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Содержание Bonanza 33 Series

Страница 1: ...ES ATP is a registered trademark of Aircraft Technical Publishers All original authorship of ATP is protected under U S and foreign copyrights and is subject to written license agreements between ATP and its Subscribers ALL RIGHTS RESERVED NO PART OF THIS PUBLICATION MAY BE REPRODUCED STORED IN A RETRIEVAL SYSTEM OR TRANSMITTED IN ANY FORM BY ANY MEANS ELECTRONIC MECHANICAL PHOTOCOPYING RECORDING ...

Страница 2: ...visions Record of Temporary Revisions List of Effective Pages 1 Introduction The Shop Manual Table of Contents Alphabetical Index Supplementary Publications 2 General Information Dimensions of Aircraft Skin Plating Diagrams Stations Diagrams Special Tools Access Openings Empennage Lubrication Power Plant Fuel System Oil System Oxygen System Approved Engine Oils Air Conditioning System Landing Gear...

Страница 3: ...yro Instrument Air Filters Ignition Propeller Suction Relief Valve Static Air and Pitot System Alternators Starters Electrical Utilization Load Chart Standby Generator System Flap System Flap Position Indicator Flap Limit Switch Alternator Troubleshooting Strobe Light Standby Generator Troubleshooting Beechcraft New Matic Autopilot Autopilot Troubleshooting Guide 4 Major Disassembly Seats Wings Wi...

Страница 4: ... Temporary Revisions Letter of Transmittal Highlights of Changes List of Effective Pages 1 Introduction The Shop Manual Table of Contents Alphabetical Index Supplementary Publications Models Serials Differences 2 General Information Servicing Dimensions of Aircraft Stations Diagrams Access Openings Skin Plating Diagrams Special Tools Empennage Lubrication Ground Handling Oil System Fuel System Lan...

Страница 5: ...stem Landing Gear Brake System Static Air and Pitot System Air Conditioning System Vacuum System Pressure System Engine Instruments Beechcraft New Matic Autopilot Autopilot Troubleshooting Guide Strobe Light Emergency Locator Transmitter Fuselage Bulkheads Cabin Entrance Door Seats Ignition Alternator Standby Generator System Starter Electrical Utilization Load Chart Troubleshooting Guides Propell...

Страница 6: ...r 5 Major Maintenance and Overhaul Main and Nose Gear Fuel Unit Flap Actuator Landing Gear Actuator Propeller Deice Boot Brake Master Cylinder 6 Electrical Wiring Diagrams Wiring Diagrams 7 Periodic Inspection Schedule 8 Accessory and Component Replacement Schedule End of Index 10 15 2003 Copyright Aircraft Technical Publishers Page 5 of 5 BC 0209 MM ...

Страница 7: ...33 SERIES SHOP IVIANUAL ...

Страница 8: ... 1 Introduction I SECTION 2 General Information SECTION 3 Systems Description and Maintenc nce I SECTION 4 Maior Disassembly II SECTION 5 Major Maintenance and Overhaul I SECTION b Ele ctricalWiring Diagrams Il SECTION 7 Replacement Schedule IC SECTION 8 Periodic Inspections t COPYRIGHT m BEECH 1989 33 590011 1C17 33 590011 1C Reissued January 21 1986 Revised May 22 1989 ...

Страница 9: ...Published By Commercial Publications BEECH AIRCRAFT CORPORATION Wichita Kansas 67201 U S A of G HA 1L Aubtion I Mcociation ...

Страница 10: ...RECORD OF REVISIONS MFG REV NO DESCRIPTION ISSUEDATE ATPREVDA INSERTED BY C17 See List of Effective Pages 5 22 89 2 23 98 ATP MB ...

Страница 11: ...RECORD OF TEMPORARY REVISIONS P ATP REV INSERT DATE REV REMOVE REV NO DESCRIPTION ISSUE DATE DATE BY REMOVED INCOR BY 4 2 Sec 4 pg 4 16 11 15 93 2 23 98 ATP MB ...

Страница 12: ...May 31 85 1 11 thru 1 12A 015 May 31 85 3 4A thru 3 40 C15 May 31 85 1 13 02 Jan 30 74 3 5 C8 Mar 8 77 2 1 Orig 3 6 013 Feb 18 83 2 2 013 Feb 18 83 3 6A and 3 68 CX10 Nov 3970 2 2A 02 Jan 30 74 3 7 CX10 Nov 1970 2 28 thru 2 20 013 Feb 18 87 3 8 C 11 Aug 1971 2 4 02 Jan 30 7P 3 8A thru 3 8H C1S Sep 18 87 2 3A Ori 3 9 02 Jan 30 74 2 5 and 2 6 Orig 3 10 and 3 10A C 10 Nov 1970 2 6A 014 Jun 20 83 3 10...

Страница 13: ...ru 6 28 0 7 Dec 1969 6 700 07 Nov 30 76 6 3 06 Oct 17 75 6 70E thru 6 70H 0 15 Dec 1972 6 4 thru 6 13 0 7 Dec 1969 6 701 07 Nov 30 75 6 14 thru 6 16 07 Nov 30 76 6 71 C 12 Sep 1971 6 17 0 7 Dec 1969 6 72 0 15 Dec 1972 6 18 07 Nov 30 76 6 72A 03 Feb 28 75 6 19 0 7 Dec 1969 6 728 07 Nov 30 76 6 20 thru 6 24 07 Nov 30 76 6 720 C1 Nov 1 73 6 25 0 7 Dec 1969 6 720 C3 Feb 28 75 6 26 C1 Nov 1 73 6 73 07 ...

Страница 14: ...SECTION INTRODUCTION ...

Страница 15: ...r SECTION 1 Introduction ...

Страница 16: ...rials CJ 105 thru CJ 148 Refer sources other than BEECHCRAFT to the BEECHCRAFT Bonanza Wiring Diagram even though outwardly identical Diagrams Manual P N 35 190102 9 for F33A in appearance may not have had airplane serials CE 148 CE 772 and after the required tests and and F33C ai rplane serials CJ 149 and i nspections performed may be after different in fabrication tech niques and materials and m...

Страница 17: ...ough 00 245 and 00 251 through 00 387 BEECHCRAFT 833 Serials 00 388 through 00 813 BEECHCRAFT C33 Serials CD 814 through CD 1118 BEECHCRAFT C33A Serials CE 1 through CE 179 BEECHCRAFT E33 Serials 00 1119 through CD 1234 BEECHCRAFT E33A Serials CE 180 through CE 289 BEECHCRAFT E33C Serials CJ l through 03 25 BEECHCRAFT F33 Serials 00 1235 through 00 1254 BEECHCRAFT F33A Serials CE 290 through CE 77...

Страница 18: ...cial Tools 2 7 Empennage Lubrication 2 7 Power Plant 2 8 Fuel System 2 8 Oil System _ _ 1 9 Oxygen System 1 9 Approved Engine Oils 2 t Air Conditioning System I IOA Landing Gear 2 IOB Storage 2 10D Battery 2 1OF Light Bulb Replacement Guide _ _ __ 1 10G EngineInstruments 2 1 1 Finishes 2 11 III S STEMS DESCRIPTION AND MAINTENANCE Cabin Entrance Door _3 1 Balancing Control Surfaces 3 1 Rigging Flig...

Страница 19: ...lief Valve _ 3 16 Static Air and Pitot System _ _ _ 3 16 Alternators __ 3 18X Starters j 18C Electrical Utilization Load Chart _ 3 18E Standby Generator System _ j 18H nap System 3 18I Flap Position Indicator _ _ _ _3 181 Flap Limit Switch 3 181 Alternator Troubleshooting 3 20 Strobe Light 3 20A Standby Generator Troubleshooting j ZOE BEECHCRAFT New Matic Autopilot 3 11 Autopilot Troubleshooting G...

Страница 20: ...inued Propeller Governor 4 15 Windows 4 lj Flap Motor 4 16 Elevator Trim Tab 4 L7 V MAJOR MAINTENANCE AND OVERHAUL Main and Nose Wheel _ j I Brakes I VI ELECTRICAL WIRING DIAGRAMS Wiring Diagrams 6 1 VI REPLACE VIEN1 SCHEDULE 7 1 VIII PERIODIC INSPECTIONS 8 1 C12 1 5 ...

Страница 21: ...8 Compressor Belt Removal 3 10G C Compressor Belt Tension Adjustment 2 108 3 108 Cabin Door Compressor Installation 3 101 Latch Adjustment 3 1 Compressor Removal 3 101 Latch Lubrication 3 i Condenser Installation 3 106 Removal Installation 3 1 Condenser Removal 3 100 quick Release Mechanism 3 1 Condenser Control Rigg ng 3 100 Cable and Adjustment Evaporator Filter Replacement 3 101 Static Ground 2...

Страница 22: ...uselage Skin Plating 2 4 Electric 4 20 Free Play Checking 4 20 G Rigging 3 4 Illus 3 5 Empennage Lubricat on Illus 2 7 Gear Rigging Landing Engine Gear Safety System Landing 3 12A Fuel Pump Adjustment 3 8E Generator Standby 3 18H Instruments 2 11 Troubleshooting 3 20E Starting 2 8 Governor Propeller Adjustment 3 15 Stopping 2 8 Governor Removal Installation 4 15 Timing the Magneto 3 140 Grimes Str...

Страница 23: ...stem Illus 3 14B 3 14A Landing Gear Uplock Rollers Adjustment 3 14A Lubrication 2 10B Filters 3 14C Leak Check Fuel Cells 3 8G Propeller 3 16 Light Bulb Replacement Gu de 2 10G Propeller Governor Limit Switch Adjustment Flap 3 181 Adjustment 3 16 Lubrication Empennage 1llus 2 7 Installation 4 15 Lubrication of Cabin Entrance Removal 4 15 Door Latches 3 1 Publications Supplementary 1 11 Lubrication...

Страница 24: ... 4 7 Air Conditioner 3 105 Removal Horizontal 4 7 Alternator 3 20 Installation Vertical 4 7 Autopilot 3 24 Removal Vertical 4 7 Standby Generator 3 20E Standby Generator System 3 18H Troubleshooting Guide 3 20E Starter Engine 2 8 V Starter 3 180 Starter Overhaul 3 180 Valve Suction Relief 3 16 Static Air Pitot Vendor Publications 1 11 System 3 16 Illus 3 17 Vertical Stabilizer Installation Static ...

Страница 25: ...BEECHCRAFT DEBONAIR BONANZA 33 SERIES SHOP MANUAL Wings Cont d Tip Removal 4 1 i Removal 4 2 Wing Skin Plating 2 Tip Installation 4 2 Wiring Diagrams Electrical 6 1 C16 1 10A ...

Страница 26: ...renced in this handbook are utilized during operation servicing and maintenance of the air plane VENDOR PUBLICATIONS ITEM PART NO PUBLICATION PUBLICATION NO VENDOR Alternator 1100657 Service Bulletin Test and 16 262 Delco Remy Division 1100643 Maintenance of Delcotrons Gener ll Motors Corp ALX 9409 Equipment List Service Parts List OF Al Prestolite Compan ALT 8403 and Technical Data 511 Hamilton S...

Страница 27: ...Parts List L552 1 Bendix Aviation Series Corporation Propeller BHC 92ZF Overhaul Instructions 110 Hartzell Propeller Inc 101 8447 Handbook Owner s Propeller Manual 106 Hartzell Propeller Inc PHC A3VF4 Hartzell Propeller 115 C Hartzell Propeller Inc V8433 4R Owner s Manual PHC C3YF Hartzell Propeller 115 C Hartzell Propeller Inc 1RF F8468 6R Owner s Manual or PHC C3YF IR 8468 6R BHC C2YF IBF Hartze...

Страница 28: ... with 33 40 58 Grimes Manufacturing Power Supply Illustrated Parts List Company 515 North Russell Street Urbana California Autopilot B 5 Flight Control System Ground 3952 Brittain Industries alid Flight Check Procedures P O Box 51370 Tulsa Oklahoma 74151 B 5 Automatic Flight Control 3950 Brittain Industries System Maintenance Manual P O Box 51370 Tulsa Oklahoma 74151 B 7 Flight Control System Flig...

Страница 29: ...12 Servicing Maintenance Instructions and Illustrated Parts Breakdown for the Main Wheel P N 36 8001 3 Nose Wheel P N 36 8002 1 and Brake Assembly P N 36 8001 9 1303761 New Matic B 4 Autopilot Operating Servicing instructions Beech Aircraft Corporation 130409 New Matic Autopilot Maintenance Instructions Beech Aircraft Corporation 98 35776 Maintenance Information and Illustrated Parts Breakdown for...

Страница 30: ...SECTION GENERAL INFORMATION ...

Страница 31: ...trl SECTION 2 General Information ...

Страница 32: ... ill CD 1012 AND AFTER j 0 0 IN FT 6 IN I 7 i 8 FT 3 IN _ e THRUS 100 W L 6 FT 6 5 IN 4 4 5 MIN CLEARANCE WITHTIRE AND SHOCK DEFLATED IN DIA ill ill FT 6 7 IN Figure 2 1 Dimensions of Aircraft Models 33 A33 B33 and C33 2 1 ...

Страница 33: ...32 FT 9 9 1N 26 FT 7 6 IN 8 FT 31N THRUST 100 W L 6 FT 6 5 IN jI I I J 4 40 7 5 MIN CLEARANCE WITH TIRE AND SHOCK DEFLATED 84 IN DIA 1 Figure 2 2 Aircraft oimensions C33n E33 E33A and E33C without Kit 33 4002 3 2 2 C13 ...

Страница 34: ...IN i i 32 FT 9 9 IN 26 FT 7 6 IN 8 FT 3 IN i THRUST 100 W L i 6 FT 6 5 IN 7 4 40 7 5 MIN CLEARANCE WITH TIRE AND SHOCK DEFLATED 84 IN DIA t I z if F33 6079 9 FT 6 7 IN Figure 2 2A Aircraft Dimensions F33 C2 2 2A ...

Страница 35: ...I r 1 8 FT 3 IN 6 FT 6 5 IN rr 3 60 7 5 IN MIN CLEARANCE WITH TIRE AND SHOCK DEFLATEDI 84 IN DIA V I 9 FT 6 7 1N GJJbOl l Figure 2 2B Aircraft Dimensions G33 F33C prior to CJ 52 except f6r CJ 39 without Kit 33 4002 3 and F33A prior to CE 316 2 29 Ci3 ...

Страница 36: ...8 IN r 100 W L 6 FT 7 IN i 7 5 IN MIN CLEARANCE WITH TIRE AND SHOCK D E F L A T E D F 3 50 84 IN DIA I 2 I I r33C 607 10 Figure 2 2C Aircraft Dimensions E33C with Kit 33 4002 3 and F33C with Kit 33 4002 1 or 3 C13 2 2C ...

Страница 37: ...ir 6FT 7 N OPTIONAL LI 00ACt DOOR i 3 50 7 5 IN IMIN CLEARANCE WITH TIRE AND SnOCK DEFLATEDI 80 IN DIA Ct 491 AND ArT P i 7 P 4 Figure 2 20 Aircraft Dimensions F33A CE 316 and after F33C CJ 39 CJ 52 and after without Kit 33 4002 1 2 20 C 3 ...

Страница 38: ...4 032 2 040 5 040 3 032 a 040 Figure 2 3 Ming Skin Phtfng Legend for Figure 2 4 1 020 rl 125 RoyaUte 2 020 12 018 3 016 13 020 4 032 14 020 5 020 15 020 s 020 Is 020 7 016 11 020 s 032 Is 020 9 020 19 020 to 020 20 125 ABSB O Plastic Sheet 2 3 ...

Страница 39: ...abilizer Item 9 is 032 inch on E33C aircraft serials of CJ 1 and after 1 c I 2 i I c ___ i L i 1 1 4 5 13 12 l r r C1 a 7 ___L I __ Jc V is 9 It 10 19 7 9 20 I c r I j r i L r 1 I i bL 3 I I r 1 c 5 33 36 Figure 24 Fuselage Skin Plating 33 A33 and B 33 2 4 C2 ...

Страница 40: ...3 2 I 2 2 I 2 CI h I 2 TL_ __ e j_ _______ cy V r 2 2 j C4 i Cola 4 125 Royallte 2 020 5 093 ABS 10 Plastic Sheet 242 3 032 3 325 c r I I r r i I i _ i ___ a 3 Z I ill Pv i i L c i 1 r I _L J Figure 2 5 Fuselage Skin Plating C33 C33A 2 5 ...

Страница 41: ... 257 808 J j 233 50 35 750 LB8 550 207 00 46 000 179 00 56 250 t 151 oo i i 45 00 23 81 lu 86 00 IU 80 047 j 94 094 23 881 108 261 122 150 31 1539 375 I 148 875 4 50 12125 33 Q45 49 00 41 r175 281 53 00 83 547 59 00 191 00 94 094 66 13 00 103 641 d 1Ls llt12a 5 36 188 148 875 162 563 175 281 1 191 00 Figure 2 6 Station Diagram ...

Страница 42: ...222 6 UPPER FORWARD WING BOLT WRENCH 112 inch hex for MS20010 bolts used interchangeably with NAS1JO bolts CD 1286 thru CD 1304 and CE 3n thru CE 400 except C 394 and CE 395 TS1222 3 UPPER FORWARD WING BOLT WRENCH 5 8 inch hex for NAS152 bolts used interchangeably with 131790 1 bolts CD 1305 and after CE 394 CE 395 CE 401 and after CJ S1 and after TS1171 1 50 590013 UPPER FORWARD WING BOLT TC 3UE ...

Страница 43: ... ELEVATOR TRIM TAB ACTUATOR 2 ELEVATOR TRIM TAB CABLE 3 AFT FUSELAGE ACCESS Figure 2 8 Fuselage Access Openings 1 1 SAE NO 20 EVERY 100 HOURS SAE NO 20 EVERY 100 HOURS ii i I 33601 6 Figure 2 9 Empennage Cubrication C14 2 7 ...

Страница 44: ...rom the IO 520 8A engine ai rplanes Seri al CC i and after with in that it has an improved crankshaft and 80 87 octane fuel or the next higher rat other changes related to the crankshaft ing 33 series airplanes Serial CE 1 and Engine maintenance and overhaul informa after and C3 1 and after must be ser tion may be obtained by referring to the viced with a fuel octane rating of 100LL applicable ven...

Страница 45: ...rating in the fuel cell and has a special sponge localities where there is an excessive core to retain its shape and an extra amount of sand or dust the strainers long connector assembly for the pickup of should be inspected at more frequent fuel intervals It is recommended that the fuel strainer located in the fuel selector tank The fuel system non collapsible reservoir valve be inspected and cle...

Страница 46: ... used on all engines for the first 20 to 30 aircraft equipped with 10 470 engines and an oil strainer hours of engine operation in order to promote faster ring the oil should be changed every 20 to 30 hours of engine seating and oil control operation While changing the old oil the strainer should be removed from the oil pump housing and cleaned thoroughly If sludge deposits are heavy subsequent OX...

Страница 47: ... Refining Corporation 8114 70 Quaker State AD Aviation Engine Oil Grades 20W 30 40 50 Shell Oil Company 8115 58 Aeroshell OilW 12 20 63 Aeroshell Oil W tin 4 grades Grade 120 Nominal SAE 60 Military Grade 1120 Grade 100 Nominal SAE 50 Military Grade 1100 Grade 80 Nominal SAE 40 Military Grade 1080 Grade 65 Nominal SAE 20 or 30 Military Grade 1065 Sinclair Refining Company 11 20 67 Sinclair Avoil 2...

Страница 48: ... milk by 3 5 psi appearance caused by an insufficient refrigerant level If it i e Close the shutoff valve disconnect the supply necessary to add refrigerant to a partially charged system cylinder replace the filler valve cap and slide the seat add refrigerant slowly until a satisfactory condition is ob forward to its normal position served through the sight glass f Slowly open the shutoff valve on...

Страница 49: ...system as noted in binding the strut CHARGING THE AIR CONDITIONING SYSTEM h Remove all foreign material from the exposed pis j Check area around filler plug for leaks If leaks ton of the shock strut with a cloth moistened with hydraulic exist do not over tighten the filler plug Remove the filler fluid plug as described in steps c and d and install a new O ring Secure the plug and recharge the syst...

Страница 50: ... 30 CE 301 and CJ 30 On airplane serials CD 1 58 and after CE 301 and after CJ 31 and after the main wheel tires are The static ground cable attached to the nose gear is designed 7 00 h h ply to discharge static electricity on touchdown and need not make contact with the runway as the charge will are from the cable The cable should not drag on the runway while taxiing CA UTION as this may create c...

Страница 51: ...ngines in airplanes that are flown only occasionally tend to tion against corrosion exhibit cylinder wall corrosion much more than engines that Remove top spark plug and atomize spray are flown frequently preservative oil MIL L 46002 Grade I at room tempera i Check for correct oil level and add oil if ture through upper spark plug hole of each cylinder with necessary to bring level to full mark pi...

Страница 52: ...ughly with corrosion preventive mixture h PITOT TUBE Apply a thin coating of grease MIL C 652Y Type 11 221 to 250 F Specification M1L G 10924 and install cover 4 Install protex plugs in each of the top spark i WINDSHIELD AND WINDOWS Close all win plug holes making sure that each plug is blue in color when dows and window vents and install covers over windshield installed Protect and support the sp...

Страница 53: ...opening the battery access door On airplane serials CD 388 and after a I volt 33 ampere NOTE BEECHCRAFT 1 18649 battery is located on the right side of the engine compartment just forward of the firewall Access Do not overfill the battery When the battery for servicing is obtained by raising the right engine cowl and cells are overfilled water and acid will spill on removing the battery box cover ...

Страница 54: ...Instrument Post Lights 3 7 periods when the ambient temperature is below 32 F the Instrument Wedge Lights Zh7 battery should be maintained in a fully charged state to Landing Gear Intransit Light 3 7 prevent freezing Particular attention should be given to Landing Gear Uplock Light 327 maintaining correct specific gravity of the electrolyte When Landing Light 1 Sgh water is added the battery shoul...

Страница 55: ...missible An amount greater than this maximum may NOTE cause the control to override center and lock The EGT indicator must have the thermocouple f Attach the control rod ball joint link to the arm leads removed from the back of the instrument assembly and pull the control to the full open position The after it has been pulled from the box assembly nap should open approximately 4 inches measured at...

Страница 56: ... Brown 118683 57 Turquoise 118684 7 75 Pumpkin 118684 79 Broadway Blue 118684 3 83 Sun Beige 118684 785 Sienna Gold 118684 8 7 Torch Red 118684 3 New Bronze 118684 475 Instrument Black ANAColor514 VIN YL Interior Colors Alpine Blue 118684 113 Chairman Gold 118684 479 Chairman Red 118684 481 Chairman Blue 118684 483 Olive 118684 485 Executive Brown 118684 487 Parchment 118684 489 Red Antique 118684...

Страница 57: ... 9 Turquoise 118684 11 San Mateo Wheat 118684 13 Lemon Yellow 118684 15 Saturn Gold 118684 17 Castle Tan 118684 11 Beaver Brown 118684 1 Flamingo 118684 j Huntsman Red 118683 5 Toreador Red 118hX4 27 Chianti Red 1186X4 9 Matterhorn White 118684 31 Black 118684 33 Sable Brown 118684 223 Sunshine Yellow 1 8684 23 1 YMetallic Gold I 1 8 684 2 60 Effective CD 1007 thru CD 1199 and CE 2 thru CE 248 ENA...

Страница 58: ...84 3 19 Champagne Gold 118684 3C 118684 3 3 Jubilee Gold 118684 221 Sable Brown 118684 223 18684 320 Capri Blue 118684 265 Metallic Gold 1 18684 271 Omaha Orange 118684 273 Kingston Gray 118684 299 Peacock Turquoise 118684 333 118684 407 Terrace Blue 118684 335 Sahara Tan 118684 337 118684 411 Prairie Beige 118684 339 Antique Gold 118684 341 118684 415 Beechwood 118684 345 118684 419 Embassy Red 1...

Страница 59: ... 18684 415 Beechwood 118684 345 1 8684 4 Marlin Blue 118684 34C 118h83 79 Bahama Blue 118684 351 118684 L 5 Pavonne Blue 118684 353 Jade Mist Green I 1 8684 3 59 lll h84 40j Gamma Gray 118684 4 7 11K684 51 1 Really Red 1 18684 499 18684 5 33 Vendetta Red 118684 501 118684 j75 Bristol Blue 118684 503 1186X4 577 Crater Blue 118684 505 1 18684 520 Bright Gold 118684 507 1 186 84 531 Calypso Orange 1 ...

Страница 60: ...SECTION SYSTEMS DESCRIPTION AND NIAINTENANCE ...

Страница 61: ...IE SECTION 3 System Description and Maintenance ...

Страница 62: ... tube Turn the tube to the right to the handle when the latter is pulled The cam on the lever shorten or to the left to lengthen the latch bolt until to which the handle is attached then rotates to actuate the properly adjusted then reconnect the latch tube to the link link that unlatches the upper and lower door latd es with the two attaching screws Simultaneously an actuator on each end of the q...

Страница 63: ... certified beam balance weighing device inches then calibrated in units of 01 pound or less e A straight edge ruler and spirit level M 150 x 10 0 M 1 50 inch pounds The product of W x D In BALANCING PROCEDURE this instance M is within the required static balance range and is therefore acceptable COUNTERBALANCING METHOD h The painted ailelon assembly mustbe nose heavy by 0 2 to 1 5 inch pounds The ...

Страница 64: ...A 5 I c B A O KNI EDGE STEEL TUBE WITH PIG LEAD D C1 MASKING TAPE PLACE NEAR AILERON HINGE LINE JIG MUST BE HORIZONTALLY LEVEL VIEW A A DETAIL B 36 151 lA Figure 3 1 Balancing the Aileron 04 3 2A ...

Страница 65: ... beam balance A nose heavy surface exhibits static overbalance T Tare i e spindle plus levelling blocks or shims on the scale platform Pounds CHECKING BA LA NCE EXAMPLE The elevator balance must be checked in a draft flee area with the elevator completely assembled in flying condition D is 13 5 inches R is 1 49 Ib and T 1 00 Ib All painting including stripes and touch up must be M 13 5 1 49 1 00 M...

Страница 66: ...p must be free to hang vertically M 7 6 inch pounds In this instance M is within the required static balance range and is CA UTION therefore acceptable Be certain the forward top screw on the i The complete elevator assembly painted c r elevator leading edge tip is secured after the unpainted including the control arm and the tab control elevator has been balanced rod must not be tad heavy over a ...

Страница 67: ...RWARD SCREW JIG MUST BE HORIZONTALLY LEVEL FOR UNDERBALANCE CHECK A MASKING TAPE A DETAIL B CONTAINER MASKING TAPE TO SECURE IN NEUTRAL 1 i I ELEVATOR i HINGE CLEVIS i 8 8 KNIFE EDGE I D E 55 1528 JIG MUST BE HORIZONTALLY LEVEL ACTUAL FORCE MEASUREMENT Figure 3 2 Balancing the Elevator 3 2D 04 ...

Страница 68: ...st be M 13 8 1 49 1 00 M 6 8 inch pounds completed The tab static wicks and hinge bolts must be M is within the range which is satisfactory attached The chord line must be horizontally level and the If M is not within the prescribed range refer to step II hinge line must be properly supported when the static CHECK BALANCE BY COUNTER BA LANCE moment is measured Although many different methods of ch...

Страница 69: ...nce D must be perpendicular to the M 8 1 inch pounds In this instance M is hinge line Measure D from the hinge line to the within the required static balance range and is suspension point of the cup therefore acceptable f Remove the cup contents and string then weigh them h The complete rudder assembly painted or unpainted including the control arm must not be tail heavy NOTE over a maximum of 8 4...

Страница 70: ...IFE EDGE 1 _ I CONTAINER JIG MUST BE HORIZONTALLY LEVEL II J G MUST BE HORIZONTALLY LEVEL ACTUAL FORCE MEASUREMENT STATIC OVERBALANCE NOSE HEAVY VIEW B B o l CONTAINER VIEW A A JIG MUST BE HORIZONTALLY LEVEL STATIC UNDERBALANCE TAll HEAVY 3 1 53 6 Figure 3 3 Baiancing the Rudder ss 04 ...

Страница 71: ...ll UP 06 inch off of full up stop elevator is reached on Model F33A aircraft serials CE 316 and after 17 Rig the aileron in accordance with the procedures outlined in plus 1 minus 1 pound force as 250 full UP 06 inch off of full up the Model 35 Shop Manual with the following exceptions with stop elevator is reached The gage readings at NEUTRAL the bungee springs connected rig the aileron system to...

Страница 72: ...Shop Manual under the heading ELEVATOR REMOVAL tion the elevator trim tab should move UF f Disconnect the elevator trim tab cables at the turn buckles in the aft fuselage Secure the forward elevator trim tab cables to prevent them from unwinding at the universal g Install the access panel located near the leading CAUTION edge of the horizontal stabilizer h Install the access panel located near the...

Страница 73: ...ed Anchor the plate in a vise and drill 3 to 015 clearance between the friction surfaces of the clutch holes in the plate to match the actuator mounting holes Bolt before tightening the setscrew Stake both setscrews the actuator to the plate 2 Locate a blade type screwdriver or similar tool that will fit the shaft on which the cable drum is NOTE mounted 3 Remove the handle from the screwdriver or ...

Страница 74: ...proximately b Connect the rudder hinges and bonding cable 450 rpm 4 inch drill inotor may be at gched to the screw c Install the rudder bell crank attach bolts torque to driver or similar tool 50 to 70 inch pounds 4 Secure the screwdriver in the M inch drill d Install the access doors e Connect the navigation light wires motor 5 Remove the access plate from the clutch 1 Install the tail cone housi...

Страница 75: ... UP CE 1 AND AFTER 27 110 DOWN CD 1255 AND AFTER tRIG CABLE TO LOWEST PERMISSIBLE TENSION WHEN TAE BEECHCRAFT NEW MATIC FLIGHT i O CONTROL SYSTEM IS INSTALLED F S 257 606 SERIALS CD 66 AND AFTER d ELEVATOR DOWN 21 I ELEVATOR DOWN ELEVATOR UP I A PULLEYS ADDED I CE 316 AND AFTER I a SERIALS CD 66 AND AFTER 1J ELEVATOR UP Model A33 and after S Y Model 33 I I e Z ELEVATOR DOWN ELEVATOR UP iJ3 irJ27 T...

Страница 76: ...o la I lrrr O CJ I THRU CJ 148 WITH KIT 33 4002 1 20 00 10 RIGHT OR 33 40 32 3 10 20 30 40 50 60 70 80 90 100 110 120 Ric CABLE TO LOWEST PERMISSIBLE TENSION WHEN Temperatvre OF THE BEECHCRAFT NEW MATIC FLIGHT CONTROL SYSTEM IS INSTALLED SERLALS CD 66 AND AFTER PULLEYS ADDED r CE 316 AND AFTER t 1 I I I 1 LEFT RUDDER CABLE I i I L B 1 I G I RIGHT RUDDER CABLE STOPS s 1 RUDDER PEDAL STOPS Figure 3 ...

Страница 77: ...signates the correct tension inpounds for eachtemperature reading Cable tensions are based on 590F Ambient Air Temperature TEMPERATURE CABLE TE JSION GRAPH 50 tt 11 Ti 7 40 i I i B i ii io o 10 20 90 40 50 60 70 80 90 100 110 TEMPERATURE OF rwol o TEMPERATURE CABLE TEPBION GRAPH 50 c i 40 tt t tt j t i ff i l i i i P 5 90 i a i 1 fi t g b BI E_ f ti t l ftl t i tl t to t Iltryt i ii it O 10 20 90 ...

Страница 78: ...10 ih tl i tre t i r t 1 cL I f ti iI c I i i 114 Cct Ctf t i t iiiC C I c l i i i I fttf 111 i iit i r i e e C Ctf c l ct I cl u t yriry fuil i ii i u iJI i lO 20 30 40 50 80 70 80 90 100 110 TEMPERATURE OF INTEPITIONALLY LEFT BLANK CAB Tawrcw wupn AND AFTER 50 I C crct tfir tfCtliTt C1 t l t I 1 I TI 11 i CT 1j i i i i i U rct c t i I i t i ji t 1 1 J I I t i iS tci tt ri ii s I t 40 f i I ii c ...

Страница 79: ...RATURE CABLE TEPsION GRAPH 60 t c 40 E ilrfct t t i F I ri I to r tt ii I ti lo z o so 40 50 80 70 80 90 100 110 TEMPERATURE OF zuot Figure 3 5B Effect of Temperature upon Cable Tension Issued November 1970 3 7 ...

Страница 80: ...To Fuel C 3 1 D Pressure _ E 3 RH Main Gage i A iii Effective Airplane 15 Serials prior to CI3 388 FLUSH VENT r CD 888 AFTER A Engine Pump Fuel Supply B Engine Pump Fuel Return F C LH Main Fuel Cell Return D LK Main Fuel Cell Supply 914il i 1 i l r Auxiliary I E LH Auxiliary Tank Supply Fuel Tank F RH Auxiliary Tank Supply B G RH Main Fuel Cell Supply Check H RH Main Fuel Cell Return Valve LH Main...

Страница 81: ...ll have only for each fuel cell Repeat existing fuel cells replaced with spare installations of the kit are fuel cells P N 35 380135 1 35 38013 2 unnecessary when new fuel cells 35 380135 3 and 35 380135 4 should are installed install Kit No 35 9009 S in the fuel cell 75ner top bottom root rib and spar as INSPECTION OF MAIN FUEL CELL described below and in Service FLAPPER VALVE Instructions No 036...

Страница 82: ...and the element should seat securely against the valve plate i Move the flapper element of the valve through its full travel There 2 If the flapper element binds should be no Binding and the element and or does not seat properly the upper should seat securely against the valve rear side of the flapper element may be plate binding against the valve plate 2 If the flapper element binds 3 The flapper...

Страница 83: ... 4 inches below the lower surface of the wing skin and have a grad j Connect transmitter wiring Turn ual curve forward 10 degrees from verti the power on and check the fuel gage for cal The end of the vent is scarfed at a empty reading 450 angle facing forward This ensures a positive vent pressure Any configura NOTE tion other than described herein may cre ate a negative vent pressure thus pulling...

Страница 84: ...onize wax fuel cell To avoid damage to the to metal flow tubes as a lubricant No fuel cells the fuel cellcavities other lubricant should be used MUST be clean of any debris before installing a replacement cell Fuel Cell Nipple Clamp Torques a Return the fuel cell through the Inside diameter tin Inch pounds outboard fuel cell access hole and snap inches of nipple of torque it into place Outside dia...

Страница 85: ... adjust idle mixture without Calibration should be done only first determining that idle pump with a bus voltage of 14 25 25 pressure is correct or 28 25 25 as applicable to the airplane system e Advance to full throttle and max imum rated engine RPM to check pump pres d Calibrate the fuel quantity indi sure and nozzle metered pressures or cater as follows flows 1 Ensure that the fuel tank that NO...

Страница 86: ...fuel cell The procedure for adjusting fuel c Release the reservoir allowing it systems without variable orifice to assume its original shape pumps early 10 470 engines is the same as above However all d Insert the connector assembly pressure values must be obtained into the reservoir while tilting both the with adjustment of the fuel pump reservoir and connector assembly upward relief valve only C...

Страница 87: ...idence of fuel seepage par i Check to make sure the reservoir ticularly around vents and drains is positioned properly on the bottom of the fuel cell b If there is evidence of seepage remove the access plates on the lower winq j Close all access openings used for and inspect the area between the fuel eel installing the reservoir and the wing skin for fuel seepage NOTE c Check the fuel cell nipples...

Страница 88: ...e red Fuel edges should also be replaced cells that are pliable and are not hard ened and have nipples that material cannot CAUTION be scraped off with a fingernail may be considered repairable Bladder type fuel cells on air planes which have been in service NOTE for extended periods may have become hard and brittle These Goodyear ETC 39 construction type fuel cells should be checked very fuel cel...

Страница 89: ...CHECK h VI Il P I n rs rs o ollll r111 L 1 o r o AUX m PUMP o s 1 1111111111111111111 11111 11111111113 C 111111111 II I I n L H FUEL TANK R H FUEL TANK tP 25 GAL 1 40 GAL OPT 25 GAL 1 40 GAL OPT D SELECTOR VALVE FWD TRAINER 3 DRAIN VtNT Il i oaalNO ODRIIN IXI VtNT STRAINER STRAINER CHECK CHECK VALVE VALVE SEAL I IIIIL 511111 DRAIN SFLUSH VENT FLUSH VENT VENT VENT 1360311 W cb ...

Страница 90: ... Exhaust Fuselage Bottom II thru CE 248 CJ l thru CJ 13 i 17 Fresh Air Intake Serials CE 1 thru CE 25 I 18 Overhead Fresh Air Shutoff Control Serials CE 26 I 19 Overhead Adjustable Exhaust Serials CE 26 thru I CE 248 CJ l thru CJ 13 I I 20 Individual Overhead Fresh AirOutlets 21 Overhead Fresh Air Scoop and Diffuser Valve Control Serials CE 1 thru CE 25 jl 22 Aft Cabin Heat Control 26 24 Fresh Air...

Страница 91: ...tlet 13 Fixed Exhaust Rear of Hatshelf 14 Overhead Fresh Air Outlet Optional ii 15 Fresh Air Intake I 18 Overhead Adjustable Exhaust a I 16 Fixed Exhaust L H Side of Fuselage 17 Overhead Fresh Air Shutoff Control 19 Individual Overhead Fresh Air Outlets 20 Aft Cabin Heat Control I 21 Vent Shutoff Control I 22 Fresh Air L H Wing Root i j 24 Defroster II 23 L H Forward Outlet 25 Overhead Fresh Air S...

Страница 92: ...t 13 Fixed Exhaust Rear Of Hatshelf 14 Overhead Fresh Air Outlet Optional I 15 Fresh Air Intake 16 Fixed Exhaust L H Side of Fuselage i 17 Overhead Fresh Air Shutoff Control I I I I i 18 Overhead Adjustable Exhaust 15 19 Individual Overhead Fresh Air Outlets 20 Aft Cabin Heat Control I 21 Vent Shutoff Control i j 22 Fresh Air L H WingRoot 23 L H Forward Outlet 24 Defroster 25 Overhead Fresh Air Sh...

Страница 93: ...2 Aft Cabin Outlet 13 Fixed Exhaust Rear of Hatshelf 14 Overhead Fresh Air Outlet Optional i I I I 15 Fresh Air Intake I 16 Fixed Exhaust L H Side of Fuselage I 17 Overhead Fresh Air Shutoff Control i I 18 Overhead Adjustable Exhaust 15 19 Individual Overhead Fresh Air Outlets 20 Aft Cabin Heat Control 21 Vent Shutoff Control I 22 Fresh Air L H Wing Root ji I 23 L H Forward Outlet 24 Defroster 334...

Страница 94: ...oil and or refrigerant loss occur and locked through the normally open contacts of the door flight position limit switch actuated closed when the gear is The condenser air scoop door under the airplane automati up and locked through the normally open contacts of the cally opens when the air conditioner is turned on On the door flight position limit switch actuated closed when the ground the door o...

Страница 95: ...ctions on servicing the system He should follow very carefully these instruc All precautions should be taken to prevent damage to fittings tions when performing the tasks that will maintain this sys or connections Even minute damage to a connection could tem in a proper functioning order cause it to leak Any fittings getting grease or dirt on them should be wiped clean with a cloth dampened with a...

Страница 96: ...er and Sight Glass 7 High Pressure Service Valve 8 Expansion Valve 9 Evaporator lO Low Pressure Service Valve 11 Low Pressure Limit Switch 12 Low Pressure Line 13 Louvers Air Duct 14 Air Duct I 15 Fan 16 Fan Motor 17 Condenser Actuator 18 Compressor Clutch and Pulley J 80S18 Figure 3 8D Air Condit oning System CEb02 and atter 3 10F C9 ...

Страница 97: ...R BELT TENSION ADJUSTMENT connected This is necessary to ensure max c Close the engine cowling imum moisture protection of the refrigeration system CONDENSER REMOVAL For charging the air conditioner or checking the oil see Section 1 a The condenser is located beneath the airplane nft of the main spar carry through b Remove the beacon light AIR CONDITIONING FUNCTIONAL TEST c Remove the fairing aft ...

Страница 98: ...CH SWITCH OIL AIR SEPARATOR SUCTION ERVICE VALVE I JGAGE VALVE VALVE SUCTIO J VNDE COPILO_T SSEAI I VALVE I VACUUM PUMP SERVICE VALVE HICH PRESSURE UNDER COPILOf S DISCHARGE AGE SEAT t RECflYER O DRYER b SIGHT GLASS EXPANSION UNDER COPILOT S VALVE SEAT EXPANSION VALVE I t IN OUT CONDENSER IN OUT L h CLAMPED ON EVAPORATOR OUTSIDE OF PLUMBING Jsaola Figure 3 8E Air Conditioning System Schematic 3 10...

Страница 99: ... and j Remove the bolts attaching the evaporator to the install the attaching bolts and nuts floor and remove the evaporator b Install compressor belt as noted in COMPRES SOR BELT INSTALLATION in this Section c Adjust belt tension as noted in COMPRESSOR BELT TENSION ADJUSTMENT in this Section EVAPORA TOR INSTALLA TION d Remove caps from lines and compressor and ins tall lines to the fittings on th...

Страница 100: ...arge d Compressor valves d Repair or replace inoperative 3 Excessive vibration of a Overcharged a Correct refrigerant charge unit b Air in system b Purge and recharge system c Mount or compressor bolts c Tighten loose d Drive pulley loose d Tighten 4 Noisy unit a Compressor oil level low a Add oil b Defective belt b Replace c Low refrigerant Level c Add refrigerant d Fan hitting shroud d Align and...

Страница 101: ...ive surface This can be checked visually without dis piece of plastic tubing may be pressed over the assembling the brake The minimum allowable thickness for bleeder screw the abrasive surface is 3 32 inch above the rivet The brake disc should be replaced when it s thickness measures 330 inch d Wipe brake fluid off brake cylinder e Reassemble TIRES DETEFIMINING Bf lAKE LINING WEAR REPLACEMENT OF S...

Страница 102: ...e tire b in erting the lubricated end of with a small ilmounl of cold patch rubber cement ih inflating needle into the guide hole of the valve wllh l g position the container end itnJ valve ill the lire rotary motion taking care not to lures the needle If the valve orifice place a handkerchtef or cloth over the head of needle doer not enter eslily relubricate il lnd the guide hole the lire gage to...

