,-sVICE - Univair Aircraft Corporation
Contents
1. ZEPAIZ ED WIDTH EKEDPAIICED es WAS TS AID WAS 603 5 060 Il d52 lw SOO UNIVERSAL AIR SRAFT INDUSTRIES E ER das I gf ENGINEERING ORDER 1 ENGINEERING RELEASE NewDwe 0 Dwg Rev et Rew No SER VICE MANUAL Fol PEeoPE KLEE ep E Ww 256 SES 1 055 SOD e tad 5 440 que v wr 750 VE 7 E IO LEGEM oo T5255 7 51 Maas E CHANGE REQUEST BY r 3 DISTRIBUTION Ie HER TRAST ION REF REIT DW SANE ry SE SHOP ERN AN FEF PURCHASIN n euer eee um mE REASON FOR CHANGE WIRE e D deside LO Mey mcr EFE RD Sh TALL EAS TIC D Inspection In addition to the methods discussed in CAM 18 another satisfactory method for detecting cracks in blades is as follows 1 Clean the blade carefully with carbon tetrachloride and dry thoroughly using a clean air blast if necessary 2 Prepare a solution of 50 non toxic non corrosive oil which has fluorescent quality and 50 kerosene 3 Completely immerse the blade in the solution and allow it to remain for a minimum of thirty minutes After this period remove the blade from the bath and allow the ex2. vouUnv 6g p FERO NOZNLLVeOduOOo LGJvesurv SrvAINnDn EEE ELE OEEC ELE OEE OE dE 0 RTT ge g3A0Hddv U 14 WiHlO 26 oie 022V MOLLOAASNI i usmoisno ONIS HOUNd NOILASI LSIC TiVd ANVN dOHS NIMYYQ ns X a 3ONVHO HOJ NOSVHH tap E js di ESE GEZ cop MERE Srp e s to S VSL py ert TE X OL2 S zrg OGL 2x Ore s 991 SUE Sco OZE S 15 OOS 71 290 5 090 5 15 WV 51 SUM MOM 57 SSS v 2 H4 OVA WNAWINIW HLOIM Q32 1Ud32 WN Winky Sm0770 4 SY 2 SINT TNN RIOS A v BIGd Ne a Lola ONIMV GALY OON ONIMVUG OL I4HOV LLV dH 01 48 sLvad 9 4H EY N21IS HON Tbt EE cen 4 3 AA Luis LON 13 p o 1590 1 WS add 1 4 221 295 ON ha AI aay mG ISAT SNIH33NIDN3 0 ON 20007 zi S3IHISQONI L2v3ONIV sc E dou N 4 UU ORE di ALNOA
3. lS TEE i 4 p T i HRS i LT i TAARA 1 ci c gu un L E EATER B LAUD OWOL 6SE O1 X02 E aan 1 BIES ub i Li E H i ti EZ tut TEEEH LT El 8081 H d H mu 4 ud HEJE GI a HE pu THERE Lu id HH ek tH FH mam it tt pita LES a ttt tit tt T ed FH EH LB z 4 Li LH imis mE EHE Li Id Ep m L 5 LI ama T t LL 7 1 559 Hs d d d i gt pe P HT H i i E tj 1 i Hn Ben HHHH wwamsovw COD BISSA 9 13440733 3 Md M Wu eie oA T NEE 2 Sae x SERVICE MANUAL Model F1 Fixed Pitch Propellers INTRODUCTION This manual contains routine inspection maintenance overhaul and minor repair procedures which can be accomplished by propeller servicing facilities These instructions are intended to supplement the criteria set forth in Civil Air Regulations Part 18 and Civil Aeronautics Manual 18 In no case are they to be construed or interpreted overriding or contradictory to the material in the regulations o
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5. of the primary coat Use benzol carbon tetrachloride or some other suitable organic solvent Use same care when applying second topcoat that preceding topcoat has not become soiled 2 The flat face of the blade will receive a three coat application one primary coat and two topcoats the camber face of the blade using any suitable method September 26 1962 27 3 The primer shall be zinc chromate thinned with toluol Apply it evenly over the surface of blade avoiding a heavy coat Allow to dry for at least 30 minutes at room temperature in a dust free atmosphere I Balancing Following any appreciable blade repair the propeller must be balanced The suspension type balancer is recommended because of the direct indication of the direction in which the propeller is out of balance no delicately adjusted balance ways are necessary and because of its ease of interpretation Small amounts of unbalance can be corrected by spraying an additional light coat of black paint on the flat face of the light blade Do not use heavy applications of paint for this purpose since unbalance will re occur as soon as the paint erodes away Appreciable unbalance can be corrected only by removing material This can best be accomplished by abrasive grinding and polishing and should be done only on the camber side of each blade and on the sides of the hub Metal removed must be held within the limits in Table I Sideways
