providing a smooth blended depression which maintains the original airfoil general shape Repairs to the blade thrust or camber should be made in the same manner as above Repairs that form a continuous line across the blade section chordwise blade leading to trailing edge are unacceptable The area of repair should be determined as follows Leading and trailing edge damage Depth of nick x 10 Face and camber Depth of nick x 20 NOTE Leading edge includes the first 10 of chord from the leading edge The trailing edge consits of the last 20 of chord adjacent to the trailing edge After filing or sanding of the damaged area the area must then be polished first with emerv cloth and finallv with crocus cloth to remove anv traces of filing Inspect the repaired area to prevent corrosion Properlv applv chemical conversion coating and approved paint to the repaired area before returning the blade to service Refer to painting after repair in t
Download Pdf Manuals
Related Search