Страница 103: ...cy for excessive speed build up This battery Care should be taken to match procedure would also be appropriate for a non instrument pol rities rated pilot who unavoidably encounters instrument conditions or in other emergencies such as severe turbulence CAUTION Excessive oper ltion of the landing gear motor NOTE without proper cooling may cause damage to the motor Allow a short period of time for ...

Страница 104: ... time ing gear wheel well and a microswitch located adjacent to required provisions for lubrication The grease the existing throttle position warning switch in the engine fittings provided to facilitate this lubrication compartment have been removed from the present landing gear since it is equipped with prelubricated Each pressure switch is connected into the pitot and static Dress in bushings th...

Страница 105: ...usted as follows serials thereafter Airplane serials with the throttle switch set at the factory at 20 i With the airplane in flight mark the throttle con inches Hg may change to 18 inches Hg trol at the control panel when the manifold pressure setting Flight Manual Supplement P N gage registers approximately 18 inches Hg 35 364170 5 dated June 8 1965 or later should be incorporated in the airplan...

Страница 106: ...re on the left the switch closes at 90 mph on the airspeed indicator side of the tester to the normally closed connection marked on the switch Connect the red wire on the right side of the t3 Turn the master switch ON and roll up the rubber tester to the common connection on the down limit switch tubing until the airspeed indicator registers 130 mph then This is a normally closed switch and the li...

Страница 107: ... place the airplane on jacks partially obstructed or pressure loss resulting from loose con Main Gear With the gear down and locked nections These conditions may be adjust the down switch located on the checked by 1 removing the forward side of the main gear V brace so inline filter from the system and that the overtravel of the switch plunger checking it for obstructions by is 050 inch after the ...

Страница 108: ...TEST GAGE REGULATOR 1 I r l TEST GAGE AUTOPILOT MASTER TURN VALVE COORDINATOR FILTER 36603 9 Figure 3 8F Pressure System Schematic FILTER CARTRIDGE FOR REPLACEMENT ORDER P N 09 14 1 NAS43003 24 SPACER58 910021 COVER MOUNT AN315 3R NUT NUT r I IIIII AN936A1 LOCK WASHER FILTER BASE AN970 3 WASHER AN960PD1716 WASHER FILTER RETAINER NUT AND WASHER STD lsO le Figure 3 8C 1JZ 1 Intake Air Filter 3 148 O...

Страница 109: ...TERS CAUTION The pressure system has an air filter Under no circumstances should the located between the gyro instruments and reading at the pressure regulator pressure regulator This filter should be exceed 7 0 psi removed and replaced every 500 hours or sooner if conditions warrant An addi tional air filter is provided at the c Locate the adjustable orifice ambient air inlet located on the engin...

Страница 110: ...vailable for internal timing of the instrument remove the air filter body magneto cover by taking out the four fillister head machine sc rews Lift out the snap NOTE ring which holds the filter in place remove the filter and replace it with a For adjustment of contact opening new one Replace the air filter body cover and internal timing of Bendix and gasket securing them with the screws magnetos re...

Страница 111: ...ven thoughthese starter adapter with a timing engines are equipped with timing marks a mark on the alternator drive positive top dead center TDC locator and pulley as the reference point timing disc may be used to time the magneto to the engine or to check the NOTE accuracy of the engine timing marks ON 10 520 series engines the WARN ING timing marks are located on the alternator drive gear Remove...

Страница 112: ... 1 piston lightly touches the locator j Rotate the engine in the normal h Note the reading on the timing direction of rotation to the compression disc Now rotate the disc toward 00 TC stroke of number 1 cylinder and until the until 1 2 of the reading noted is shown pointer arrives at the number of degrees noted last in step h 1 2 of the first noted reading in step h 3 14F C16 ...

Страница 113: ...timing light installed on the engine and check alignment of magneto drive coupling slot and magneto q Secure the right magneto impulse coupling lugs If not aligned pull engine gear out of mesh but not out of the oil seal and r Repeat steps p and q on the left magneto turn to alignment Push geilr back into mesh s Recheck the magneto setling to confirm the i i 2 has not been exceeded n Place new gas...

Страница 114: ... and McCauley propellers do not need to be installed counterclockwise to decrease it On airplane serials CD 826 in any particular position relative to crankshaft through CD 1118 and CE I through CE 179 turn the position adjusting screw counterclockwise to increase or clockwise to decrease the suction setting McCauley Propeller Airplane Serial CD 662 and after Approved as spares on aircraft prior t...

Страница 115: ... FUEL FLOW INDICATOR AIRSPEED INDICATOR DRAIN CD 1014 AND AFTER STATIC LINE CE I AND AFTER I PITOT LINE RATE OF CLIMB INDICATOR OPTIONAL EMERGENCY STATIC AIR SOURCE I PITOT MAST AND HEAD CD 899 AND AFTER Fi gure 3 9 Pitot and Static System 3 17 ...

Страница 116: ...ad must be removed to gain access to the cap drain The cap may be removed with an 11 16 wrench to allow the drainage of any water accumulation c Secure the rolled up tubing so that it will hold the Disconnect the line at the airspeed indicator and blow this airspeed indicator reading line clear On airplanes equipped with the optional emergen d If there is no decline in the reading after several cy...

Страница 117: ...ve the electrical system inspected and repaired The precaution for servicing The alternator output is controlled by a transisterized volt the 60 ampere alternator should also be observed for the age regulator overvoltage relay Current to excite the alter maintenance of the 70 ampere alternator Complete service nator field is normally derived from the airplane bus through information will be found ...

Страница 118: ...serious damage to the wir ing harness and alternator may result from acci dental grounding NOTE The voltage regulator is set and sealed at the f Start the engine and check for oil seepage and factory Breaking the seal prior to the warranty proper operation limitations voids the warranty Once the warranty limitations have been reached and it PFIEPARA flON FOR NEWAL TERNA TOFI INSTALLA T1ON should b...

Страница 119: ... to service requires isolating the relay from the power source If an overvoltage To allow the overvoltage relay to reset all power condition occurs in flight the following procedure may be must be momentarily removed from the unit used i Momentarily move the BATTERY switch some e Recheck the adjustment models may be placarded BAT ALT switch to the OFF f Readjust the voltage regulator to 28 5 75 vo...

Страница 120: ...orn when compared to a new brush they should be replaced Make sure the brush holder CAUTION are clean and that the brushes are not binding in the holders The full brush surface should ride on the commutator to give Do not clean in any degreasing tank or with grease proper performance Check by hand to ensure that the dissolvingsolvents this will dissolve the lub brush springs are giving firm contac...

Страница 121: ...tor capacity Total continuous load consists of loads listed as continuous and the avionics receiving loads Transmit loads are intermittent loads NOTE The loads listed as continuous loads are for equipment which will be operated for periods of 15 minutes or longer However the intermittent loads and the avionics transmitting loads should beconsidered for determining possible overloading during short...

Страница 122: ...20 20 Electrothermal Prop Anti Ice 2 Blade 1 10 00 lo oo 3 Blade 1 15 00 15 00 Ammeter 1 01 01 Timer 1 10 10 Power Supply Strobe 1 5 00 5 00 LIGHTING 5th and 6th Seat Reading 30 Power Supply Strobe 1 00 5 00 Clock Control Wheel 8 Day 1 04 04 Instrument Post Light Single 26 04 1 04 Instrument Post Light Dual 37 04 1 48 Instrument Wedge Light Sing1e 14 024 34 Instrument Wedge Light Dual 16 024 38 Ma...

Страница 123: ... Relay Dynamic Brake 1 1 75 1 25 Relay Starter 1 3 30 3 30 Starter Engine 1 100 00 100 00 Relay Landing Gear Latch I OH 08 LIGHTING Alternator Out 1 04 04 Courtesy Light 2 17 34 Door Ajar 1 04 04 Landing Gear Indicator 4 04 16 Landing Light I 8 93 8 93 Condenser Door Open 1 04 04 INTERMITTENT LOADS 28 Volt Syetem Optional Equipment Actuator Elevator Trim 85 85 Resistor Trim Shunt 38 38 LIGHTING Ta...

Страница 124: ...he switch and voltmeter are located on the right side of short exists therein and to save battery power for lowering the instrument panel The switch is placarded OFF ON the flaps and gear if the problem is determined to be only a GENITEST The voltage regulator overvol age relay is faulty alternatorlgenerator After turning the swithces mounted aft of the firewall and controls the generator OFF turn...

Страница 125: ... indicated loosen the transmitter attachment bolts and adjust transmitter fore and aft or rotate slightly until the reading is correct then tighten the transmitter attaching HREE POSITION FLAPS bolts CJ 150 and alYe CE 816 and after c Run the flaps up and check the indicator for up On the three position flaps the flap travel is adjusted by flaps reading moving the limit switches The left flap is r...

Страница 126: ...the flap is in the up position and or down position and flap rollers must not A distinct change in the sound of the flap motor bottom in tracks at full up and or down position near the completion of the flap up travel may indicate an excessive outward adjustment of the bumper CAUTION g Operate the flaps through full travel to ensure that If the flaps are removed for any reason place the flaps cont...

Страница 127: ...ATOR F o A a P TRANSMITTER INDICATOR INDICATOR CD 1044 THROUGH CD 1304 CJ 150 AND AFTER CE 60 CE n THROUGH CE B1B CE 816 AND AFTER TO ADJUST LOOSEN MOUNTING CJ 1 THROUGH 01 149 BOLTS AND MOVE FORE AND AFT OR ROTATE SLIGHTLY FLAP TRANSMITTER AND INDICATOR APPROACH POSITION DOWNLIMIT SWITCH i ai a SWITCHES UPLIMIT SWITCHES SWITCH CD 1044 THROUGH CD 1304 CE 815 AND CE 60 CE 77 THROUGH CE 815 CJ 150 A...

Страница 128: ...water excessively VOLTAGE LIMITER CONTACTS BURNED 1 Shorted or grounded field coil or circuit 2 Brushed pig tail wires touching each other at times NOISY ALTERNATOR I Defective bearing 2 Shorted rectifier magnetic noise 3 L ose worn or frayed drive belts 4 Bentfan 5 Loose rear housing or improperly installed stater 6 Loose pulley not seated against bearing 7 Loose mounting bolts AMMETER POINTER OR...

Страница 129: ...areas power unit gers If the SCR does not trigger measure the voi lamp assembly or wiring A quick method of isolating tage across R7 100 ohms This voltage will be be the trouble source is to remove the lens of the xenon low 5 volts If the voltage is indicated place an lamp and test the lamp Inspect the lamp to see if it oscilloscope across R7 and look for a positive going is broken or loose in its...

Страница 130: ...J1I CR3 ER4 39 1 5 Rissn I II I 24 6150 1 C2 7 TRIO loon 300LL1 04 23 CS CRS 1 5 23 3 10 71145 2 MEOn 25pf 4 GND 71543 OR 36 C3 RS 1 5 MEO n 2511671 i 330R Iopr o 03 c4 IP1T T 37 100 n OIILICTED TO D1UST R tE 35 603 1 Figure 3 10 Bullock Power Supply Schematic Internal 3 20B Issued November 1970 ...

Страница 131: ...procedure when removing and installing the f Remove the 2 screws on the bottom of the subas power supply sembly and remove the flash tube g Reverse the preceding steps to reinstall the strobe light assembly STROBE LIGHT WIRING An incorrect hook up of the wires at either the power input or between the strobe light assemblies and the power supply unit will cause a reversal of polarity that results i...

Страница 132: ... injury from electrical shock assembly observe the precautions outlined under STROBE LIGHT WIRING in this section be fore removing or installing the strobe light as sembly STROBE LIGHTLAMP REPLACEMENT BULB NUMBER GUIDE G33 F33A Tail Strobe Light Lamp Grimes 633 G33 F33A Tail Strobe Light Flash Tube Grimes 3 1 2440 1 I F33A F33C Tail Strobe Light Flash Tube Grimes 28 volt 30 0815 1 F33A Wing Strobe...

Страница 133: ...h d Defective BAT TEST d Replace lamp lamp e Defective ON OFF TEST e Replace switch switch 2 With STBY switch to ON a Defective power relay a Replace relay and PWR XFER switch to NAV COM 1 COMM 1 NAV i Audio Amplifier Turn Co ordinator and Engine In struments are inoperative 3 With STBY switch to ON a PWR XFER switch de a Replace switch and PWR XFER switch to fective or wired in or rewire as NAV C...

Страница 134: ...relay TEST engine at 1200 RPM relay GEN TEST light illuminates dimmly but will not get b Rheostat out of b Bench set rheo brighter as engine RPM is adjustment stat or replace increased c Faulty generator c Replace generator d Faulty voltage reg d Replace faulty ulator component of regulator 6 With the STBY switch to a Faulty overvoltage a Replace relay TEST engine at 1200 RPM relay GEN TEST light ...

Страница 135: ...tem does completely non tumbling Yaw roll and turn detection not use a gyro for reference but uses the airspeed is made by a tilted gyro EVT turn coordinator rate of airspeed change and inertial signals to electrical vacuum torquing combination mounted in control the elevator through the pitch servos An the instrument panel A dampened miniature aircraft altitude hold sensing unit works in conjunct...

Страница 136: ... a YAW 1 r 5 re a a c c S C n e o C a a m r 3 O ImcDoqci C R RUDDER SERVO a a fi a 1 O 9 3 1 CONTROL VALVE c D a o c I r n p Dr a ct O W I r AIRCRAFT MASTER SW O D a S 1 PILOT DISPLAY t 2 POSITION AUTOPILOT MASTER PNEUMATIC 3 a t I m m 3 CO pr 3 5330 r PITCH CONTROL s o t o 0 S 33 a O DcCZ D 5i C 1 tr omc am m 5 3 C I O n cE j cD m o PRF SSIRE q m D O cr to a AIR SPEED 3 a 1 C1 a a m 8 ELEVA OR SE...

Страница 137: ...3 cUlaYwK a sau wum pU II I1IPLTCW LT AMPHEIOL I II 7PIN I WWEP r SENSOP No WPPLY 3 ILTHOLDVhL E u un crrr P BL O _rr _W I IPYI L CI II Ila UEIIOINB MAGNETIC r nuv Shaora g 5EN50P P1 BU iwlmo wej i Bl nx I P es m B MbSTEPV CM 6 voc 4 IfBii PCCY FLO F1 614a28 W so 256 P qr s eEDLICEP FILTEP II ypW U NT40L m Ylan a o R LY FLO VP LVE i HALE BLLLCK PUDCEe 5EP O TUeN COOPDINP M4 IPCP f QIIlKIUD PIN L F...

Страница 138: ...ELLDW 301 Nnv CEN ERING r k G HDG GRADIWT II 1 VOR GRIN IF ADJUSTED RECHECK Il I I AD3UST 1 C jl FhCTORY AD3USTS II I r 90 I I MAN CENTERING Q QUADRATUKE ADJUST ser AT 450 Figure 3 12 BEECHCRAFT New Matic B 5 and B 7 Heading Lock Navigation Coupler System Adjustment Points Issued May 1970 3 23 ...

Страница 139: ...achment or excessive friction in aileron binding etc and adjust as and or rudder cables pulleys outlined in Section 3 bell cranks or loose servo cables c Leak in servo or servo lines c Check for leaks d Obstruction in servo lines d Check for foreign matter e Faulty turn coordinator gyro e Replace turn coordinator 3 Autopilot sluggish a Low system pressure setting a Check system filters and adjust ...

Страница 140: ...magnetic heading hold magnetic headings sensor b Faulty heading selector b Replace controller amplifier resolver c Faulty controller amplifier c Replace controller amplifier 12 Magnetic headings consistently a Heading sensor misaligned in a Check for proper installation high or low aircraft b Heading azimuth dial shifted b Tighten screw and recalibrate on shaft c Improper adjustment or c Calibrate...

Страница 141: ...ators 23 Voltage output in MAN CAP a Polarization pins reversed a Reverse pins See Figure 3 11 TRK and APP mode but none in on heading sensor plug HDG mode 24 Nav indicator needle deflects a One of the components is a Check for shorts left or right when controllerl shorted to ground amplifier or radio is turned on 25 Low or high intercept angle a Incorrect setting on controllerl a Adjust intercept...

Страница 142: ...ustment amplifier b No EVT potentiometer output b Replace turn coordinator 11 System will not respond a Pitch altitude amplifier a Adjust as required to altitude gain adjustment limiter improperly set 12 Aircraft has long term a Decay rate improperly adjusted a Adjust as required oscillation a ut pitch axis with altitude hold OFF b Pitch altitude gain improperly b Adjust as required adjusted c Fri...

Страница 143: ...SECTION NIAJOR DISASSEIVIBLY ...

Страница 144: ...C SECTION Major Disassembly ...

Страница 145: ...F TEMPORARY REVISIONS REVISION DATE DATE REASON PAGE NUMBER INSERTED REMOVED REMOVED NUMBER 4 1 Dec 11 92 Nov 15 93 Temporary 4 16 Revision 4 2 4 2 Nov 15 93 4 16 NOTE Insert this Record of Temporary Revisions after the Section 4 divider tab Page 1 Nov 15 93 ...

Страница 146: ...e snap the retaining strap into position removal procedure THIRD AND FOURTH SEAT REMOVAL SEA T BACK ADJUSTMENT CD B14 and after CE 1 and after CJ I and after CD 388 and after CE 1 and after CJ l and alter a Remove the seat track stops b Engage the fore and aft adjustment lever and slide A lever located on the inboard side of each se l oper3te the seat off the tracks the seat back adjustment The se...

Страница 147: ...ean all wing attach fittings inboard landing gear doors are fully open and hardware bolts washers and nuts inspect the wing h Disconnect the inboard door actuator rod from attach fittings bolts washers and nuts as instructed under the control horn WING BOLT NUT AND FITT NG INSPECTION i Disconnect the landing gear uplock cable at the inboard connection in the wheel well j Disconnect the landing gea...

Страница 148: ...I IRM 1 FUSELAGE FITTING WING FITTING MS20002 10 WASHER CD I THRU CD 1285 CE 1 THRU CE 375 CJ 1 THRU CJ 30 L105090A032 12J WASHER CD 1 THRU CD 12BS CE 1 THRU CE 376 CJ 1 THRU CJ 301 MS20002 12 WASHER CD 1286 THRU CD 1304 CE 3n AND AFTER CJ 31 AND 1105090A032 12K CD 1286 AND AFTER CE 3f7 AFTER AND AFTER CJ 31 AND AFTER WFT 80LT TORQUE 1180 TO 1300 INCH POUNDS PRIOR TO CD 1305 CE 401 AND CJ 31 2480 ...

Страница 149: ...OLE WING FITTING MS20002 10 WASHER WET BOLT TORQUE 1180 TO 1300 INCH POUNDS COAT THE COMPLETE BOLT NUT WASHERS WING FITTING BOLT BORES AND EXPOSED BOLT THREADS WITH MIL C 16173 GRADE 2 CORROSION PREVENTIVE COMPOUND CHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS ONE OR TWO MS20002 10 WASHERS MAY BE USED AS REQUIRED BETWEEN THE NUT AND THE MS20002 10 OR THE 95 110025 7 WASHER TO PROVIDE A PROPER ...

Страница 150: ...LT HEAD A lLP 128126 NUT INTERNAL WRENCHING 131790 2 BOLT 4 MS 20002 12 1 LMS 20002 12 WASHER WASHER LZP WET BOLT TOROUE 2480 TO 2600 INCH POUNDS COAT THE COMPLETE BOLT NUT WASHER WING FITTING BOLT BORES AND EXPOSED THREADS WITH MIL C 16173 GRADE 2 CORROSION PREVENTIVE COMPOUND ONE OR TWO MS 20002 12 WASHERS MAY BE USED UNDER THE NUT TO PROVIDE BOLT GRIP ADJUSTMENT 33 3 4 Flgu 61B Lov r FomRTd WIR...

Страница 151: ...E 934 CJ 1 THRU CJ 155 WET BOLT TORQUE 1180 TO 1300 INCH POVNDS COAT THE COMPLETE BOLT NUT WASHERS WING FITTING BOLT BORES AND EXPOSED BOLT THREADS WITH MIL C 16173 GRADE 2 CORROSION PREVENTIVE COMPOUND CHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS e ONE OR TLVO MS20002 10 WASHERS MAY BE USED AS REQUIRED BETWEEN THE NUT AND THE MS20002 10 OR 95 110025 7 WASHER TO PROVIDE PROPER BOLT GRIP ADJUS...

Страница 152: ...les at the tutnbuckles e Tighten the upper forward and aft nuts j Connect the electrical wiring in the wheel well k Connect the pitot line in the wheel well LH only CAUTION I Connect the fuel lines m Connect the landing gear actuator rod When torquing the wing nuts assure that the n Connect the landing gear uplock cable wrenches do not bottom out on the wing o Connect the inboard door actuator rod...

Страница 153: ...LATION OF LEADING EDGE AND MAIN SPAR The wing must be removed from the airplane before the leading edge or main spar can be removed a Before assembling the spar to the wing sections it is advisable to drive a hinge pin through the hinge sections To remove the main spar disconnect the landing gear to remove any burrs or foreign matter b Use a new hinge pin coated liberally with MIL M 7866B molybden...

Страница 154: ...ng both wings years old or older lsee Chart I Wing bolts and The aluminum washers between the upper wing fittings nuts that are removed in compliance with the must be replaced each time the position of the wing is schedule shown in Chart I or because of changed If both wings have been removed install the right condition must be rendered unserviceable wing with the trailing edge at the highest poin...

Страница 155: ...lt binding is encountered and the wing must be shifted the outline will be helpful in returning the wing to its original position d If the bolts and nuts do not exceed the life limit shown in Chart i visually inspect each bolt and nut with a WARNING I0 power or stronger magnifying glass inspect for corrosion cracks and mechanical damage The cadmium Use only the components specified in the plating ...

Страница 156: ...ow dry do Figure 4 113 and 4 IE not wipe dry Paint the treated areas with zinc chromate j Coat the exposed threads that protrude through primer 4 Chart I and allow to dry the nut with MIL C 16173 Grade II corrosion preventive g Coat the bearing faces and bolt bores of the compound Chart 2 fittings the complete bolt washers and nut with MIL C k Check that the decal shown in Figure 4 1F is 16173 Gra...

Страница 157: ...285 or ICD 1 thru CO 1304 or 1 thN CE 376 9 16 inch Alien DE 1 thru CE400 90 590013 1 thru CJ 30 Wrench Bxceot 08 394 and 395 150 38 M 1 CJ 1 tt ru CJ 30 or 0 23 TS1222 6 for 1286 thru CD 1304 MS20010 23 only 377 thru 08 400 1 2 inch hex 08 394 and 395 52 3nM lT51222 3 t2NB126 TIS1171 2 or 1 5 8 inch hex a D 1305 and after 31790 1 trsl 222 5 E 394 CE 395 CE 401 1305 and after 1 9 16 inch hex tt ru...

Страница 158: ...ce of the leakage 1 INCH 5 INCH 6300 field denoting the discontinuity is detected by the use of finely divided ferromagnetic particles over the surface of Amperage requirement is the ampere turns value divided the part Some of the particles are mageticaily gathered and by the number of turns on the coil For example A I inch held by the leakage field to form an outline indicating the diameter x 5 i...

Страница 159: ...for corrosion accomplished in the following manner a Examine the forward and aft sides of the spar cap WARNING where it meets the skin If a whitish salt like nonmetalic substance is noted in these areas a thorough inspection All areas of the spar cap from the wing attach should be performed to determine if corrosion has fitting to the outboard end of the spar cap must occurred Wax or paint trapped...

Страница 160: ...n Prior to CD 640 except CD 62S CD 63 CD 637 and CD Disconnect the elevator tab cables from the tab actuator 638 c Disconnect the elevator push rods d Remove the bolts attaching the elevators to the a Remove back plate from brake assembly on main bracket that is mounted over the stabilizer rear spar wheel Remove guard assembly from nose landing wheel e Remove the remaining attaching bolts in the r...

Страница 161: ...earing grease Aero Shell 5 Shell Oil I b Remove the outer dust shield and hub cap from Co Houston Texas and center in the O ring groove the main wheel Place the other wheel half over it using the bolt ends as a c After removing the retaining cotter pin unscrew guide Apply a light downward force to the outer wheel the axle nut half if the wheel halves do not bottom solidly together the d Remove the...

Страница 162: ...er f Lock the wheel assembly together with the three bushing spacer may remain on the axle retaining washers and self locking nuts g Tighten the self locking nuts of the main wheel evenly tin rotation until a torque of 140 inch pounds is reached The nuts on the retaining bolts of the nose wheel MAIN WHEEL ASSEMBLY INSTALLATION must be tightened to a torque of 83 inch pounds CE 301 and after CD 125...

Страница 163: ... wheel name plate a Remove the snap ring washer felt seal washer f Clean the bearings and other components in and bearing on the right side of the wheel PD680 solvent g Replace any worn or damaged parts h Pack the bearings with 4ero Shell No grease IShell Oil Company One Shell Plaza P O Box 14C 3 Houston Texas or alternate grease MIL G 81322 too NOTE not mix these greases they are not compatible i...

Страница 164: ...AKES I fitting and drain brake fluid from brake cylinder Cap the CD 625 CD 632 CD 637 CD 638 CD 640 through plate to hold it while disconnecting the brake lines NOTE NOTE When the bottom of the brake housing is Avoid getting brake fluid or other oil on the within 1 32 inch of the landing gear torque brake linings flange lining replacement is indicated The maximum wear limit on the anvil lining is ...

Страница 165: ...ng support at the center REASSEMBLY OF CLEVELAND BRAKES a Apply a thin coat of MIL H 5606 hydraulic fluid Prior to CD 640 8XC6Pt CD 625 CD 632 CD 637 to the cylinder wall of the housing and to the contacting and CD 638 surfaces of the piston b Lubricate the piston O ring seal with MIt H 5606 hydraulic fluid prior to installing it on the piston NOTE c When installing the piston in the brake housing...

Страница 166: ...ton from the housing 18 b Remove the clevis 1 nut 2 and cotter pin II DISASSEMBLY AND REASSEMBLY OF BEECH from rod 16 this will allow the removal of rctai ning BRAKES washer 4 rod wiper 5 guide bushing 6 and O rings 7 CD 1106 through CD 1271 CE 173 through CE 300 8 from the piston rod cJ 1 through CJ 30 c Remove the piston 10 and O ring 9 from the piston rod and remove the spring washer 15 For dis...

Страница 167: ...ide Bushing 23 O Ring 7 O Ring 24 Cap End andBearing 8 O Ring 25 O Ring 9 O Ring 26 Snap Ring 10 Piston 27 Collar 11 CotterPin 28 Spacer 12 Cotter Pin Modified 29 O Ring 13 Valve Assembly 30 O Ring 14 Valve Stop 31 Piston 15 Spring Washer 32 Spring 16 Piston Rod 33 Snap Ring 17 Spring 34 Spring 18 Housing 35 Housing Figure 4 2 Brake Master Cylinders 4 14 C12 ...

Страница 168: ...e housing j Clean all parts with solvent PD 680 k Check all parts for cracks corrosion distortion c Cover the governor base and engine pad to and wear protect them d Install the governor by reversing the above procedure ASSEMBL Y NOTE a Lubricate all parts with hydraulic fluid Torque the mounting bolts per Teledyne M1L H 5606 Continental Motors Torque Chart 530321 WINDOWS NOTE WINDOW SURFACE REFIN...

Страница 169: ...o and rotate the retainer 90 e Keep inboard pressure on the retainer and tighten both retainer set screws f Secure the flap drive cable to the mounting support by tightening the nuts Tighten the inbcard nut to ensure that there is sufficient clearance between the outboard edge of the retainer and the cable housing to allow the retainer to rotate without coming into contact with the cable housing I...

Страница 170: ... The existing cover plate over the access hole Presstite 576 sealer to the windshield frame where it may be retained to cover the enlarged hole makes contact with the canopy section g Place the windshield in position and cleco in place h Using AN470AD4 rivets secure the windshield a Place the flap motor in position and secure with to the canopy section the flap motor attaching bolts Ensure that th...

Страница 171: ...operate properly the flap motor should be replaced No attempt should be made to overhaul the motor in the field ELEVATOR TRIM TAB a Place the flap motor in position and secure with the ELEVATOR TRIM TAB ACTUATOR DISASSEMBLY flap motor attaching bolts CE 1 thru CE 616 CE 743 and after CJ 1 thru b Connect the flap motor electrical wiring at the CJ I10 CJ 142 thru CJ 148 except airplanes which quick ...

Страница 172: ...stortion Replace bushings and any parts screw 4 that rotate counterclockwise when showing evidence of deterioration Lubricate all parts with screwed into the nut assembly 2 Mll G 23827 grease prior to assembly ELEVATOR TRIM TAB ACTUATOR ASSEMBLY f Install nut assembly 2 into housing 11 secure CE 1 thru CE 616 CE 743 and after CJ 1 thru CJ 110 with snap ring 1 CJ 142 thru CJ 148 except airplanes wh...

Страница 173: ...prior to assembly WARNING ELEVATOR TRIM TAB ACTUATOR ASSEMBLY The trim tab actuator to be installed on the left CE 617 thru CE 742 CJ 111 thru CJ 141 except hand horizontal stabilizer must have threads on airplanes which incorporate kit 33 4002 1 or kif its actuator screw 4 that rotate clockwise when 33 4002 3 screwed into the nut assembly 6 The trim tab Figure 4 4 actuator to be installed on the ...

Страница 174: ...he nut assembly 7 out of the housing MIL G 23827 grease prior to assembly b Remove the actuator screw 6 from the nut Lubricate the O ring with MIL S 8660 assembly c Remove nut 1 washer 2 and shoulder pin 3 The bushing 5 can now be removed from the screw f Install screw 6 into nut 7 d Remove check nut 12 and screw out the end adjusting bushing 11 with appropriate spanner wrench WARNING e Remove O r...

Страница 175: ... aluminum or equiv r t 8 1 1 4 Dia x 2 corrosion res stl 7 1 1 4 Dia x 1 corrosion res stl II I II 1 1 6 IN 8 1 1 4 28 nut 9 1 3 8 x 5 x 10 rubber 31 IN 10 1 3 8 x 2 x 10 rubber 11 1 114 x 2 x 10 corrosion res stl 12 2 1 2 x 13 x 3 VLIER Torque screw _I 13 2 KN813 Keensert or tap 112 13 14 2 1 8 x 1 x 3 4 rubber SECTION A A P N of Federal Products Corp Providence R I THIS GROOVE TO BE A SNUG FIT T...

Страница 176: ...rol surfaces to prevent movement of the elevators Set the elevator tabs in the X Y E neutral position b Affix the dial indicator check fixture so that the dial indicator point is positioned on the outboard edge of 6 0 05 inch maximum the tab 3 30 inches aft of the hinge line as measured along the top of the tab c Apply a small piece of masking tape for paint NOTE protection 4 50 inches aft of the ...

Страница 177: ...SECTION NIAJ O R NIAINTENANCE AND OVERHAUL ...

Страница 178: ...IF SECTION 5 Major Maintenance and Overhaul ...

Страница 179: ...should be replaced if scoring is present Small nicks and scratches h Inspect the cylinder walls and the contacting should be sanded smooth surfaces of the piston for damage Small scratches and nic ks can he removed by polishing the damaged area with fine f Bearing cups and cones should be inspected sandpaper 400 grit carefully for damage and discoloration Bearing cones should be repacked with clea...

Страница 180: ...ut the piston lining RELINING BEECH BRAKES CD 1106 through g Blow out the piston lining recess to remove any CD 1271 CE 173 through CE 300 and CJ 1 loose foreign matter through CJ 301 h Attach the new piston lining with the self locking screw For relining brakes on the above aircraft refer to i Secure the new anvil lining to the anvil backplate BEECHCRAFT Supplementary Publications Manual P N with...

Страница 181: ...SECTION ELECTRICAL VVIRING DIRAGRAIVIS ...

Страница 182: ...SECTION 6 Electrical Wiring Diagrams ...

Страница 183: ...n with single foldout on which most of the electrical circuits are shown The page adjacent to the General Diagram contains a keyed index of the individual circuit components For optional circuits or circuits with later serial effectivities refer to the Index of Wiring Diagrams for the applicable Model and the BEECHCRAFT Bonanza Wiring Diagram Manual P N 35 590102 7 The wiring diagrams for those ai...

Страница 184: ...ng Cigarette Lighter 6 9 Beacon 6 6 Control Landing Gear 6 4 Cylinder Head Temperature L Indicator 6 9 P Landing Gear Control 6 4 F Lighter Cigarette 6 9 Pitot Heated Optional 6 9 Lights Cabin 6 10 Flap Control and Position Compass 6 10 S Indicator 6 7 InstrumentFlood 6 10 Fuel Quantity Indicator 6 8 Landing Gear Visual Stall Warning Indicator 6 7 Indicator 6 10 Starter Battery and 6 5 ef Navigati...

Страница 185: ...lap Control and Position 6 14 Optional Instrument 6 19 Instrument Lights Strobe 6 16 E Standard 6 17 Optional 6 19 Elevator Trim 6 15 External Power cd i a h 6 14 L Strobe Lig lt 6 16 Landing Gear T With Safety System 6 22 Flap Control and Lights PositionIndicator 6 14 Instrument 6 17 Trim Elevator 6 15 Issued Dece nber 1969 6 2A ...

Страница 186: ... 25 Radio Protection 6 24j Stall Warning 6 33 Rotating Beacon 6 28 D Turn and Bank 6 26 instrument Lights Opti s 6 32 Interior Lights 6 29 S Deice Propeller 6 46 StallWarning Indicator 6 33 E L Starter Battery and 6 23 Strobe Light 6 38 Elevator Trim 6 45 Landing Gear Control ExternalPower 6 24 and Position Indicator T WithoutSafetySystem 6 36 With Safety System 6 37 F Landing Light 6 28 Trim Elev...

Страница 187: ...rument Post With Safety System 6 62B Lights 6 74A Lighters Cigarette 6 53 Stall Warning 6 54 Engine Instrument Wedge Ligh s 6 74 Lights Standby Generator 6 82 Engine Instrument With Cabin and Map 6 72 Starter and Ignition 6 52 Vertical Instruments 6 74B Courtesy 6 81 Strobe Lights 6 78B ExhaustGasTemperature 6 701 Engine Instrument Post 6 74A External Power Battery and 6 50C Engine InstrumentWedge...

Страница 188: ... Warning Horn Circuit Breaker 8 Up Brake Switch 7 3 Landing Gear Motor Circuit Breaker 9 Up Limit Switch 3 10G9 10 4 FuselageWing Break 10 Down Brake Switch F6 18 TO GREEN INDICATOR LIGHT 5 Landing Gear Safety Switch L1 Down Limit Switch 6 Landing Gear Reversing Switch 12 Landing Gear Motor F5 18 TO RED INDICATOR LIGHT LANDING GEAR CONTROL Models 33 and A33 Isrued December 1969 6 4 ...

Страница 189: ... e Ps 18 I f I 4 i Bus Bar 4 Generator Switch 2 Circuit Breaker 35A Std 5 Generator 50A Optional 35A Std G F 3 Voltage Regulator 35A Std 50A Optional 50A Optional 5 GENERATOR Models 33 and A33 P6 18 tP7 18 P17 2 Ps z f7 3 4 I P16 2 I L P12 8 53 1 Bus Bar r g 0 2 Starter Switch 3 Relay 4 Battery P10 Pll 8 5 Master Switch 6 Starter 7 Ammeter zi BATTERY AND STARTER Models 33 and A33 Issued December 1...

Страница 190: ...d ground terminals as shown on the 3 Rotating Beacon Switch lower beacon circuit when a Whelan 4 Upper Beacon l ht dual beacon is installed 5 Lower Beacon Light OPTIONAL DUAL ROTATING BEACON 5A OFFI OIA ON L F A N31 1 4 i BusBar 3 Switch 2 Circuit Breaker 4 Booster Pump N32 WELD N BOOST PUMP Models 33 and A33 2 I i Bus Bar 3 Indicator 2 Circuit Breaker TURN AND BANK INDICATOR Models 33 and A33 6 6...

Страница 191: ...onnect Splice Position Light Circuit I I 5 Down Limit Switch Breaker 6 FlapMotor 11 7 Up Limit Switch FLAP CONTROL AND POSITION INDICATOR Model 33 NOTE See Model A33 Navigation Light Circuit for Flap Indicator Circuit and Landing Gear Indicator Circuit W LB W8 L8 WS3 LB 3 X 4 1 N51 18 5 i Bus Bar 4 FuselageWing Break _L 2 Stall Warning Indicator Circuit Breaker 5 Wring StallDetector Unit 3 StallWa...

Страница 192: ...ell Quantity Indicator 10 Auxiliary FuelCell Quantity Indicator Selector Switch Left Right Selector Switch Left Right 6 RightWing Break Connector II Auxiliary Fuel Cell Transmitter Unit Left 6 Left Wing Break Connector 12 Auxiliary Fuel Cell Transmitter Unit Right FUEL QUANTITY INDICATOR Models 33 and A33 E1 183 E2 18 1 Bus Bar 3 Oil Temperature Indicator 2 Oil Temperature Indicator Circuit Breake...

Страница 193: ... NOTE All items of this circuit are 1 optional except wire H2 i Bus Bar 3 Switch 2 Circuit Breaker 4 Disconnect Splice 5 Heated Pitot HEATED PITOT CIRCUIT OPTIONAL Models 33 and A33 LWA1 1 i Bus Bar 2 Cigarette Lighter CIGARETTE LIGHTER Models 33 and A33 L1 14 L2 14 N1 14 20A 3 i 1 Bus Bar 3 Landing Light Switch 2 Circuit Breaker 4 Nose Landing Light NOSE LANDING LIGHT Models 33 and A33 6 9 Issued...

Страница 194: ... 18Q 10 Cabin Lights Switch MISCELLANEOUS LIGHTING Model 33 iiiiiiiiiiiii 5A r 2 L5A 18 ion L5 18 tOF_F_ _I L8 18 3 L6 18 4 1 I r i 50nL8D 18 L8A 18 L10 18 L86 18 L21 18 Lll 18 1 Bus Bar 2 Circuit Breaker 5 Tab Position Indicator Light 1 1 3 3 Disconnect Splice 4 Rheostat 6 Resistor 7 Instrument Flood Light 8 Landing Gear Visual Indicator 9 Compass Light Q 10 Cabin Light N7 18 C C 11 Switch e c C ...

Страница 195: ...18 t LaO tS18 L4A 18 L7 18 t L8 18 F2E 18 OVt F3 18 jTO FLAP UP LIMIT SWITCH F2D 18 I F4 18 t F6 18 j TO FLAP DOWN LIMIT SWITCH F2G 18 6 F5 18 TO L G UP LIMIT SWITCH F2F 18 6 F6 18 jTO L G DOWN LIMIT SWITCH 1 Bus Bar 7 LH Navigation Light Red 2 Circuit Breaker 8 Resistor 3 Navigation Light Switch 9 Flap Up Indicator Green 4 Disconnect Splice 10 Flap Down Indicator Red 5 RH Navigation Light Green 1...

Страница 196: ...tch 77 Voltage Regulator 50 Amp L H Inboard 49 Turn and Bank Circuit 78 Generator Switch 14 FuelLevel Transmitter Breaker 5 Amp 79 Generator L H Outboard 50 Turn and Bank Indicator 80 Ammeter 15 Fuel Level Transmitter 51 Flap Power Circuit 81 BatteryRelay RH Outboard Breaker 10 Amp 82 Battery Switch 16 Fuel Level Transmitter 52 Flap Control Switch 83 Starter Ignition Circuit R H Inboard 53 Landing...

Страница 197: ... 0 8 9 EFCEtTIVL I I T 88AIS 07A 18 AIR LIAIB t0 88 SCPEW I Uqd A r 4G 18 q7Alg O UB 07A1B RH I d3 B P t _L CIICVa I aNo IFTER I 40 cal lo I Ptruu pllU R tO 9 I ZC L 1010i PS L c tog wzBle56 1 81 PIDZ 98 iw ls 936 s wvcs 1 P742 I I I 8 w tl 6 2910 I I I I lOblg WIM FOUR Q9Agii 39 Yzcs A18 37 o TRAn51111TTERS 100 IbA TERnlllALS 13 16 1Q 20 S Gtlt O PlclB 3f B 039 18 STAIJDARD FIM 8 c la14 1513BIL Z...

Страница 198: ... I C3A12 DN GREEN p C4A12 C10 12 O PI C25 14 I I WHITE C161gZO L C2A12 C13 12 C24 14 L 1 Itl BLACK N24 14 f sy C1 B20 C17A20 t O 3 1 Bus C18B20 C18A20 2 C1116Plll 41 2 Circuit Breaker 3 Flap Control Switch 4 UpLimitSwitch C19A20N 5 Down Linhit Switch L 6 FlapMotor CD 1200 AND AFTER 7 Flap Position Transmitter 8 Flap Position Indicator FLAP CONTROL AND POSITION INDICATOR Model C33 and E33 CD 1044 t...

Страница 199: ...Le c P C22A18 REI CD 1202 AND AFTER C2iA18 13BLACK P MTR i Pitch Trim and Ignition Boost Circuit Breaker 2 Control Column Coil Cord 9 Control Switch 4 Trim Actuator Assembly 5 Shunting Resistor 6 Speed Adjust ELEVATOR TRIM OPTIONAL Model E33 00 1119 thru 00 1304 6 15 C7 ...

Страница 200: ...owerSupply 3 Strobe Light LSTROBE LIGHT HOSKINS OPTIOWAL IModel E33 CD1199 thru CD 1304 Il jA L76A20 cl 2 L76B20 L79A20N 7 4 L79B20N ZD a WKITE BLACK RED 1 Strohe Light Cirouit Brei er g 2 Power Supply 3 Strohe Light STROBE LIGHT BULLOCK OPTIONAL Model E33 CD 1227 thru CD 1304 a is C7 ...

Страница 201: ...A20N L L6A20 L5A20 L34 18 NOTE VENDOR FURNISHED WIRES ARE NOT CODED 1 Instrument Light Rheostat 2 Fuel Panel Placard Light 3 Outside Air Temperature Light 4 Landing Gear Visual Indicator Light 5 Trim Tab Indicator Light 6 Switch 7 Compass Light 8 Engine Instrument Cluster Lights 9 Glareshield Instrument Lights INSTRUMENT LIGHTS Model E33 CD 1119 thru CD 1202 Issued December 1969 6 17 ...