6. station since equipment necessary to accomplish the accuracy required is not normally available to line maintenance personnel A Propeller Installation 0 320 D2B Engine 1 Without Spinner a Rotate the engine until the TC 1 mark on the starter gear a ligns with the dot on the engine starter housing b Slide the propeller onto the engine shaft indexing it so that the blades lie approx at the 5 o clock and 11 o clock positions c Install the 6 propeller retaining bolts and washers tighten evenly and torque to 300 inch pounds d Secure the bolts with safety wire September 26 1962 4 2 With Beech 169 910030 Spinner Assy a Rotate the engine until the TC 1 mark on the starter gear aligns with the dot on the engine starter housing b Slide the spinner rear bulkhead onto the engine shaft indexing it so that the tabs which have the corners cut off lie approx at the 6 o clock and the 12 o clock positions c Slide the propeller onto the engine shaft indexing it so that the blades lie approx at the 5 o clock and 11 o clock positions d Insert the 6 propeller retaining bolts and washers into the holes in the spinner front bulkhead and slide the assembly onto the propeller aligning the bulkhead cutouts with the blades Tighten the bolts evenly and torque to 300 inch pounds e Secure the bolts with safety wire f Slide the spinner dome onto the bulkheads and install the 10 retaining screws and w
7. Pitch Range 50 in to 70 in Weight 30 5 1b B Installations Propeller Propeller Diameter Aircraft Engine Rating Model Max Min Beech Lycoming 160 HP 1 7660 2 74 74 Musketeer 23 0 320 28 2700 RPM SECTION II SERVICE TOOLS AND EQUIPMENT No special tools are required for maintenance and overhaul of these propellers Standard equipment necessary is Propeller Assembly Table Suspension Type Propeller Balancer September 26 1962 dac SECTION III PERIODIC INSPECTION NATURE OF INSPECTION INSPECTION TIME Security of mounting and mounting Postflight bolts safetied Minor nicks scratches and cracks Postflight CAUTION Due to the high stresses to which the propeller blades are subjected their careful maintenance is vitally important particularly on the leading edge of each blade from the tip inboard for approximately 8 inches 11 nicks and scratches must be repaired before the airplane is flown Nicks and scratches set up concentrations of stress which can exceed the strength of the blade material the result will be a crack and pre mature failure of the blade Corrosion cracks nicks and 30 hours dents beyond permissible limits Overhaul At engine overhaul SECTION IV MAINTENANCE AND REPAIR In general all instructions and procedures outlined in CAM 18 for all inspection maintenance and repair should be adhered to Balancing the propeller should be performed by an FAA certificated propeller repair
8. The World s Oldest Aircraft Propeller Manufacturer ROT Pay A oC NES oni 2d s M SERVICE 72 MANUAL MODEL FIXED PITCH PROPELLER y Lo MANUFACTURING COMPANY INTERNATIONAL AIRPORT ST PETERSBURG 32 FLORIDA 1 4 4 FL dre ee 1 o 25 i4 HO 4 A ont 44 es I whe 2 ae 1d EES FR 2 E g Bek i LEN STS E 4 4 1 re i4 m i 7 e i 11 T 1 T i ib E mama IS is Ss S ee i I ur 1 0098 IT ER Lii ie 8 Be LLLI i i ERI t ien 4 i SIRE 04 1 1 VIT E i OEE ERE ET ERE EE EEE bots ERE fH i 4 4 DES ERTES SEE DS 44 1 E GEES panne zi 11 E t DRESS PS TERESETA SU T iT EET T P I it HER cas Fea ERE E EUER lt i iH t f lt E EG Ll FE i414 t4 te LLLI E S505 dE PNE A m 28 il TEESE ESES pangenan E AK E ee SEKE ETH ET LH FT tr EL E a 1 a 2m H Lr Te 4 21 En PAGE 6 du RU 2 iH uns If i L3 gt amp ow a gt Ma rs 7 i
9. ashers B Propeller Removal 0 320 D2B Engine 1 Without Spinner a Remove the 6 propeller retaining bolts and washers b Remove the propeller from the engine shaft 2 With Beech 169 910030 Spinner Assy a Remove the 10 spinner dome retaining screws and washers and remove the dome b Remove the 6 propeller retaining bolts and washers and the spinner front bulkhead c Remove the propeller and the spinner rear bulkhead from the engine shaft C Cleaning For cleaning use warm fresh water and soap unleaded gasoline or kerosene and suitable brushes or cloths After the blades have been cleaned all cleaning substances must be immediately removed Soap in any form should be removed by thoroughly rinsing with fresh water after which all steel surfaces should be dried and coated with clean engine oil Scrapers power buffers steel brushes and any other tools or substances that will scratch or otherwise mar the surface must not be used on blades In special cases where a high polish is desired a good metal aircraft polish may be used however upon completion of the polishing all traces of polish should be immediately removed In no instance shall the blades be polished with a power buffer September 26 1962 D ASR iha 8 z ange ATTACHED TO DRAWING s V zi ea INCORPORAT ED ON DRAWING E TW WES M E ils tw Sea ale Lk Se EE SS em Onl PACE S SOF SOBIECT MANUAL