Страница 202: ...V_ L2A20 L16A18N IL B20Lsi L6A18 L34 18 ILzczo L21 0N I_V I i LB N JLiD20 i Oil Temp Radio Inst and Cabin Lights Circuit Breaker 2 Dim Control Rheostat 3 Compass and OAT Light Switch 4 OAT Light 5 Fuel Selct Light 6 Engine Instrument Lights 7 Trim Tab Light 8 Landing Gear Visual Indicator Light 9 Glareshield Connector 10 Glareshield Lights 11 Compass Light INSTRUMENT LIGHTS Model E33 CD 1203 thru ...

Страница 203: ...L341 18 rL3A18 L12F18 t L12G18 L 6 18S L L3B18 L6A18 4 L13C18 1 Oil Temperature Instrument and c c c c c L9A18N L4A18N HORIZON AIR SPEED CLOCK L L Cabin Lights Circuit Breaker 2 Radio and Instrument Lights Dim Control 3 Instrument Flood Lights Dim Contl ol L13C18 4 Instrument Lights L13M18 t L13D18 r L13E18 L13F18 r LL3Gi8 14 5 Panel Edge lights 6 Fuel Panel Light L13N18 7 Compass Light L13L18 L13...

Страница 204: ... L5A18 L L34 18 rL3A18 L 6A18N L L3B18 L6A18 13 C L13C18 c I c 1 I C I C I c Q 1 Oil Temperature instrument and L9A18N L4A18N HORIZON AIR SPEED CLOCK L I Cabin Lights Circuit Breaker 2 Radio and Instrument Lights Dim Control 3 Instrument Flood Lights Dim Control L13C18 4 Instrument Lights 5 Panel Edge lights L13M18 t L13D18 r L13E18 t L13F18 T L13G18 6 Fuel Panel Light Compass Light L13N18 II L13L...

Страница 205: ...1 OFF BLACK WHITE oio 1 OFF i Avionics Bus 2 Constant Copilot Solenoid Valve 3 Constant Copilot Switch 4 Constant Copilot Wheel Switch 5 Constant Copilot Autopilot Circuit Breaker CONSTANT COPILOT OPTIONAL Model E33 CPlliS thru CD 1304 C7 6 21 ...

Страница 206: ... Landing Gear Motor 10 90 MPH Pressure Switch 11 Landing Gear Safety System Switch i ALR GlOA12 e c losl2 eczs8 12 up 12 Landing Gear Safety Relay UP 13 Throttle Control Switch Gl lA12 G4B12 14 120 MPH Pressure Switch r I i LRED DWN 15 Diode 16 Bus 17 Landing Gear Down Indicator I I GllB12 18 Landing Gear Up Indicator 19 Landing Gear and Flap Indicator G6A10 I WHITE BLACK G31 B10 Lights Circuit Br...

Страница 207: ... K4A2 10A fl J5B18N MOTOR I 55A18N P1AZ K5AaN P7A2 K OCP1DB _L O P24B2 L P1B6 P16A2N I P1C18 m II Plijl c P3A18N II P6A6 r A Or I V d P4A18Na i Bus Bar 2 Circuit Breaker 8 Starter Motor 3 Ibmition Switch 9 Battery 4 Magneto L H 10 External Power Receptacle Optional 5 Magneto R H 11 Ammeter 6 Vibrator 12 Battery Relay 7 Starter f7 elay 13 Battery Switch 14 Terminal Board and Bus BATTERY AND STARTER...

Страница 208: ...Power Polarity Relay rP16A2N 3 Diode 4 External Power Receptacle EXTERNAL POWER OPTIONAL Models C33A and E33A CE 102 thru CE 612 I P25A8 P26A8 EOI S P24A1BN I II RADIO BUS I Bus Bar P27A18j STARTER RELAY REF 2 RadioSolenoid RADIO PROTECTION Models C33A E33A and E33C 6 24 1 C7 ...

Страница 209: ...and E33C 10A IEl Q1A18 T O 2A18 i Bus Bar 3 Auxiliary Fuel Pump Switch 2 Circuit Breaker 4 Auxiliary Fuel Pump 5A AUXILIARY FUEL PUMP d I d Models C33A E33A and E33C PI E3A18E4A18 I Bus Bar 3 Cylinder Head Temp Indicator 2 Circuit Breaker 4 Cyl Head Temp Transmitter CYLINDER HEAD TEMPERATURE INDICATOR Models C33A E33A and E33C Issued December l969 6 25 ...

Страница 210: ...6A18 NBD I Q8A18 7A18 4 nll I OUTED LH RH C33A 369 243A i Bus Bar 7 Fuel LevelTransmitter R H Outboard 2 Circuit Breaker 8 Fuel LevelTransmitter R H Inboard 3 Fuel Level Indicator R H 9 Fuel LevelIndicator R H 4 Fuel LevelIndicator L H lO FuelZevelIndicator L H 5 FuelI evel Transmitter L H Inboard 11 Fuel Level Transmitter L H 6 Fuel LevelTransmitter L H Outboard 12 Fuel Level Transmitter R H FUEL...

Страница 211: ... ARE REMOVED TO PREVENT INDICATOR DAMAGE i Circuit Breaker 2 Auxili ary FuelQuantity Indicator 3 Indicator Select Switch 4 Tip Tank Fuel Quantity Transmitter WING TIP FUEL QUANTITY OPTIONAL Models C33A and E33A O 20GA 20GA 1 Aircraft Bus 2 Fuse 3 Switch 4 Solenoid Valve N C WING TIP FUEL SOLENOID OPTIONAL Models C33A E33A and E33C Issued December 1969 6 27 ...

Страница 212: ...A E33A and E33C L25B14 15A L27A14N Il L26A14N I I 1 Bus Bar 3 Upper Beacon Light 2 Circuit Breake9 4 Lower Beacon Light ROTATING BEACON OPTIONAL Models C33A E33A and E33C 02b A L28A12 I L28B12 1 Bus Bar 3 Landing Light L29A12N 2 Circuit Breaker LANDING LIGHT Models C33A E33A and E33C 6 28 Issued December 1969 ...

Страница 213: ... VENDOR FURNISHED WIRES L34 18 P ARE NOT CODED L3A18 I L3B18_L L9A18N L CI L4A18N i Instrument Light Rheostat 2 Fuel Panel Placard Light 3 CabinLights 4 Landing Gear Visual Indicator Light 5 Trim Tab Indicator Light 6 Compass Light Resistor 7 Compass Light 8 Engine Instrument Cluster Lights 9 Glareshield Instrument Lights 10 Interior Lights Circuit Breaker INTERIOR LIGHTS Model C33A Issued Decembe...

Страница 214: ... L16A20N L I 1 7 L5A20 NOTE VENDOR FURNISHED WIRES ARE NOT CODED 1 Instrument Light Rhedstat 2 Fuel Panel Placard Light 3 Outside Air Temperature Light 4 Landing Gear Visual Indicator Light 5 Trim Tab Indicator Light 6 Switch 7 Compass Light 8 Engine Instrument Cluster Lights 9 Glareshield Instrument Lights INTERIOR LIGHTS Models E33A CE180 thru CE250 6 30 E33C CJ1 thru CJ13 Issued December 1969 ...

Страница 215: ...L6A18 L5A18 L IL2B20 O i L34 18 ILzczo 1 0 L21B20N L9A18N ILqD20 1 Oil Temp Radio Inst and Cabin Lights Circuit Rreaker 2 Dim Control Rheostat 3 Compass and OAT Light Switch 4 OAT Light 5 Fuel Selct Light 6 Engine Instrument Lights 7 Trim Tab Light 8 Landing Gear Visual Indicator Light 9 Glareshield Connector 10 Glareshield Lights 11 Compass Light INTERIOR LIGHTS Model E33A CD 251 thru CD 1304 Mod...

Страница 216: ...TIMETER RATE OF CLIMB DIRECTION TURN AND BANK ADF L12F18 t L12G18 L30A18 NOTE UNCODED WIRES ARE FURNISHED WITH LIGHTS I P C c I I C I C i C L30B18 L30C1B L30C18 j L30A18 HORIZON AIR SPEED CLOCK r T L30R18 T L30S18 L30D18 L30E18 L30F18 T i Oil Temperature Instrument and L30P18 L30Nr8 L30M18 L30L18 L3 0K18 L30J18 L30H18 L30G18 Cabin Lights Circuit Breaker B ch Q G cix x tiX d 2 Radio and Instrument ...

Страница 217: ...14 o Ir A 3 C15A18PJrll C12A18 i BusBar 5 Flap Down Indicator Light Amberj 2 Flap Circuit Breaker 6 FlapMotor 3 Position Indicator Light 7 Flap Control Switch Circuit Breaker 8 Flap Up Limit Switch 4 Flap Up Indicator Light Green 9 Flap Down Limit Switch FLAP CONTROL AND POSITION INDICATOR Model C33A CE1 thru CE70 except CE60 6 34 Issued December 1969 ...

Страница 218: ...LSSA1B I 1 Bus Bar 2 Circuit Breaker 3 Subpanel Lights 4 Right Wing Navigation Light Green 5 Left Wing Navigation Light Red LIIIIIIIIII J 6 TailNavigation Light Clear NAVIGATION LIGHTS Models C33A E33A and E33C I W32A18 f W32B18 O I Bus Bar 2 Circuit Breaker 3 Stall Warning Detector 4 Stall Warning Horn STALL WARNING INDICATOR Models C33A E33A and E33C 6 33 Issued Decembel5 1969 ...

Страница 219: ... 14 C17B20 tC17A20 O 3 1 El BLACK 1_ C18B20 tC18A20 t 02 C19ABON i BusBar 6 FlapMotor 2 Flap Circuit Breaker 7 Flap Position Transmitter 3 Flap Control Switch 8 Flap Position indicator 4 Flap Up Limit Switch PC Board 5 FlapDown LimitSwitch 9 Flap PositionIndicator FLAP CONTROL AND POSITION INDICATOR Model C33A CE 60 and CE 71 thru CE 612 C7 Model E33A E33C 6 35 ...

Страница 220: ... G288 10 4 GllC10 i Bus Bar 7 L C Motor 12 Flasher 2 L G Power Circuit Breaker 8 L G Down Limit Switch 13 L C Warning Horn 3 L G Warning Circuit Breaker 9 L G Up Limit Switch 14 Throttle Warning Limit Sw 4 L G Flap Ind Circuit Breaker 10 L G Down Brake 15 L G Safety Limit Switch 5 L G Down Ind Light Green Limit Switch 16 Landing Gear Switch 6 L G Up Ind Light Red ii L G Up Brake Limit Sw 17 L G Wa...

Страница 221: ...10 i IP 9 Landing Gear Motor 10 90 MPH Pressure Switch 11 Landing Gear Safety System Switch AIR G10A12 e Glosl2 eczss la UP 12 Landing Gear Safety Relay UP 13 Throttle Control Switch GllA12 14 120 MPH Pressure Switch r I i G4B12 15 Diode LRED DWN 16 Bus 17 Landing Gear Down Indicator I I I I I I GllB12 18 Landing Gear Up Indicator 19 Landing Gear and Flap Indicator L G6A10 I WHITE BLACK G31B10 Lig...

Страница 222: ...ler Supply 3 Strobe Light STROBE LIGHT HOSKINS OPTIONAL Models C33A E33A and E33C eisA L76A20 2 L76B20 I L79A20N 4 L79B20N 113 n WHITE BLACK RED 1 Strobe Light Circuit Breaker I El 2 Power Supply 3 Strobe Light STROBE LIGHT BULLOCK OKTIONAL Models C33A E33A and E33C 6 38 Issued December 1969 ...

Страница 223: ...18NP REF ge P31A16 L n P3ZA16 C Im P12 d14 P3A18N L P20A18 P18A18 rP29A18N GND FLD BAT I IP i Bus Bar 2 80A Circuit Breaker 3 10A Circuit Breaker 4 Alternator 70A 5 Indicator 330 Lamp 10 Battery Relay 6 Overvoltage Relay 11 Connector 7 Alternator Switch 12 Plug and Cable Assembly 8 Voltage Regulator 13 Battery Switch 9 Suppressor 14 Perm Splice ALTERNATOR 70A Model C33A CE 1 thru CE 87 6 39 Issued...

Страница 224: ...THRU CE 147 P21A20N THRU CE 159 L P32A16 P17A16N P22A18NI m rr BAT I P10A6 i Bus Bar 7 Overvoltage Indicator 2 Alternator Circuit Breaker 8 BatterySwitch 3 Overvoltage Relay Circuit Breaker 9 Suppressor 4 Alternator 10 Alternator Switch 5 Voltage Regulator and Overvoltage Relay 11 Connector 6 Connector ALTERNATOR 70A Model C33A CE 88 thru CE 159 6 40 Issued December 1969 ...

Страница 225: ... P21A20N I 3A3 P17A16N P32B16 L3 P22A1 m F BAT P1OA r R7 1 Bus Bar 7 Overvoltage Indicator 2 Alternator Circuit Breaker 8 BatterySwitch 3 Overvoltage Relay Circuit Breaker 9 Suppressor 4 Alternator 10 Alternator Switch 5 Voltage Regulator and 11 Connector Overvoltage Relay 12 Fuse 6 Connector ALTERNATOR 70A Model C33A CE 160 thru CE 179 6 41 Issued December 969 ...

Страница 226: ...OR AIRCRAFT SERIALS MODIFIED IN ACCORDANCE WITH S I 0111 350 P22A18N1 P40A18 GND BAT im r P10A6 I i Bus Bar 7 Alternator Out Indicator 2 Alternator Circuit Breaker 8 Battery Switch 3 Overvoltage Relay Circuit Breaker 9 Suppressor 4 A Ite rnato r 10 Alternator Switch 5 Voltaffe Regulator and Overvoltage ii Connector Relay 12 Alternator Out Relay 6 Connector 13 Fuse 14 Resistor ALTERNATOR 70A MODEL ...

Страница 227: ...P32C18 F1 P22A1 8N J P32A18 1 Bus Bar 8 Battery Switch 2 Alternator Circuit Breaker 9 Suppressor 3 Overvoltage Relay Circuit Breaker 10 Alternator Switch 4 Alte rnator 11 Not Used 5 Voltage Regulator and Overvoltage 12 Alternator Out Relay Relay 13 Fuse 6 Connector 14 Filter Capacitor 7 Alternator Out Indicator 15 Resistor ALTERNATOR 70A Model E33A CE 249 thru CE 265 Model E33C CJ 14 thru CJ 22 6 ...

Страница 228: ...2C18 IL r JA OC3 P3 F1 P22A18N i C33A 369 265 i BusBar 7 Aiternator Out Indicator 2 Alternator Circuit Breaker 8 BatterySwiech 3 Overvoltage Relay Circuit Breaker 9 Suppressor 4 Alternator 10 Alternator Switch 5 Voltage Regulator and Overvoltage 11 Not Ilsed Relay 12 Alternator Out Sensor 6 Connector 13 Fuse 14 Filter Capacitor ALTERNATOR 70A Model E33A CE 266 thru CE 612 Model E33C CJ 23 thru CJ ...

Страница 229: ...K C21A18 MTR i Pitch Trim and Ignition Boost Circuit Breaker 2 Control Column Coil Cord 3 Control Switch 4 Trim Actuator Assembly 5 Shunting Resistor CE 245 and after CJ 10 and after 6 Speed Adjust Resistor CE 180 CE 182 CE 239 and after ELEVATOR TRIM OPTIONAL Models C33A E33A and E33C Issued December 1969 6 45 ...

Страница 230: ...ice Boot PROPELLER DEICE OPTIONAL TWO BLADED Models C33A E33A and E33C H3slo r_K filWr B4B1 t B1 SHBB10 H8B14 6 1 B F r HllB14 H12B14 A X H9B14 H10B14 Il C I I H7B14H13A16N C A r H6B14N i Bus Bar 2 Circuit Breaker Switch 3 Ammeter 4 Timer I a Brush Block Q 6 Slip Ring 7 Deice Boot PROPELLER DEICE OPTIONAL THREE BLADED Models C33A E33A and E33C 6 46 Issued December 1969 ...

Страница 231: ...LOW I 1 Bus Bar PRESS b PRESS I 2 Circuit Breaker Quick Disconnect LI_ OFF 7i 3 Auxiliary Fuel Control Panel 4 Auxiliary Fuel Pump High Pressure 5 Auxiliary Fuel Pump Low Pressure O 2A18 QCIOA18 t Q BLACK O BLACK BLACKI 8 BLACK I FUEL BOOST PUMPS HIGH AND LOW PRESSURE Model E33C Issued Decembercl969 6 47 ...

Страница 232: ...6900 11 16 7 E10A8 EllA18 I E12A18N K1A18 E13A18N ACE C20A18 i Pitch Trim and Ignition Boost Circuit Breaker 2 Fuel Boost Light 3 Fuel Pressure Switch FUEL BOOST LIGHT Model E33C 6 48 Issued December 1969 ...

Страница 233: ...ITE 1 610 V35 369 60 OFF i Avionics Bus 2 Constant Copilot Solenoid Valve 3 Constant Copilot Switch 4 Constant Copilot Wheel Switch 5 Constant Copilot Autopilot Circuit Breaker CONSTANT COPILOT OPTIONAL Model E33A CE 236 thru CE 612 Model E33C 6 49 C7 ...

Страница 234: ...LE AND LANDING ALTERNATOR FIEL A GEARWARNING TO PllB4 BATTERY LANDING MASTER LANDING GEAR GEAR PROP SAFETY I DEICE RELAY r H25A10 P5B4 II I O LANDING TAXI NAV ROT STROBE PITOT LIGHT LIGHT LIGHTS BEACON LIGHTS HEAT PllA4 P23A4 P26A8 TG ALTERNATOR 36 369 69 P27A18 Z TO STARTER RELAY i DC Bus P21A18N 2 Avionics Bus 3 Avionics Protection Relay 4 Power Terminal Board POWER DISTRIBUTION Model 533 CD 123...

Страница 235: ...XILIARY FUEL PUMP FLAP POSITION O O DOOR WARN AND ALTERNATOR OUT ALTERNATOR FIELD a O THROTTLE AND LANDING GEAR WARNING TO PllB4 BATTERY LANDING MASTER LANDING GEAR SAFETYGEAR I DEICEPROP RELAY r HZSA10 P5B4 II P PllC4 It L C I D LANDING TAXI NAV ROT STROBE PITOT LIGHT LIGHT LIGHTS BEACON LIGHTS HEAT PllA4 TO ALTERNATOR nss sss loo 1 DC Bus 2 Power Terminal Board POWER DISTRIBUTION Vertical Instru...

Страница 236: ...Y FUEL PUMP FLAP MOTOR O a LANDING GEAR POSITION FLAP POSITION DOOR WARN AND ALTERNATOR OUT ALTERNATOR FIELD O THROTTLE AND LANDING GEAR WARNING TO PllB4 BATTERY LANDING MASTER LANDING GEAR GEAR PROP SAFETY I I DEICE RE LAY r H25A10 P5B4 I 1 LANDING TAXI NAV ROT STROBE PITOT LIGHT LIGHT LIGHTS BEACON LIGHTS HEAT PllA4 TO ALTERNATOR A36 369 306 1 DC Bus 2 Power Terminal Board POWER DISTRIBUTION Ver...

Страница 237: ...LAPMOTOR RAD OAND INSTRUMENT LIGHTS FLAP POSITION LANDING GEAR POSITION DOOR AND ALTERNATOR ALTERNATOR FIELD OUT wARNING LANDING GEAR I I THROTTLE AND LANDING SAFETY SWITCHA V GEARWARNING TO PllB4 BATTERY MASTER LANDING GEAR RE LAY r P5B4 LANDING TAXI NAV ROT STROBE PITOT LIGHT LIGHT LIGHTS BEACON LIGHTS HE AT PllA4 TG ALTERNATOR F33A 369 300 i DC Bus 2 Power Terminal Board POWER DISTRIBUTION with...

Страница 238: ...GHTS FLAP POSITION n LANDINGGEAR POSITION DOOR AND ALTERNATOR ALTERNATOR FIELD OUT wARNING LANDING GEAR THROTTLE AND LANDING SAFETY SUrITCH V GEARWARNING TO PllB4 BATTERY MAST EP LANDING GEAR RE LAY r P5B4 LANDING TAXI NAV ROT STROBE PITOT LIGHT LIGHT LIGHTS BEACON LIGHTS HEAT PllA4 TG ALTERNATOR F33A369301 1 DC Bus 2 Power Terminal Board POWER DISTRIBUTION without standby generator Model F33A CE ...

Страница 239: ...ON STARTER LIGHTER RELAY AUXILIARY FLAP MOTOR FUEL PUMP FLAP POSITION THROTTLE AND LANDING ALTERNATOR FIELDA V GEARWARNING TO PllB6 BATTERY LANDING MASTER GEAR LANDING GEAR RELAY SAFETY r P5B4 O PllC6 1 t D LANDING TAXI NAV ROT STROBE PITOT LIGHT LIGHT LIGHTS BEACON LIGHTS HEAT PllA6 TG ALTERNATOR G33 369 90 1 DCBus 2 Power Terminal Board POWER DISTRIBUTION Model G 33 CD 1255 thru CD 1289 C1 6 505...

Страница 240: ... GEAR RADIO AND INSTR LIGHTS POSITION STARTER LIGHTER RELAY AUXILIARY FLAP MOTOR FUEL PUMP PITCH TRIM FLAP POSITION THROTTLE AND LANDING ALTERNATOR FIELDA V GEARWARNING TO P11B6 BATTERY I I LANDING MASTER GEAR LANDING GEAR RELAY SAFETY r P5B4 LANDING TAXI NAV ROT STROBE PITOT LIGHT LIGHT LIGHTS BEACON LIGHTS HEAT PllA6 3 TO ALTERNATOR oj3 Jss soa POWER DISTRIBUTION Model 033 Cb 1290 thru Cb 1304 6...

Страница 241: ... P1A2 I P3A2 P24B2 7 TO S TARTER P2A2N AND IGNITION L P24A2 1 I L P24B2 P25B20 P i 1 Diode 2 Battery Master Relay 3 Battery Master Switch 4 Fuse OPTIONAL 1 5 Shunt 8 Ammeter 7 Battery 8 External Power Relay 9 External Power Recepticai 10 Diode BATTERY AND EXTERNAL POWER Model F33 CD 1235 thru CP1254 Model 033 CD 255 thru CD 1304 V358 369 78A Model F33A CE 290 thru 06 612 Model F33C CJ 26 thru CJ 3...

Страница 242: ...NAL P1A2 I TO ENGINE INSTRUMENT P3A2 LIGHTS VERTICAL P24B2 h 7 TO STARTER P2A2N AND IGNITION I P24A2 I LP24B2 P25A20 V358 369 308 P25B20 1 Diode 2 Battery Master Relay 3 Battery Master Switch 4 Fuse OPTIONAL 1 5 Shunt 6 Ammeter 7 Battery 8 External Power Relay 9 External Power Receptical 10 Diode BATTERY AND EXTERNAL POWER Model F33A CE 350 thru CE 408 6 50H 01 ...

Страница 243: ...TESY L81A20 LIGHTS OPTIONAL P1A2 I P3A2 P24B2 r TO STARTER P2A2N AND IGNITION P24A2 P25B20 f i Diode 2 Battery Master Relay 3 Battery Master Switch 4 Fuse OPTIONAL 5 Shunt 6 Engine Instrument Cluster 7 Battery 8 External Power Relay 9 External Power Receptical 10 Diode V35 3BB6A BATTERY AND EXTERNAL POWER F33A CE409 thru CE 1304 F33C CJ 31 th u CJ 1304 07 6 5 ...

Страница 244: ...POWER K5A2N I i Engine Start Relay Circuit Breaker 2 Ignition Switch 3 RH Magneto 4 LH Magneto 5 Starter 6 Starter Relay v3 s 3 9 a STARTER AND IGNITION Model 533 CD 1235 thru CD 1254 Model F33A 05 290 thru CE 315 and CE 324 Model F33C CJ 26 thru CJ 30 Aircraft prior to incorporation of S i 0410 354 Revision I 6 52 Issued December 1972 ...

Страница 245: ...ERIALS CD 1256 AND AFTER OR ON MODEL F33A SERIALS CE 350 AND AFTER F33C SERIALS CJ 31 AND AFTER i Engine Start Relay Circuit Breaker 2 Ignition Switch 3 RH Magneto 4 LH Magneto 5 Starter 6 Starter Relay G33 369898 STARTER AND IGNITION Model G33 CD 1255 thru CD 1304 Model f33A CE 316 thru CE 612 Model F33C CJ 31 thru CJ 104 and prior airplanes in compliance with S I 0410 344 Rev I 07 i 6 52A ...

Страница 246: ...BLACK H1A18 BLACK i Circuit Breaker 2 Cigarette Lighter CIGARETTE LIGHTERS Models F33 G33 F33A and F33C Issued August 1971 6 53 ...

Страница 247: ...0 i Stall Warn Circuit Breaker V35B36911 2 Stall Detector S vitch 3 Stall Warning Horn STALL WARNING Models F33 G33 F33A and F33C s P F4A18 F4B18 10A F5A18N _L V358 36913 1 Pitot Heat Circuit Breaker 2 Pitot Heater PITOT HEAT OPTIONAL Models F33 G33 F33A and F33C 6 54 Issued August 1971 ...

Страница 248: ...inator Indicator TURN COORDINATOR Models F33 G33 F33A and F33C 20A L28A12 L28B1210_ 2 OA L1 6A12 L16B12 1 Landing Light Circuit Breaker 2 Landing Light 3 Taxi Light Circuit Breaker V358 369 18 4 TaxiLight LANDING AND TAXI LIGHTS Models F33 G33 F33A and F33C Issued August 1971 6 55 ...

Страница 249: ...9C20 L18C20 El L36B20N L36A20N j 1 Navigation Lights Circuit Breaker 2 RH Navigation Light 3 Tail Navigatidn Light 4 LH Navigation Light NAVIGATION LIGHTS Model F33 CD 1235 thru CD 1254 Model G33 00 1255 thru CD 1304 Model F33A CE 290 thru CE 435 Model F33C CJ 26 thru CJ 30 6 56 t CQ ...

Страница 250: ...0 t3BB20N GND 20 L i I L36A20N 7 5 I V358 389 208 CE 524 AND AFTER CJ 52 AND AFTER i Navigation Lights Circuit Breaker 2 RH Navigation Light 3 Tail Navigation Light 4 LH Navigation Light NAVIGATION LIGHTS Model F33A 06 436 thru CE 612 Model F33C CJ 31 thru CJ 104 6 56A C7 ...

Страница 251: ...INALS GROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N CYLINDER HEAD E42A20N AND E44A20N FUEL QUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT I FuelQuantity Circuit Breaker 2 Printed Circuit Board 3 Fuel Quantity Indicator 4 Inboard Fuel Cell Transmitter 5 Outboard Fu l CellTransmitter FUEL OUAN71TY Model 533 CD 1235 thru CD 1254 Model G33 CD 1255 thru CD 1304 Model F33A CE 290...

Страница 252: ...URE E42A20N AND E44A20N FUEL OUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT oureoARD OUTBOARD E1 _ _ _ _ _i L _ _ _ _ I _ _I LEFT FUEL TANK RIGHT FUEL TANK E19A20N i 111 1ZN L TO ENGINE INSTRUMENT LIGHTS i Cir uil ereuker 2 Fuel Quan i y Indiro or 35 36975 3 Inboard Fuel Oucinti y Tr nrmi ter 4 Ouiboard Fuel Qu nti v Tron mi ter FUEL QUANTITY Vertical Instruments Model F33A CE 350 thru CE 40...

Страница 253: ...FORWARD V3636616A UPPER SIDE OF THE FIXED INSTRUMENT PANEL CE 471 THRU CE 479 sGROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N CYLINDER HEAD E42A20N AND E44A20N FUEL QUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT 1 Fuel Quantity Circuit Breaker 2 Printed Circuit Board 3 Fuel Quantity Indicator 4 Inboard Fuel CellTransmitter 5 Outboard Fu l CellTransmitter FUEL QUANTITY OPTION...

Страница 254: ...RUMENT PANEL I GROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N CYLINDER HEAD E42A20N AND E44A20N FUEL QUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT 1 Fuel Quantity Circuit Breaker 2 Printed Circuit Board 3 Fuel Quantity Indicator 4 Inboard Fuel CellTransmitter 5 Outboard Fuel Cell Transmitter FUEL QUANTI TV OPTIONAL Model F33A CE 480 thru CE 612 Model F33C CJ 52 thru CJ 104 ...

Страница 255: ...CJ 51 IT IS F33369 302 MOUNTED ON THE FORWARD UPPER SIDE OF THE FIXED INSTRUMENT PANEL CE 471 THRU CE 479 GROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N CYLINDER HEAD E42A20N AND E44A20N FUEL QUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT i Fuel Quantity Circuit Breaker 2 Printed Circuit Board 3 Fuel Quantity Indicator 4 LH FuelCell Transmitter 5 RH FuelCell Transmitter FUEL...

Страница 256: ...TRUMENT PANEL L tGROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N CYLIMDER HEAD E42A20N AND E44A20N FUEL QUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT 1 Fuel Quantity Circuit Breaker 2 Printed Circuit Board 3 Fuel Quantity Indicator 4 LH Fuel Cell Transmitter 5 RH Fuel Cell Transmitter FUEL OUANTltY STANDARD Model F33A CE 480 thru CE 612 IModelF33_C_ CJ 52 thru CJ 104 C11 6 5...

Страница 257: ...xiliary Fuel Pump Motor FUEL BOOST PUMP Models F33 and F33A CE 290 thru CE 349 5A18 TO LANDING GEAR POSITION IND PI OFF 1A18 r 2A18 10A O YO ON G33369 87 1 Auxiliary Fuel Pump Circuit Breaker 2 Auxiliary Fuel Pump Switch 3 Auxiliary Fuel Pump Motor FUEL BOOST PUMP Medal 033 Model F33A CE 350 thru CE 612 6 58 07 ...

Страница 258: ...W PRESS Y PRESS LOFF 1 Q3A18 Q4A18 Y 1 Fuel Quantity Cylinder Head Temperature BLACK and Auxili ary Fuel Pump Circuit Breaker 3 Auxiliary Fuel Pump High Pressure MOT 2 Auxiliary Fuel Control Panel 4 Auxiliary Fuel Pump Low Pressure Q3A18N BLACK I V358 36923 FUEL BOOST PUMP Model F33C Issued Au6 ust 1971 6 59 ...

Страница 259: ...Flap Motor Circuit Breaker UPIC C3A14 i C3 2 Flap Control Switch 3 Flap Down Limit Switch C5A14 4 Flap Up Limit Switch C3B14WHITE I WIRE FURNISHED 5 F lap Motor GREEN BY VENDOR BLACK V358 369 24 FLAP MOTOR Models F33 G33 F33A and F33C 6 60 Issued August 1971 ...

Страница 260: ... T C17A20 C17B20 4 C19A20N PRINTED CIRCUIT BOARD o O o 3 O 1 Flap Position Indicator Circuit Breaker 2 Printed Circuit Board 2 O 3 Flap Position Indicator I OO O 4 Flap Position Transmitter 1 O V35 369 1 FLAP POSITION INDICATOR Models F33 033 F33A and F33C 6 61 Issued August 1971 ...

Страница 261: ...F LANDING WHITE 2 Landing Gear Control Switch UP GEAR AND RED 3 Landing Gear Up Brake Switch THROTTLE A 4 Landing Gear Down Brake Switch WARNING B DWN 5 Landing Gear Up Limit Switch 6 Landing Gear Down Limit Switch BLACK 7 Landing Gear Safety Switch 8 Landing Gear Motor G20A12N WIRE FURNISHED I3Y VENDOR LANDING GEAR WITHOUT SAFETY SYSTEM Model F33 CD 1235 thru CD 1254 vnss 369 a Model F33A CE 290 ...

Страница 262: ...cuit Breaker REF LANDING WHITE 2 Landing Gear Control Switch UP 3 Landing Gear Up Brake Switch GEAR AND RED h THROTTLE A 4 Landing Gear Down Brake Switch WARNING O DWN 6 Landing Gear Up Limi Switch 6 Landing Gear Down Limit Switch BLACK 7 Landing Gear Safety Switch 8 Landing Gear Motor G20A12N L WIRE FURNISHED BY VENDOR G33 369 81 LANDING GEAR WITHOUT SAFETY SYSTEM Model G33 CD 1255 thru CD 1304 M...

Страница 263: ...8A11 0 070812 1 I I I I 03A12 L ___ UP LIMIT SWITCH I I I I I I 015A20 i J t I 012012 r 03812 t 03A12 LL I__I ObiA12 I I 013320 DOWN LIMIT SWITCH 04B11 i WHITE 04A12 MOTOR n r NO1 1 068812 018020 BLACK 020A12N Q WIII VINISHID 81 VINDOL bGUH T NC SWITCH LNCJ_ __j 133 369 31 LANDING GEAR WITHOUT SAFETY SYSTEM Model F33A 05 535 thru 05 541 05 543 CE545 05 546 and CE 548 thru 05 612 Model F33C CJ 62 t...

Страница 264: ...2 C20A12N C12B12 L 13 Lalldin r Gear Safety Systcln S itcIl AIR 14 120 IPH Pressure Switch C L3hZO IPINO D I NOt IL1 lj Tllrotfle Coalrol Sn ilch G10X12 Y 16 IJandin Grnl Co ltrol SI itc h G10n17 I COM G18C20 AND THROTTLE GND WARNISC G12X12L t t G24A12 o NC UP I I I NO LATCHINC SOLESOID DWN r G3A12 VIRE FU INISHED I Y VESDOI f G6A12 G5A20 G12A12 I C 8 1312 I t I C8A12 I 1 I ir 7 T_ G7A12N G3A12 I ...

Страница 265: ...Safety System Switch MDICATOR DWN NO L A R 14 120 MPH Pressure Switch BAR LlAP O UP NO s NOt 15 Throttle Control Switch GIOA12 16 Landing Gear Control Switch G15A20 I I II Ct tt GIOCta e G10B12 1 COM 17 Fuse LANDING NC NC G1SCZO AND THROTTLE P G13A20 GND WARNING G24A12 I i r NC I G4B12 UP NO LATCHING SOLENOID DWN G3B12 WIRE FURNISHED BY VENDOR 10D12 ffcS 1L G5A20 C12A12 1 GBB12 f I GSA11 I I 1 i t...

Страница 266: ...b CIRCUIT BREAKER G12A12 I G68A12 G23AZO G3A12 G14A20 G6A20 GIAIZN FUSE SAFETY I GZZA20 G22B12 5 2 aFF r 4 3 G881Z A f G31L 12 G30AZON1 6 OFF r SAFETY RELAY ON 120MPH G8C1 DOWN PRESSURE THROTTLE CONTROL SWITCH CONTROL G56A12 SWITCH SWITCH DIODE LATCHINGSOLENOID GZ1A12 WIRE FURNISHED BY YENOOR GEinl N L___J i d NOTE CiRCUITSHOWhWITH AIRCRAFT ONGROUNDANDTHROTTLEOFF S0MPH PRESSURE SWI Cil G64AA12 G13...

Страница 267: ...SWITCHI 4 _I G1BB O G67A20 UP r c13Azo G13B20 G18C2D ftcean SAFETY SWITCH 61 CIRCVITBREAKER GIZAI I UBLIAIZ I I G23PZO G3A12 G14A20 I C G5AZO G7A12NPI FUSE I SAFETY SYSTEM 6A SWITCH GZZA O t C OFF o TEST 4 OZgA20 7bG30A2ON 6 1 3 e G31A12 L _U_ 1 OFF 1 ON I20MPH DOWN THROTTLE PRESSURE CONTROL SWITCH SWITCH CONTROL G56A12 d L TCHING S ILENOID SWITCH DIODE NI I IV RII O BY Y NOOR GzlAI2 oasnlzw L___ ...

Страница 268: ...m 1 5 1 I I I I i I L G47820 G47A20 SWITCH TYPE CIRCUIT BREAKER i I I I I 1 4 If I I I I I I C50D20 t G50A20 G44C20 m 6 3 DwN 1 Landing Gear And Throttle Warn Circuit CQ 1 Breaker 2 Navigation Lights Circuit Breaker m G33A20 21 m G32A20 e c32szo 3 Landing Gear Position Circuit Breaker 4 Warn Lights Test Switch 5 Warn Lights Dim Relay 2 I m 6 Landing Gear Position Lights 1 m G33B20 Gear In Transit ...

Страница 269: ... i I I I I p ti tJ LG36A2Ci t G36B20 t J I I 0 f LH m 5 G47B20 f G17X20 SWITCH TYPE CIRCUIT BREAKER G57A20 Z G26f320 0 4 j G50B20 t G OA20 G4 3C20 m 3 1_ w 1 1 Landing Gear And Throttle Warn Circuit 1 Breaker IP G6C20 G33A20 2 Navigation Lights Circuit Breaker 2 1 m G32A20 t G32 B20 3 Landing Gear Position Circuit Breaker 4 Warn Lights Test Switch TO LANDING m 6 Landing Gear Position Lights 1 hi G...

Страница 270: ...G54D20 G54C20 G47 820 C G47A20 SWITCH TYPE CIRCUIT BREAKER I I I I I I i G57A20 G26B20 Z 4 INO G50B20 t G50A20 54F20 I 1 5 6DWN L 1 Landing Gear And Throttle Warn Circuit 1 Breaker G3 3A20 2 Navigation Lights Circuit Breaker G6C20 2 3 Landing Gear Position Circuit Breaker h G32A20 G32B20 4 Warn Lights Test Switch I I I TOLANDING 2 Im 5 Warn Lights Dim Relay GEAR I I L G33B20 6 Landing Gear Positio...

Страница 271: ...C GND G13B20 G28A20N G13A20 G27A20 I Landing Gear and Throttle Warning Circuit Breaker Ca 2 Throttle Control Switch UP 3 Flasher 4 Landing Gear Safety Switch 5 Landing Gear Warning Horn DOWN 8 Landing Gear Control Switch G33 369 80 LANDING GEAR AND THROTTLE WARNING Model F33 CD 1235 thru CD 1254 Model G33 CD 1255 thru CD 1289 Model F33A CE 290 thru CE 547 except CE 545 and CE 546 Model F33C CJ 26 ...

Страница 272: ...THROTTLE 5A CONTROL SWITCH NC O NOG18A20 REFrLANDINGGEA CLOSED FLASHER XG18B20 G18C20 f G68B12 G69A 1 2 j I G27A2o RSQUAT L SWITCH I__ ____1 G28AZON I G13B20 LANDING DN 6 CISXIU LANDING GEAR GEAR CONTROL J WARNING L HORN F33 369 319 LANDING GEAR AND THROTTLE WARNING Model F33A CE 545 thru CE 612 except CE 547 Model F33C CJbP thru CJ 66 CJ 69 thru CJ 74 and cJ n thru CJ 104 C7 6 65 ...

Страница 273: ...P14I318 r T I y I P15A4 1 G F TO POWER DISTRIBUTION T 1 Generator Circuit Breaker 2 Voltage Regulator PllA6 3 Generator Switch 4 Generator 5A P14A18 P10A4 P15A4 BFG F33369 93 GENERATOR 35A Model F33 6 66 Issued August 1971 ...

Страница 274: ... 60A P10A6 P 1A6 P10A18 I G33 1 Alternator Field Circuit Breaker 2 Alternator Switch 9 Voltage Regulator 4 Alternator 5 Capacitor 6 Alternator Circuit Breaker 033 38479 ALTERNATOR Optional Model 933 CD 1235 thru 00 1254 Model 033 CD 1255 thru 091 1279 except CD 1276 Is ued December 1972 6 66A ...

Страница 275: ...WER F DISTRIBUTION A T Pl1A4 60A P10A6 tP11AG I P10A18 71 G33 i Alternator Field Circuit Breaker 2 Alternator Switch 3 Voltage Regulator 4 Alternator 5 Capacitor 6 Alternator Circuit Breaker G35369 105 ALTERNATOR Model 033 CD 1276 CD 1280 thru CD 1304 6 660 CQ ...

Страница 276: ...TO LANDING GEAR 5 L49A20 L POSITION INDICATOR A P14A16 I 3A I OFF P13A20 B P12A20 v P13B20 C I P17A20N I ON m J r F33n 3sossn 1 Bus 2 Alternator Field Circuit Breaker 3 Navigation Lights Circuit Breaker 4 Alternator Out Circuit Breaker 5 Alternator Circuit Breaker 6 Alternator 7 Alternator Master Switch 8 Fuse 9 Overvoltage Relay 10 Low Voltage Sensor 11 Alternator Out Light 12 Warning Light dim R...

Страница 277: ... I POSITION INDICATOR P14A20 A I OFF P13A20 3A B P12A20 P13B20 C C P17A20N 1_ I P ON 1 Bus 2 Alternator Field Circuit Breaker 3 Navigation Lights Circuit Breaker 4 Door and Alternator Out Circuit Breaker 5 Alternator Circuit Breaker 6 Alternator 7 Alternator Master Switch 8 Fuse 9 Overvoltage Relay 10 Low Voltage Sensor 11 Alternator Out Light 12 Warning LightDim Relay 13 Diode 14 Warning Lights S...

Страница 278: ...A16 P13A20 I B P12A20 Arl P13A20 I C i 7 m P17A20N 1 F33A 369 107B CJ 52 AND AFTER ONLY CE 489 AND AFTER EXCEPT CE 511 AND CE 512 CJ 52 AND AFTER 1 Bus 2 Alternator Field Circuit Breaker 3 Navigation Lights Circuit Breaker 4 Alternator Out Circuit Breaker 5 Alternator Circuit Breaker 6 Alternator 7 Alternator Master Switch 8 Fuse 9 Overvoltage Relay 10 Low Voltage Sensor 11 Alternator Out Light 12...

Страница 279: ...313 FUEL SELECTOR LIGHT Model F33A CE 290 thru CE 464 Model F33C CJ 26 thru CJ 51 TO ALTERNATOR L6B20 WHITE WHITE IIL6C20N9 FUEL SELECTOR LIGHT L6A20N I f33 369 312 FUEL SELECTOR LIGHT Model 5334 CE 465 thru CE 612 Model F33C CJ 52 thru CJ 104 6 68B C7 ...

Страница 280: ...enlblg 6 Deice Boot L 7 Brush Dlocle 8 Bus PROPELLER DEICE THREE BLADED Models F33 G33 F33A and F33C r P IEl LH25A10I H14A10H15A10 B 1 H17A14 C H18A14 D H19A14 1 E H21A14 F H23A14N A B C H20A14 1 V358 369 43 Y I A H22A14 c H16A16N i Prop Deice Circuit Breaker 2 Ammeter 3 Connector 4 Timer 5 Slip Ring Assembly P 6 Deice Boot 7 Brush Block 8 Bus PROPELLER DEICE TWO BLADED Models F33 G33 F33A and F33...

Страница 281: ...AD E42A20N AND E44A20N FUEL OUANTITY DO NOT GROUND ANY OTH ER WIRES AT TH IS POINT i Cylinder Head and Oil Temperature Circuit Breaker 2 Cylinder Head OilTemperature and Oil Pressure Indicator 3 Cylinder Head Temperature Transmitter Bulb CVLINDER HEAD TEMPERATURE INDICATOR Models F33 G33 F33A CE 290 thru CE 349 and F33C 6 70 Issued September 1971 ...

Страница 282: ... TEMPERATURE E39A20N CYLINDER HEAD TEMPERATURE E42A20N AND E44A20N FUEL OUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT i Breaker 35 369 73 2 Cylinder Head Temperature Indicator 3 Cylinder Head Temperature Tranrmitter CYLINDER HEAD TEMPERATURE INDICATOR Vertical Instruments Model F33A CE 350 thru CE 408 Issued December 1972 6 704 ...

Страница 283: ...e Indicator 3 Oil Temperature Transmitter Bulb GROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N CYLINDER HEAD E42A20N AND E44A20N FUEL OUANTITY DO NOT GROUND ANY OTH ER WI R ES AT THIS POINT 01L TEMPERATU 11 E I ND ICATO R Model F33 CD 1235 thru CD 1254 Model G33 CD 1255 thru CD 1304 Model F33A CE 290 thru 65 349 Model F33C CJ 26 thru CJ 51 6 700 r Cg ...

Страница 284: ... 2 Oil Preriure Indirator 3 Oil Temperature Indirotor 4 Oil Preirure Tranrmi er 5 Oil Temperature 35 369 74 Y GROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N OIL TEMPERATURE E30A20N CYLINDER HEAD TEMPERATURE E42A20N AND E44A20N FUEL QUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT OIL TEMPERATURE AND OIL PRESSURE INDICATOR Verticel Instruments Model F33A CE 350 thru CE 408 Issu...

Страница 285: ...IL TEMP 4 E4OA29N E31A20 I OIL TEMP TRANSMITTER BULB E33A20N 1 1 OROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT ESIA1ON CYLINDER HEAD E42A29N AND E44A20N FUEL QUANTITIJ DO NOT GROUND ANY OTHER WIRES AT THIS POINT F33R388299 CYLINDER HEAD AND OIL TEMPERATURE INDICATOR Model F33A CE 409 thru CE 612 Model F33C CJ 52 thru CJ 104 C7 6 70D ...

Страница 286: ...A20 RED s E28A20 L70A20 L e WHITE TO ENGINE INSTRUMENT LIGHTS i Ciriuit Breokor 2 Manifold Pre rure IndiIo or 3 Manifold Prariure 35 369 72 MANIFOLD PRESSURE INDICATOR Vertical Instruments Model F33A CE 350 thru CE 408 6 70E Issued December l972 ...

Страница 287: ...O_i BLACK El 4 C F24426 R 5 E25A20 L71A20 WHITE L TOENGINEINSTRUMENT LIGHTS i Circuit Breoker 2 Fuel Flow Indico or 35 369 71 3 Fuel Flow Tranrducer FUEL FLOW INDICATOR Vertical Instruments ModelF33A CE 350 thru CE 408 6 70 5 Issued December 1972 ...

Страница 288: ...4 BLACK 1 111 1 I El L72A20 WHITE TOENOINEINSTRUMENT LIGHTS I Circuit Breaker 2 Tachometerlndicator 3 Tachometer Pickup Probe 35 3 9 77 TACHOMETER Vertical Instruments Model F33A CE 350 thru CE 385 6 706 Issued December 1972 ...

Страница 289: ...l 20 I 4 BLACK 1 III ill IIP L72LL20 _1 i WH17E I TOENGINEINSTRVMENT LIGHTS i Cirtuif Breok r 2 3 Ta hom tsr PiIkup Probe 35 369 77 4 Rerir or TACHOMETER Vertical Instruments Model F33A CE 386 thru CE 408 0 70H Issued December 1972 ...

Страница 290: ...ERATURE Model F33 CD 1235 ti ru Cr13 1254 Model G33 CD 1255 thru 00 1904 Model F33A CE 290 thru CE 349 CE 409 thru CE G1P Model F33C cJ ns thru CJ 104 r45a2ou I C RED 1 9 YELLOW 3 INITIIVMINT REPLACEMENT PARTS MUST BE IDENTICAL OR ENTIRE UNIT MUST BE REPLACED i EOT Indito or 2 EGT Bulb 35 369 70 EXHAUST GAS TEMPERATURE INDICATOR Vertical Instruments Model F33A CE 350 thru CE 408 c7 6 701 ...

Страница 291: ...15A eL25A14 01 L25814 L27A14N L26A14N I i i Rotating Beacon Circuit Breaker 2 Upper Rotating Beacon 3 Lower Rotating Beacon ROTATING BEACON Models F33 G33 F33A and F33C Issued September 1971 6 71 ...

Страница 292: ...0 O L32B20 L31B20 10 I I v i i Cabin and Map Lights Circuit Breaker OPTIONAL 2 Compass and OAT Light Switch 3 OAT Light 4 Glareshield Connector 5 Compass Light 6 Cabin Light Switch 7 Cabin Light 8 Reading Light Switch 9 Reading Light 10 Map Light Switch 11 Map Light V358 369 50 CABIN AND MAP LIGHTS Model F33 CD 1235 thru CD 125Q Model F33A CE 290 thru CE 349 Model F33C CJ l thru CJ 30 6 72 ssued D...

Страница 293: ...20N I L108A20 FOURTH SEAT 1 Cabin and Map Lights Circuit Breaker READING LIGHT 2 Cabin Lights S c itch 3 Light 4 Reading Light Switch 5 Reading Light 8 Coiled Cord 7 Light Switch 8 Glareshield Connector L101 20N 9 Compass Light 10 OAT Indicator Light L100D20 1L Map Light Llosazo FIFTH SEAT OPTIONAI READING I IGHT SWITCH 031 P 991 CABIN AND MAP LIGHTS Model F33 CD 1255 thru CD 1304 Model F33A CE 35...

Страница 294: ...1 Cabin and Ma Lightr Circuit Breaker FDURTH SEAT 2 Cabin Lights Scvic h READING LIGH7 3 Cabin Light 4 Reading Light Switch 5 Aeabing 6 Coiled Cor 7 Light SWifCh 8 Clarerhield Connector 1P L100020 It Map Light L101020N READING LIGH T OPTIONAL I I O L SWITCH SIXTH SEAT REI DING LIGHS LIO E10N iap rlov rl 0 L11OA20 Falas eln CABIN ANB MAP LIGHTS Model F33A CE 360 thru CE 612 Model F33C CJ91 th u CJ ...

Страница 295: ...O le L2F20 L2G20 i Flood Lights Circuit Breaker 2 Dim Contro Rheostat 3 Dim Control Tranaistor 4 Trim Tal Light 5 L d Gear Visual Li ht fj Fuel Select Light 7 Clr ck Light Optional 35369109 8 I lareshic ld Connectot y C larc shield Flood Ligtis INSTRUMENT FLOOD LIGHTS Model F33 CD 1235 thru CD 1254 Model F33A 05 290 thru 05 349 Model F33C CJ 26 thru CJ 30 C1 6 72C ...

Страница 296: ... L102E20 I I L103B20N 0 I L102F20 L102G20 i Flood Lights Circuit Breaker 2 Dim Control Rheostat 3 Dim Control Transistor 4 Trim Tab Light 5 Landing Gear Visual Light B 6 Not Used vn a 369 51 7 Not Used 8 Glareshield Connector 9 Glareshield Flood Lights INSTRUMENT FLOOD LIGHTS Model G33 CD 1255 thru CD 1304 Model F33A 05 350 thru CE 469 6 72 63 ...

Страница 297: ...102C20 I L103B20N O L L102C20 L102C20 1 Flood Lights Circuit Breaker 2 Dim Control Rheostat 3 Dim Control Transistor 4 Trim Tab Light 5 Landing Gear Visual LigM 88 6 Not Used v35e3as 54s 7 Not Used 8 Glareshield Connector 9 Glareshield Flood Lights INSTRUNIENT FL000 UGHTS Yodel F33A CE470 thru CE 612 Model F33C CJ 52 thru CJ 104 C7 6 73 ...

Страница 298: ...O LH FUEL QUANTITI 8LACK I WHIIE L L lo oi RH FULL OUANTITY I LACK WHITE i Rodio ond Lighll Cirruil r oL r O O r i Din Con rollh ol t A MMETER i DilnlControl Irclnli or 4 Omni Lioh l 5 181481 Liph 6 611 No 3 1 8ur No 4 OMNI LIGHTS CONNECTED TO FLIGHT INSTRUMENT DIMMING WHEN OPTIONAL IIIOH1INS IIUM1NI LIGHTS INSTALLED OU 38986A ENGINE INSTRUMENT WEDGE LIGHTS Model F33 CD 1235 thru CD 1254 Model G33...

Страница 299: ...IOP QUANTITy r II ANTI ICE I PRESSURE J LHFUEL QVANTITY i 8ur No l 2 Bur No l TP CHOM TER EI 9 Po t Light 4 Omni Lighfr L84B20 OMNIINDICIIOR LIGHTS II CONNECTED TO FLIGHT INSTRUMENT LIGHT CIRCUIT IF OPTIONAL FLIGHT INSTRUMENT LIGHTS ARE INSTALLED G33 369 84 A ENGINE INSTRUMENT POST LIGHTS Models F33 G33 F33A CE 290 thru CE 349 and F33C Issued September 1971 6 74 A ...

Страница 300: ... LbBe 20 h ro oprloua B C L80A20 j FLIGHT INSTRUMENT L73820 OIL TEMP F L69P 202 DIMMING O TACHOMETER L72A20 L73C20 LB0A20 r FUEL FLOW I L71AZ AMMETER 5 L64A EGT L74A20 L73D20 LH FUEL OUANTITYI L65A20 1 Cir uit Bre ker L80820 2 Rheos t Rodio nd Engine Instrument Dimming OMNI II r 3 Tr nsir or R dio end Engine Instrument Dimming g cr t ora HEAD TEMP Lb7b 2O 7 L73 20 4 lerirtor En9inF Inrtrumlnl Ligh...

Страница 301: ...RE LBOI BLACK 00 WHITE L 1I TACHOMETER OMNI 1 OMNI 2 ACK WHITE 00 LH FUEL OUANTITY BLACK WHITE 00 RH FUEL OVANTITY BLACK lo oi WHITE I Rodio ond Inilrum nt Liphti Cirruit k a r O O L86A20N 2 Dim Control Rhooitot AMME ER r 3 Dim Control Tron iitor Omni Lighh 5 Wodp Ligh i n CONNECTI TO TuOn7 INlrRUMPNT DIMMING WHEN OPTIONAL FLIGHT INSTRUMENT LIGHTS INSTALLED 033 38985A ENGINE INSTRUMENT WEDGE LIGHT...

Страница 302: ...D FUELrRESSU E BU WHITE TACHOMETER OMNII OMNI1 Bt WHITE LH FUEL OUINIITI L CK Btfi WHITE INSTRLIGHTS 71 L84 10 RH FUEL OUANTITI LIGHT GND 8 L86B10N 1 Radio and Inltrul nt Li lhll Clr uil 1 Dir Con rollh ol at 5 Ois Control Tranciltor 4 Olnni Light 5 Rul No 3 i ul No m I LIOHT INSTIUMINI Inttrula nt Clu r DIMMING WHEN OPTIONAL FLIGHT INSTRUMENT LIGHTS INSTILLED G33YB86C ENGINE INSTRUMENT LIGHTS Mod...

Страница 303: ...N 01 100 L12B20 LBZA20N VERTICAL SPEED 1 L6F20Lb020 BLACK rWHITE 3 L1 L82CZON O b L12A20 AIR PRESSURE L12A20 L12P20 LI O I I TO RADIO AND L30A20N INSTRUMENT LIGHTS L 1 Wedge Lighl 2 Bur No 1 3 Bur No 2 033 369 86 4 Flop Pori ion 5 Trim 70b Light 6 Lending Gear ViruaI Light 7 Clo k FLIGHT INSTRUMENT WEDGE LIGHTS OPTIONAL Model F33 CD 1235 thru CD 1254 Mofel G33 CD 1255 thru CD 1304 Model F33A CE 29...

Страница 304: ...K t L1 D WHITE 3 L6F20 LB C DN L L12C20 UZA20 C6020b AlR PRESSURE IP bl L90 20 LllC20 L30A20N I W dp Li ht 6 L ndinl O r Vilu l Liph tC 2 I 2 Bui No 1 7 ClocL 3 Bui No 2 8 Dimminp Troniiilor I b L46820 L46A20 p 4 Flop Poii ion 9 Rh oila L45A20N I L44A20 5 Tiim Tab Li lh 10 Radio and In trum n Lighle Cirruil I r o r rC 11 Omni fndicator Lamp TO ENGINE G3338886C 12 Conltol Wh l CIDIL Poll Li ht INST...

Страница 305: ...0 L L L TO OPTIONAL To ol FLIGHT yL80A20 j INSTRUMENT MANIFOLD AND FUEL LIGHTS PRESSURE LB0B20 OMNI LIGHTS BLACK WHITE ek D oO TACHOMETER OMNI 1 OMNI 2 BLACK WHITE 00 LH FUEL OUANTITY BLACK WHITE 00 RH FUEL OVANTITY BLACK 7 L84820 B lo ol LB6AZON AMMfTER r INSTR LTS 7 GND 8 L86B20N II I l n O r INIIRVMINr INSTRUMENT DIMMING WHEN OPTIONAL FLIGHT INSTRUMENT CLUSTER LIGHTS INSTALLED F33A 369 298 OPTI...

Страница 306: ...ACK WHITE LBOA20 d r0 OPrlDNPII O O FLIGHT MANIFOLD INSTRUMENT LIGHTS AND FUEL PRESSURE LB0B20 OMNI LIGHTS BLACK WHITE PI 00 TACHOMETER OMNI 1 OMNI 2 BLACK WHITE 00 LH FUEL OUANTITY BLACK Go o WHITE 00 RH FUEL OUANTITY BLACK Cllo 3 WHITE LB4820 00 8bA20N AMMETER r INSTR LTS 7 GND 8 LB6B20N P ENGINF n INSTRUMENT DIMMING WHEN OPTIONAL FLIGHT INSTRUMENT CLUSTER LIGHTS INSTALLED F33A 369 298A OPTIONAL...

Страница 307: ...OF CLIMB B I HORIZON FLAP POSITION CLOCK LB0A20 DIREtTIONAL OYRO s J180810 P i BUS NO 1 2 BUS NO 2 OMN12 OMNII 3 POST LIGHT 4 RADIO AND INSTRUMENT LIGHT CIRCUIT BREAKER 5 RHEOSTAT 6 DIMMING TRANSISTOR G33 368 31 PLIGHT INSTRUMENT POST LIGHTS Model P33 CP1235 thru CP1254 Model 433 CP1255 thru CP1304 Model F33A CE 350 thru CE474 Model F33C CJ l thru CJ 52 07 6 74 ...

Страница 308: ...O lbrs O CLIMB I El HORIZON FLAP POSITION IEl CLOCK LBOA20 El rDl rCTION4L GlsO r M i BVS NO 1LBOB20 P 2 BUS NO 2 OMN12 OMNII 3 POST LIGHT 4 RADIO AND INSTRUMENT LIGHT CIRCUIT BREAKER S RHEOSTAT G33 369 838 6 DIMMING TRANSISTOR FLIGHT INSTRUMENT POST LIGHTS Model F33A 05475 thru CE 612 Model F33C CJ 53 thru CJ 104 07 6 75 ...

Страница 309: ...IT SWITCH PANEL BREAKER PA JEL IP I I PANEL V358369 57 i Flood Lights Circuit Breaker 2 Electroluminous Panel Lights Dim Transistor 3 Dim ControlRheostat 4 Inverter 5 Electroluminous Panel ELECTROLUMINOUS PANEL LIGHTS Model F33 CD 1235 thru CD 1254 Model G33 CD 1255 thru CD 1304 Model F33A CE 290 thru CE 469 Model F33C CJ 26 thru CJ 51 6 76 C3 ...

Страница 310: ...ER L5E20N CIRCUIT L5D20N BLACK BLACK BLACK L5F20N e RH SWITCH PANEL BR AKER PANEL I PANE L V35B38957A i Flood Lights Circuit Breaker 2 Electroluminous Panel Lights Dim Transistor 3 Dim Control Rheostat 4 Inverter 5 Electroluminous Panel ELECTROLUIIIIINOUS PANEL LIGHTS Model F33A CE 470 thru CE 612 Model F33C CJ 62 thru CJ 104 C7 6 76A ...

Страница 311: ...itch Trim and Ignition Boost Circuit Breaker 2 Control Column Coil Cord 3 Control Switch 4 Trim Actuator Assembly 5 Shunting Resistor 6 Speed Adjust Resistor 7 Pitch Trim Switch ELEVATOR TRIM OPTIONAL Model F33 00 1235 thru CD 1254 Model 033 CD 1255 thru CD 1304 Model F33A CE 290 thru 05 469 Model F33C CJ 26 thru CJ 51 6 766 63 ...

Страница 312: ...I IP ____ D 1711 ONLI BLACK BLACK 1 Pitch Trim and Ignition Boort Circuit Brsoker 2 Control Column Coil Cord 3 Control Switch 4 Trim Actuotor Aiiemblv 5 Shunting R i or F33A 6 Sp d Adiuct Rerirtor F33A 7 Pitch Trim Switch ELEVATOR TRIM Model f33A CE 470 thru 06 612 Hodel F33C CJ 52 thru CJ 104 07 6 77 ...

Страница 313: ...BLACK WHITE oio OFF V35369 60 i Avionics Bus 2 Constant Copilot Solenoid Valve 3 Constant Copilot Switch 4 Constant Copilot Wheel Switch 5 Constant Copilot Autopilot Circuit Breaker CONSTANT COPILOT OPTIONAL Models F33 G33 F33A and F33C 6 78 Issued August 197 1 ...

Страница 314: ...33 590011 10 12 BLANK PAGE Issued September 1971 6 78A ...

Страница 315: ...D WHITE WING LAMP CABLE ASSEMBLY Al RED I I A B WHITE I C BLACK I WING LAMP CABLE ASSEMBLY A RED B WHITE REFER 70 NAVIGATION LIGHTS C BLACK 1_ L36BC2 POWER SUPPLY BLAC f RED1 RANGE WHITE BLUE F33A 369 96A TAIL CONE LAMP ASSEMBLY STROBE LIGHT GRIMES OPTIONAL Models G33 and F33A 6 788 1 C1 ...

Страница 316: ... Supply V35 369 63 3 Strobe Light STROBE LIGHT HOSKINS OPTIONAL Models F33 G33 F33A and F33C I L76A20 2 L76B20 4 L79B20N WHITE BLACK RED 01 i Strobe Light Circuit Breaker 2 Power Supply 3 Strobe Light V358 369 62 STROBE LIGHT BULLOCK OPTIONAL Models F33 G33 F33A and F33C 6 79 Issued August 1971 ...

Страница 317: ... C IA TO ALTERNATOR P20B20 P19C20 8A20 QgA2O i Diode 2 Resistor 3 Fuel Boost Indicator 4 Fuel Boost Pressure Switch 1 3 4 2 BRIGHT DIM TEST SIGNAL F33C 369 95 FUEL BOOST LIGHT Model F33C 6 80 Issued August 1971 ...

Страница 318: ... LIGHT OPTIONAL Model 533 CD 1235 andu CD 1254 Model G33 CD 1255 thru CD 1304 Model F33A CE 350 thru CE 464 Model F33C CJ 26 thru CJ 51 L81B20 2A L81D20 BLACK BLACK L81E20 V36B36967A 1 Battery Bus 2 Courtesy Light Fuse 3 Courtesy Light Switch 4 Courtesy Light couRrEsv LIGHT OPTIONAL 6110401 6224 CE 465 thru CE612 622C CJ 52 thru CJ 104 6 81 C7 ...

Страница 319: ...VERVOLTAGE RELAY AMPLIFIER O P54A18N 046818 i P47A4 P39P 18 r61 2 P46A4 I I psoa18N P5SB18 TRANSPONDER STANDBY 4cn COMM NAV COMM NAV GENERATOR L 1 2 2 I O O r RESISTOR 041018 NAV COMM 1 P411B181 REISIX RI I P 3Cls I LITRANSISTOR TO 20 GA NAV 2 053818 ZE UER DIODE DIODE zocn P54n p52A18 i 1 TERMINAL TO BOARD 20 GA NAV 1 20 GA I ToAVlONlcs 041018 TO L GROUNDED TO I I II TRANSISTOR 20 GB COMM 2 STRUC...

Страница 320: ...N DIODE L INDICATOR TO k H33F18 eH33C1 LANDING I OEPIR 070P112 LLrS S H31C18 HJ 1118 r O LH SOUAT FLIGHT POSITION H40A10 SWITCH SWITCH 4 1 PARTIAL OPEN H30B18 s I I CLOSED 10 3 RED 11 I H3BA20 CONDENSORI RC42CF OOR 7 K H31A1B 0 H39A I_WH17E CTUATOR 2 CONDENSER sl rx I P19D20 101 P19820 DOOR LIGHT L _ _ OPEN _I r 6 RESISTOR 9A20 1 P20A20 r CONDENSER b 1 LH LANDING GEAR 4 aoa OPEN LIGHT POSITION SWI...

Страница 321: ...SECTION R E P LACEIVI E NT SCHEDULE ...

Страница 322: ...SECTION 7 II Replacement Schedule ...

Страница 323: ...he operator has an NOTE approved monitoring system The required periods do not constitute a The time periods for inspections noted in this manual are guarantee the item will reach the period without based on average usage and average environmental malfunction as the aforementioned factors conditions cannot be controlled by the manufacturer NOTE SPECIAL CONDITIONS CAUTIONARY NOTICE On condition ite...

Страница 324: ... hours or on condition Shimmy dampener Every 1000 hours Wheels and tires On condition Brake assembly On condition Master cylinder On condition Shuttle valve assembly On condition Parking brake valve On condition All hose On condition Power Plant Engine Every 1500 hours Engine controls On condition Engine vibration isolator mounts At engine change Exhaust system On condition Starter Overhaul at eng...

Страница 325: ...intake filter Every 500 hours All hose Hoses carrying flammable liquids at engine overhaul or every 5 years All other hoses on condition Vacuum pump Every 1200 hours Flaps And Flight Controls Flight Controls On condition Elevator tab actuator On condition Flap motor and drives Every 2000 hours Flap motor brushes On condition Flap gearbox Every 2000 hours Flap actuators Every 2000 hours Flap flexib...

Страница 326: ...ments Turn coordinator On condition Altimeter Every 24 months per FAA directive Inspect and calibrate Directional gyro On condition Gyro horizon On condition Gyro pressure gage On condition Engine gage units On condition Airspeed indicator On condition Rate Of Climb On condition Fuel flow manifold pressure indicator On condition Tachometer On condition Clock On condition Flap position indicator On...

Страница 327: ...iscellaneous Hand fire extinguisher Inspect every 12 months recharge as necessary Cabin heating and ventilating ducts On condition inspect every 12 months Heater muff On condition Oxygen regulator On condition Oxygen cylinder Light weight ICC 3HT 1850 Hydrostatically test every 3 years or replace every 24 years or 4380 fillings ICC Regulation Oxygen cylinder Heavy weight ICC 3AA 1800 Hydrostatical...

Страница 328: ...EM OVERHAUL OR REPLACE Miscellaneous Cont d Wing bolts Replace 10 years after the initial inspection or on condition See Section 4 Refer to Teledyne Continental Motors Service Bulletin M74 20 Rev I dated November 7 1974 or later issue 7 6 C16 ...

Страница 329: ...SECTION PERIODIC INSPECTIONS ...

Страница 330: ...SECTION 8 Periodic Inspections ...

Страница 331: ...le diameter is greater than 251 inboard hinge mount hole inch replace elevator torque in center of elevator fitting torque fitting Check elevator rod end If hole diameter is greater than 379 mounting hole in the inch ream to 436 inch 001 elevator torque fitting inch and install one for proper diameter BS 105740 X XC 0500 bushing 3 i 50 Horizontal and vertical I Horizontal stabilizer If bolt holes ...

Страница 332: ...r cracked Hours and cracks Check rod end bearing for I Replace rod end bearing if excessive freeplay excessive freeplay is noted Check rod end mounting If more than 378 inch in diameter hole diameter replace rod end 8 50 Trim Tab Check for cracks Replace if noted conditions exist Hou rs Check freeplay as indicatedl Replace tab bushing and or tab in Chapter 27 30 00 pushrod ends andlor trim tab act...

Страница 333: ... Bolt elevator pushrods Check for straightness and Replace if bent or worn smaller Hours to elevator bell crank wear than 370 14 50 Inboard elevator hinge Check for cracks Check Replace if noted conditions exist Hours casting hinge bearing for looseness C13 8 3 ...

Страница 334: ...in the performance of inspection In the final analysis it is the responsibility of the his duties As the one primarily responsible for the owner or operator to ensure that the airframe and airworthiness of the airplane the owner or operator should powerplant mechanic inspecting the airplane has access to select only qualified personnel to maintain the airplane the previously noted documents as wel...

Страница 335: ...heck for proper indication and unusual fluctuations 12 H EATING AN O VENTI LATINO SYSTE M Check for proper operation heat and airflow output Check controls for freedom of operation 13 FIREWALL SHUTOFF VALVE Check for proper operation and freedom of movement 14 IDLE RPM AND MIXTURE SETTINGS Check for both proper rpm and mixture settings Check controls for freedom of operation 15 IDLE CUT OFF Check ...

Страница 336: ...ONER Operate the air conditioner and verify that the retractable condenser moves to the ground extended position when tu rned on and retu ms to the retracted position when tu rned off Check for proper operation and unusual noise 30 OXYGEN SYSTEM Functionally check the oxygen system for proper operation Check the oxygen bottle shutoff valve for proper operation 31 SWITCHES CIRCUIT BREAKERS Check fo...

Страница 337: ...S Check for condition and security Check the tip of the blades for evidence of lightning strikes If there is evidence of lightning strikes consult the propeller manufacturer the eng ine manufactu rer and Beech Ai rcraft Corporation Inspect the blades for cracks dents nicks scratches erosion corrosion security and movement in the hub 15 PROPELLER SPINNER Check for deformation security and cracks 16...

Страница 338: ...rol arm for security I 1 31 ENGINE CONTROLS Check controls and associated equipment for condi ion attachment alignment and rigging Every 300 hours remove the cable connec tion bolts and check for weer 32 IGNITION HARNESS Inspect for fraying and attachment 33 ELECTRICAL WIRING AND EQUIPMENT Inspect electrical wiring and associated equipment and accessories for fraying and attachment 34 ALL DRAINS A...

Страница 339: ...rt Check for security and attachment D Check deicer boots for wrinkles loose or torn areas C CABIN AND BAGGAGE COMPARTMENT MECH INSP 1 SKIN Inspect skins for deformation cracks and loose or missing rivets If damage is found check adjacent structure 2 STRUCTURE Check for cracks and deformation Check for loose or missing rivets and concealed damage 3 CABLES AND PULLEYS Inspect for condition attachme...

Страница 340: ...mounts ground straps for cracks and security 15 SEATS SEAT BELTS AND SHOULDER HARNESSES Inspect cabin seats seat belts and shoulder harnesses for proper operation condition and security of attachment Inspect floorboards for condition and seat attachment Check for operation of the seat stops 16 OXYGEN SYSTEM Check condition of the oxygen system and check the oxygen masks for cleanliness and stowage...

Страница 341: ...ING Check for leakage chafing condition and security 8 ELECTRICAL WIRING AND EQUIPMENT Inspect far chafing damage security and attachment 9 FLAP LIMIT SWITCHES Check for condition and security freedom of operation 10 FLAPS AND ACTUATORS Check for condition security binding or chafing of actuator cables Check flap skin and structure for cracks loose or missing rivets Check roller bearings and track...

Страница 342: ...ondition and proper clearances and attachment 10 VISUAL INDICATOR Check for condition F MAIN GEAR AND BRAKES MECH INSP 1 BRAKE LINES LINING AND DISCS Check for condition wear and security Check lines for chafing and signs of leakage or cracks Check discs for wear or warping Check brake discs for cracks 2 WHEELS AND TIRES Check wheels for cracks and tires for wear damage condition and proper inflat...

Страница 343: ...sion and for possible fraying 5 EMERGENCY EXTENSION Check system for freedom of operation and positive engagement of the downlocks Check for unusual noise 6 DOWNLOCK TENSION Check for proper deflection force on the main gear knee joints 7 UPLOCK ROLLERS Check condition and clearance of uplock rollers and lubricate as indicated in the appropriate Shop Manual Check for binding 8 LIMIT SWITCH RIGGING...

Страница 344: ...complete landing gear system 5 VISUAL INDICATOR Inspect for proper adjustment and operation 6 NOSE GEAR STEERING Check for condition and security I REAR FUSELAGE AND EMPENNAGE MECH INSP 1 SKIN Check for deformation cracks and obvious damage Check for loose or missing rivets If damage is found check adjacent structure 2 INTERNAL FUSELAGE STRUCTURE Check for cracks and deformation Check for loose an...

Страница 345: ...ff power Turn the deicer systems switch ON and observe doors pertaining to the wiring and components of the deicer the nmmeter for at least 3 minutes If the ammeter needle system Turn the deicer switch ON and station an assistant does not rest within the shaded band except for a flicker at in the cockpit to observe the system ammeter Flex all ac 10 second intervals when the step switch of the time...

Страница 346: ...h danger of a cylinder firing wllcn a propeller is solvent a product of Corrosion Reaction moved Cunsu I tan ts Inc of Philadelphia Pennsylvania A ftcr such a cleaning allow a run in time of 5 hours of engine operation before turning on the deicer system CA UTION f If uneven wear or wobble is detected check the alignment of the slip rings to the prop shaft with a dial indicator While turning the p...

Страница 347: ...h lft for SPEED distortion C Check the points of actu ltor attachment to both I Check flap rollers and bolts for visible damage and the wing and the flap for cracks and distortion di roriion d Check the skin for cracks and distortion h Check fl p fles drive ends 11 the motor and ac C13 8 17 ...

Страница 348: ...35 SERIES SHOP NIANUAL ...

Страница 349: ...Raytheon Aircraft Company 3eechcraft BONANZA 35 SERIES D l thru D 10119 except D 10097 Shop Manual ...

Страница 350: ...pany The export of these commodoties technology or software are subject to the US Export Administration Regulations Diversion contrary to U S law is prohibited For guidance on export control requirements contact the Commerce Department s Bureau of Export Ad ministration a 202 482 4811 or at www bxa doc gov aiymeee 3 Member ot GAMA Aircraft Company O nera rarlalon CA HA Manufacturers Association ...

Страница 351: ...OF REVISIONS 35 Series MFG REV NO DESCRIPTION ISSUE DATE ATP REV DATEI INSERTED BY 819 See Highlights 3 22 96 2 23 98 ATP MB 820 See Highlights 9 3 01 1 9 02 ATP RCL 821 See Highlights 8 29103 10 29103 ATP JB ...

Страница 352: ...d By No Datelnoerted By No Datelnserted By f319 2 25 98 MB ATP B20 1 9 OF RCL P I U1 B 03 When a revision is inserted the revision number the date the revision is inserted into the manual and the initials of the person s inserting the revision should be recorded on this page ...

Страница 353: ...RECORD OF TEMPORARY REVISIONS p ATP REV INSERT DATE REV REMOVE REV NO DESCRIPTION ISSUE DATE DATE BY REMOVED INCOR BY 4 2 Sec 4 pS 4 6 1 1 15 93 2 23 98 ATP MB 3 1 Sec 3 pg 3 2 10 31 97 2 23 98 ATP MB ...

Страница 354: ...ECORD OF TEMPORARY REVISIONS REVISION CHAPTER DATE INSERTED DATE REASON REMOVED NUMBER PAGE INSERTED BY REMOVED REMOVED BY AFFECTED 2 23 98 ATP 3 2 23 98 NOTE Insert this Record of Temporary Revisions after the Record of Revisions page Page 1 ...

Страница 355: ...rd of Revisions page of this manual The Highlights Page may be retained with the manual for future reference HIGHLIGHTS Volume DescrSption of Change Chapter Section Revised format of manual 7 Changed references to FARs to Title 14 Code of Federal Regulations 14 CFR Changed voltages Added and changed inspection requirements Changed inspection interval for Main Fuel Cell Flapper Valve Added Unschedu...

Страница 356: ...with the attached Instruction Page Enter the revision number and the date inserted on the Record of Revisions page of this manual The Highlight Page may be retained with the manual for future reference Chapter Section Description of Change Section 2 Added WARNING to identify cables plumbing electrical connectors and wiring to facili tate correct reassembly Section 3 Added procedures for FORWARD CA...

Страница 357: ...formation Section 3 Revised one page of art Revised the elevator rudder balancing Section 4 Added Temporary Revision 4 1 affecting the Flap Drive Cable Connection Added elevator rudder removal Added elevator rudder installation Added elevator tab removal Added elevator tab installation Added 3 new pieces of art Section 7 Elevator rudder inspection was added to the Inspection Guide Section 8 Change...

Страница 358: ...SECTION PAGE SECTION DATED Title Page Title Page Aug 29 03 Logo Page Logo Page A Page A Page 821 B Page 8 Page 821 C Page C Page 821 D Page D Page 821 E Page E Page 821 All 7 1 thru 30 7 Aug 29 03 All 8 1 thru 7 8 Aug 29 03 NOTE These instruction pages may be discarded after the above revision has been properly incorporated into the Maintenance Manual Page 1 of 1 ...

Страница 359: ...096814 September 27 1979 1 2 3 6 and 8 35 590096815 February 3 1984 2 4 and 8 35 590096816 January 31 1986 1 and 2 35 590096817 August 28 1987 1 2 and 3 35 5900968 18 May 18 1989 3 821 Basic publications are assigned a part number which appears on the title page with the date of the issue Subsequent revisions are identified by the addition d a revision code after the part number Al after a part nu...

Страница 360: ...ny BONANZA 35 SERIES SHOP MANUAL LIST OF EFFECTIVE REVISIONS Continued PART NUMBER DATE SECTIONS AF ECTED 35 590096819 March 22 1996 2 3 4 7 and 8 35 590096820 September 3 2001 2 and 3 35 590096821 August 29 2003 7 and 8 821 ...

Страница 361: ...4A May 12 78 148 thru 140 Aug 28 87 148 Sep27n9 15 Nov1972 15 Sep 27 79 16 Feb 11 66 16 and 17 Nov 29 74 16A and 168 Nov 29 74 16C Nov1972 2 1 Sep 3 01 17 thru 18C Mar f5n9 2 FeblOn7 19 Mar15n9 3 Jan15 64 20 Jan15 64 4 and 5 Original 21 thru 22A Nov 29 74 6 Oct 22 65 23 Sep 1971 7 Oct 27 61 24 Original 8 Oct 22 65 25 May 18 89 9 Oct 27 61 26 and 26A Nov 29 74 10 and 11 Original 27 Original 12 Feb ...

Страница 362: ...thru 60 Mar 22 96 36 thru 39 Oct 27 61 7 Jan 15 6 4 40 Original 8 thru 88 Mar 1972 41 thru 47 Oct 27 61 9 FeblOn7 48 thru 52A Jan 1970 1O thru 1 OH Mar 22 96 53 Jan 1970 11 and 12 Mar 22 96 54 Sep 1971 13 and 14 Mar 15 79 54A and 548 Dec 1972 15 and 16 Feb 11 66 54C and 540 Mar 7 77 17 thru 19 Nov 29 74 55 and 56 Jan 1970 5 1 thru 4 Original 56A and 568 Dec 1972 5 Dec 1969 57 Mar 7 77 6 Original 5...

Страница 363: ... 77 96A Sep 1971 77 Oct 17 75 968 Nov 1 73 78 and 78A Sep 1971 97 Mar 7n7 788 Mar 7 77 98 and 98A Dec 1972 78C Oct 17 75 988 Nov 1n3 79 Mar 7 77 98C and 98D Mar 7 77 80 Dec 1972 988 Oct 17 75 80A Mar 7 77 99 Mar 7 77 81 and 82 Jan 1970 100 Oct 17 75 82A and 828 Sep 1971 100A Mar 7 77 83 and 84 Sep 1971 1008 Nov 1 73 85 Dec 1972 100C Mar 7 77 86 and 86A Oct 17175 101 thru 104A Mar 7n7 868 and 86C M...

Страница 364: ...SECTION INTRODUCTION ...

Страница 365: ...Il SECTION 1 Introduction ...

Страница 366: ...ased from sources other than BEECHCRAFT even within Section 6 of this Shop Manual though outwardly identical in appearance may not have had the required tests and inspections performed may be ditfer Refer to the BEECHCRAFT Bonanza Wiring Diagram Manu ent in fabrication techniques and materials and may be al P N 35 590102 7 for the wiring diagrams pertaining to the dangerous when installed in an ai...

Страница 367: ...N PAGE INTRODUCTION I 1 II GENER L INFORh lXTION 2 I III SYSTEMS DESCRIPTION ND j L IV MAJOR DISASSEMBLY 4 L V 1XJOR I INTENXNCE AND OVERH UL j I vl ELECTRICAL WIRING DIAGRAMS 6 1 VII PERIODIC INSPECTION GUIDE 7 1 VIII OVERH UL AND REPL I CE IENT SCHEDULE S 1 817 1 3 ...

Страница 368: ...shooting 3 40D Microswitch 3 18A Approved Engine Oils 2 20A Landing Gear Position Arm Control Column Light 3 22 Installation 3 t Landing Gear Pressure Rtmoval 3 2 Switch 3 18B Assembly Nose Wheel Travel Gerdes Master Cylinder 5 17 Illus 5 18 Stop 3 22A Main Gear Strut 5 8A Stall Warning Switch 3 28 Illus 3 20 Nose Gear Shock Strut 5 14 Static Ground Cable 2 23 Paramount Master Cylinder 5 16 Illus ...

Страница 369: ...oler One Pressure Cylinder Type 4 68 Prior to D 4866 3 15 Goodyear Brake Unit Disassembly Rubber Seals 2 22 Repair and Reassembly of Suction Relief Valve Screen 3 30G Two Pressure Cylinder Type 4 7 Windshield and Windows 2 22 Master Cylinder 3 26 Illus 3 27 Clearing Static Lines 3 28 Linkage Adjustment 3 26 Clutch Magnetic Overhaul 5 16 Installation 3 7 Removal and Installation 3 26A Removal 3 6K ...

Страница 370: ... Master Cylinder 5 18 Illus 5 18 Oils 2 20A Shimmy Dampener 5 8A Illus 5 9 Removal and Installation 4 108 Door Adjustment Cabin Entrance 3 328 Starting 2 18 Door Adjustment Landing Gear 3 188 Illus 3 23 Stopping 2 19 Door Lock Cabin 3 328 Turbocharger lllus 4 11 4 12 Drop Off Check Magneto 3 346 Evaporator Air Conditioner Dual Brake System Bleeding 3 25 Filter Replacement 3 30F Installation 3 30F ...

Страница 371: ... Compressor Air Conditioner 3 30D Disassembly 5 10 Compressor Belt Air Conditioner 3 30D Repair 5 10 Condenser Air Conditioner 3 30D Testing 5 10 Control Column Arm _ _ Fuselage Bulkheads Inspection of 3 32A Electric Trim Tab Actuator 3 6J Fuselage and Empennage Skin Plating lllus 2 7 Elevator Trim Tab Illus 3 6F Elevator Trim Tab Actuator 3 6H Empennage 4 108 G Engine _ _ _ 4 108 Evaporator Air C...

Страница 372: ...9 3 20 Leading Edge Wing Installation 4 2A Landing Gear 4 5 Illus 3 20 3 23 3 24 Leading Edge Wing Removal 4 2A Leak Test Procedure Turbocharger 3 368 Leak Detection Air Conditioner 3 308 N Leveling 2 17 Light New Matic Autopilot BEECHCRAFT 3 30K Bulb Replacement Guide 2 28 Illus 3 30K 3 30L 3 30M Instrument Wedge 2 28 New Tab Cable Installation 3 6K Strobe 3 32 Normal Tie Down 2 19 Tray Installat...

Страница 373: ...lus 4 12 4 13 4 14 Brush Block Resistance Check 3 57 Illus 3 57 Replacement and Overhaul Schedule 8 2 Deicer Electric 3 55 Retract Rod Removal and Installation 4 5 Boot Installation 4 17 Illus 4 18 Rigging Boot Removal 4 17 Control Column Chain 3 2 Boot Repair 5 16 Control Surfaces 3 2 Brush Replacement 3 55 Illus 3 55 Cowl Flap 3 16C Continuity Test 3 57 Elevator Tab Indicator 3 61 Heat Test 3 56...

Страница 374: ...olumn 3 2 Filters Pressure 3 303 Iilus 3 30I Skin Plating Illus 2 7 2 9 2 11 Flap 3 17 111us j 19 Slip Ring Alignment 3 57 Flight Controls 3 2 111us 3 3 3 4 3 8 Spar Main Removal Fuel Servicing 2 20B Illus 3 14D 3 16 and Installation 4 2 4 4 3 16A 16B Spark plugs 3 34A Heat and Vent 3 30 Special Tools Illus 2 12 2 13 Inspection Flight Control 3 2 Stability Augmentat7on System Illus 3 14 Landing Ge...

Страница 375: ...urer s Tolerances 5 9 Temperature Effect on Cable Models Serials Differences 1 16 Tension Illus 3 2C of Contents 1 3 Testing Emergency Locator of Lubricants 2 14 Transmitter 3 32A of Torques Wing Bolts 4 2 Testing Shimmy Damper 5 10 Taxiing 2 19 Throttle Warning Horn AdJustment 3 25 1 10B 817 ...

Страница 376: ... Tab Installation Elevator Illus 3 6F Vent Lines Inspection of Fuel Tanks 3 148 Trouble Analysis Strobe Light 3 308 Ventilating System 3 29 Ilius 3 28C Troubleshooting Voltage Regulator Illus 3 20 3 34 Air Conditioning System 3 308 Alternator System 3 40D Aitimeter 3 49 W Directional Gyro 3 50 Flap Control Indicator Circuit 3 43 Warning Horn Landing Gear 3 5 Fuel Quantity Indicator Circuit 3 46 Wa...