10. cess fluid to drain Spray the blade with carbon tetrachloride to completely remove the remaining solution Allow the blade to stand for fifteen minutes so that the solution will bleed out of any cracks present 4 Carefully inspect the entire blade under a near ultraviolet light source The inspection must be conducted in a darkened booth or room Solution bleeding from a surface crack will show up under the light as a bright fluorescent line E Repairs Major and minor repairs only within the limitations of CAM 18 are permissible In any case do not exceed the repair limits for width or thickness as specified in Table I TABLE I BLADE REPAIR LIMITS Blade Station Distance from hub Minimum Minimum center line in Repaired Width Repaired Thickness 7 13 32 ec 2 NE d 11 3 32 5 320 77 1 100 e 16 21 32 5 440 7 2 75 74 TOO n 22 13 64 5 270 60 2 27 3 4 TSO te 443 39 33 19 64 3 740 3 27 294 237 The only acceptable methods of repairing cuts nicks cracks ete are those by which the damaged portion is removed to leave a smooth well faired surface Methods which attempt to relocate metal by cold working to cover or conceal the defect rather than remove the damage are not permissible September 26 1962 6 feci Checking Propeller Track the Shop 1 Mount it on a protractor bench mandrel 2 Place a stationary object at the tip of one of the blades and make a mark on th
11. e object where the center of the blade touches it 3 Rotate the propeller 180 degrees and repeat the above operation with this blade 4 Measure the distance between the centerlines of the two marks The allowable difference is 1 8 inch 5 If the distance is greater than 1 8 inch the propeller should be sent to an FAA certificated propeller repair station for further inspection and repair Checking Propeller Track on the Aircraft The following precedure should not be attempted unless it is known that the engine shaft is not out of line The airplane must be in a hangar where air currents will not rock it Use the following procedure 1 Place a stationary object at the tip of one of the blades and make a mark on the object where the center of the blade touches it 2 Rotate the propeller 180 degrees and repeat the above operation with this blade 3 Measure the distance between the centerlines of the two marks The allowable difference is 1 8 inch 4 the distance is greater than 1 8 inch the propeller should be sent to an FAA certificated propeller repair station for further inspection and repair Painting Carefully touch up minor paint damage due to repair operation or wear Propellers requiring complete repainting shall first be stripped of their remaining paint and then painted according to the following instructions 1 All surfaces to be painted shall be thoroughly cleaned immediately before the application
12. r manual The use of this manual by any propeller servicing facility shall not under any circumstances be interpreted or construed as an approval of the facility by Flottorp Manufacturing Company This manual revised September 26 1962 and the following addenda have been approved by the FAA FAA Approved Lat Pel lms Approval Signature Chief Engr amp Mfg Branch October 4 1962 Approval Date aqu TABLE OF CONTENTS Page SECTION I Specifications and Description 3 A General Specifications 3 B 1 11 1 3 SECTION II Service Tools and Equipment 3 SECTION III Periodic Inspection 4 SECTION IV Maintenance and Repair 4 A Propeller Installation 0 320 D2B Engine 4 B Propeller Removal 0 320 D2B Engine 5 SOLAN ING xu e cesi D INSPECTION 2 26 4 E i299 EVI T 6 F Checking Propeller Track in Shop 7 G Checking Propeller Track on the Aircraft CAE S dq Ue EY ew 7 Painting 355 Va x33 ER Wek bass 7 I Balancing TER E 8 SECTION V Parts List 9 September 26 1962 SPECIFICATIONS AND DESCRIPTION General Specifications Type Fixed Pitch Material Aluminum Alloy Engine Shaft SAE Flanged AS 127 No 2
13. unbalance can often be best corrected by removal of metal on the camber side close to the leading edge of one blade and to the trailing edge of the other blade on the heavy side It is important not to leave any abrasive scratches across the blade Always finish the polishing operation so that any abrasive marks that may remain run along the blades not across them In any case remove all deep scratches For those who have conventional balancing arbors adapter cones and parallel knife edges the procedure is identical to the preceding instructions However instead of unbalance being indicated by a disc indicator it is indicated by a tendency of the propeller to rotate toward the heavy side should be noted that the knife edges arbors and adapters must be free from all foreign matter and must be smooth and true The ways should be checked for parallelism prior to balancing the propeller September 26 1962 SECTION PARTS LIST Item No Part No Nomenclature No Req 1 1 7660 2 11 1 2 169 910030 5 Rear Spinner Bulkhead 1 3 169 910030 3 Front Spinner Bulkhead 1 4 169 910030 1 Spinner Dome 1 5 336 Bolt 6 6 AN960 616 Washer 6 7 AN525 10R8 Screw 10 8 AN960 10 Washer 10 MS20995C41 Safety Wire as req Beech Aircraft Corp Part No Flottorp Mfg Co Part No Optional Equipment 3t Figure 1 Propeller Assembly September 26 1962 9
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