Страница 377: ...5 1 E165 E185 E225 Parts Catalog X30017 Teledyne Continental Motors E185 8 Aircraft Products Division E185 ll P O Box 90 E225 8 Mobile Alabama 36601 E185 I E165 E185 E225 Operators Hand X30018 Teledyne Continental Motors E185 8 book Aircraft Products Division E 185 11 P O Box 90 E225 8 Mobile Alabama 36601 0 470 G Operators Handbook for 0 470 X30097 Teledyne Continental Motors Series Aircraft Prod...

Страница 378: ... Tips on Engine Care Teledyne Continental Motors Aircraft Products Division P O Box 90 Mobile Alabama 36601 Fuel Overhaul Manual and Illustrated X30091 Continental Motors Corpo Injector Parts Catalog for Continental ration Fuel Injection System Turbo TE06 Overhaul Manual and Parts Catalog X30055 Continental Motors Corpo charger for TE06 Turbocharger ration Propeller F12A 3 UNIVAIR Service Manual U...

Страница 379: ...ps Series RD 7430 RD 7790 Romec Handbook Operation Lear Romec Division Service and Overhaul Instructions Lear inc with Parts Catalog Series RD 7750 and RD 7790 Aircraft Fuel Pumps TF 1900 Thompson Aircraft Engine Driven Thompson Products Inc Fuel Pump Model TF 1900 TF 1100 Thompson Aircraft Engine Driven Thompson Products Inc Fuel Pump Model TF 1100 2 TF 100 I Thompson Aircraft Engine Driven Thomp...

Страница 380: ...ompany ALV 9407 511 Hamilton St ALT 9422 Toledo Ohio 43694 642056A 1 Service and Overhaul X30 531 Teledyne Continental Motors Instructions Aircraft Products Division P O Box 90 Mobile Alabama 36601 Starter 1109660 Test Specifications DR 3248 Delco Remy Division Gen eral Motors Corpor ltion Parts List Group 70 Delco Remy Division Gen eral Motors Corporation Yaw YK631 Automatic Flight Systems Bullet...

Страница 381: ...ndix Aviation Corporation Parts List Numbers 380208 7 380223 4 391318 5 391330 7 391583 1 391629 3 Bendix PS Series Carburetor Manual 15 86 Bendix Products Division Bendix Aviation Corporation PSH SBD Overhaul Instructions for Injection 15 137 Bendix Products Division Carburetor Model PS SBD Bendix Aviation Corporation Illustrated Parts Catalog for Injection 15 127A Bendix Products Division Carbur...

Страница 382: ...emy Division Gen eral Motors Corporation 1118358 Test Specifications DR 3243 Delco Remy Division Gen 1118384 eral Motors Corporation 1118385 Parts Lists Group 6 D Delco Remy Division Gen eral Motors Corporation 1118713 Test Specifications DR 324S Delco Remy Division Gen 537486 eral Motors Corporation Parts List Group 6 E Delco Remy Division Gen eral Motors Corporation 1118891 Test Specifications D...

Страница 383: ...tics Corp Light Pomona California Strobe Light 60 1750 3 Overhaul Manual with 33 40 58 Grimes Manufacturing Power Supply Illustrated Parts List Company 515 North Russell Street Urbana Ohio 43078 Landing 27 4 35 380094 Component Maintenance 32 31 24 Electro Mech Inc Gear 27 8 96 380022 5 Manual with Parts List Wichita Kansas Motor Continental Motors Corporation part number Same as Model PS 5BD exce...

Страница 384: ...ance Instructions and Illustrated Parts Breakdown for Ihe Main Wheel Nose Wheel and Brake Arsembly 93 and al er I 98 35776 Maintenance Information and Illustrated Parts Breakdown for 35 380094 Landing Gear Motor 98 35655 B 5 and B 7 Owner s Manual Automatic Flight Control System 98 36486 Overhaul Instructions for Vertical Display Engine Indicators used on BEECHCRAFT Bonanza series aircraft 98 3328...

Страница 385: ...F35 1955 0 3999 through 0 4391 2750 E 225 8 215 84 Optional auxiliary wing fuel tanks G35 1956 0 4393 through 0 4865 2775 E 295 8 115 84 H35 1957 D 4866 through D 5330 2 00 0 470 G 278 84 Hydraulic governor Front seats individually adjustable in night 535 1958 D 533 1 through D 5 725 C OO IO 470 C 278 82 Fuel injection engine Electric fuel boost pump K35 195C D 5716 through 0 6161 2 50 IO 470 C 78...

Страница 386: ...9068 2A36C23 84B 0 Vertical instruments V35B TC TS10 520 D 2A36C82T 84B 2 V35B 1970 D 9069 through 3400 1O 520 BA Optional strobe light D 9204 and 2A36C23 84B O New parking brake V35B 0 9207 through TS 10 5 20 D system TC D 9211 2A36C82T 84B 2 B7 autopilot Instrument wedge lighting New fuel cell New fuel gaging transmitters V35B 1971 D 9205 D 9206 3400 10 5 20 BA New propeller gov D 9212 through 2...

Страница 387: ...SECTION GENERAL IN FORNIATION SERVICING ...

Страница 388: ...SECTION 2 General Information Servicing ...

Страница 389: ...Some of the most important information about the Bonanza lubrication cleaning and shop handling will be found in this section Particular attention should be paid to these items since they are among the items which the customer sees and consequently can influence directly his decision to come back again or to go elsewhere The section includes a three view drawing giving the major dimensions of the ...

Страница 390: ...earance tire and shock deflated 11 5 Normal ground attitude 6 75 Min Clearance tire and shock deflateb iD PIIB UPU 0 5330 and D 73aj10dafter 7 8 Min Clearance with nose tire and shock deflated D 5331 thru D 1309 12 5 Normal ground attitude loaded to gross weight 4 DZA 10 I 9 7 1 8 1 vJsso7a Prior to D 3999 D 3999 thru D 5330 and D 7310 and after D 5331 thru D 7309 Figure 2 1 Dimensions of Airplane...

Страница 391: ...t Y j 256 90 j 146 30 23j 50 207 00 1 2 79 00 151 00 i 23 8145 00 66 00 80 047 94 094 108 281 23 881 122 750 31 75 39 37 7 00 148 875 4 50 11 115 33 345 49 00 175 281 53 00 94 0941 IVcl I L y191 00 33 00 103 641 1 113 172 12175 D 136 1 148 875 t 162 563 603 7 1 5181 g r 19100 m m 9u jO c Z NL Fie ure 2 2 Stations Diagrlm ...

Страница 392: ...2680 3 Elevator Tab Cable Pulley RH 13 Differential Mechanism LH 4 Empennaffe Control Linkage 14 Carburetor Air Screen 5 Baggage Compartment 15 Differential Mechanism Lower 6 Cabin Entrance 16 Rudder and Elevator 7 Access Plates for Engine Cables 8 Hinge Bolts for Nose Wheel Strut 17 Rear Spar Jack Point 9 Engine Cowl 18 Landing Gear Actuator 10 Oil Filler Neck D 4866 after 19 Fuel Strainer Figure...

Страница 393: ...and Rear Spar Bolts 7 Flap Ringe Bolts 8 Fuel and Pitot Lines D 6562 and after 9 Auxiliary Fuel Tank D 4000 to D 6561 10 Fuel Lines Pltot Lines in LH Wing Prior to f g562 11 Landing Light Prior to D 6562 Fuel Lines 0 6582 and after 12 Main Fuel Cell D 6562 and after 13 Landing Gear Hinge Bolt and Main Fuel Cell 14 Lower Front and Rear Spar Bolts 15 Auxiliary Fuel Tank D 4000 to D 6561 16 Aileron C...

Страница 394: ...D 1575 after replaced with index no 7 9 020 2024 13 D 1515 after 10 016 2024 T3 D 1575 after replaced with index no 9 11 11 016 2024 T3 D 1575 thru D 2076 020 2024 T3 D 2077 after 12 025 2024 0 D 1 thru D 4865 032 2024 0 D 4886 after 13 025 2024 T9 D l after Y14 020 2 324 0 D l after 15 025 2024 T3 D l after 16 016 2024 T3 D l thru D 8561 032 2024 T3 D 6562 after 17 020 2024 T3 D 4866 thru D 6561 ...

Страница 395: ...ORMATION 00 a 5 n LE FT IIAND VIEW 14 1516 i I17 35 1310 TOP VIEW Skin Splice Moved Aft to Sta 179 as Shown Effective 0 8747 and After Figure 2 5 Fuselage and Empennage Skin Plating Sheet 1 of 2 Revised October 27 1961 2 7 ...

Страница 396: ...2801 after 9 025 2024 13 D l after 10 020 2024 T3 D l after 11 025 2024 13 D l after 12 025 2024 13 D l thru D 4865 032 2024 T3 D 4866 after 13 016 2024 13 D 1575 thru D 2076 020 2024 T3 D 2077 after 14 016 2024 T3 D 1575 after replaced with index no 13 15 15 020 2024 T3 D 1575 after 16 025 2024 T3 D l after 17 016 2024 T3 D l after 18 016 2024 T3 D l after 19 020 2024 T3 D l after 20 020 2024 T3 ...

Страница 397: ... 5 6 7 8 I 04 02 RIGHT HAND VIEW Skin Splice Moved Aft to Sta 179 as Shown Effective D 6747 and After 17 15 19 20 21 26 25 24 23 22 BOTTOM VIEW 35 3 1 Figure 2 5 Fuselage and Empennage Skin Plating 8heet 2 at 2 Revised October 27 1961 2 B ...

Страница 398: ...501 032 2024 T3 D 1501 to D 4866 040 2024 T3 D 4866 after 12 025 24S T3 D l to I 1501 032 2024 13 D 1501 after 13 020 245 T3 D l to D 1501 025 24S T3 D 1501 to D 3999 032 24S T3 D 3999 after 14 016 24S T3 D l to D 1245 020 2024 T3 D 1245 after 15 016 245 T3 D l to D 1693 020 2024 T3 D 1693 after 16 016 245 T3 D l to D 1821 020 2024 T3 D 1821 after 17 016 24 STAL D l to D 1245 020 24 STAL D 1245 af...

Страница 399: ...I 1 8 cr I O A ci tO 21 27 26 1251 21 23 22 33 32 31 30 29 35 127 r Ir Figure 2 6 Wing Skin Plating t ...

Страница 400: ...097 TS1222 4 LOWER FORWARD WING BOLT WRENCH D or 7310 thru D 10119 except D 10097 TS1222 4 UPPER FORWARD WING BOLT WRENCH 9 16 TS1222 8 or inch hex for MS20012 and 131790 1 bolts used TS1222 8 interchangeably with NAS152 bolts on airplane TS1171 1 LOWER FORWARD WING NUT TOROUE serials D 9379 D 9415 thru 0 10119 except D or WRENCH ADAPTER D l thru D 1500 10097 TS1176 1 or TS1171 1 UPPER FORWARD WIN...

Страница 401: ...d with 35 590076 assemblies when rigging airplanes 0 2681 end after 932 5 35000001 Jack Dinerential Mechanism TK1518 Jack Point Adapter 35 590087 D 2681 end after 0 9415 and akr a O NOTE 35 590087 9 Stop Used with 35 590087 assembly when POINTING HAND rigging airplanes 0 5725 and after DENOTES CHANGE Tow Handle 36 590015 replaces Tow Handle 35 590002 35 590021 Tall Tieaown Assembly Gear Tension Ga...

Страница 402: ...0 100 Hr DETAIL E 1 Trim tab control 1 SAE No 20 100 Hr DETAIL F 1 Door handle 2 SAE No 20 100 Hr DE AIL C Door han die 1 SAE No 20 1 100 Hr 1 Landing gear motor gear box MIL C 8133 300 Hr 2 Landing gear actuator gear box 1 Mobil Compound GG 300 Hr DETAIL H 1 Fuel unit linkage 3 SAE No 20 100 Hr 2 Fuel unit shaft 1 MIL G 81323 100 Hr DETAILI 1 Flap motor gear box 1 MIL G 23827 300 Hr DETAIL J Diff...

Страница 403: ...AILE DFTAIL H DETAILC 2 D1455 TO D 2901 RIGHT AND LEFT SIDE 1 n rl 1 RIGHT AND LEFT SIDE DETAILR ks D l THROUGH D 3998 03 DETAILM jr DETAILF D AILD 21 111 DETAILI DETAIL N Except D 5058 D 5126 thru D 5156 and D 5159 RIGHT AND LEFT SIDE EFFECTIVE SERIAL D 4866 thru D 5162 XII IDETAILS kiL DEIAIL G 1 15 2 3 r j i 50 hours jl 100 hours Cr 250 hours O 300 hours a3 500 hours O As required O 1000 hours ...

Страница 404: ...anding gear components may require lubrication 25 or 50 hours depending on operation 3 Care should be exercised when using grease MIL G 81322 and MIL G 23827 since they contain a rust preventive which will discolor painted surfaces 4 MIL G 81322 grease is NOT compatible with Aeroshell 5 grease DO NOT MIX I Do not overfill When properly filled the oil level measured on a dip stick inserted through ...

Страница 405: ...e is level laterally on other paved surfaces as desired When using only the two front jack points secure the tail skid to a TOWING stationary object and place 100 pounds of sand bags on the fuselage between the stabilizers MAIN WHEEL JACgING IWARNINCI A wheel jack adapter is included with each aircraft On fuel injection aircraft if the engine is prior to aircraft serial 0 9222 The adapter is warm ...

Страница 406: ...l in a tail engaging starter after engine starts turn auxiliary low landing and to provide attachment for the fuel pump switch to Low Boost as needed to purge tail tie down vapor from the system during ground operation STARTING ENGINE ICIUTIONI I Generator Switch On Alternator ton after englne st rts Battery Switch On Do not over prime engine In event of Ignition Both flooding place mixture in Idl...

Страница 407: ...each tating wing mooring lug fastening each end to a ground Cowl Flaps Open point one forward and one alt of the wing Run a Parking Brake On line through the hole in the tail skid and anchor at the sides of the airplane approximately 5 feet from the base of the stand If a storm is anticipated two NOTE lines may be secured to each main landing gear strut near the V brace and also a line may be atta...

Страница 408: ...eg Check the NOTE up lock roller for free movement and a maximum clearance of 010 to 020 inch between the roller and the up lock On Bonanzas 0 7310 and after a torque from block If this clearance is not correct the up lock must be 15 to 18 foot pounds should be applied to the adjusted as indicated under RIGGING THE LANDING center of the oil filter when the filter element is GEAR in Section 3 of th...

Страница 409: ...ning Corporation 8 14 70 Quaker State AD Aviation Engine Oil Grades 20W 30 40 50 Shell Oil Company 8 15 58 Aeroshell OilW 12 20 63 Aeroshell Oil W tin 4 grades Grade 120 OVominal SAE 60 Military Grade 1 120 Grade 100 NominalSAE 50 Military Grade 1100 Grade 80 Nominal SAE 40 Military Grade 1080 Grade 65 Nominal SAE 20 or 30 Military Grade 1065 Sinclair Refining Company 11 20 67 Sinclair Avoil 20W 4...

Страница 410: ...ion the leading edge of the wing in the fuse check the plumbing for security and leaks lage to eliminate static electricity arc through the inspection panels along the ing during the filling operation The wing bottom of the wings Wiring for the fuel tank drain is located on the underside of quantity transmitters and the navigation the wing and is accessible through a small lights follow the same a...

Страница 411: ...the shock strut with fluid Lower the strut barrel and with a cloth moistened with hydraulic fluid the strut in the fully compressed posi tion allow the excess fluid to drain out SERVICING THE SHIMMY DAMPENER e inf ateClean and install the filler p ltn To check the fluid level in the shimmy and the strut On airplanes dampener insert a wire of approximately thru 0 1500 the sh ock strut 1 16 inch dia...

Страница 412: ... Section 3 for bleeding the the floating piston and remove the piston brake system e Push the piston rod to the end of SERVICING TIRES its travel toward the clevis end and fill the barrel with MIL H 5606 hydraulic flu The nose wheel tire is a 5 00 x 5 4 ply id tire The main wheel tires are 6 50 x 8 4 ply prior to serials 0 7725 and 7 00 x f Slowly actuate the piston rod 6 6 ply tires on airplane s...

Страница 413: ...sition and mixture control is retract system with the possi in the IDLE CUT OFF position bility of damage to the landing Always stand in the clear while gear doors and retract mechanism turning the propeller STORAGE 1 Arrangements should be made to have the airplane flown at least 30 The storage procedures ii sted are intended minutes each week in order to keep the to protect the airplane from det...

Страница 414: ...he plugs Preflight the airplane and while the engine is still warm and replace flight test the drain plug INDEFINITE STORAGE 1 Fill the sump to the full mark on the dipstick gage with lubricatin meeting the requirements of MIL C oil a MOORING See FLYABLE STORAGE Type II which will mix with normal oil b ENGINE PREPARATION FOR INDEFINITE and provide protection against corrosion STORAGE Drain the eng...

Страница 415: ... to prevent wicking of can be sealed tight and is dust proof moisture into the sealed area Also F laces in the storagec o n t a i n e r a 1 2 Ib bag of silica gel crysta so it 10 If the propeller has not been can not touch the carburetor removed affix a tag in a conspicuous place with the following notation DO NOT After sealing the first container wrap TURN PROPELLER ENGINE PRESERVED it in moistur...

Страница 416: ...hains con b Remove all cylinder plugs and all trol rods and quadrants and coat lightly paper tape and dehydrating agent used with corrosion preventive compound to preserve the engine 1 Lock with internal and c Drain corrosion preventive mix external locks ture and reservice with recommended lubricating oil h GROUNDING Static ground the airplane securely and effectively d Rotate the propeller to cl...

Страница 417: ...odate only the NOTE Willard battery On airplane serials D 1 through On Bonanza serials 0 1911 and 0 1116 the R33 Reading battery after and ai rp lane serials and the AW 12 25 battery are 0 1117 through 0 1910 that have interchangeable provided the incorporated Kit 35 562 the proper battery spacer blocks are BEECHCRAFT 36 380025 battery used Gill P N 6 GCAB 11 may be used B17 2 201 ...

Страница 418: ...ates limit the rate of charge should be reduced The manufac turer recommends charging the battery at a rate of 1 amperes until four consecutive hourly readings show no rise in spe cific gravity and voltage for each cell Refer to the Service Manual P N GSM 1277 for additional information on the NOTE charging procedure recommended by the battery manu facturer Teledyne Battery Products Do not overfil...

Страница 419: ...ing the exterior cover the wheels making scratching and cracking Apply the wax in a thin even coat certain the brake discs are covered attach pilot cover se and bring to a high polish with a clean soft cloth curely install plugs in or mask off all other openings Be particularly careful to mask off both static air buttons before washing or waxing NOTE Do not use gasoline benzene acetone carbon NOTE...

Страница 420: ... the system excessive oil b Remove the access panel from the center of the PROPELLER BLADE IIIIAINTENANCE partition located directly beneath the forward side of the pilot s and copilot s seats then close the shutoff valves on Due to the high stresses to which propeller blades are sub both the cylinder and console jected their careful maintenance is vitally important par c Slide the pilot s seat sl...

Страница 421: ...le eyes may cause loss of sight Pilot s Operating Manual and run the air conditioner Run air conditioning system for 15 minutes with the engine running at low rpm to allow oil to accumulate in the compressor Ob When working on a refrigerant air cooling system observe serve engine operating limitations as noted in the applicable the following special servicing precautions Pilot s Operating Manual S...

Страница 422: ...ating length The belt tension should be b Adjust the tip of the cable to provide 5 75 f 12 checked at this time and adjusted by torquing the adjustment inches of free cable between the attaching bolt and the bottom bolt on the idler pulley bracket so that a belt tension gage of the cable The cable should then be between 1 4 to In inch placed at a point midway between the idler pulley and the from ...

Страница 423: ...4 X X X X X X X X X Black 118684 133 X Black 42 3 514 X X Blue 246 23714 Blue 118684 471 X Blue Antique 118684 494 X Blue Banff 118684 241 X Blue Broadway 118684 283 X Blue Chairman 118684 483 X Blue Colonial 246 57300 X X X X X X Blue Glacier 246 57286 X Blue Gulf 118684 429 X X X X X Brown 7 5YR3 5 2 X Brown 6YR2 2 X Brown 5 272 X 10758 Brown Executive 118684 487 X Brown Sable 118684 257 X X Dri...

Страница 424: ...5 7 X Smoke Autumn 118684 155 X X Smoke Autumn 118684 255 Vinyl X X Green 246 38249 Green 11 684 461 X X Green Lakewood 246 55911 X X X X X X Green Mjst 31S684 277 X Olive 31 368j485 X Red Antique 111 684 191 X Red Chairman 1 i684 481 X Red Torch 111 684 329 X X Gold Chairman 1113684 479 X I Gold Maize 118684 455 X Pumpkin 138684 79 X X Sienna 115684 327 X Turquoise 1lY684 275 X X Nairobi Peal 27H...

Страница 425: ...118684 505 X Blue Martin 118684 349 X X X X 118684 163 Blue Morning G or 118684 3 X X X X X X X X X X X X X X X X 118684 143 Blurt Pacific 118684 1 X X X X X X X X Blue Pavonne 118684 353 118684 397 X Blue Terrace 118684 335 X i Brown 83 1017 X X X X X 118684 1 11 Brou n Beaver I i 8684 2 1 X X X X X X X X X X X X 118684 7r BroH n Sable 118684 223 118684 3 0 X Coppertone 83 58454 X X Tan 83 11256 ...

Страница 426: ...84 55 X Red Really 118684 99 11868J 523 X X X X 118683 175 Red Toreador 118684 77 11868 1 16 X XXXXXX XXXX X X Red Vendetta 118684 501 1186 1 525 X X X X 118684 135 Turquoise 118684 11 X XX XXXX X X Turquoise peacock 118684 333 11868 liU37 X Cream 83 3987 9 XX X X X X 118684 153 White Matterhorn 118684 31 118684 318 XX XX X X XX XXXX X X White Matterhorn X Gold Antique 118684 331 1186tlr 415 X Gol...

Страница 427: ...cess to the Fuel Select Light 327 instruments Instrument Post Lights 327 Instrument Wedge Lights 267 NOTE Landing Gear Intransit Light 317 Landing Gear Uplock Light 3 7 Instruments located at the lower edge of the Landing Light 4 96 panel may be removed if necessary to gain ac Light Tray Assembly Zh7 cess to the light tray at the top of the instru Map Light 149 ments Navigation Light Tail A7517 4 ...

Страница 428: ...SECTION SYSTEM DESCRIPTION AND NIAINTENANCE ...

Страница 429: ...6 SECTION 3 System Description and Maintenance ...

Страница 430: ...asic drawing either photographs or line drawings show the exact locations of the com ponents and their adjustment or other maintenance procedures where ever practical cable tensions pressures measurements clearances and the like are tabulated directly on the illustration or shown on the details Detailed explanations of procedures have been limited to those instances such as rigging the landing gea...

Страница 431: ... and slide the control column arm off the housing CONTROL COLUMN ARM INSTALLATION a Position the control arm vertical as shown in Figure 3 0 Make sure that the slot in the lower sprocket is approximately parallel to the sides of the arm and that the turnbuckles between the long and short chains are opposite each other near the access opening b The ailerons MUST be in the neutral position c Pull th...

Страница 432: ...Rayeheon Aircraft BEECH BONANZA 35 SERIES SHOP MANUAL THIS PAGE INTENTIONALLY LEFT BVL NK Page 2 of 2 oct 31 97 Temporary Revision No 3 1 ...

Страница 433: ...buckles are accessible in the fuselage just forward of rear truss On n With the control wheel in the neutral position many airplanes the music wire has been re he pellow marks on the sprockets must align with the placed with cables on these airplanes the ellow marks on the chain system is identical to the later style b The slot in the sprocket as shown in Figure 3 0 be in alignment with the yellow...

Страница 434: ...nnect ing the aileron to the wing bellcrank to obtain the aileron IWARNINC i neutralposition Neutral position of the aileron is de termined by aligning the inboard end of the aileron with the outboard end of the flap the flap being in up position Check for correct direction of aileron travel 8 Remove control surface lock and set aileron travel by moving the controlwheel When the control by adjusti...

Страница 435: ... c r r I I YELLOW MARK ON SPROCKET AND CHAIN i I i c I I I h I I I I I I I I r cf _i I I TURNBUCKLE ACCESS OPENING YELLOW MARK ON SPROCKET AND CHAIN SLOT IN SPROCKET Figure 3 0 Control Column 3 ZB Issued December 1869 ...

Страница 436: ...ABLE TENSION O WHEN THE BEECHCRAFT NEW MATIC FLIGHT i7j 20 CONTROL IS INSTALLED ti 10 AILERON CABLE TENSION 20 30 40 50 60 70 80 90 100 110 59 6CI TEMPERATURE F 50 50 O Ifi i ttlvnroaa ELEV rOll U tit i I ii f i i tii 1 Iii iI i i t t t t I f i i i 1t i t i ttrttt tit i j i sg 40 t th u ii it o ab I F orn t t 1500 I it t T04a g h t tt i Z it i so 30 M 7k O o i tc u ff a D 1 0 z Tth_ry itil i lthr ...

Страница 437: ...UP CABLE 1 u D 1501 AND AFTER D l THROUGH 0 1500 I i LEFT UP RIGHT UP d i i ii REAR SPAR CARRY THROUGH B BALANCE CABLE LEFT AILERON F 2 I UP CABLE f r r x u i l i I k j 4Ci 2 ii I I i G t II ii Y D 1 THROUGH 0 7975 0 7976 IbND AFI R I1Zlu DOER INTER CONNECT i l 1I 1 i Ailci cn Clilltr l Systc ilcvise i C c I Lw t 22 19fi5 3 3 ...

Страница 438: ...AVEL DOWN TRAVEL POSITION FROM 00 ELEVATOR ELEVATOR HINGE LINE LEFT TAB RIGHT TAB D TWsOUGHD 2100 13 60 15001 10 20 1 300 20 00 f 10 00 10 0 2201 THROUGH D 2680 100 hO 1 310 20 00 00 10 00 f 10 0 2681 THROUGH D 4 8 6 5 1 0 15002 8 1 20 1 310 20 00 00 1 00 f 10 D 4B66THROUGHD 6561 4K 1 1 1 23 10 0 00 1 00 f 1 0 6562 THROUGH 0 7309 5 h0 O 1 230 29 0 20 IOUP 00 1 EXCEPT D 7140 ELEVATOR DOWN 0 7140 0 ...

Страница 439: ...ing careful not to shear the felt control column seal Reinstall the three countersunk screws Screw the two halves of the unit c Straighten the nose wheel and together by holding the clutch body and adjust the pilot s rudder pedals to the turning the clutch body nut Care should same position Install a 43 inch diameter be taken to see that the tangs of the straight steel aligning rig pi n 5 drive nu...

Страница 440: ...t The differential mechanism is in for yawl The tabs are at 00 when its neutral position when with their trailing edges align with the rudder elevator and tab sys the trailing edgesof theeleva tems correctly adjusted and in tors neutral the 3 center differen tial mechanism arm top bolts are g Set the elevators in the neutral engaged in 3 plates of the posit on 00 by adjusting the elevator 35 59000...

Страница 441: ...ect tighten rod end jam nuts safety anism jig assembly to position the dif turnbuckles and recheck travels and ten ferentialmechanism in neutral position sions Remove rudder pedal rig pin NOTE k Changing elevator rigging may change rudder travels Check rudder trav When ri ggi ng ai rplanes 0 2681 els after changing elevator rigging through 0 5725 the 35 590076 differential mechanism jig pssem WARN...

Страница 442: ...nspring in neutral when the differential cable turnbuckle thus with the tab sys mechani sm jig assembly is cor tem set at 00 a force of 11 1 2 pounds rectly installed the rudder rig applied on the control column is required pin is insta lled the control to return the elevators to neutral 00 j col umn block is installed and the with the tabs set at 100 up nose down elevators are at the 00 position ...

Страница 443: ...bubble protractor should temperature tension graph The differen not be used for any elevator rig tial mechanism control column and rudder ging procedure peda is are still to be in their neutral positions after cable tensions are a Adjust the stops on the aft fuse adjusted lage bulkhead to permit maximum combined elevator rudder travel as shown on the NOTE overall travel tables on Figure 3 2 The di...

Страница 444: ...emoved before the control column block trim tab control is moved toward is removed to prevent damage to the jig the nose up position the trim tab assembly The elevator trimsystem may be should move DOWN When the eleva repositioned to minimize downspring tor trim tab control is moved effect on the elevator arm and elevator towa rd the nose down posi ti on cable tensions After the downsprlng the tri...

Страница 445: ...e moved away from the stops Trim tab actuator stops on the The use of a bubble protractor is cab not adequate to setthe elevator in the fuselage travels A travel board must be used for this However with the b Rotate the elevator trim tab con elevator set at neutral a tab trol wheel to full nose up on the indica travel board or a bubble protrac tor tabs down Check the tab actuator tor may be used t...

Страница 446: ...OP MANUAL j l itiiiiititiii iitiiiiiiiiiirl 8 It I itili B i 1 o cz zz o 0 _2 o o o o O O o c i 0 o ii 1 3 RIGHT RIGHT 3 3 o o 0 0 0 0 0 0 3 0 lo n 1 E F io WRONG WRONG 35 133 6A Elevator Trim Tab Installation Figure 3 2C 3 6F B17 ...

Страница 447: ... trim tab cables tab actuator and the trim tabs to each aft of the bell crank to obtain the trim other tab down position as shown in Figure 3 23 and and establish the initial trim tab g Move the tab system to neutral cable tension per the applicable 00 position Check and readjust cable temperature tension graph In Figure 3 1 tension per the applicable temperature Loosen the tab cable stop if neces...

Страница 448: ...e maintained cable stops are to be tightened to 20 5 0 inch pounds of torque and safetied CAUTION WARNING Do not damage kink or put bends in the cables After rigging the elevator and elevator trim tab control system e Identify the cables on the check for correct movement of the actuator being removed so that the cables control surfaces with respect to on the replacement actuator are recon the move...

Страница 449: ... Wrap surplus cable leys around the shaft Beginning on the right hand side of the small hole wrap the f If the two tab cable pulleys cable toward the hole 4 turns Insert the located directly below the actuators were cable into the hole and pull it through removed to provide clearance for the cable Wrap surplus cable around the shaft twist ends of the actuator cables install the the two cables toge...

Страница 450: ...desi rabl e to use grease or oil on the tial readjustment to reduce the bolt for this willmerely cause dirt to rudder effect can be accomplished collect in one tab only In the event the above procedure does not give RIGGING ELEVATOR TABS TO CORRECT enough correction for yaw each FOR YAW tab can be adjusted 10 more from neutral in the same direction as The elevator tabs can be rigged to func before...

Страница 451: ...ab b Loosen the setscrew in the clutch NEW TAB CABLE INSTALLATION rotor and armature hubs Note the position of the old cable in c Remove the motor from the clutch relation to the cable drum and forward end housing cable fittings Install the new cable in the same position This will ensure ade d Slide the cable drum and shaft quate cable length in both directions assembly from the clutch housing all...

Страница 452: ... and the white Locate a blade type screwdriver or similar electrical lead to the power source Using a torque wrench tool that will fit the shaft on which the cable drum is check that the clutch holds with 30 inch pounds of torque mounted applied at the actuator shaft 3 Remove the handle from the screwdriver or b If the static torque of the clutch is less than 30 fabricate a similar tool so that a ...

Страница 453: ... 130 10 DOWN 420 t29 UP 40 2 DOWN R H INCHES AFT OF NEUTRAL POSITION 0 7310 AND AFTER 230 O UP 260 UP 44 O UP 370 r20 DOWN L H D 7310 AND AFTER NEUTRAL POSITION 38 70 45 260 1 DOWN 130 1 DOWN 350 20 UP 40 DOWN R n INCHES AET OF NEUTRAL POSITION RUDDER BALANCE CABLE It i i I 35 590087 i I 1 O MECHANISM JIG ASSEMBLY STOP BOLT j I r RUDDER PEDAL 7 POSITION ADJUSTING RIGHT RUDDER CABLE LINK I I II I 1...

Страница 454: ...NOTE pin as described below When rigging airplanes prior to On ai rp lane serials D l through 0 2681 the 35 590007 differen 0 6561 the left and right rudder tial mechanism jig assembly can pedals are to be evenly aligned with be used or the 35 590076 differ the rudder system in neutral ential mechanism jig assembly can be used by removing the 35 590052 On airplane serials 0 6562 through adapters W...

Страница 455: ... Adjust the main rudder cable ten block in place to prevent elevator system sions to the tension shown on the influence on rudder rigging temperature tension graph The cables can be adjusted simultaneously with the j Set the rudder travel by adjusting rudder balance cable The balance cable the stop bolts just aft of the pilot s is adjusted by adding or removing washers rudder pedals Figure 3 3 Ref...

Страница 456: ...ssed hinge the right elevator should move up and the left elevator should move EQUIPMENT REQUIRED TO PERFORM BAL down When the right rudder pedal ANGING is depressed the left elevator should move up and the right ele a A stand with knife edge supports vator should move down as illustrated in Figure 3 4 The knife edger must be in the same horizontal BALANCING CONTROL SURFACES plane BALANCING THE AI...

Страница 457: ...e acceptable the chord line level Check this by hold ing the spirit level aligned with the marked chord line h The painted aileron assembly must be nose heavy by 0 2 to 3 5 inch pounds e The distance D must be erpen The center of gravity of the aileron is dicular to the hinge 7ine Measure D from forward of the hinge centerline ca us i ng the hinge line to the suspension point of the surface to be ...

Страница 458: ... torque tube and the center of gravity when the chord line is horizontally other end is centered on the trailing edge Mark the level The weight is measured in pounds and the dis chord line by a grease pencil or other means on the tance in inches The static moment of a 100 percent rib Remove the straightedge Fit the correct sized balanced elevator rudder control surface is 0 0 bolts in the hinge br...

Страница 459: ...ightedge at NOTE the lower closure rib of the elevator rudder so that one Since any weighing error is magnified by end is aligned with the center of the torque tube while the distance D weighing is important the other end is centered on the trailing edge Mark and must be done carefully on scales the chord line with a suitable marker such as a that are certified for accuracy within I grease pencil ...

Страница 460: ... 660042 washers outboard tip of the elevator rudder if more than six install up to three 35 660042 1 washers on the washers are required Distribution of the washers on inboard screw and up to three 35 660042 3 washers the screws are as follows on the outboard screw Distribute the washers accord 1 When the maximum number of 11 ingly if fewer than the maximum are needed washers are required install ...

Страница 461: ... ON ELEVATOR INBOARD SCREW AN520 10 36 SCREW HINGE CLEVIS D l THRU D 7309 AN970 3 WASHER WITHOUT MODIFICATION AN365 1032 NUT 2 EACH MASKING TAPE PLACE NEAR ELEVATOR HINGE LINE MASKING TAPE FORWARD PLACE NEAR ELEVATOR HINGE LINE TOP SCREW MASKING TAPE MASKING TAPE CONTAINER v I KNIFE D 73 IO AND AFTER D l THRU D 7309 b CONTAINER EDGE TAIL B DETAIL E TAIL D O t D VIEW C C JIG MUST BE HORIZONTALLY LE...

Страница 462: ...ntered the system does exist suitable in fuel start and operate the engine on the ground until all air is The fuel inlet hose between the firewall removed from the system both and the fuel pump should be inspected at right and left sidePilot1 Refer to the each periodic inspection for leakage and applicable Operating looseness between the hose and the hose Handbook and Airplane Flight Man fittings ...

Страница 463: ...used to vented to atmosphere IThls gage should be make this check on turbocharged fuel pump pressures engines it must be of the vented type and be referenced to deck b Adj usf the engine idle speed to pressure in the same manner as the the specified RPM with the throttle plate airplane fuel flow gage adjusting rotate the screw clockwise to increase or counterclockwise to decrease Criteria for full...

Страница 464: ...ck the fuel gage the fuel system at rated RPM by for empty reading controlling manifold pressure with the throttle partly closed NOTE FUEL TRANSMITTER REPLACEMENT If the gage does not read empty reinspect all transmitters to a Turn off electrical power ensure the float arm is on the down stop and the float clears the b Drain and purge fuel cell bottom of the fuel cell Check all wiring for faulty c...

Страница 465: ...tend 1 50 opening extended or flus s edraa y R ltg each vent inches below the skin surface This vent assure that tube should also be scarfed at a 450 angle air is passin_g through all branches of the on the forward side and should be set vent system for the cell and continue to between canted forward 50 and perpendic blow air through each branch until any ular to the skin obstructions have been re...

Страница 466: ...r YINT MUII E 5 IHOWN VINI D1 O DI1 VENT Z B B r 1 L 31 Iii i 3 i ci 5 U1 O 01465FUELtnRU D1900UNIT O FUEL UNlt O FUEL UNIT D1 IHRU 01454 02901 IHIIU 05530 Figure 3 6 Fuel System D l through D 5330 3 14D Bg ...

Страница 467: ...e airplane To get the best replaced fuel cells fuel lines service from this type of fitting it is etc air may enter the system necessary to exercise certain precautions This condition could cause rough at the time of installation The specific engine operation or loss of power precautions other than the general care If the possibility that air has in handling are as follows entered the system does ...

Страница 468: ...ell area to be patched When synthetic rubber fuel cells are lightly and thoroughly with fine sandpaper tendency to extract the PB asoline has a and wash wi th methyl ethyl ketone to placed in service the asticizer from remove buffing dust the inner liner of the cell This extraction of plasticizer is not detri d Cement the buffed area with two mental as long as gasoline remains in the coats of Minn...

Страница 469: ...Before closing the zipper outside except US Rubber Company repair inspect the fuel cell for any material 5200 5187 must be used foreign matter INSTALLATION OF VELCRO TAPE WITH REPLACE f Close the zipper and refer to MENT FUEL CELLS SERIALS 0 5726 THROUGH REMOVAL AND INSTALLATION OF THE FUEL CELLS 0 9068 for further instructions on installing the fuel cell Ai rp lanes that have had or will have exi...

Страница 470: ...al or phenolic type pressure oil system with a 2 1 3 gallon suppl tank r If the flapper valve is metal it should be inspected The oil system consists of the oil tank oil radiator oil and repaired if necessary as described below temperature indicator oil pressure indicator oil pressure relief valve oil drain on the supply tank and an oil pump i Move the flapper element of the valve through which is...

Страница 471: ...atitv 57 g l l Tho op ionol ydem it th I me e Ihe r ondard ryl m Ihown j bove errapt for Ihs llr which ore I ngsr P Il ilij lj l iilil lii i i _iil i i i ii i llii ii iii ii 5 I6 jiijjjijjiiijiiijjijjiiiliiiiiiiiiiiii i iiiiiiiiiiiiiiiiiiiiliiiiiii i iiiii iiiiii liiiii ii i Iiiii li i 1 li iiiiiii iiiii ii i i liii ii l iiiiaixnl fIl i iiii iiiiiii ii iilliil i i i iiEiiii I i l zl i l i i iiii i...

Страница 472: ...Vt 1 u5 sle OIlll i 1 L PI 12 GAL 37 GAL OPT 1 c AUx PUMP Z 1111 i L H FUEL TANK R H FUEL TANK 25 OPI1 1 4O O L OPI i l llr l 25 Gbl i D G L OPT SELECTOR VALVE rWD ULDR IN VSNIIII X d oavNO ODlb lN n X YtNI STRAINER STRAINER CHECK CHECK VALVE ill i vnLvr SEAL DRAIN FLUSH VENT FLUSH VENT nrolll 0 7829 d AFTER Figure 3 7A Fuel System D 6875 and after Without Turbocharged Engina Bg 3 16A ...

Страница 473: ...12 CIL 31 OIL OPT I I HIGH LOW PREIS PRESS ii f 5 5 UX AUX PUMP PUMP 1 f c j 5 I 25 GAL 40 OAL OPT DRI NO I CWO L H TUEL TANK R H IUEL TANK t II GLL I O aIl o r I SELECTOR VALVE C GRAIN OoallN i ENI VENT CHECK STRAINER STRAINER C fCI VALVE 3 1 oa lN i VALVE SEAL o l VENT VENT Figure 3 7B Fuel System With Turbocharged Engine 3 168 Bg ...

Страница 474: ...ained that the c Adjust the control rod linkage so that tl t door interior is completely filled with cleaner Do not remove pulls in snug against the opening the check valve from the tank If a vat or tank of sufficient size to permit submersion of the oil tank is not available the openings in the oil tank may be plugged and the tank NOTE completely filled with kerosene or distillate The tank should...

Страница 475: ...n a jam nut is tightened against the clevis loosen the locknuts on the upper limit switch and adjust as to prevent further movement The control cable clevis is necessary to stop the flaps in the neutral position Actuate pinned to the cowl flap control arm by means of a quick the subpanel switch to landing position and measure the release pin which must be installed before the engine access degrees...

Страница 476: ...t conditions the lowering Adjust the 16 limit outboard switch in its mounting slot of the landing gear will reduce the tendency for until the flap is positioned at 15 5 to 16 after the flap has excessive speed buildup This procedure would been actuated from the down to takeoff position also be appropriate for a non instrument rated 3 Adjust the downlimit switch in its mounting slot until it pilot ...

Страница 477: ...d June 8 19hS or later should be compartment incorporated in the airplane if the manifold pressure is changed to IX inches Hg pressure switch is connected into the pitot and static system The pressure switch in the gear up circuit is acttlated by the pressure differential that exists between the By the same token the landing gear will automatically pitot and static air system and will close with i...

Страница 478: ...e mark was milde while the airplane was in the two installed in the left main ge lr wheel well follows flight 3 Adjust the micioswitch until the cam clicks the switch a Secure the rolled up tubing so that it will hold the closed with the throttle in the position indicated in the airspeed indicator re lding 110 or 120 mph preceding step b Connect a continuity tester across the contacts of the press...

Страница 479: ...nd check the rigging The 2 Disconnect nose wheel door linkage at attilching point following procedure for rigging the landing gear was written on the door itnd remove links by unscrewing at the upper on the assumption that the entire landing gear is out of rig joint 3 Remove bolts attaching the main gear outboard door links at main strut Remove inboard door actuator rod bS NOTE unscrewing from inb...

Страница 480: ...0178 AND AFTER 3 FLAP ACTUATOR DO NOT BEND TAB OR ROTATE ACTU ATOR TO ADJUST SWTTCH SETTING FLAP LIMTT SWTTCHES LOOSEN JAM NUTS ON SWITCH AIRPLANE SERIAL NO D l THROUGH D 3701 PLUNGERS AND MOVE SWITCHES UP OR DOWN INDIVIDUALLY FLAP UMTT SWTTCHES FLAP LIMIT SWrrCHES FLAP TRANSMITTER 510 a r AIRPtANE SERIAL NO 0 3702 THROUGH 0 10178 AIRPLANE SERIAL NO 0 10179 AND AFTER AIRPLANE SERIAL NO 0 7977 AND ...

Страница 481: ... i _ _ Md ntr in xin n lln lyU 3 II HI C rmc L 3 IInll m oual I o ond oh 1 run t 71 Vij CQ e C3 rr a Eun uu n r wru CI NC urue ulas o aul a a c L 2Y1 OW CLDVt cOllranllsn olon ururl run A osrun r tl Inr r ihn a DUU rr u ubpul YI D UI h IL D1UI DUU Lnup D lbl IWY UU O run LOUIO 11 I IIW L I um olu n r onm un IuOm c an in ah UI o4W Dual Figure 3 9 Elrrtric Systrm 3 20 RePised Jvnuuy 15 1964 ...

Страница 482: ...d gear extended to the nothing for spring adjustments New bushings actuator assembly are 2 5 8 plus 1 16 minus 0 will shorten the linkage again permitting inches from the center line of the stop bolt See adjustment of the spring Figure 3 11 14 With the gears extended check the force required 6 Extend gear and check hand crank There should to deflect the knee joint of the nose wheel be 1 8 to 1 4 t...

Страница 483: ...ht mechanism or preventing the gear from should be on retracting 22 Recheck limit switch adjustment and remove aircraft from jack 17 Connect nose door linkage and rig nose door Check closely to see that right hand aft hinge clears the tire LANDING G EA R POSITION L I G H T Adiust the nose gear doors by varying the length of the ADJUSTMENT 0 9069 and afrerl push pull linkage rods in the nose wheel ...

Страница 484: ...s during a Loosen the locknuts on the adjustment bolts so retraction thus permitting extension of the nose gear At that they clear the stops on the nose wheel straightener the same time the slip joint pin was replaced by a pin b Turn the nose wheel to the extreme left turn designed to fail at loads lower than the failure point of position the adjustment bolts must be clear of the srop other parts ...

Страница 485: ...TMB T up a b a n n b u Irmi b uupIu hiH into ih I nd nL bour 6 ine hh unpin nm b up rr m hn d h i atdkd H ih hund in poiltb g dnrnnrurd it rill nut v 6 L L i j 2 J O 2 RTI SWnOl L CHKKun Mni cuJ1 ooWm we rwwcm Non GUI mane oJun an Z L n CUI i JIIRTISWITCH DJUSTMWT CILILPe 5 10 Lulls GePT s stlm esued SepDmber 1911 5 29 ...

Страница 486: ...g gear up br c xit h diult so tbot h to this point h inrhtrorcl of pro DOWN WI1TION up limit sxitrh MMI rong hr odjurting i la or i required 10 OOY I1C opmting petition liO ope olion boding gear doun limit iritrb m up brohe 2 dt SUO d operotion Londing gear x ming horn I iLh I I a II in Third opcmlion L nding gear down br Le switih Pi ot 9 Plunge I Itu tor T b je L Up BII Ixit h C3 p i u l n st dl...

Страница 487: ...ly procedure recommended Use AD USTMENT electric or gravity only when pressure bleeding is not possible a With the aircraft in flight place the propeller control in low pitch and slowly pull the throttle control out until 12 to 14 inches of manifold pressure is indicated GRA VITY BL EEDING b Mark the position of the throttle control c After the aircraft has landed and with engine shut The reservoi...

Страница 488: ...on to the disc reaches 7 16 inch with brakes less applied Replace the steel brake disc when the thickness is 170 or below measured at thinnest section Also replace Aircraft D 9193 and after are equipped with single dise the disc when the distance from key to disc key slot reaches brakes The brake lining should be replaced before the 040 metal back plate is exposed through the abrasive surface This...

Страница 489: ... ensure correct reinstallation NOTE d Remove the master cylinder attaching bolts and nuts and remove the master cylinder If the parking brake system fails to hold the e If a new master cylinder is to be installed note the valve and connections should be checked for position of the 45 degree elbow fittings evidence of leakage and the seal in the valve f Reinstall the master cylinder by reversing th...

Страница 490: ...luid reservoir SINGLE BRAKE SYSTEM 2 Master cylinder 3 Parking brake valve located forward of firewafl above nose wheel well 4 Shuttle valve iP I k fi I i1 5 S _ 2 3 r DUAL BRAKE SYSTEM I rZ 2 I 1 2 I J i 35 21910 Figure 3 12 Brake System 3 27 ...

Страница 491: ... hose sections ing in the left side of the baggage compartment and should be visually inspected for signs of deterioration is drained by removing the drain cap on the tube end There are two sections of hose in the pitot system one hose at the pitot mast accessible by removing the mast NOTE from the underside of the wing on serials prior to D 4866 or removing the inspection door adjacent to Wax or ...

Страница 492: ... stalling decelerate no faster noting the speed at which the warning horn and light than one mph per second It may be necessary to make come on and the speed at which the full stall occurs NOTE On airplanes Serial D 6842 and after the stall warning horn and light are replaced by a warning buzzer which is activated in the same manner as the warning horn and light Issued June 1971 3 28A ...

Страница 493: ...r6 141 0 CLIM i 1111 110 NDICITO INDIC TOI uur iaom 0 6112 ND IPnD IT TIC LI l rr ne soar I rr or cuma aNr olalN I oear n ArOT LIN D I nnOUCY D I B IND IAT h o ND ITR a OPIIONIL TMIIGrNCI ITPITIC 1II IOVICI B nro un IND P g a Fyure 3 13 Pitot and Statir Systenl ...

Страница 494: ...n Outlet 13 Fixed Exhaust Rear of Hatshelf i I 14 Overhead Fresh Air Outlet Optional I 15 Fresh Air Intake i i 16 Fixed Exhaust L H Side of Fuselage i 17 Overhead Fresh Air Shutoff Control i 15 18 Overhead Adjustable Exhaust 19 Individual Overhead Fresh Air Outlets I 20 Aft Cabin Heat Control 21 Vent Shutoff Control 22 Fresh Air L H Wing Root 23 L H Forward Outlet 24 Defroster 25 Overhead Fresh Ai...

Страница 495: ...the drains and wicks may be filled with salts and mineral The heat exchanger should be checked at each 100 hour deposits If so replace the wicks as follows inspection for cracks and leaks which could introduce carbon monoxide gas into the heating system This can be accomp i Fill the wick box with water and soak the lished as follows wick assembly for a few hours to loosen the salts and minerals ar...

Страница 496: ...hrough the left landing gear uplock position switch s normally closed contacts clos AIR CONDITIONING SYSTE REFRIGERATIVE ed with the landing gear extended which will indicate a door D9787 D 9806 and after open condition while the gear is extended The optional air conditioning system is a recirculating 12 000 The high pressure sensing switch monitors the pressure of BTU cooling system The system is...

Страница 497: ...tered into the evaporator at a rate of checking the refrigerant level checking compressor oil level 55 psi which allows most of the liquid to return to a gas The and changing the system air filter Recharge the system heat required for evaporation is absorbed from cabin air whenever the refrigerant level is low air has entered the passing over the evaporator coils After passing through the system o...

Страница 498: ...d by detergent bubbles or an electronic detector have to be replaced Use a small amount of clean 500 viscosity refrigeration oil Texaco Capella E or equivalent on all tube COMPF ESSOR EEL T TEIVSION ADJUSTMENT joints and dip the O ring in this oil before assembling the joint This will help in making a leak proof joint After 36 to 48 hours operating time a new belt will stretch to its normal operat...

Страница 499: ...ht Glass 7 High Pressure Service Valve 8 Expansion Valve 9 Evaporator 10 Low Pressure Service Valve II Low Pressure Limit Switch 12 Low Pressure Line 13 Louvers Air Duct 14 Air Duct 15 Fan I 16 Fan Motor 17 Condenser Actuator 18 Compressor Clutch and Pulley awa lo i FiIlure 3 130 Air Conditioning Syaont 0 9787 D gsOG ond odor 99 8 890 ...

Страница 500: ...re to bleed off then disconnect the fitting h Remove the electrical lead from the motor i Remove the refrigerant lines and cap the four openings c Disconnect refrigerant lines at the compressor j Remove the bolts attaching the evaporator to the Cap refrigerant lines and compressor fittings floor and remove the evaporator d Remove compressor belt as noted in COMPRES SOR BELT REMOVAL in this Section...

Страница 501: ...IL AIR SEPARATOR SUCTION SERVICE VALVE I GAGE VALVE VALVE SUCTlON UNDER COPILOT S SEAT I VALVE I VACUUM PUMP ERVICE VALVE HIGH PRESSURE DISCHARGE COPILOT S GAGE SEAT t RECEIVER O DRYER a SIGHT GLASS UNDER COPILOT S EXPANSION VALVE SEAT EXPANSION v lvr i TEMPERATURE BULB IN OUT II i CONDENSER IN OUT h CLAMPED ON EVAPORATOR OUTSIDE OF PLUMBING Figure 3 13D Air Conditioning System Schematic Is 3 30C ...

Страница 502: ...ower not functioning b Repair c Leak in system c Leak test and recharge d Compressor valves d Repair or replace inoperative 3 Excessive vibration of a Overcharged a Correct refrigerant charge unit b Air in system b Purge and recharge system c Mount or compressor bolts c Tighten loose d Drive pulley loose d Tighten 4 Noisy unit a Compressor oil level low a Add oil b Defective belt b Replace c Lowre...

Страница 503: ... the oil fitter becomes air into the vacuum pump and it is essen clogged the oil that would normally drain tial for proper operation of the vacuum backinto the engine sump will be forced operated instruments that the relief valve out through the separator vent tube on the screen be kept clean Frequency of clean underside of the fuselage Therefore the ing the screen will vary with the condS oil sep...

Страница 504: ... safely operate or operation of the instrumen s the gyros and or the autopi lot indicates a fluctuation of the system system pressure or a decrease in the system pressure check for The pressure system provides the air excessive pressure a partial required for operation of the autopilot restriction in the lines a filter and instruments Air pressure from an partially obstructed or pressure externall...

Страница 505: ...uipped with an autopilotl the kinks and excessive carbon With pressure regulator should be adjusted to the discrepancy repaired or obtain a reading of 5 0 0 5 psi on the whenever any components are test gage in the turn coord nator supply replaced in the pressure system line with the engine operating at 2300 rpm adjust the pressure as follows and the autopilot ON Normally a pressure of 6 5 psi on ...

Страница 506: ...ure regulator should be adjusted CAUTION NOTE In the event of a malfunction of an instrument or the dimming cir Airplane serials 0 9588 and after cult check the electrical circu do not have the adjustable itry wiring and connectors If orifice Pressure system adjust the fault Is not in these Itms ment for these airplanes will be do not attempt to repair the the same as noted in steps a instrument i...

Страница 507: ...ystem does not use a gyro for reference roll and turn detection is made by a but uses the airspeed rate of ai rspeed tilted gyro EVT turn coordinator elec change and inertial signals to control the trical vacuum torquing combi nati on elevator through the pi tch servos An mounted in the instrument panel A damp altitude hold sensing unit works in con ened miniature airplane serves as the junction w...

Страница 508: ... UII 110 1010110 I lllwn II II 111 11 IW LI I I I UII II tll llll O ii U I i la on a II I YUII rtri s Ii 5 g 4 VIO 1011 L Illlp ii i s uoc Iml n II II II oMoom ao II Y UP I IUW I I1Y Di II I IN1 I 00 llol 11111 lull rr 11 I I I I II IY I I ii II 010 nl 111 1 1 110 I n l I I P II uoltl OllvI d lular usl l 1100 m a o i la rut Figuta 3 14C BEECHCRAFT NewMetic B 7 Syttem Block Diagram 3 30L ...

Страница 509: ...LOW sls JII NAV CLNTERINC 13y G HDG GRAD OJT VOR CAIN Ir aPJVmD SECHECn LI i t INTERCEPT PD3UST 22 FACTORY i 3 A 3USTS C e o n I MAN CWTWNG Q QUAI RRTUSe AD3U TT STDIBZS ser A7 450 Figure 3 14D BEECHCRAFT New Matic B 5 and B 7 Heading Lock Navigation Coupler System Adjustment Points 3 30M 89 ...

Страница 510: ...raft primary cables b Check security of attachment or excessive friction in aileron binding etc and adjust as out and or rudder cables pulleys lined in Section 3 bell cranks or loose servo cables c Leak in servo or servo lines c Check for leaks d Obstruction in servo lines d Check for foreign matter e Faulty turn coordinator gyro e Replace turn coordinator 3 Autopilot sluggish a Low system pressur...

Страница 511: ...t fails to turn a Faulty magnetic heading a Replace magnetic heading sensor to and hold magnetic headings sensor b Faulty heading selector b Replace controlier amplifier resolver c Faulty controller amplifier c Replace controller amplifief 12 Magnetic headings con a Heading sensor misaligned in a Check for proper installation sistently high or low aircraft b Heading azimuth dial shifted b Tighten ...

Страница 512: ...a Wrong nav input signals a Check wiring mode decays to 0 voltage b Defective switching console b Repair or replace console if installed c Dirty input signal AC c Check indicators volts 23 Voltage output in MAN a Polarization pins reversed a Reverse pins See Figure 3 14C CAP TRK and APP mode but on heading sensor plug none in HDG mode 24 Nav indicator needle a One of the components is a Check for ...

Страница 513: ...m will not respond to a Primary pressure not set a Adjust as outlined in Section 3 airspeed changes properly b Pitot pressure inadequate b Check pitot plumbing c Decay rate improperly c Adjust as required adjusted 10 System will not respond a Defective pitch altitude a Replace pitch altitude amplifier to up command adjustment amplifier b No EVT potentiometer output b Replace turn coordinator 11 Sy...

Страница 514: ... when displaced inoperative b Leak in altitude system b Check for leaks c Altitude limiter improperly c Adjust as required adjusted 16 Aircraft descends or a Servo control valve not a Apply positive 6 6 volts max to ascends continually when phased correctly blue lead and verify nose up system engaged response 3 30R gg ...

Страница 515: ...iggers If method of isolating the trouble source is to remove the lens the SCR does not trigger measure the voltage across R7 of the xenon lamp and test the lamp Inspect the lamp to 100 ohms This voltage will be below S volts If the see if it is broken or loose in its socket If the lamp is intact voltage is indicated place an oscilloscope across R7 and use a DC voltmeter to check for approximately...

Страница 516: ...K CR3 C1 4 R1B2I II I R4 C2 MEG 100 I1 I TIIIC 300rl Q4 RE 05 CR5 dj j ll 1 5 7114542 MEO 1 25r I ICND 71543 OR RI C3 RS 1 5 MIG II 2111671 330 ri 10p 03 c4 T 5 R7 100 n OSELIC110 10 DIUlr I tT 3 601 1 Figure 3 14E Bullock Power Supply Schematic Internal Issued March 1971 3 31 ...

Страница 517: ...e strobe light procedure when removing and installing the assembly power supply Removal and Installation of Wing Stiobe Lights WARNING Strobe Light Wiring An incorrect hook up of the wires at either the power input or between the strobe light assemblies and the power supply To avoid damage to the strobe light sy tem or unit will cause a reversal of polarity that results in serious possible physica...

Страница 518: ...at fifty percent of its useful life or when the transmitter has been in use for more than one cumulative hour NOTE The battery furnished with the ELT in the Bonanza has a shelf life of two years Therefore the bat tery must be replaced in one year To replace the battery proceed as follows a Place the ARM OFF ON switch in the OFF position b Disconnect the antenna cable and remove the ELT from the ai...

Страница 519: ...witch on the ELT to the OFF position The audio signal should disappear completely e Place the switch in the ARM position There should be no audio signal present NOTE If a signal is heard the impact switch has probably been activated and should be reset f Firmly press the reset switch on the front of the ELT and listen to ensure the audio signal disappears from COM 1 INSPECTION OF FUSELAGE BULKHEAD...

Страница 520: ...the rear of the handle This will free the handle spring and allow the handle to be disengaged from the actuating assembly d After fitting the new lock to the key install the new lock barrel in the unlocked position into the handle e Bevel the edges of the square hole in the locking cam unless these edges are beveled proper installation cannot be made and place the cam on the end of the lock barrel...

Страница 521: ...e outside handle To adjust the handles on serials D 4146 through D 4150 D 4306 and D 4379 and after remove the small upholstery panel above the door window by removing small upholstery panel above the door window by re moving the screws and releasing the push fasteners and remove the nut and bolt on the door catch Adjust the cable to proper length by screwing the turnbuckle in of out 035 FRONT SEA...

Страница 522: ...racket se curing the left hand bracket and install the nut H35 FRONT SEA TS The Model H35 has sliding individual front seats which can be adjusted fore and aft in flight The latching mechanism is operated by a lever under the right front side of each seat FRONT SEA TREMOVAL MODEL H35 The adjustable individual front seats of the H35 Bonanza series D 4866 and after are secured by pins through the af...

Страница 523: ...AR COVER INSTALLA TION ICAUTIONI CAUTION Improper installation of the forward car y through spar cover may interfere with the landing gear emergency hand crank operation Ensure the landing gear hand crank will rotate without interfer ence with the spar cover a Centersparcoveron theforward spar b From inside of RH access cover install air duct on plenum and grill assembly and tighten clamp c Instal...

Страница 524: ...Raytheon Aircraft BEECH BONANZA 35 SERIES SHOP MANUAL THIS PAGE INTENTIONALLY LEFT BLANK B20 3 33C ...

Страница 525: ...t The flare installation should be serve the tachometer for any change in rpm during inspected at each 100 hour inspection for security the leaning process Caution should be exercised to of mounting since it is possible for the recoil to return the mixture control to the Full Rich position damage the flare bracket if a flare is fired Inspect before the rpm can drop to a point where the engine the ...

Страница 526: ...only 0 018 1 0 006 OFF mcilns electrical circuits are inoperative Bendix S6RN I OI and SbRN IZ05 to 793 thru BATT means the battery electrical circuit is except 13 8622 and D 8623 operative main 0 01h C 0 003 L means the left magneto battery circuit and retard breaker SbRN IZOI only 0 01h e 0 006 generator circuit are operative Slick 662 D 8h22 D l h 3 D XKW thru D X Xh except D R means the right ...

Страница 527: ...and over the number I cylinder cylinder spark plug hole and rotate the crankshaft in the direction of normal rotation until the compression stroke is indicated by SLICK MAGNETOS positive pressure inside the cylinder lifting the thumb off the spark plug hole On Slick mayentos turn the magneto drive in the direction 3 After locating the compression stroke of number i opposite to normal rotation this...

Страница 528: ...he engine being timed 13 Rotate the engine in the normal direction to the NOTE specified before top center BTC firing position this is to remove gear backlash Further movement of the engine Do not engage the impulse coupling should not be necessary until the magnetos are installed 21 If the timing lights do not respond at the same time NOTE loosen the magneto that is either early or late and repe ...

Страница 529: ...ght inch they must be replaced To replace the brushes lift the brush retaining springs remove the old brushes and insert the new brushes If the armature is dirty it may be cleaned with unleaded gasoline or other suitable solvent CAUTION If adjusting screw is turned down clockwise CAUTION beyond the normal adjustment range the spring support may fail to return when pressure is Do not use carbon tet...

Страница 530: ...the overvoltage relay energized To reset the relay and attempt to return the alter VOLTAGE REGULATOR ADJUSTMENTS Airplane se nator to service requires isolating the relay from the power rials D 10097 D 10120 and after source If an overvoltage condition occurs in flight the fol lowing procedure may be used The output of the alternator is regulated by a fully transis torized voltage regulator locate...

Страница 531: ...50 to 180 inch pounds ALTERNATOR D 7310 and after in diagonally opposite pairs d Connect the electrical wiring to the alternator On serials D 7310 through D 10119 except D 10097 a 12 volt 70 amp alternator is installed On serial D 10097 D 10120 and after a 8 volt 50 amp gear driven alternator is standard CAUTION equipment although a 100 amp alternator may be installed as optionalequipment Never tu...

Страница 532: ... event of loss of electrical power on the is removed When the overvoltage relay is actuated it main system bypasses the ON OFF switch to lock the relay in the actuated position until the engine is shut down at which The standby generator system is an independent electrical time the regulator will reset Generator and battery fuses system incorporated into the main system in such a manner are on the...

Страница 533: ...move the two hex nuts and washers from the mounting studs and remove the starter If the brushes are excessively wol n when comp lrc d lo l neH STARTER INSTALLATION 10 520 engine blush they should be replaced NI ke sul e thc bl l zh holJsl s are clean and that the brushes u e not binding in the 0 7310 and after The full brush surface shollld ride on rt K commutator to give a Install a new O ring on...

Страница 534: ...ction manifold As the pressure tion is supplied by regulated engine oil pressure at the oil it senses decreases it expands extending a metering pin cooler and directed from a tee outlet to the housing provid which reduces the flow of oil through the body of the unit ing a constant oil flow over the bearings The oil then drains and increases the pressure across the actuator diaphragm by gravity int...

Страница 535: ... and P N 632555 12 for arm 10 5 If the manifold pressure REACHES 32 5 IN HCI 2 Install arms 10 and 11 on the new unit in the BEFORE THE APPLICATION OF FULL THROTTLE same position they had on the old unit and safety wire arm 11 Due to the serrations on the control a Shut the engine down ler shaft do not torque the castellated nut on arm b Loosen the lock nut on screw 13 10 until the final setting h...

Страница 536: ...IIOT LE BUTTEI FLY LINKAGE nM 3 _I FWD 2 cl s c1 2 Xo f 9 VIEW LOOI ING DO K ON F110 1 I II O I S SII I 10 It DOLT llOLE 4 O j 09 1 81 O 6 B 3 8 I IOLI 7 9 O 36 240 1 Figure 3 15A Turt ochar ler Controller 66 3 366 ...

Страница 537: ...T1 L I 33255 3 7 11 1 VASIIEI CONTINENTAL P h 025327 2 HOLE F01 COTTEI I EY FLAT VASHERS RIAY DE ADDED I1I I E AS REQUIRED TO EXERT PRESSURE ON COTTER KEY FLAT WASHER CONTINENTAL P N 537690 LI AGE 35 240 2 Figure 3 15B Control Arm In tallation 336D 86 ...

Страница 538: ...tion is noted remove the exhaust discharge With the exhaust valve in the open position stack and apply Kano Kroil penetrating oil or Mouse Milk g The waste gate flanges With the exhaust valve in liberally to the area behind the wheel around the turbine the open position shaft seal After a few minutes attempt to turn the shaft A light tap on the shaft end with a soft mallet will often assist in fre...

Страница 539: ...ich 32 5 IN Hg can be i i maintained 3 C1 i i i i j f 18000 i i i i i I i f i f ii ic I 1 I c i 1 t a i i i i 1 1 E 17000 16000 ACJ W g f I i I I I i 15000 I il l I I I 1 l l r I I I I I I I I I 14000 i i j Ii i j i i j i jlj I I i I 11 1 11 11 1111111 1 i I i j j j i j j i j i 40 20 0 20 40 80 35 601 6 OUTSIDE AIR TEMP F Figure 3 15C Critical pressure Altitude Vs OAT Graph 3 365 Bg ...

Страница 540: ...INE SUMP TO CHECK I tl II VARIABLE INTAKE CONTROLLER ENGINE VALVE SCAVENGE CASE PUMP II IICOMPRESSOR TURBINE BELLOWS I I jl ALTERNATE AIR i I II 1 1 I I EXHAL ST SOURCE PULL TO _ I II II I I BYPASS OPEN j ENGINE EXHAUST TANK j VENT I ONE WAY 11 111 1 I II TYtWASTEGATE CHECK VALVE IIEXHAUSf TAILPIPE iJ CONTROL SYS VENT LACTUATOR SUMP TANK OVERBOARD 56 l b Figure 3 16 Tut bocharger Schematic Be 336G...

Страница 541: ... quantity indicator 1 30 Landing gear indicator 2 10 Oil temperature indicator Z 12 Stall warning indicator 1 LD Throttle warning horn 1 3 0 Fuel boost pump warning indicator 1 08 Tab indicator 1 10 Cabin dome light 1 56 Instrument light 2 56 Landing light 2 19 00 Navigation light 3 i 15 Flap motor 1 6 0 Landing gear motor 1 20 0 Fuel boost pump motor 1 5 0 Battery relay 1 59 Starter 1 210 0 Turn ...

Страница 542: ...ne Serial No D 6X42 thru D 10119 except D 10097 The following are lists of those standard and optional items which place continuous loads on the aircraft s circuitry These loads must be tabulated when performing an electrical load analysis on the airplane The lists include only items that are physically able to function at the same time When computing the load analysis the load for items of option...

Страница 543: ...17L 8A Transmitter 4 6 51X 3 Receiver 3 5 344D 2 Omni Converter Indicator 166 ADF T 18 Automatic Direction Finder 1 2 NAV COM M 135 6 96 2 54 NAV COM 23743 8 0 1 6 5607D Glideslope 1 3 5613A 1 5 5537A 7 5642A 6 96 1 04 236A 3 11 T 5 D Transceiver 9 4 4 0 T 9 RA Transceiver 9 9 5 0 UDI 8 DME Distance Measuring Equipment 8 5 Mark II VTR SA Omnigator 5 4 4 0 Mark V Transceiver 8 5 6 5 Mark VI Omni Re...

Страница 544: ...airplane may be determined Intermittent items should not be figured into the total figure since the short duration of their usage will not significantly alter the standard load The electrical load has been divided into 4 catagories as follows a Continuous road standard equipment b Continuous load optional equipment c Intermittent load standard equipment d Intermittent load optional equipment We re...

Страница 545: ...4 60 Potentiometer Light Dim 4 03 12 Relay Annunciator Dim 1 04 04 Relay Master Battery 1 50 50 Sensor Alternator Out 1 04 04 Turn Coordinator 1 40 40 Voltage Regulator 1 3 00 3 00 Clock Panel 1 01 01 LIGHTING 3rd and 4th Reading Light 2 30 60 Cabin Light 2 17 34 Elevator Tab 1 04 04 Flap Position 1 04 04 Glareshield Flood 12 17 2 04 Tail Position 1 1 02 1 02 Wing Tip Nav Light Z 93 1 86 OAT 1 04 ...

Страница 546: ...01 01 Timer 1 10 10 Power Supply Strobe 1 5 00 5 00 LIGHTING 5th and 6th Seat Reading 2 30 60 Clock Control Wheel 8 Day 1 04 04 Instrument Post Light Single 26 04 1 04 Instrument Post Light Dual 37 04 1 48 Instrument Wedge Light Single 14 024 67 Instrument Wedge Light Dual 16f 024 77 Map 1 30 30 Rotating Beacon Lower 1 3 22 3 22 Rotating Beacon Upper 1 3 22 3 22 Tail NavlStrobe 1 1 02 1 02 1 Inter...

Страница 547: ...4 Relay Dynamic Brake 1 1 25 1 25 Relay Starter 1 3 311 3 30 Starter Engine 1 100 0 100 0 Relay Landing Gear Latch 1 08 08 LIGHTING Alternator Out 1 04 04 Courtesy Light 2 17 34 Door Ajar 1 04 04 Landing Gear Indicator 4 04 16 Landing Light 1 8 93 8 93 Condenser Door Open 1 04 04 INTERMITTENT LOADS Opb onaleguipment Actuator Elevator Trim 1 85 85 Resistor Trim Shunt 1 38 38 LIGHTING Taxi Light 1 8...

Страница 548: ...tinuity of circuit f Defective starting motor f Check brushes springs condition and commutator Replace if necessary GENERATOR SYSTEM i No ammeter indication a Loose connection a Check connection throughout circuit b Open field circuit in b Test resistance of field generator defective Check field circuit con armature nections Replace gen erator if defective c Brushes not contacting com c Clean brus...

Страница 549: ...ions through out system b No alternator output b Check alternator output c Defective voltage regulator c Replace regulator d Overvoltage relay tripped d Check overvoltage relay see item 2 e Defective ammeter e Replace ammeter 2 Overvoltage relay trips a Alternator overcharging a Check alternatoroutput Repair or replace as necessary b Defective voltage regulator b Replace regulator c Defective over...

Страница 550: ...ght light will not illuminate b Fuses between battery b Check for and and ON OFF TEST switch correct cause of blown blown Fuse Replace fuse c Faulty diode between c Replace diode battery and ON OFF TEST switch d Defective BAT TEST d Replace lamp lamp e Defective ON OFF TEST e Replace switch switch 2 With STBY switch to ON a Defective power relay a Replace relay and PWR XFER switch to NAV COMM 1 CO...

Страница 551: ... RPM is adjustment stat or replace increased c Faulty generator c Replace generator d Faulty voltage reg d Replace faulty ulator component of regulator 6 With the STBY switch to a Faulty overvoltage a Replace relay TEST engine at 1200 RPM relay GEN TEST light will illum inate dimmly but goes b Rheostat out of b Bench set rheostat out as engine RPM increases adjustment c Defective voltage c Replace...

Страница 552: ...ate li ten tor S 200 series magnetos for buzzing of vibrator dur S 1200 series magne tos ing starting If no buzzing is heard either the vibrator is defective or the circuit from the output terminal on the vibrator to the retard dual breaker magneto is open Check both Switch and Retard circuits Also check for good electrical ground c Retard breaker or impulse c Points may not be closing coupling no...

Страница 553: ... off timing g Retard points opening too late g Check timing of retard or impulse coupling timed wrong points or impulse coupling 3 Rough running engine a Spark plugs loose or fouled a Clean and regap spark plugs b Spark plugs leads or connec b Clean leads and connectors tors oily dirty or cracked and replace damaged con nectors c Defective ignition harness c Make continuity and high voltage tests ...

Страница 554: ...IT 1 Warning horn inoperative a Tripped circuit breaker a Check for short circuit Reset circuit breaker b Throttle switch out of adjust b C leck throttle switch for ment proper adjustment and continuity c Open circuit c Check circuit for continuit3 and loose connections FLAP CONTROL AND INDICATOR CIRCUIT i Flaps will not lower a Tripped circuit breaker a Check circuit Reset cir cuit breaker b Defe...

Страница 555: ...Both position lig lts inoperative a Open circuit or tripped a Check continuity of circuit circuit breaker Reset circuit breaker STALL WARNING CIHCUIT Serials D l through D 2680 I Stall warning lights inoperative a Tripped circuit breaker a Check circuit Reset cir cuit breaker b Defective relay b Check continuity of relay when landing gear safety switch is actuated Replace if necessary c Defective ...

Страница 556: ... 1 Warning buzzer inoperative a Tripped circuit breaker a Check and reset circuit breaker b Open circuit b Check continuity of cir cult c Defective switch c Check switch for proper operation Replace if necessary d Defective indicator d Check buzzer for proper operation 2 Buzzer operates continuously a Grounded circuit between a Test for ground in cir buzzer and switch cult b Defective switch b Che...

Страница 557: ...Reset circuit breaker b Open circuit b Check continuity of cir cult MANIFOLD PRESSURE GAGE i Instrument fails to indicate a Defective instrument a Repair or replace instru or give correct indication ment b Loose or broken line or fitting b Repair or replace 2 Excessive error at baro a Leak in pressure lines a Repair lines metric pressure b Condensation in lines b Clean lines c Faulty mechanism c R...

Страница 558: ... 3 Pointer vibrates a Excessive vibration a Check panel mounts b Tubing vibration b Check tubing clamps 4 Hand oscillates a Leak in pitot or static line a Repair leaks b Leak in Rate of Climb or b Repair all 3 lines Altimeter c Defective mechanism c Replace instrument d Leaking diaphragm d Replace instrument RATE OF CLIMB INDICATOR i Does not indicate zero with a Ageing aneroid a Return pointer to...

Страница 559: ...upply fluctuating c Check for constant and or not properly set correct vacuum 2 Pointer fails to respond a Inlet cap or screen clogged a Clean or replace 3 Vibrating hand a Excessive vibration a Check panel mounts b Damping screw not properly b Readjust adjusted c Defective mechanism c Replace instrument 4 Hand sluggish returning to a Damping screw improperly a Readjust zero adjusted b Defective m...

Страница 560: ...or venturi e Vacuum line kinked or leaking e Repair or replace 2 Horizon bar does not settle a Defective mechanism a Replace instrument b Insufficient vacuum b Readjust vacuum c Excessive vibration c Check panel mounts 9 Horizon bar oscillates or a Air filter dirty a Clean or replace filter vibrates b Vacuum regulating valve b Readjust valve improperly adjusted c Faulty vacuum gage c Replace gage ...

Страница 561: ...luctuating c Checle for constant and or not properly set correct vacuum MAGNETIC COMPASS I Excessive card error a Compass not properly a Compensate instrument compensated b External or internal magnetic b Locate magnetic interfer interference ence and eliminate if pos sible 2 Excessive card oscillation a Insufficient liquid a Add fluid Specification MIL L 5020 b Excessive vibration of instru b Cor...

Страница 562: ...eplace pump c Insufficient lubrication of c Provide proper lubrication vacuum pump d Leak or break in suction line d Locate and repair e Defective gage e Replace 2 Excessive suction gage a Air filter clogged a Clean filter element reading b Suction relief valve not b Adjust valve properly adjusted c Suction relief valve failure c Repair or replace d Defective gage d Replace gage 3 Suction gage ino...

Страница 563: ...ity of circuit 2 One flare will not release a Defective switch a Check continuity of switch Replace if necessary b Open circuit b Check continuity of circuit c Defective flare release c Inspect the release mecha mechanism nism Replace if neces sary TURBOCHARGER SYSTEM i Turbocharger inoperative a T C rotor jammed a Replace b Controller malfunctioning b Replace c Wastegate linkage not c Adjust or r...

Страница 564: ... ruptured in controller b Replace c T C bearing seals leaking c Replace 5 Oil leaking from actuator a Actuator piston seal ruptured a Replace drain 8 High manifold pressure at a Controller out of calibration a Replace take off b Controller malfunctioning b Replace c Controller pressure sensing c Replace line broken d Wastegate linkage not d Adjust or replace functioning e Controller pressure sensi...

Страница 565: ...charge duct c Eliminate ally leaks loose or leaking 11 Excessive noise or vibration a Improper bearing lubrication a Clean or replace oil line clean oil strainer and supply oil pressure IF trouble still persists overhaul turbocharger b Leaking el ine intake or b Tighten connections or exhaust manifold I eplace manifold gaskets as necessary 12 Engine will not deliver rated a Clogged manifold system...

Страница 566: ...by the centrifugal effect of propeller brush holder then slide the springs off the brushes rotation and by the blast of the airstream The timer cycles e Unsolder the wires for the brushes being replaced power to the two heating elements on each blade in the noting which pin on the cannon plug they correspond to following sequence outboard inboard outboard inboard f Solder the wire from the new bru...

Страница 567: ...nd nuts making After obtaining a voltage reading of 14 volts DC hold the certain that 1 16 plus or minus 1 32 inch is maintained voltmeter probe on the pin until the voltage drops to zero between the brush block and slip ring surface To prevent before moving the probe on to the next pin in the sequence damage to the brushes the brush block assembly should be noted above After establishing the corr...

Страница 568: ... plug to the outboard terminal of one between the slip ring assembly and the spinner bulkhead prop boot d Pin F of the plug to the inboard terminal of one prop boot NOTE e PinG oftheplugtoground f Ground terminal of one prop boot to ground The above adjustments may affect the clearance between the brush block and slip rings consequently after slip ring alignment a check DEICER RESISTANCE CHECK sho...

Страница 569: ...tem In general for most Consequently it is recommended that to determine which effective use of the troubleshooting chart all of the circuits are involved troubleshooting be preceded by the indication entries should be read to locate that which ammeter test outlined in step 1 of the 50 hour inspection matches conditions of the particular system being checked and the heat test described in this Sec...

Страница 570: ...n heat test rent part of cycle zero cur and firewall connector to find Deicers not heating and test rent rest of cycle for voltage on that pin of ftrewall connector If zero over 2 minu tes locate and fix open in wiring from timer to firewall b Open between firewall and b If voltage OK to firewall plug try Deicer lead straps voltage at junction of Deicer lead and slip ring lead If no voltage find a...

Страница 571: ...uding ring contact check for ground ground brush circuit from slip ring lead to bare prop while flexing slip ring and Deicer leads Ifa ground is indicated locate and correct c Short between two adjacent c Check for shorts or low resistance circuits between circuits if any locate and correct d Timer faulty d Test timer as indicated in para graph on timer check 7 Ammeter does not flick a Timer groun...

Страница 572: ...rs on 9 of 100 hour inspection Look for rough or dirty slip rings IT this is the cause clean machine or replace slip ring assembly Check for slip ring alignment b Loose connection b Refer to step 8 above c Switch faulty c Try jumper wire across switch If radio noise disappears replace the switch d Wiring located within less d Replace at least 8 inches from in than 8 inches of radio equip put wirin...

Страница 573: ...SECTION IVIAJ O R DISASSEMBLY ...

Страница 574: ...L SECTION 4 Major Disassembly ...

Страница 575: ...EMPORARY REVISIONS REVISION DATE DATE REASON PAGE NUMBER INSERTED REMOVED REMOVED NUMBER 4 1 Dec 11 92 Nov 15 93 Temporary 4 6 Revision 4 2 4 2 Nov 15 93 4 6 NOTE Insert this Record of Temporary Revisions after the Section 4 divider tab Page 1 Nov 15 93 ...

Страница 576: ...s special points on removing and installing major assembles of the Bonanza Step by step procedures are given only where it is considered necessary because the process is complex such as the removing and installing of the wing and the installing of the wing panel leading edge 4 1 ...

Страница 577: ...which attach the leading edge On airplanes prior g Operate the landing gear switch until the inboard to D 4866 disconnect the pitot mast and rubber tube from the landing gear doors are fully open left wing before removing the leading edge h Disconnect the inboard door aCtuator rod at the door To remove the main spar remove the landing gear i Disconnect the landing gear uplock cable housing at the ...

Страница 578: ...he bolt through the spring scale attaching point To calculate the force in pounds scaie reading required to obtain the specific torque divide the torque in inch pounds by the distance in inches between the center of the bolt and the scale attaching point For example if the specified torque is 5 000 inch pounds and the distance is 25 inches a pull of 200 pounds must be applied Unless torque values ...

Страница 579: ...PROVIDE A PROPER BOLT GRIP ADJUSTMENT POSITION WITH COUNTERSINK TOWARD BOLT HEAD WET TORQUE TO 1180 TO 1300 INCH POUNDS INSPECT THE WING ATTACH FITTINGS TO ENSURE THAT THE DRAIN HOLES ARE CLEAR NOTE OYIU I REFER TO CHART 3 FOR THE o I WING BOLT WRENCHES AND TORQUE ADAPTERS USED WITH THIS WING BOLT AND NUT 35 31 32 Figure 4 18 Upper Famerd Wing BoA IneteIletIen ID i thru 9 1500 Except Alrpknw with ...

Страница 580: ...LOCATION TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT POSlnON WITH COUN7EIRSINH TOWARD BOLT HEAD WE7TOROUE fO 1 801P_13PO INCH POUNOS 35 31 aC NOTE eoncunrJnt w th me scheduled torque NOTE c eck inspect the oepsr wing attach J cJO oD REFERTOCNART3FORTHE ILthgs to aaaure that the dtein hOkep WING BOLT WRENCHES AND are clear TORQUE AIIAPTERS USED WITH THIS WING BOLT AND NUT Figure 4 C Upper Fonu rel Win...

Страница 581: ...TTING 000 110100 1 BUSHING WING FITTING 1 0 9344 THRU 0 9414 fMS20002 10 WASHER I EXCEPT 0 9379 WET BOLT TORQUE 1180 TO 1300 INCH POUNDS A SECOND MS20002 10 WASHER MAY BE USED TO PROVIDE BOLT GRIP ADJUSTMENT NOTE INSPECT THE UPPER WING ATTACH FITTING TO ENSURE THAT THE DRAIN HOLES ARE CLEAR NOTE REFER TO CHART 3 FOR THE WIND BOLT WRENCHES AND TORQUE ADAPTERS USED WITH THIS WING BOLT AND NUT o I o ...

Страница 582: ...PT D 10097 NAS152 37 OR 131790 1 BOLT D 9379 9415 THRU 0 10119 EXCEPT DRAIN I lt3F I I o loas r HOLE XIli Xii iii3ii l iiZi WING FITTING M520002 12 WASHER FUSELAGE FITTING 0 9379 0 9415 THRU 0 9445 WET BOLT TORQUE 2480 TO 2600 INCH POUNDS f CHECK FOR A SMOOTH COMPLETE RADIUS f AN MS20002 12 WASHER MAY BE USED BETWEEN THE NUT AND THE MS20002 12 OR 95 110025 1 WASHER AS REQUIRED TO PROVIDE BOLT GRIP...

Страница 583: ...S143 10 WASHER MAY BE ADDED AT THIS LOCATION TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT POSITION WITH COUNTERSINK TOWARD BOLT HEAD WET BOLT TORQUE 1180 TO 1300 INCH POUNDS INSPECT THE WING ATTACH FITTINGS TO ENSURE THAT THE NOTE DRAIN HOLES ARE CLEAR REFER TO CHART a FOR THE WING BOLT WRENCHES AND TORQUE ADAPTERS USED WITH THIS WING BOLT AND NUTI o lo 35 3127 Frgure 4 15 Upper Rear Win Bolt Inetalla...

Страница 584: ...DRAIN HOLE jijl ii WING FITTING FUSELAGE FITTING ONE MS20002 10 WASHER MAY BE ADDED TO OBTAIN PROPER BOLT GRIP ADJUSTMENT WET TORQUE TO 1180 TO 1300 INCH POUNDS NOTE INSPECT THE WING ATTACH I I REFER TO CHART 3 FOR THE FITTINGS TO ENSURE THAT I I WING BOLT WRENCHES AFID THE DRAIN HOLES I I ToRaUE ADAPTERS USED WITH ARE CLEAR I I THIS WING BOLT AND NUT O O O 35 3t 28 Figure 4 16 Upper Bear Wing Bol...

Страница 585: ...l50 29 Mi BOLT FUSELAGE FITTING WHEN UWN1O B NUTS ARE REMOVED REPLACE WITH 121 18108 NUTS ONE MS20002 10 WASHER MAY BE ADDED AT THIS LOCATION TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT f POSITION WITH COUNTERSINK TOWARD BOLT HEAD 1180 TO 1 35 31 8 Figure 4 1H Lower Forward Wing Bolt Installation D 1 thru D 1500 Except Model 355 and Airplanes with BEECHCRAFT Kit No 55 5545 Installed 4 48 815 ...

Страница 586: ... i j j i j j i liiiiisi i _i i l j jiiiiiibbi i lj i _ i i I i j l i i 1 ii i ilili i i i _ i i i iii4L j l j i i i i i i 1018 N 4i l r j i n i_ i iiiiiiii l MS20010 26BOLT A i FUSELAGE FITTING WHEN UWN1O1B NUTS ARE REMOVED REPLACE WITH 12NB1OB NUTS ONE MS20002 10 WASHER MAY BE ADDED OR OMITTED AT THIS LOCATION TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT POSITION WITH COUNTERSINK TOWARD BOLT HEAD WET...

Страница 587: ...iiiii 8i i i ifiii8i I l i ai i I i i i i i j i i i i iiii 35 190014 NUT NAS 152 35 BOL NOTE REFER TO CHART 3 POR THE WING BOLT WRENCHES AND TORQUE ADAPTERS USED WITH FUSELAGE FITTING THIS WING 80LT AND NU7 POSITION WITH COUNTERSINK TOWARD BOLT HEAD WET TORQUE TO 2480 TO 2600 INCH POUNDS 3531 39 Figure 4 15 Lower Forward Wing Bolt Installation Model 339 0 3 el 0 92 0 122 2 329 0418 P532 P535 P588 ...

Страница 588: ... WASHER lil il l li iiiiiiiii I ijiiii i iiii iiliilii FUSELAGE FITTI BOLT TORQUE WET 2480 TO 2600 INCH POUNDS COAT THE COMPLETE BOLT NUT WASHER WING FITTING BOLT BORES AND EXPOSED THREADS WITH MIL C 16173 GRADE 2 CORROSION PREVENTIVE COMPOUND 4 POSITION WITH COUNTERSINK TOWARD BOLT HEAD 3531 41 Figure 4 18 Lower Fomatd Wing Bolt inotelletion Yodd 359 with BEECHCRAFT Kit No 35 6948 inetelled 815 4...

Страница 589: ... 10119 EXCEPT D 10097 f MS200002 12 WASHER 1 Wl i NAS152 43 BOLT 0 1501 THRU D 4865 BOLT 0 4866 THRU FUSELAGE FITTING MS20012 28 BOLT D 7310 THRU CHECK WASHER FOR A SMOOTH COMPLETE OUTER RADIUS 0 9343 MS20012 31 BOLT D 9344 f ONE MS200002 12 WASHER MAY BE ADDED FOR PROPER THRU D 10119 EXCEPT BOLT GRIP ADJUSTMENT D 10097 OR WET TORQUE TO 2480 TO 2600 INCH POUNDS 131790 2 D 9344 THRU D 10119 EXCEPT ...

Страница 590: ...B NUTS ONE NAS143 10 WASHER MAY BE ADDED AT THIS LOCATION TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT POSITION WITH COUNTERSINK TOWARD BOLT HEAD WET TORQUE TO 1180 TO 1300 INCH POUNDS FUSELAGE FITTING NASt43 10 WASHER UWN1018 NUT NAS150 29 M BOLT WING FITTING f NAS143 10C WASHER 35 31 31 Figure 4 1M Lower Beer WLng Bolt lnetelletlon P1 thru P1500 815 495 ...

Страница 591: ...111 3 WASHER POSITION WITH FITTING FITTING COUNTERSINK TOWARD BOLT HEAD D 10113 THRU 0 10119 CHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS l ii8 i L LIP 6 r3 i 12NB108 NUT 10 WASHER NAS150 35 M BOLT D 1501 THROUGH 0 10119 EXCEPT D 10097 ONE MS20002 10 WASHER MAY BE ADDED TO OBTAIN PROPER BOLT GRIP ADJUSTMENT WET TORQUE TO 1180 TO 1300 INCH POUNDS 3531 25 Figure 4 1N Lower Rear Wing Bolt Instal...

Страница 592: ...d NUT INSPECTION and REPLACEMENT CVCLE 5 YEARS 5 YEARS 5 YEARS 5 YEARS NEW 1 INITIAL SECOND FIRST REPLACEMENT REPEAT INSPECTION AIRPLANE INSPECTION INSPECTION INTERVAL AND REPLACEMENT CYCLE 5 YEARS 5 YEARS 5 YEARS AIRPLANES SECOND FIRST REPLACEMENT REPEAT INSPECTION 5 YEARS OLD INSPECTION INTERVAL AND REPLACEMENT CYCLE OR OLDER INITIAL INSPECTION NOTE NOTE The first inspection for airplanes five y...

Страница 593: ...he inboard door actuator rod be in place prior to installation of the wing bolts p Connect the hydraulic brake lines and bleed the brakes c Move the wing into position align the wing fittings r At the first scheduled inspection after the wing has with the carry through fittings install new soft aluminum been installed check the attaching bolts for proper torque washers between the upper fittings a...

Страница 594: ...or approximately five minutes These components may be identified by the When the five minutes have elapsed wash the coated area green dye on the head of the bolt and on the nut with water and blow dry do not wipe dry Paint the treated areas with zinc chromate primer Item 5 Chart II WARNING and allow to dry g Coat the bearing faces and bolt bores of the fittings Use only the components specified in...

Страница 595: ...el 35R and airplanes T51222 8 except Model 35R TS1176 1 with BEECHCRAFT Kit or 35 6949 installed 50 590013 MS20010 26 T51222 7 35 190014 None Airp anes w th BEECHCRAFT or Model 35R except Kit 35 6945 installed TS 1222 6 airplanes with except Model 35R or BEECHCRAFT Kit TS1222 9 35 6945 installed NAS152 35iM TS1171 3 r2NB126 TSlr71 2 Model 35R except with Torque Wrench D 1501 thru or BEECHCRAFT Kit...

Страница 596: ... close to the coil detected by the use of finely divided ferromagnetic particles inside wall with the bolt length perpendicular to the winding over the surface of the part Some of the particles are direction The magnetic particle suspension is flowed on the magnetically gathered andheld by the leakage field to form bolt and the appropriate current is applied to achieve an outline indicating the lo...

Страница 597: ... sides of the spar cap WARNING where it meets the skin If a whitish salt like nonmetailic substance is noted in these areas a thorough inspection All areas of the spar caps from the outboard end should be performed to determine if corrosion is present of the spar cap to the wing attach fitting must be Wax or paint trapped between the skin and the exposed inspected portion of the spar caps should n...

Страница 598: ...e upper barrel assembly Department of Beech Aircraft Corporation for evaluation of the problem and corrective action to be taken a With the aircraft on a jack partially retract the ADJUSTING THE WINGS landing gear to take the load off the retract rod compression spring After a wing has been reinstalled or repaired flight tests may b Disconnect the steering yoke at its fitting at the show the wing ...

Страница 599: ... f Disconnect the hydraulic line where the flexible hose couples to the tubing at the wing front spar the landing gear door actuating rods at the actuator g Disconnect the safety switch wires right gear e Remove the four screws securing the landing gem li it switch assembly on the left hand side of the h Remove the bolt attaching the Ilft leg to the strut i Remove the access door in the lower surf...

Страница 600: ...l go and rotate the retainer 90 e Keep inboard pressure on the retainer and tighten both retainer set screws f Secure the flap drive cable to the mounting support by tightening the nuts Tighten the inboard nut to ensure that there is sufficient clearance between the outboard edge of the retainer and the cable housing to allow the retainer to rotate without coming into contact with the cable housin...

Страница 601: ...semblies D 839 thru D 8872 is replaced by a b Remove the access cover 35 380109 motor the larger size of the new motor makes it necessary to c Detach the clamp that supports the electrical wir enlarge the flap motor access hole ing from the right hand flap shaft housing located under the front seat by 0 75 d Disconnect the motor electrical wiring except inch on the aft edge to provide clear ground...

Страница 602: ...the retainer e Rotate the retainers 90 and push it onto the The nap motor used on serials 0 9966 and after is NOT interchangeable with motor drive shaft until it bottoms out against the end of the motor shaft the flap motor used on pn or serials If the flap motor fails or major overhaul is f Keep inboard pressure on the retainer and tighten required for the flap motor to operate both retainer lock...

Страница 603: ...rials In FLAP SHAFT INSTALLATION the event of flap motor failure or it is Effectivity D 1 thru 0 838 1 determined that major overhaul is required for the flap motor to operate a Lubricate the shaft lightly using MIL G 23827 properly the flap motor should be grease replaced No attempt should be made to b Pull the flap shaft through the wing and attach to overhaul the motor in the field the actuator...

Страница 604: ...CTUATOR INSTALLATION the shaft as far as it will go NOTE d Align the shaft key of the flap drive cable with the retainer key slot and insert the shaft into the motor Install the flap actuator with the vent drive shaft Insert the shaft until the key on the shaft is hole on top to prevent the loss of lubri past the key slot on the outboard end of the retainer cant e Rotate the retainers 90 and push ...

Страница 605: ... Replacement of either linings or disc will require the Care should be taken to properly install following disassembly the disc clips in the wheel flange a Remove the hubcap DISASSEMBLY OF GOODYEAR BRAKE b Remove the wheel retaining nut UNIT ONE PRESSURE CYLINDER P PE c Remove the brake disc clips When obvious leakage is noted around the wheel and d Remove the wheel brake housing disassemble the b...

Страница 606: ...dry with a lintfree cloth NOTE i Wash seals in clean hydraulic fluid j Repair or replace all worn or damaged parts Position the wheel so that the five wide slots k Brake discs which have dished tin excess of 1116 between the teeth of the disc are in alignment inch may cause disc clips to become disengaged and with the missing teeth in the wheel flange This should be replaced will permit the instal...

Страница 607: ...D 8460 except D 7213 D 7214 and D 7923 hinge bolt sleeve and washer Tighten the hinge bolt until approximately five pounds of force is required to pivot the a Apply a thin coat of MIL G 7711 grease or its brake assembly equivalent to the cylinder wall of the housing and to the k Secure the hinge bolt with safety wire contacting surfaces of the piston i Pack the wheel bearings and install the wheel...

Страница 608: ...ssembly Care must be taken to prevent damaging the seal as it is installed in the gland assembly After the lips DISASSEMBLY AND EASSEMBLY OF BEECH of the seal have been started into the gland cavity the BRAKES D 9193 and after pusher ring should be used to press the seal into the savit until the seal touches botl m When the brake has ber 11 For disassembly and reassembly of brakes on the above ass...

Страница 609: ...e order of disassembly making certain solution After one minute wash off the Dow No 1 the 0 ring seal installed with tubeless type wheels are Solution with clear water Allow the surfaces to dry then lubricated with MIL G 81322 bearing grease or equivalent prime the treated areas with two coats of zinc chromate Install the 0 ring in the brake side wheel half Torque the primer wheel half bolts to 14...

Страница 610: ...ide inflation tubeless tires on both the nose and main ing even pressure around the entire circumference of each gears The wheel is especially designed for the sidewall sidewall with suitable tire tools inflating tubeless tire and cannot be used with tube type tires To convert the wheel of the sidewall inflating tubeless tire to an inner tube type wheel see CONVERTING WHEELS CAUTION FOR INNER TUBE...

Страница 611: ...lange and the other half with a hole through the side in addition to the cut out in the flange In wheel half P N 9524232 the half not containing the brake 1 In wheel half P N 9524193 locate the large hole in the flange 275 005 000 inches from the 1 Locate the hole for the valve half way inner edge and half way between two bolt holes 60 between two bolt holes 30 from either one and from each Do not...

Страница 612: ...instructions pliers and pull it through the upper latch opening bers Refer to CONVERTING MAIN GEAR WHEELS Remove the safety wire from the cable REMOVING AND INSTALLING THE CABIN DOOR NOTE TELEFLU CABLE a Remove the three machine screws on the door Braze or silver solder two AN340 832 upper facing nuts to new AN742 4 clamps b Remove the door upholstery panels f Prior to installing the upper clevis ...

Страница 613: ...provide additional f Disconnect the elevator tab cables at the tab support to the stabilizer leading edge These kits are g Remove the guide block located on the tab cable to be installed on the aft fuselage at the leading edge at the front of the ruddervator of each stabilizer and do not require removal of the h Remove the cotter pins from the hinge bolts stabilizer for installation i Remove the n...

Страница 614: ...P MANUAL STABILIZER 2 BOLT 3 WASHER 4 ELEVATOR RUDDERVATOR INBOARD HINGE SUPPORT 5 NUT b WASHER 7 WASHER 8 TORQUE FITTING 2 3 X t 8 7 6 5 4 C95W2785132 C Figure 4 1U Ruddervator Installation D l through 0 2680 919 4 10C ...

Страница 615: ...OP MANUAL STABILIZER 2 BOLT 3 WASHER 4 ELEVATOR RUDDERVATOR INBOARD HINGE SUPPORT 5 NUT 6 WASHER 7 WASHER 8 TORQUE FITTING 2 3 V u O O 8765 4 C95012783131 Figure 4 1V Ruddervator Installation 0 2681 and after 4 100 019 ...

Страница 616: ...should move DOWN When the elevator trim tab control is moved toward 2 The inboard hinge requires two AN960 416L the nose down position the trim tab and one AN960 416 washers Install one AN960 416L should move UP washer under the bolt head and one between the tor que fitting and the bulkhead support fitting One ELEVATOR TRIM TAB REMOVAL AN960 416 washer should be installed under the nut 3 Torque th...

Страница 617: ...missible to install an E 185 1 engine in a Remove the propeller and cowling and disconnect models 835 and C35 Also although the E 185 8 and the engine controls plumbing and wiring harness E 185 11 engines are approved for 205 horsepower b Support the tail Hoist the engine enough to take this high horsepower cannot be used when the the strain off of the shock mount bolts engines are installed in mo...

Страница 618: ...N 2 TAB HORN CABLE BOLT DETAIL A DETAIL B RIGHT Cs II to o o ac o RIGHT DETAIL D m sC TAB HINGE PIN RUDDERVATOR DETAIL G DETAIL H WRONG O O O O O O O WRONG DETAIL E DETAIL F C95012783133 C Figure 4 IW Elevator Trim Tab Installation B19 4 1 OG ...

Страница 619: ... K N 3 P35 V35TC 835 V35B Serials D 10179 and after M35 V35 ATC V35 V35 BTC V35A 3 V35B IO 470 C IO 470 N TSIO 520 D IO 520 B IO 520 BB IO 520 BA If IO 520 BA engines are not available IO 520 BB engines may be used when the proper fuel pump is installed APPROVED ALTERNATE ENGINES 35 A35 835 H35 E 185 8 E 185 8 E 185 11 0 470 G CI E 185 11 E 185 11 4 1 OH B19 ...

Страница 620: ...A SERIES SHOP MANUAL THROTTLE AhTD MIXTURE CONTROL CONTROL SYSTEM EXHAUST SYSTEM INTAKE MANIFOLD INDUCTION SYSTEM ALTERNATE AIR INTAKE AIR INTAKE 35240 3 Figure elX Turbocharger Exhaust and Air Induction System 4 11 B19 ...

Страница 621: ...OUTLET ENGINE SCAVENGE PUMP I V II _I AIR DUCT FUEL VAPOR RETURN LINE WASTE GATE ACTUATOR CHECK VALVE WASTE GATE ACTUATOR DRAIN AIR INDUCTION Y TURBOCHARGER SUMP TAM VENT TO ENGINE CASE LOWER END BREATHER LINE TO FUEL PUMP HOSE OIL SUMP VENT TO SELECTOR i i VALVEMANIFOLD TURBO CHARGER DRAIN MOUNT BAR TURBINE COMPRESSOR ROSE TURBINE DRAIN CHECK VALVE W i X 35 140 4 OIL SUMP TANK Figure 4 1Y Turboch...

Страница 622: ...series magnetos have B A35 D 2141 through D 2200 proved unreliable in service and current C A35 D 1823 D 1950 through D 2140 production magnetos do not have this feature D A35 D 1501 through D 1949 except To be safe treat all S series magnetos as hot D 1823 whenever the ground lead is disconnected To E 35 D l through D 1500 ground the magneto connect a wire to the switch lead of the magneto and gr...

Страница 623: ...d be installed with one blade pointing down three stud to a two stud electrical connection and the when the number 1 cylinder is at the top dead center replacement outboard transmitter has been changed from a position After installation of the propeller check that the two stud to a one stud electrical connection Either the spinner is located to assure proper clearance of the propeller inboard tran...

Страница 624: ... 3 Wiring Diagram Inboard and Outboard Transmitters BUSS EXISTING OUTBOARD 95 380012 5 95 380012 3 INBOARD TRANSMITTER I _ 4 STUD FULL 2 STUD 3 STUD DASH UNIT 1 STUD 1 STUD ATTACH TO ON AIRCRAFT WITHOUT MOUNTING SCREW EMST NG JUMPER WIRE ADD 18 GAGE WIRE PER 55 369262 MIL W 5086 WHEN REPLACING INBOARD TRANSMITTER ONLY Figure 4 4 Wring Diagram Replacement Inboard Transmitter 4 15 Revised February 1...

Страница 625: ...XISTING INBOARD 95 380012 7 95 380012 1 OUTBOARD TRANSMITTER 2 STUD 4 CONN 4 STUD 2 STUD 7 FULL _t MKTY DASH UNIT Y 1 STUD 1 STUD 3 STUD 55369 263 Figure 4 5 Wiring Diagram Replacement Outboard Transmitter 4 16 _Revieed February 11 19661 ...

Страница 626: ... the c Remove the windshield and trim off excess split in the propeller blade clamp and 1 inch outboard of material as determined in step b the clamp The center line at the outboard end should fall d Place the windshield in position and cleco in place on the blade leading edge Be sure the lead strap is in the using the pilot holes provided proper position to be clamped to the blade retaining clamp...

Страница 627: ...tion for clamping to the blade retaining carefully over each side of the blade contour Avoid clamp Moisten the cement lightly with methyl ethyl trapping air pockets under the boot see Detail C ketone or toluol and tack the boot center line to the blade i Roll outward from the center line to the edges of leading edge If the center line of the boot deviates from the boot If excess material at the ed...

Страница 628: ... edge of the boot n Connect the lead terminals and install the clip on i Apply one even brush coat of A 56 B cement the spinner bulkhead To assure enough slack between the around the edges of the boot allowing a 1 16 to 1 8 inch clip and the clamp on the blade to allow propeller overlap on the boot and extending the cement to the feathering there must be no slack between the terminal and masking t...

Страница 629: ...SECTION NIAJ OR MAINTENANCE AND OVERHAUL ...

Страница 630: ...SECTION 5 Major Maintenance and Overhaul ...

Страница 631: ...n a parts replacement basis only Repair procedures such as welding brazfng building up with weld material and machining to size etc cannot be given a blanket endorsement since each such case must be evaluated individually This section is intended rather as a guide to normal overhaul its goal being the restoration of the parts to full serviceability As a requirement for them appears or the informat...

Страница 632: ...bly 6 Barrel Assembly i j i 7 Torque Knee Bushings 4 t 8 Piston and Fork Assembly 9 Brace Assembly 1 si 12 10 Center Bearing O Ring 11 Upper O Ring liW I si 12 Lubricating Felt Pad B i 13 FeltPads 14 Rebound Control Pin O Ring i c g e a 8 is Brace Assembly Bearings 15 Rebound Control Tube O Ring 17 Air Valve O Ring 35 206 5 Figure 5 1 Nose Gear Shock Strut Prior to D 6582 5 2 ...

Страница 633: ...R TORQUE KNEE PIN 11 PISTON RING i Li 12 SHIMMY DAMPER 13 BARREL 14 15 UPPER TORQUE K N E E T O R U EKNEE BUSHING ji 16 BEARING 6 6 17 SCRAPER ADAPTER 18 SCRAPER 19 SNAP RING 22 LOWER TORQUE KNEE PIN 7 20 PISTON 21 LOWER TORQUE KNEE 23 PLUG 24 FORK ASSEMBLY 8 d 10 9 13 3 L 16 I Is y 1 15 4 i 20 21 22 j I j o 5 24 36 206 1 Figure 5 2 Nose Gear Shock Strut Serlal D 6562 and After 5 3 ...

Страница 634: ...brace as required to barrel Remove the felt pads 13 from inside the align the dampener rod end and bracket brace assembly e Slide the snap ring scraper and wiper over the top of the piston Slide the piston into the barrel and connect the torque la ees DISASSEMBLY OF NOSE GEAR SHOCK STRUT Serial f Insert the rebound control assembly into the barrel D 6562 and After and install the 0 ring 14 washer ...

Страница 635: ...emove the snap ring and adapter D 5791 thru h Install the compression ring and the 0 ring on D 7132 only and scraper Remove the felt pad and 0 the orifice tube Install the orifice tube in the barrel ring from the barrel assembly Install the orifice tube retaining snap ring with the beveled side down REPAIR OF MAIN LANDING GEAR SHOCK STRUT i Inflate the strut to approximately 100 psi Coat the cap a...

Страница 636: ... AND OVERHAUL 2 1 Snap Ring 2 Lock 7 3 Barrel End Plug 5 4 Rebound Control Pin Retaining Nut 5 Rebound Control Slotted Head 6 SnapRing D 8 7 O Ring 8 Torque Knee BusNngs Figure 5 4 Main Gear Shock Strut Prior to Serial D 5791 5 6 ...

Страница 637: ...azed Bearing 14 Scraper Ring 12 Adapter Ring 13 Snap Ring 17 21 D 14 Piston 15 Upper Torque Knee 16 Upper Torque Knee Pin I 17 Lower Torque Knee 18 18 Lower Torque Knee Pin 9 19 Axle Socket 22 20 Upper Torque Knee Bushing 21 Lower Torque Knee Bushing 22 23 AxleBrazed Retaining Bolt 35 202 9 Figure 5 5 Main Gear Shock Strut Serial D 5791 tkru D 7132 Revised January 15 1964 5 7 ...

Страница 638: ... 8 13 Piston 14 Upper Torque Knee 15 Center Torque Knee Bushing 9 16 Lower Torque Knee 10 17 Lower Torque Knee Bushing 18 Lower Torque Knee Pin 19 Axle Socket i Il 20 Axle 21 Brazed Retaining Bolt 15 13 22 Cross Arm Strut Attach Bolt 23 Main Landing Gear Brace Bolt 16 24 Main Landing Gear Hinge Bolt 25 Cross Arm Strut Bushing 27 26 Main Landing Gear Cross Arm 19 27 Spacer 17 28 Strut 18 362021 Fig...

Страница 639: ...s it completely allowing the excess air and fluid to escape through the air valve body DISASSEMBLY OF THE SHIMMY DAMPENER NOTE a Remove cotter pin 8 washel 7 nft retainer ring 1 and the scraper ring 2 Force the barrel If thil strut has been properly refilled a little end 3 out of the barrel 21 by working the piston fluid will escape through the air valve body back and forth Remove the 0 ring 4 fro...

Страница 640: ...0 860 MIL H 5606 hydraulic fluid prior to assembly PistonOutside Diameter Max 0 857 Icnurlowl Min 0 853 Piston RodOutsideDiameter Max 0 5745 Min 0 3135 For replacement use 0 rings approved for use with mineral base hydraulic fluid Piston Rodlnside Diameter Max 0 250 Reservoir Portion Min 0 248 TABLE OF MANUFACTURER s TOLERANCES Max 0 240 Floating Piston Diameter Min 0 255 NOTE BarrelEnd InsideDiam...

Страница 641: ...sembly Secure the spring and piston with the through the center inlet hole The hole in the selector washer 7 and the cotter pin 8 To check the fluid valve should line up with the inlet hole when the handle level in the shimmy dampener spread the portion of is turned to that position Pressure relief and check the cotter pin within the piston rod and insert a wire valve stems 7 must work freely in t...

Страница 642: ...283 1 i Housing 8 Pressure Relief Valve Spring 2 Fuel Selector Valve 9 Plug 3 Plug 10 0 Ring Selector Valve 4 O Ring 11 O Ring Piston Head and 5 Guide Cylinder Head 6 Check Valve Spring 12 0 Ring Piston Rod 7 Valve 13 FeltWasher Figure 5 7 Fuel Unit Revised February 11 1966 5 11 ...

Страница 643: ...e the piston plug 13 drill out the pin 17 and drive the plug out of the piston D l thru D 837 0 838 and after refer to Figure 5 8 during disassembly To reassemble the flap actuator reverse the above disassembly procedure for this series D 838 and after CAUTION Pour 2 3 oz of M1L L 6086 Grade M gear lube or No On aircraft serials D 838 through D4865 two 9615 Homoco heavy duty gear oil P N Home Oil ...

Страница 644: ...1 11 Housin 7 15 9 8 2 O 12 Retaillill 13 PistuitPlu 35 161 1014 PiStoflBearin 16 0 Ring 17 Plug Attachin Riret Flap Actuator D l Thru I3 837 i 11 i FlesShaft 2 SnapRing 3 Spacer 4 Spacer 5 Seal 6 Bearing 8 7 HousingPiston 9 Pin 10 Piston Plug 2 1 11 O Ring 34 2nd Snap Ring Installed Between Seal And Bearing D 838 thru D 4865 35 16111 Flap Actuator D 838 and After Fieure5 8 FlapActuators 5 13 Revi...

Страница 645: ... Gear 10 forln a one piece unit With this using Perfect Seal Sealing Compound No R 134 B exception all mainten u ce procedures are Product of Ford Motor Co Dearborn Michigan the same as on earlier aircraft Reassemble the actuator in the reverse of the above procedure Remove the filler plug from the actuator d Remove the screws 8 and the bolt 9 from the housing and fill the housing with 1 2 pint of...

Страница 646: ... Screw 3 12 Actuator Hand Crank 1 29 13 Spacer 2 14 0 Ring Seal 15 Screw 16 1 Hand Crank Shaft 8 c Housing 17 Retainer Nut 18 Half ring 19 Worm Gear 26 Bearing 20 Bearing 27 SnapRing 21 Lock Nut 28 Actuator Retract Arm 22 Seal 29 Bearing 23 Bearing 30 Grease Fill Plug 24 Bearing 31 BallCheck 25 Seal 32 Sector Gear Stop Assy 26 27 33 Spacer Figure 5 9 Landing Gear Actuator Issued December 1989 5 18...

Страница 647: ...l parts with solvent PD680 d Apply an even coat of EC 1403 cement linnesota g Check all parts for cracks corrosion distortion and Mining and Manufacturing Company Saint Paul wear Minnesota to the damaged portion of the boot and to the patch Allow the coated surfaces approximately one hour to dry before applying a second coat of cement and ASSEMBL Y allowing it to dry e Moisten surfaces of the patc...

Страница 648: ...31 i Remove spring 34 from the housing d Install piston on shaft 21 j Clean all parts with solvent PD680 e Install spring 32 and snap ring 33 on shaft k Check all parts for cracks corrosion distortion and f Install O ring 29 on shaft at clevis end wear g Install spacer 28 thrust collar 27 and snap ring 26 on shaft h Install O ring 25 to cap end and bearing 24 ASSEMBL Y i Install cap end and bearin...

Страница 649: ...Pin Modified 21 Shaft 29 O Ring 4 Retaining Washers 13 Valve Assembly 22 Snap Ring 30 O Ring 5 Rod Wiper 14 Valve Stop 23 O Ring 31 Piston 6 Guide Bushings 15 Spring Washer 24 Cap End 32 Spring 7 O Ring is PistonRod Bearing 33 Snap Ring 8 O Ring 17 Spring 25 O Ring 34 Spring 9 O Ring 18 Housing 26 SnapRing 36 Housing Figure 5 10 Brake Master Cylinders Be 5 18 ...

Страница 650: ...SECTION ELECTRICAL VVIRING DIRAGRANIS ...

Страница 651: ...SE TION 6 I Electrical Wiring Diagrams ...

Страница 652: ...n introduced for the Models P35 and S35 This diagram pro vides the technician with single fold out on which most of the electrical circuits are shown The page adjacent to the Gen eral Diagram contains a keyed index of the individual circuit components For optional circuits or circuits with other serial effectivities refer to the Index of Wiring Diagrams for the applicable Model The wiring diagrams...

Страница 653: ...dio 6 34 Control LandinB Gear 6 13 Turn and Bank 6 3 Rotating Beacon Light 6 46 Control Propeller 6 32 Cylinder Head Temperature Indicator 6 8 L S Landing Gear Control 6 13 Stall Warning Light 6 17 E Landing Gear Position Indicator 6 5 Starter 6 19 Landing Gear Warning Horn 6 9 Landing Light 6 42 ExternalPower 6 44 Lighter Cigarette 6 42 T Lights Airpath Compass 6 42 F Cabin Lamp 6 38 Temperature ...

Страница 654: ... Lights Engine 6 98A CabinLights 6 91 HighandLowPressure 6 70 Instrument Wedge Lights Cigarette Lighters 6 61 Fuel Flow 6 90D Engine 6 98 ConstanrCopiiot 6 102 FuelPump Auxil ar 6 69 Fllgh 6 99 Coordinator Turn 6 63 Fuel Quantity 6 64 Courtesy Light 6 105 Fuel Selector Light 6 86A L Cylinder Head G Temperature 6 90 Landing Gear Gas Temperature Exhaust 6 80 Without Safety System 6 73 D Gear Landing...

Страница 655: ...100A Pressure Oil Temperature 6 89 Temperature Exhaust Gas 6 80 Rotating Beacon 6 80 PropellerDeice 6 87 Temperature Oil 6 88A Strobe 6 103 Pump Auxiliary Fuel 6 69 Temperature Oil and Taxi 6 66 OilPressure 6 89 M Throttle Warning Manifold Pressure 6 90C Q LandingGearand 6 79 Map Lights Cabin and 6 93 Trim Elevator 6 101 Motor Flap 6 71 Quantity Fuel 6 64 Turn Coordinator 6 63 N R W Navigation Lig...

Страница 656: ...ss bar 1516 109 BUSS AND BATTERY CIRCUIT Airplane SerialNo D l thru D 1116 P2 8 e C II EFFECTIVE 01885 OV I PI 2 13 Nlz e 1 Q Q 1 Navigation light circuit breaker r 2 Flare switch circuit breaker o 1 3 RH landing light circuit breaker 4 LH landing light circuit breaker QV P14 18 5 Instrument light circuit breaker P49 18 6 Flap motor circuit breaker gu I I 1 7 Radio circuit breaker 8 Prop governor ...

Страница 657: ...0 P 86 2 a P98 18 RE PLACES P81 18 20 Battery master switch P94 8 P17 8 8 ITEM 19 21 Ignition switch 22 Ammeter 23 Bus bar 835 369 1 11 BUS AND BATTERY CIRCUIT Airplane SerialNo D 2391 thru D 6561 O Q O P102 2 I I I I 13 Plon e I I 1 Navigation light circuit breaker 2 Flare switch circuit breaker f v t 8 3 RH landing light circuit breaker 4 LH landing light circuit breaker I 4G7H I 1 5 Rotating be...

Страница 658: ... 2 Landing gear position indicator light circuit brealrer 3 Navigation light switch 4 Resistor located on navigation light switch 100 ohm 5 Connectors 6 Landing gear up indicator light red 7 Landing gear down indicator light green 8 Up limit switch 9 Down limit switch LANDING GEAR POSITION INDICATOR CIRCUIT Airplane SerialNo D l thru D 1500 6 5 ...

Страница 659: ...rcuit breaker 2 Bussbar 3 Landing gear position indicator light circuit breaker 4 Navigation light switch 5 Resistor located on navigation light switch 100 ohm 6 Landing gear up indicator light red 7 Landing gear down indicator light green 8 Connector 9 Down limit and brake switch 10 Up position light and up limit switch 11 Down position light and up brake switch LANDING GEAR POSITION INDICATOR CI...

Страница 660: ...NG GEAR MOTOR V TO LANDING GEAR c s sro l Is 1 Landing gear motor circuit breaker 2 Bussbar 3 Landing gear position indicator light circuit breaker 4 Navigation light switch 5 Resistor located on navigation light switch 100 ohm 6 Landing gear up indicator light red 7 Landing gear down indicator light green 8 Connector 9 Landing gear up brake switch 10 Landing gear up limit switch ii Landing gear d...

Страница 661: ...ar motor circuit breaker 6 Landing gear up indicator light red Awriliary fuel pump circuit breaker 7 Landing gear down indicator D 6562 and after light green 2 Bus bar 8 Connector 3 Landing gear position indicator 9 Landing gear up brake switch light circuit breaker 10 Landing gear up limit switch 4 Navigation light switch 11 Landing gear down brake switch 5 Resistor located on navigation 12 Landi...

Страница 662: ...Oil temperature indicator and cylinder head 4 Firewall connector temperature indicator circuit breaker 5 Cylinder head temperature thermocouple CYLINDER HEAD TEMPERATURE INDICATOR CIRCUIT 12V RESISTIVE ELEMENT 0 4974 0 5084 thru 0 6161 except 0 5352 55 6 8A ...

Страница 663: ...ture indicator 4 Cylinder head temperature thermocouple CYLINDER HEAD TEMPERATURE MDICATOR CIRCUIT Airplane SerialNo D 6162 thru D 6841 wis is W I 1 8 O W4 IW2 I3 8 35 155 115 i Landing gear reversing switch 2 Landing gear warning horn circuit breaker 3 Firewall connector 4 Throttle warning horn switch 5 Warning horn LANDING GEAR WARNING HORN CIRCUIT Airplane SerialNo DI1 thru D 1SO Revised Octobe...

Страница 664: ...horn LANDING GEAR WARNING HORN CIRCUIT Airplane SerialNo D 151 thru D 2680 O O wis ie ws is wi ia 1 eti 28 181 t35368l21 O TO LANDING GEAR SAFETY 1 Busbar swlTcn 2 Landing gear warning horn circuit breaker 3 Landing gear warning horn switch 4 Firewall connector 5 Throttle warning horn switch 6 Warninghorn 7 Resistor 7 5 ohm 10 watt 8 Flasher LANDING GEAR WARNING HORN CIRCUIT Airplane SerialNo D 26...

Страница 665: ...orn 9 Resistor 7 5 ohm 10 watt LAND G GEAR WARNING HORN CIRCUIT Airplane SerialNo D 2801 thru 0 3319 P O O W18 I 8 6 3 Wb 18 t W3 ss le p wJ44 la wl le O i 24 1 O W23 IO j i C35 36 123 Q i Busbar 2 Landing gear warning horn circuit breaker 3 Connector 4 Landing gear warning horn switch 5 Firewall connector 6 Throttle warning horn switch 7 Flasher 8 Warninghorn 9 Resistor 7 5 ohm 10 watt LANDING GE...

Страница 666: ...n 9 Resistor 7 5 ohm 10 watt LANDING GEAR WARNING HORN CIRCUIT Airplane Serial No D 4866 thru D 6161 CFF OTIVE 1361182 a AFTER w i is O O O ws I 55 le w344 le wss le o O O waa M35369125 TO LANDING GEAR SAFETY SWITCH i Bus bar 2 Landing gear warning horn circuit breaker 3 Connector 4 Landing gear warning horn switch 5 Throttle warning horn switch 6 Flasher 7 Warning horn 8 Resistor 7 5 ohm 10 watt ...

Страница 667: ... Connector 10 Landing gear motor 11 Warning horn circuit breaker LANDING GEAR CONTROL CIRCUIT Airplane SerialNo D l thru D 150 cii io G12 10 FII IL TO DOWN LIGHT s i 6 Q TO STALL WARNING CIRCUIT BREAKER Fio ie O O L C7 0 f L WIJ ID CIO IO GB lO O G2 IO F12 LB 01 1 a G6 K GO 10 i W14 IO CJ lO TO STALL WARNING RELAY f HrS lO G4 IO f CS lO O i I Bussbar 2 Landing gear motor circuit breaker 3 Landing ...

Страница 668: ... Bussbar 2 Landing gear motor circuit breaker 3 Landing gear reversing switch 0 0 I I L Q C CJ2 4 Landing gear safety switch G18 14 5 Connector G23 14 6 Connector 7 Up limit switch G29 le 14 I4 C CI CCCI I 1 8 Down limit switch 9 Dynamic brake 5 14 10 Connector 0 0 GI3 l4 1 I I I I I I L tG2g lO 11 Landing gear motor 18 14 tl I I G28 IO it GI IO N23 IO G19 14 G27 IO t G9 10 0 0 C24 18CZO g L _ j 3...

Страница 669: ...ONTROL CIRCUIT Airplane SerialNo D 1501 thru D 2680 O PO O Gll lo C48 IO TO FLASHER wl4 le q 0 919 947 1 r 1 O ea I TO RED INDICATOR LIGHT wio ia IQ TO GREEN INDICATOR LIGHT I 01 C45 IO F12 ls t39 IO C26 0 G3 IO O oc G42 IO G41 IO C4d IO C rNPBIO C43 IO o 50 C35 369 130 C27 IO Cg IO i Bussbar 7 Connector 2 Landing gear throttle warning horn circuit breaker 8 Up brake switch 3 Landing gear motor ci...

Страница 670: ...wn limit switch 6 Landing gear reversing switch 12 Landing gear motor LANDING GEAR CONTROL CIRCUIT Airplane SerialNo D 2801 thru D 3319 i PO O O wlj ls q o GII IO 048 10 GB lO OJI I aI o L i _ 1 wao la 10 1 0288 10 O ii I Q C49 I0 oc 042 10 O C461 C39 IO irN2 IO O F122 18 TO GREEN INDICATOR LIGHT C3 369 32 F100 18 TO RED INDICATOR LIGHT 1 Buss bar 7 Connector 2 Landing gear warning horn circuit br...

Страница 671: ... Up brake switch 3 Emergency switch panel bus bar 10 Up limit switch 4 Landing gear motor circuit breaker 11 Down brake switch 5 Fuselage wing break 12 Down limit switch 6 Landing gear safety switch 13 Landing gear motor LANDING GEAR CONTROL CIRCUIT Airplane Serial No D 4866 thru D 6841 O Na ie OO W20 WPI 18 O I W9 18 O WIJ IB W14 18 t WIG 18 L 1_ _ _ I_ _I O N7 le O O wt I I a C wzz la 00 O Is c ...

Страница 672: ... stall detector unit STALL WARNING INDICATOR CIRCUIT Airplane SerialNo D 2681 thrm D 4865 w3e leW28 ISN2 18 I O EFFECTIVE D8662 a FTER O F3 T 7 W44 18 Wj7 l 1 i Bus bar 2 Stall warning indicator circuit breaker 9 Stall warning horn 4 Stall warning indicator light 5 Fuselage wing break 6 Wing stall detector unit STALL WARNING INDICATOR CIRCUIT Airplane Serial No D 4866 thru D g841 6 18 Revised Octo...

Страница 673: ... thru D 359 If Service Letter No 10 has been complied with see wiring diagram page 6 2 O r P7 2 I r P23 2 I O O I P20 1Z i P22 12 L _J I O LP21 12 P33 I tPll IZ _J O P2 8 r 1 bI P14 2 O O Re is To BATTERY NIZ L MASTER SWITCH 4 i Radio circuit breaker g Starter motor 2 Busbar 7 Connector 3 Starter switch 8 Battery master switch 4 Ffrewall connector relay 5 Starter relay 9 Battery STARTER CIRCUIT Ai...

Страница 674: ...e 1Js 1 Busbar 2 Starter switch 3 Firewall connector 4 Starter relay 5 Starter motor 6 Connector 7 Battery master switch relay 8 Battery 9 Relay circuit breaker 10 4 1 2 volt relay 11 Latching relay 12 lavoltrelay 13 Battery master switch 14 Battery switch 15 LH magneto switch 16 RH magneto switch 17 Generator switch STARTER CIRCUIT Airplane SerialNo D 519 thru D 1116 If Service Letter No 10 has b...

Страница 675: ...n com plied with except the following 0O D l to D 359 Inclusive O P18 L8 P13 IB0 P42 18 P Wire P21 will connect to the starter switch Wire P22 will connect to wire P21 and the energizing terminal on the starter relay i Bussbar Il lavoltrelay 2 Starter switch 12 Relay circuit breaker Firewall connector 13 Battery master switch relay 4 Starterrelay 14 Battery 5 Resistor 15 Battery master switch 6 St...

Страница 676: ... PJB IP P 0 s 2 P43 ls 0 P41 18 I pet O P13 18 0 P42 l8 1 Bussbar 11 lavoltrelay 2 Starter switch 12 Relay circuit breaker 3 Firewall connector 13 Battery master switch relay 4 Starterrelay 14 Battery 5 Resistor 15 Battery master switch 6 Starter solenoid 16 Battery switch 7 Starting motor 17 LH magneto switch 8 Connector 18 RH magneto switch 9 4 1 2 volt relay 19 Generator switch 10 Latchingrelay...

Страница 677: ... o r P61 12 Q S O D o POI IB 4 o p16 le PIJ 18 01d0 P42 18 t Bussbar 11 lavoltrelay a Starter switch 12 Relay circuit breaker 3 Firewall connector 13 Battery master switch relay 4 Starterrelay 14 Battery 5 Resistor 15 Battery master switch 6 Starter solenoid 16 Battery switch 7 Starting motor 17 LH magneto switch 8 Connector 18 RH magneto switch 9 4 1 2 volt relay 19 Generator switch 10 Latchingre...

Страница 678: ...rialNo D 1950 thru D 2390 rFFEcrlvToeTei P 9 2 1 01 EFFECTIVE D2681 AFT R 7 THROUGn D 2BBO r 1 I D P94 8 PBJ 8 P14 18 L OBATTERY OC l _MASTER RELAY LI_ P81 18 P87 2 f l 7t pee 2 L I PB8 2 O r P20 12e I NOT USED ON D 488I AND AFTER WITH RELAY MOUNTED ON STARTER 3 O O 7 L __ _ _ _J 7 IB d P O IIJ Lq_ P22 18 O 83 16e 144 i Buss bar 6 Bussbar 2 Battery master 7 Starter switch relay 3 Connector 3 Batte...

Страница 679: ...tery 10 Battery master 5 Starting Motor switch 6 Starter relay ii Ignitionswitch STARTER CIRCUIT Airplane SerialNo D 8162 thru D 6561 r 10 P104 P119 8 P93 8 O 1 P14 18 P98 18 1 L LL J 4H7H O r TO 07497100 P112 18 L _ _ _ _ _ rJ VIBRATOR 1 Bus bar 5 Batterymaster 2 Ammeter switch 3 Master relay 6 Starter relay 4 Battery 7 Starting motor STARTER CIRCUIT Airplane Serial No I 8582 thru D 6841 6 25 Rev...

Страница 680: ...itch 4 Generator circuit breaker 9 Ignition switch 5 Voltage regulator 10 Generator GENERATOR CLRC IT Airplane SerialNo D l thru D 1116 O Plb 2 P24 e 3 J J P4 8 5 8 Cf7 PIB le O 4 Pld l 1 Bus bar 5 Capacitor 2 Ammeter 6 FirewaU disconnect 3 Generator circuit 7 Generator switch breaker 8 Ignition switch 4 Voltage regulator 8 Generator GENERATOR CIRCUIT Airplane SerialNo 0 1117 thrm 0 1500 6 26 ...

Страница 681: ...Firewall disconnect 4 Voltage regulator 9 Generator GENERATOR CIRCUIT Airplane SerialNo D 1501 thru D 2485 O P18 12 P7 12 111 Q Q P82 12 PB3 2 JO t O B P59 18 PIE 18 U 18 P87 18_r F_J L I EO P84 12peo le y v o 1 Busbar 5 Generator switch 2 Ammeter 6 Ignition switch 3 Generator circuit 7 Connector breaker 8 Firewall disconnect 4 Voltage regulator 9 Generator GENERATOR CIRCUIT Airplane 1SerialNo 0 2...

Страница 682: ...Ignition switch 3 Generator circuit 7 Connector breaker 8 Firewall disconnect 4 Voltage regulator 9 Generator GENERATOR CIRCU1T Airplane SerialNo D 2681 thru D 4865 O P93 8 TO BATTERY MASTER RELAY O PB9 8 O O 392 8 P91 B C O B 8 P84 18 P87 IB O O O f 1 p92 8 35 369 182 I Bus bar 5 Generator switch 2 Ammeter 6 Ignition switch 3 Generator circuit 7 Connector breaker 8 Firewall disconnect 4 Voltage r...

Страница 683: ...witch 3 Generator circuit breaker 7 Connector 4 Voltage regulator 8 Generator GENERATOR CIRCUIT Airplane SerialNo D 6162 thru D 6561 P118 8 10 BATTERV MASTER RELAY P118 8 P92 9 P91 8 G Br F t i Bus bar 4 Voltage regulator 2 Generator circuit breaker 5 Generator switch 3 Ammeter 6 Generator GENERATOR CIRCUIT Airplane SerialNo D 6562 thru D 8841 Revised October 27 1981 g 29 ...

Страница 684: ...tage regulator 9 Generator 50 AMP GENERATOR CIRCUIT Optional Airplane Serial No D 4376 D 4392 thru D 6841 TO GENERATOR PIB I8 B0 rPB4 IB TO GENERATOR SWITCH HT O O II O HIT 0O1 Q Q J2 16 II o 0 NS 18 O d or I EFFECTIVE 04866 a AFTER TO BATTERY SWITCH 1 RH magneto 5 LH magneto switch 2 RH magneto filter unit 6 Battery master switch 3 Generator switch 7 LH ma neto filter unit 4 RH magneto switch 8 L...

Страница 685: ...16 L I J r Sw SWITCH SHOWN IN START POSITION r L I J N35 369 157 1 Bus bar 4 LHmagneto 2 Ignition switch 5 RH magneto 3 Starting vibrator IGNITION CIRCUIT Airplane Serial No D 6562 thru D 6841 o MS 18 r 8S O M4 8 7 1 IO jdllo M 2e Mj le 7 I i 1 J I I I SHIELDING GROUNDED i L I SHIELDING 35369158 GROUNDED 1 Bus bar 3 Flare switches 2 Flare circuit breaker 4 Flares FLARE CIRCUIT Optional Airplane Se...

Страница 686: ... switches INC 2 8 Relaypanel 53 18 9 Connector 5 8 KZ IL IS OFF tl w 9 O K4 I 4 d oEC Q I I 514 12 1J J K19 12NI 12 m 513 12 5 K 518 12 K28 16 6 I K28 16 35 IE K10 18 Q O 7 613 18 O 1NC K7 16 H H KJO 18 AAN3 18 633 18 i 638 IZ D I K34 18 INC 632 1 8 DEC 617 16 537 18 K38 1e 639 18 631 18 ax DEC L_ 514 1 5 369 159 PROPELLER CONTROL CIRCUIT Airplane SerialNo D l thru D 1116 ...

Страница 687: ... O r 1 H i H ns le n8o ls P H w w P I I I 1 K3LI Ie x L 2 Propeller control circuit breaker L I Co trol switch 5 Firewal connector KT l 1 6 Propeller control motor E i 1B 7 Limit sWlitches B Relay panel PROPELLER CONTROL CIRCUIT Airplane Serial No 0 1117 thru 0 1820 88 6 33 ...

Страница 688: ...onnector 3 Propeller control switch 6 Propeller control motor PROPELLER CONTROL CIRCUIT Airplane SerialNo D 1821 thru D 4865 R3 14 Q RI 14 Ili I I i Bus bar 3 Radio master switch 2 Radio circuit breaker 4 Connector RADIO CIRCUIT Airplane SerialNo D l thru D 2148 except D 2119 thru D 2126 O O 619 14 616 14 TO MAIN RADIO HARNESS 1 Bus bar 3 Radio filter capacitor 2 Radio circuit breaker 4 Connector ...

Страница 689: ...olt gages without adaptors i Bus bar 4 Tank selector switch 2 Fuel quantity indicator circuit breaker 5 Tank transmitter unit right 3 Fuel quantity indicator 6 Tank transmitter unit left FUEL QUANTITY INDICATOR CIRCUIT Airplane SerialNo D l thru D 300 Qo le Q12 18 0911 1 44 18 t Qa I d 0 OR GnT 8 O 1 Busbar 5 Right wing break connector 2 Fuel quantity indicator circuit breaker 6 Tank transmitter u...

Страница 690: ...2 thru D 6841 f 24 18 O OQ o ie e f 08 18 21 18 I a fos I a O 0 O 97 le fae le p s oas lol i Busbar 7 Tank transmitter unit RH auxiliary 2 Fuel quantity indicator circuit breaker 8 Tank transmitter unit LH auxiliary 3 Fuel quantity indicator 9 Tank transmitter unit RH main 4 Tank selector switch main auxiliary 10 Tank transmitter unit LH main 5 Auxiliary tank selector switch left right 11 Left win...

Страница 691: ...G FUEL QUANTITY INDICATOR CIRCUIT Airplane SerialNo D 5331 thru D 6561 027 18 if 036 18 O i Busbar 5 LH fuel cell transmitter unit 2 Fuel quantity indicator circuit breaker 6 RH fuel cell transmitter unit 3 LH fuel cell quantity indicator 7 RH wing break connector 4 LH wing break connector 8 RH fuel cell quantity indicator OPTIONAL FUEL QUANTITY INDICATOR CIRCUIT Airplane Serial No D 6562 thru D 6...

Страница 692: ...r 8 ohms 100 11 LH navigation light red ohms effective D 3999 and after 12 Landing gear circuit breaker 5 Navigation light circuit breaker Awiliary fuel pump circuit breaker 6 Landing gear position indicator circuit breaker D 6562 and after 7 Landing gear position indicator resistor 8 13 Left wing break connector ohms 100 ohms effective D 3999 and after 14 Right wing break connector NAVIGATION LIG...

Страница 693: ...4 12 OLIIT EFFEC IYE 0510 Z FTE O P N24 12 n o 12 ft2J 12 f 025 _I f F8 ca O O O F9 18 PI Is Fzile YF 28 18 Pea Is D EPFECT VE 06180 a I FTER i Busbar 9 Flap up indicator green 2 Flap circuit breaker 10 Flap down indicator red 3 Flap position switch ii Resistor 4 Connector 12 Flap position indicator and 5 Down limit switch position light circuit 6 Flapmotor breaker 7 Up limit switch 13 Right wing ...

Страница 694: ...ELLANEOUS LIGHTING CIRCUITS Airplane SerialNo D l thru D 1015 b O O O L26 18 t L27 13 LI ll NB 18 r r 9 LJI 18 t L41 IBr 4 IB L42 le I L17 13 Q O L29 18 1 L22 L3O 13 i Ng 8 _J L L32 18 _J VQ L33 13 SER1 L NO 33331 4 AF ER id L l L1J 18 l NIO 18 L34 13 I O SERIIL U OZe01 a AFTER 35 369 177 L 414 13 OPTIONAL SERIAL NO 03293 a 03401 BlrTER 1 Busbar 6 Tab position indicator light 2 Instrumentlight cir...

Страница 695: ...US LIGHTING CIRCUITS Airplane SerialNo D 5535 thru D 6561 O O 1 LS8 I8 L26 18 fL 27 18 N8 18 O Oh r L43 I8 r L 42 18 L 41 8 L30 18 O O L29 18 fL4 Is L44 18 N6 8 OPTIONL LQ L JL J LJJ IB o Lss ie L48 18 NIO 18 N61 ls t N62 181 I L60 18 L2C O L49 l8 NBO 18 O L2D TO CABIN LIGHTS I Busbar 5 Fuel pump placard light 10 Resistor 50 ohms 2 Instrument light 6 Tab position indicator light 11 Landing gear vi...

Страница 696: ...o D l thru D 6841 b 10 iOi LWA 2918 18 AIRPLANE SERIAL NO BEFORE 0 4868 USE WIRE NO MI 18 35 369 181 i Bus bar 2 Cigarette lighter CIGARETTE LIGHTER CIRCUIT Airplane Serial No D l thru D 6841 O O Q a L 24 14 0 L 1 2 14 t L 18 14 O L25 14 Oc 6 L L15 14 if L18 14 h 36 368 182 i Bus bar 6 Landing light LH 2 Landing light circuit breakers RH 7 Wing break connector 3 Landing light switch RH 8 Landing l...

Страница 697: ...Airplane Serial No D 6562 thru D 6841 B 1 O O Feo le F28 18 1 Dus bar 3 Turn and bank indicator switch 2 Turn and bank indicator circuit breaker 4 Turn and bank indicator TURN AND BANK INDICATOR CIRCUIT Airplane SerialNo 0 1501 thru D 2680 O 6 __ I Bus bar 2 Turn and bank indicator circuit breaker 3 Turn and bank indicator TURN AND BANK INDICATOR CIRCUIT Airplane SerialNo D 2681 thru D 4865 i H 13...

Страница 698: ...re indicator 4 Engine oil temperature circuit breaker resistance bulb OIL TEMPERATURE INDICATOR CIRCUIT Airplane Serial No D 6162 thru D 6841 s e O O Is 6 3 D2 18 HEATERD4 18 D 7 1 TO PITOT N31 18 EFFECTIVE D 6562 THRU D 6841 i C35 369 189 1 Bus bar 3 Pitot tube heater circuit breaker 2 Oil temperature and cylinder head 4 Pitot tube heater switch temperature circuit breaker 5 Connector OPTIONAL PJ...

Страница 699: ...ar 3 Fuel boost pump circuit breaker 2 Stall warning indicator 4 Fuel boost pump switch circuit breaker 5 Fuelpump OPTIONAL FUEL BOOST PUMP CIRCUIT Airplane SerialNo D 4866 thru D 5330 0 B sab I I O J 030 18 029 18 j O932 18 0 025 18 A 54 L 1 026 18 W46 18 I EFFECTIVE 06562 8 AFTER i Busbar 4 Fuel boost pump switch 2 Stall warning indicator 5 Fuel boost pump warning indicator circuit breaker 6 Fue...

Страница 700: ...pump Airplane Serial No D 3999 thru D 5330 when Kit 35 548 has been complied with P46 0 0 P48P47 saaaa cl I I Q Q 15 36e les 1 Busbar 2 Cabin light circuit breaker 3 Primer switch 4 Firewall connector 5 Primer solenoid PRIMER CIRCUIT Airplane Serial No D l thru D 5330 Lb O OL46 L48 18 L45 18 a O 35 es lss I Bus bar 2 Rotating beacon circuit breaker 3 Rotating beacon switch 4 Rotating beacon connec...

Страница 701: ... R B SW 181 GND 23 _h 1 Busbar 2 Rotatingbeacon circuitbreaker N35 519 97 3 Rotatingbeacon switch 4 Rotatlngbeacon connector 5 Rotatingbeacon OPTIONAL ROTATING BEACON LKiHT CIRCUIT Airplane Serial No 0 8786 thru 0 6841 Revised October 27 1961 6 47 ...

Страница 702: ... Oil temperature indicator 16 Left wing navigation light 50 Oil temperature transmitter 17 Right wing navigation light 51 Alternator switch 18 Tailnavigation light 52 Voltage regulator 19 Flap up indicator light 53 Alternator 20 Flap down indicator light 54 Generator 21 Flap motor 55 Generator switch 22 Flap down limit switch 56 Ammeter 23 Flap up limit switch 57 Ignition switch 24 Flap control sw...

Страница 703: ...Ie C wic is Lsels 1 29A12Z L IL r l l s SCIlelo I Llal i 38 c46 PIp2 _L B9 a D oso thru D 309 1 I wis ie OF II 62 i T LI AIB L13AI LEFT r 1 r 29 Lzi ie Lu a L15A18 p PICIB AEHT Q AIB wZB16 11Ci 1 GZ tb lo 1 8 m 39 39 9 40 L Cld T il 40 L i 16 P3A1BP 64 i A18 44 Q5 PLBG SYSTEJI311 CAL L EL 818 T 30 r p Ales czi is Lieia Oi T EQI1PJIESTI YOTOH I L I b b 67 63 u zcie 34 G 4 1D L3 18 QIClsolols PSALB ...

Страница 704: ... LIJAI C 66 ILZI 18 LI AIB tOl T EQ IFa EST T 1 r T CIOs10 ysAl i gs la 29 LtA18 L6A1 CIICIO11 1r c45 pt IY192J 111 I 8 1 8 11 1 y cla II H L1SAI q r ls 8 G288 1 Oo ir 44 PIA18H plC PID2 U ll68 r nio iilru 63 Ic I usle rsale e s 1 o 30 Is iiii j 2 o GIB i 79 O 64 tog T r P3A1BN qa ie P cis p ois aals A r A s P1A2 K1 5 I QsA1e 9tcls 0 012 QsAls 9 9 ai 9ii ls y Ala 5 CAL FUEL C23A18 Wt 18 L3 bii R J...

Страница 705: ...y 22 Flap down limit switch 64 External power receptacle 23 Flap up limit switch 65 Starter 24 Flap control switch 66 Terminal board 25 Landing gear warning limit switch 61 Radio protection relay 26 Throttle warning limit switch 68 Battery switch 27 Landing gear warning horn 69 D C bus 28 Landing gear safety limit switch 70 Flasher 29 Landing gear up brake limit switch 71 Turn bank indicator 30 La...

Страница 706: ...ing relay 22 Flap down limit switch 64 External power receptacle 23 Flap up limit switch 65 Starter 24 Flap control switch 66 Terminal board 2 Landing gear warning limit switch 67 Radio protection relay 26 Throttle warning limit switch 68 Battery switch 27 Landing gear warning horn 69 D C bus 28 Landing gear safety limit switch 70 Flasher 29 Landing gear up brake limit switch 71 Turn bank indicato...

Страница 707: ... oo PIO S C35A18 P28A18 P28A18 G131 10 I LP1CIBJ 81 Z 4 P171 16S 52 EST P30 16 iI LL E P AIBNLLOWRED N P17X16N 81 RE iELLOW N PlnG c I s A 77 L1 P22A 8 V ULACK RE L 1 31 1 16 CIIAII PJA1BE 68 I C 52 1 P30A16 GS I ED P23 2G YELLOW IDN J P31A16 i F 75 10A IIAT 78 31 51 k P31A16 P32A16 C30A18N P3A18N G333 10 P 7A16N P3AIBN 1_ 1 3381843 i n r eP32X1C F AT P19A14 P12A13 REF C31C18 tC288 1 j 173 REF t C...

Страница 708: ... FUEL UANTITY CYLINDER HEAD TEMPERATURE AND AUXILIARY FUEL PUMP CIGARETTE LIGHTER THROTTLE AND LANDING GEAR WARNING P38A8 n OrL TEMPERATURE RADIO INSTRUMENT AND CABIN LIGHTS PITCH TRIM AND IGNITION BOOST ALTERNATOR FIELD STALL WARNING L HJBIO O PROPELLER DEICE B P23A8 P2 6A8 I P27A18 j TO STARTER AND IGNITION P21A18N _L i Main Bus 2 Avionics Bus 3 Avionics Protection Relay POWER DISTRIBUTION D 797...

Страница 709: ...PUMP FLAP POSITION DOOR WARN AND ALTERNATOR OUT ALTERNATOR FIELD LI O THROTTLE AND LANDING GEAR WARNING TO PllB4 BATTERY LANDING MASTER SAFETYGEAR I DEICE LANDING GEAR PROP RE LAY r H25A10 P5B4 B PllC4 LANDING TAXI NAV ROT STROBE PITOT LIGHT LIGHT LIGHTS BEACON LIGHTS HEAT PllA4 P23A4 I P26A8 TO ALTERNATOR 1 V858 369 102 P27A18 i DC Bus 2 Power Terminal Board 3 Avionics Protection Relay P21A18N 4 ...

Страница 710: ... O O AUXILIARY FUEL PUMP FLAP POSITION DOOR WARN AND ALTERNATOR OUT ALTERNATOR FIELD I O THROTTLE AND LANDING GEAR WARNING TO PllB4 BATTERY LANDING MASTER SAFETYGEAR I DEICE LANDING GEAR PROP RE LAY r H25A10 P5B4 s 1 O LANDING TAXI NAV ROT STROBE PITOT LIGHT LIGHT LIGHTS BEACON LIGHTS HEAT PllA4 TO ALTERNATOR A36 369100 1 DC Bus 2 Power Terminal Board POWER DISTRIBUTION Verticel Instruments Model ...

Страница 711: ...RY FUEL PUMP FLAP MOTOR O O LANDING GEAR POSITION FLAP POSITION DOOR WARN AND ALTERNATOR OUT ALTERNATOR FIELD 1 THROTTLE AND LANDING GEAR WARNING TO PllB4 BATTERY LANDING MASTER SAFETYGEAR I DEICE LANDING GEAR PROP RE LAY f H25A1D P5B4 a L LANDING TAXI NAV ROT STROBE PITOT LIGHT LIGHT LIGHTS BEACON LIGHTS HEAT PllA4 TO ALTERNATOR A36 369 306 1 DC Bus 2 Power Terminal Board POWER DISTRIBUTION Verti...

Страница 712: ...ER FLOOD LIGHTS FLAPMOTOR n n RADIOAND INSTRUMENT LIGHTS FLAP POSITION n LANDINGGEAR POSITION DOOR AND ALTERNATOR ALTERNATOR FIE LD OUT WARNING LANDING GEAR I I THROTTLE AND LANDING SAFETY SWITCHA V GEAR WARNING TO PllB4 BATTERY IASTEP LANDING GEAR RELAY pjB4 PllC4 L IL t U LANDING TAXI NAV ROT STROBE PITOT LIGHT LIGHT LIGHTS DEACON LIGHTS HEAT PllA4 TG ALTERNATOR 1 DC Bus 2 Power Ternlinal oard P...

Страница 713: ...OAND INSTRUMENT LIGHTS FLAP POSITION r LANDINGGEAR POSITION DOOR AND ALTERNATOR ALTERNATOR FIELD OUT wARNING LANDING GEAR I I THROTTLE AND LANDING SAFETY SUrITCH V GEARWARNING TO PllB4 BATTERY MASTER LANDING GEAR RELAY r P5I34 LANDING TAXI NAV ROT STROBE PITOT LIGHT LIGHT LIGHTS BEACON LIGHTS HEAT PllA4 TO ALTERNATOR F33A369301 1 DC Bus 2 Power Terminal Board POWER DISTRIBUTION without Standby Gen...

Страница 714: ...i 1 RED P29A B T IEj YELLOW P2A2 N L P4A18N P3A18N 9 1 r 1 Ammeter I 2 Battery Relay P7A2 3 Terminal Board 4 Battery PTIONALJ 5 Battery Master Switch 6 External Power Receptacle 7 Bus 8 Diode L BATTERY AND EXTERNAL POWER D 7977 thru D 8295 6 55 Issued January 1970 ...

Страница 715: ...1 O P29A18 P3A18N T P4A18N YELLOW I_ J P2A2N L P24AZ IC P24B2 P25A20 1 Ammeter 2 Battery Relay 3 Terminal Board P25B20 4 Battery 5 Battery Master Switch 6 External Power Receptacle 7 External Power Relay 8 Diode OPTIONAL 9 Bus BATTERY AND EXTERNAL POWER D 8296 thru D 9068 6 56 Issued January 1970 ...

Страница 716: ...NAL I P3A2 aiBZ yB TO STARTER P2A2N AND IGNITION L I pa4Aa C I t P25B20 2 Battery Master R e l a y 1 Diode L 3 Battery Master Switch 4 Fuse OPTIONAL 1 5 Shunt 6 Ammeter 7 Battery 8 External Power Relay 9 External Power Receptical 10 Diode BATTERY AND EXTERNAL POWER Model V35B V35B TC D 9069 thru D 9221 V358 369 78 Issued December 1972 6 56A ...

Страница 717: ...HTS OPTIONALI P1A2 _L TO ENGINE P3A2 INSTRUMENT LIGHTS VERTICAL P24B2 B r TO STARTER I P2A2N AND IGNITION L I L P24A2 J i L P24B2 P25A201 ril V358 369 309 P25B20 PI i i Diode 2 Battery Master Relay 3 Battery Master Switch 4 Fuse OPTIONAL 1 5 Shunt 6 Ammeter 7 Battery a External Power Relay 9 External Power Receptical 10 Diode BATTf RY AND EXTERNAL POWER Vertical Instruments Model V35B D 9222 thru ...

Страница 718: ...RTESY L81A20 LIGHTS OPTIONAL P1A2 I P3A2 P24B2 T TO STARTER P2A2N AND IGNITION L I I L P24A2 t P 2 4 B 2 1 P25A20 P25B20 P I Diode 2 Battery Master Relay 3 Battery Master Switch 4 Fuse 5 Shunt OPTIONAL 6 Engine Instrument Cluster 7 Battery 8 External Power Relay 9 External Power Receptical 10 Diode nssaes BATTERY AND EXTERNAL POWER D 9391 thru D 9817 B10 6 57 ...

Страница 719: ...2 I P1D2 1 TO BATTERY AND P27A18 I I 13 EXTERNAL POWER K5A2N I K3A18N L 1 Ignition Boost and Pitch Trim Circuit Breaker 2 Ignition Switch 3 RH Magneto 4 LH Magneto 5 Starter 6 Starter Relay 7 Vibrator STARTER AND IGNITION D 7977 thru D18621 D 8624 thru D 8627 D 8629 thru D 8999 D 9001 D 9008 D 9019 D 9027 D 9039 D 9048 D 9055 6 58 Issued January 3970 ...

Страница 720: ... BATTERY AND EXTERNAL POWER K5A2N _L K3A18N 1 Ignition Boost and Pitch Trim Circuit Breaker 2 Ignition Switch 3 RH Magneto 4 LH Magneto 5 Starter 6 Starter Relay 7 Vibrator STARTER AND IGNITION D 8622 D 8623 D 8628 D 9000 thru D 9068 except D 9001 D 9008 D 9019 D 9027 D 9039 D 9048 and D 9055 Issued January 1970 _ 6 59 ...

Страница 721: ...ICS PROTECTION P271A 8 I K4A2 J I L 0 tP3A2 1 TO BATTERY AND EXTERNAL POWER K5A2N I 1 Engine Start Relay Circuit Breaker 2 Ignition Switch 3 RH Magneto 4 LH Magneto 5 Starter 6 Starter Relay V358 3L9 8 STARTER AND IGNITION Model V35B V35B TC D 9069 thru D 9222 6 60 Issued December 1972 ...

Страница 722: ...VIONICS PROTECTION P27X B r I K4A2 P3AZ TO BATTERY AND EXTERNAL POWER K5A2N i 1 Engine Start Relay Circuit Breaker 2 Ignition Switch 3 RH Magneto 4 LH Magneto 5 Starter 6 Starter Relay STARTER AND IGNITION D 9223 thru D 9817 and airplanes in compliance with S I 0410 354 Rev l 810 6 60A ...

Страница 723: ...sA BLACK H1A18 Pai BLACK i Circuit Breaker 2 Cigarette Lighter V35 369 9 CIGARETTE LIGHTER 0 7877 thru 0 9817 B10 _ 6 61 ...

Страница 724: ...er 2 Stall Detector Switch 3 Stall Warning Horn STALL WARNING D 7977 thru D 9068 TO BATTERY AND EXTERNAL 5 W1A20 5A W1B20 t W1C20 0 POWER rW32A20 W32B20 i Stall Warn Circuit Breaker 2 Stall Detector Switch 3 Stall Warning Horn STALL WARNING 0 9069 thru 0 9817 B10 6 62 ...

Страница 725: ... and after 1 Turn Coordinator Circuit Breaker 2 Turn Coordinator indicator TURN COORDINATOR 0 7977 thru 0 9817 D4 18 F4A18 F4B18 I A 10A r N31 le B F5A18N D 7977 thru D 9068 1 i Pitot Heat Circuit Breaker 2 Pitot Heater PITOT HEAT D 7977 thru D 9817 6 63 B10 ...

Страница 726: ...iliary Fuel Pump Circuit Breaker FUEL QUANTITY D 7977 thru D 9068 E3A18 CYLINDER HEAD TEMPERATURE 1A18 AUXILIARY FUEL PUMP 4A18 65A18 94D18 94C18 Q6A18 1 Fuel Quantify Indicator Cylinder Head Temperature LfC 1 and Auxiliary Fuel Pump Circuit Breaker 2 LH FuelQuantity Indicator CASE 3 RH FuelQuantity Indicator I CASE Q7A18 4 LH Inboard Transmitter QIA1S 5 RH Inboard Transmitter 6 LH Outboard Transm...

Страница 727: ...OUNTED ON INDICATOR TERMINALS CROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N CYLINDER HEAD E42A20N AND E44A20N FUEL QUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT 1 Fuel Quantity Circuit Breaker 2 Printed Circuit Board 3 Fuel Quantity Indicator 4 Inboard Fuel Cell Transmitter 5 Outboard Fue l Cell Transmitter FUEL QUANTITY Vertical Instruments Model V35B D 9069 thru 0 9221 I...

Страница 728: ...TURE 542A20N AND 544A20N FUEL QUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT r 1 OUTBOARD OUTBGARD E1BA20 _ I z _l LEFT FUEL TANI RIGHT FUEL TANK E19A20N E17A22N I I TO ENGINE INSTRUMENT LIGHTS 35 369 75 1 Circuit Br aker 2 Fuel Ouantily Indicator 3 Inboord Fuel auantiiy Tranimittar 4 Outboard Fuel Ovantity Tran mitlsr FUEL QUANTITY Vertical Instruments Model V35B D 9222 thru D 9390 6 64B Is...

Страница 729: ...RD V35JB916A IS MOUNTED ON INDICATOR TERMINALS rGROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N CYLINDER HEAD E42A20N AND E44A20N FUEL QUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT I Fuel Quantity Circuit Breaker 2 Printed Circuit Board 3 Fuel Quantity Indicator 4 Inboard Fuel Cell Transmitter 5 Outboard Fu l CellTransmitter FUEL OUANTITY Optional Model V35B 09391 thru D 956...

Страница 730: ... FIXED INSTRUMENT PANEL tGROU ID THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31 20N CYLINDER HEAD E42A20N A TD E44A20N FUEL QUANTITY DO PSOT GROUND ANY OTHER WIRES AT THIS POINT i Fuel Qunntity Circuit Drenker 2 Printetl Circuit nonl d 3 FuelQuantity Indicator 4 Inl oartl Fuel Cell Transmittfr 5 Outl onrd Fuel Cell Trnnsniitter FUEL QUANTITY OPTIONAL 8 9869 thru 0 9817 6 648 814 ...

Страница 731: ... CIRCUIT BOARD FJ3369 M2 IS MOUNTED ON INDICATOR TERMINALS sGROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N CYLINDER HEAD E42A20N AND E44A20N FUEL QUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT 1 Fuel Quantity Circuit Breaker 2 Printed Circuit Board 3 Fuel Quantity Indicator 4 LH el CellTransmitter 5 RH Fuel Cell Transmitter FUEL QUANTITY STANDARD Model V35B D 9391 thru 0 956...

Страница 732: ...XED INSTRUMENT F33 364302 PANEL GROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N CYLINDER HEAD E42A20N AND E44A20N FUEL QUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT 1 Fuel Quantity Circuit Breaker 2 Printed Circuit Board 3 Fuel Quantity Indicator 4 LH Fuel Cell Transmitter 5 RH Fuel Cell Transmitter FUEL QUANTITY STANDARD 0 9599 thru 8 9817 814 6 65 ...

Страница 733: ...ding Light 3 Lower Landing Light Circuit Breaker 4 Lower Landing Light LANDING LIGHTE D 7977 thru D 9068 20A L28A12 L28812 I0 1 20A L16A12 L16B12 i Landing Light Circuit Breaker 2 Landing Light 3 Taxi Light Circuit Breaker 4 TaxiLight LANDING AND TAXI LIGHTS 0 9069 thru D 9817 6 66 B10 ...

Страница 734: ...17C20 B R C G L36B20N L36A20N B I WIRES FURNISHED BY VENDOR ARE NOT CODED i Navigation Lights Circuit Breaker 2 LH Navigation Light 3 Tail Navigation Light 4 RH Navigation Light 5 Circuit Breaker Panel Lights NAVIGATION LIGHTS D 7977 thru D 9068 Issued January 1970 6 67 ...

Страница 735: ...7A20 L18A20 I L19A20 L17A20 L18B20 L19B20 L17C20 L19C20 L18C20 L36B20N L36A20N I i Navigation Lights Circuit Breaker 2 RH Navigation Light 3 Tail Navigation Light 4 LH Navigation Light NAVIGATION LIGHTS Model V35B D 9069 thru D 9467 6 68 Bg ...

Страница 736: ...XV LIGHT 20 NAV LIGHT 20 NA LI HT o GND 80 L36B20N GND 20 L I I L36A20N I i Navigation Lights Circuit Breaker 2 RH Navigation Light 3 Tail Navigation Light 4 LH Navigation Light NAVIGATION LIGHTS 0 9468 thru 0 9817 B10 _ 6 68A ...

Страница 737: ...nder Head Temperature and Auxiliary Fuel Pump Circuit Breaker 2 Auxiliary Fuel Pump Switch 3 Auxiliary Fuel Pump AUXILIARY FUEL PUMP D 7977 thru D 9068 OFF 1A18 r 2A18 10A 0 0 ON 1 Auxiliary Fuel Pump Circuit Breaker 2 Auxiliary Fuel Pump Switch 3 Auxiliary Fuel Pump Motor AUXILIARV FUEL PUMP P9069 thru P9817 B10 6 69 ...

Страница 738: ... LOFF 3A18 4A18 1 Y 1 Fuel uantity Cylinder Head Temperature BLACK and Auxiliary Fuel Pump Circuit Breaker 3 Auxiliary Fuel Pump High Pressure MOT 2 Auxiliary Fuel Control Panel 4 Auxiliary Fuel Pump Low Pressure Q3A18N BLACK I FUEL BOOST PUMP HIGH AND LOW PRESSURE Models V35 TC V35A TC and V35B TC 6 70 Issued January 1970 ...

Страница 739: ...4 Flap Up Limit Switch WHITE 5 Flap Motor GREEN BY VENDOR BLACK 1 FLAP MOTOR D 7977 thru D 9068 15AI UP C12A14 I a OFF C2A14 DN O C2B14i C4B14C4A14 1 Flap Motor Circuit Breaker DN CBA14 3 Flap Down Limit Switch UP C3A14 t 2 Flap Control Switch 4 Flap Up Limit Switch C5A14 C3B14WHITE I WIRE FURNISHED 5 Flap Motor GREEN BY VENDOR BLACK L FLAP MOfOR 0 9069 thIu 0 9817 B10 6 71 ...

Страница 740: ...18A20 C18B20 3 I C 7A20 C17B20 4 C19A20N PRINTED CIRCUIT BOARD 1 IQlja O O O 3 O i Flap Position Indicator Circuit Breaker 2 Printed Circuit Board 2 O 3 Flap Position Indicator O I I O O 4 Flap Position Transmitter I O FLAP POSITION INDICATOR D 7977 thru D 9817 6 72 B10 ...

Страница 741: ...NOTE CIRCUIT IS SHOWN WITH GllA12 1 AIRCRAFT ON THE GROUND GND GllB12 WHITE i Landing Gear Circuit Breaker UP 2 Landing Gear Control Switch 3 Landing Gear Up Brake Switch DWN 4 Landing Gear Down Brake Switch 5 Landing Gear Up Limit Switch 6 Landing Gear Down Limit Switch 7 Landing Gear Safety Switch BLACK 8 Landing Gear Motor I 9 Bus WIRE FURNISHED BY VENDOR LANDTNG GEAR WITHOUT SAFETY SYSTEM D 79...

Страница 742: ...ar Circuit Breaker G13B20 REF LANDING WHITEUp 2 Landing Gear Control Switch GEAR AND RED h 3 Landing Gear Up Brake Switch THROTTLE A 4 Landing Gear Down Brake Switch WARNING PI DWN 5 Landing Gear Ilp Limit Switch 6 Landing Gear Down Limit Switch BLACK 7 Landing Gear Safety Switch 8 Landing Gear Motor G20A12N WIRE FURNISHED BY VENDOR V358 369 18 LANDING GEAR WITHOUT SAFETY SYSTEM D 9069 thru D 9176...

Страница 743: ...NC G18C20 GllB12 I G13B20 G1lC12 ct i Landing Gear Circuit Breaker REF LANDING WHITEUp 2 Landing Gear Control Switch GEAR AND RED 3 Landing Gear Up Braite Switch THROTTLE 4 Landing Gear Down Brake Switch WARNING P DWN 5 Landing Gear Up Limit Switch 6 Landing Gear Down Limit Switch BLACK 7 Landing Gear Safety Switch 8 Landing Gear Motor G20A12N WIRE FURNISHED BY VENDOR G33 369 81 LANDING GEAR WITHO...

Страница 744: ...TCH 012612 CONTROL SWITCH r 06612 I c laa 1 035 12 r 0TD612 I I I 1 03 11 L Ur LIMIT SWITCH I i I I I I oisA o 01 20 I DOWN_I 012012 r 03612 9 03612 013 10 LL L J 06 11 DOWN LIMIT SWITCH 04R12 WHITE 04A11 MO OI O r 1 013C20 ILACK Ol lN WIRE UINISWED 6r VENDOR 310111 SOLIAT NC SWITCH LNCI_ j 133 369 36 LANDING GEAR WITHOUT SAFETY SYSTEM D 9691 thru D 9Bi7 6 748 BiO ...

Страница 745: ... GND 8 Landing Gear Up Limit Switch GJ8 10 n P 9 Landing Gear Motor g 10 90 MPH Pressure Switch II Landing Gear Safety System Switch UP AIR GrOA12 t G10B12 eC288 12d UP 12 Landing Gear Safety Relay GllA12 13 Throttle Control Switch r 1 i G4B12 7 14 120 MPH Pressure Switch L RED DWN 16 Bus15 Diode C11812 CI A10 L t WHITE BLACK UP 1 C31B10 G12A10 m I L LATCHING SOLENOID G8A10 I 1 G 333 10 th I ia ua...

Страница 746: ... lr Sr l etp S itc h G4A12 G20 12N 13 Lalldill Gear Syslelll Su itch DWN NO _L AIR 14 120 LIPH Prcjsure G12B12 lj Thrt ttle Cr nLrol S itch G13120 UPINO B r tot 16 Ccar Colltr ol S I itc h GIO 412 GIOn12 1 COM NC G18C20 AND T 1ROTT LE G13E 20 REF GI D rZRNING G12A12 L f t G23A12 ONC I I I VP I I I INO LATCH NC SOI ESOID D E N I I GqA12 I I IRE FCRBISI1ED I1Y VESnOR G6A12 C5 20 G12A12 C8 1 1 2 t I ...

Страница 747: ...afety Snitch G4A12 G20A12N 13 Landing Gear Safety System Switch INDICATOR DWN NO L AIli 14 120 MPH Pressure Switch TO LANDING I1D 15 Throttle Control Switch GEAR WARNING o a r NO 16 Landing Gear Control Switch G10A12 G15A20 J I I I G10B12 COM 17 Fuse 13B20 REF LANDING NC NC THROTTLE G13A20 GND WARNING G2JA12 NC O r la C4B12 LATCHING SOLENOID i 5 NO UP DWN G3B12 WIRE FURNISHED BY VENDOR 10D 2 fSC6A...

Страница 748: ... G 1 O SA O G3 12 THo sauAT SWITCII 4_1_1 cleam G67A20 I3s2a r ctsc o SIFETISWI C y G6A12 C1RCUITBREAKER G12A12 I C68A 2 C 3P120 G3A12 G14A20 G7A12N SAFETY II FVSE SYSTEM 5A SWITCH GYn l G22A20 0228 OFF TEST 4 G gA O CG31A12 G30 20N1 6 3 ON 1 OMPH DOWN PRESSURE THROTTLE CONTROL SWITCH CONTROL G bA12 SWITCH n L TC INO SOLENO1D SWITCH DIODE G21A12 n WIAE PURNISHEO BY VEnOOR MY IN L I yirrTvncur NOTE...

Страница 749: ... G20A12N INDICATOR TO LANDING DWn 1 No I GEAR UP NO 1 G15A20 I I II C1OB1 NC G13A20 G24A12 F C4B12 NO DWN G3B12 OD12 f G6A12 G12A12 C8A12 G7A12N I I F e C 3B12 G14A20 5A m G22A20 G OFF G29A20 m 8tB 1__ __ n ON 120 MP DWN LANDING GEAR WITH SAFETY SYSTEM D 9177 thru D 9690 A I osl s ed By 88 ...

Страница 750: ...20 G36B20 CS4D20 Gj4C20 LH m t 1 5 I I I I I I L_ _ G47 820 C C47A20 SwITCH TYPE CIRCUIT BREAKER G50B20 t Gj0A20 G44C20 m 6 3 DwN 1 Landing Gear And Throttle Warn Circuit m 1 Breaker G33A20 2 Navigation Lights Circuit Breaker m 3 2 1 m G32A20 e G32 B20 3 Landing Gear Position Circuit Breaker 4 Warn Lights Test Switch jD 5 Warn Lights Dim Relay 2 6 Landing Gear Position Lights 1 P1 G33820 7 Gear In...

Страница 751: ...36B20LH Gj4B20 G54A20 6 3 SWITCH TYPE CIRCL IT BREAKER I I I I IB G571 20 5 5 G47 B20 e G47A20 z C26B20 41 I I r I I yGsosz0 t G50A20 I r 1 C44C20 m 6 3 m DwN i Landing Gear And Throttle Warn Circuit 1 Breaker 2 Navigation Lights Circuit Breaker m G33A2j 21m G6C20 2 3 Landing Gear Position Circuit Breaker 3 G32A20 e G32820 4 Warn Lights Test Switch TO LANDING m 5 Warn Lights Dim Relay 2 GEAR G33B2...

Страница 752: ... 1 I III 1 3LI C 36 20 t 3c J20 Gj D20 G54C20 G 7 n20 e G 17 20 S ITCH TYPE CIRCUIT UREAI ER C j7A20 z I I L t I I TCS0 320 C54F20 I I I I I I 1 1 6 0 7 L 1 Gear And Throttle Warn Circuit 1 nreal er C 33A20 2 Nai ib ation Lights Circuit Rreaker I I I c czo 2 3 Gear Position Circuit Dreaker I I I s 1 I r G321 20 4 lrn Lights Test Su itch j U arn Lights Dim Relay 2 Im TO L NDISC GEAR G33n20 6 Landin...

Страница 753: ...arning Horn 7 Landing Gear Control Switch DOWN LANDING GEAR AND THROTTLE WARNING V35B 0 7977 thru D 9068 NOTE CIRCUIT SHOWN WITH AIRCRAFT ON GROUND TO LANDING GEAR G46B20 POSITIONINDICATOR C47B20 r OPEN G53A20 POI I CLOSE AIR g G18P20 m IO NC L XI C Gf 5A20 G18B20 C G18C20 NO G13B20 G28A20N GND t L G13A20 G27A20 3 Landing Gear and Throttle Warning Circuit Breaker 2 Throttle Control Switch UP 3 Fla...

Страница 754: ...INDICATOR OPEN G17A20 C G5352A2 G15hl Q THROTTLE 5A CONTROL SWITCH NC O NOG18A20 REF LANDINGGEAT CL OSED XG18B20 G18C20 t f G6881 G69A 1 2 J FLASHER r G27AZo L L R SQUAT L SWITCH 1_ _ _ _ _ _ _I G28A20N I C13B20 b 1 LI NDING I LANDING GEAR GEAR CONTROL WARNING L HORN F33 369 319 LANDING GEAR AND THROTTLE WARNING 0 7977 thru D 9817 B10 6 79 ...

Страница 755: ...OR YELLOW P V35 369 33 EXHAUST GAS TEMPERATURE Model V35B V35B TC D 7977 thru D 9221 D 9391 and after 2 I II1ON _L r aLLOW I Is RED e LI lO INn UMINr RIPLACEMENT PARTS MUST RE IDEN IICIL OI ENTIRE UNn MUST RE REPLACED i EQT Indico cr 35 369 70 i EQr Bulb EXHAUST GAS TEMPERATURE Vertical Instruments Model V35B D 9222 thru D 9390 6 80 Issued December 1972 ...

Страница 756: ...15A eL25A14 L25B14 L27A14N L26A14N I I i Rotating Beacon Circuit Breaker 2 Upper Rotating Beacon 3 Lower Rotating Beacon V356 369 32 ROTATING BEACON Model V35B V35B TC 0 7977 and after B10 6 80A ...

Страница 757: ...F R rP29AlsNP P30A16 CND REF pm P91A167 P32A16 Im P12A14 P3A18N L P18A1B I P29A BN GND FLD BAT 1 Bus Bar 2 80A Circuit Breaker 3 10A Circuit Breaker 4 Alternator 70A 5 Indicator 330 Lamp 10 Battery Relay 6 Overvoltage Relay 11 Connector 7 Alternator Switch 12 Plug and Cable Assembly 8 Voltage Regulator 13 Battery Switch 9 Suppressor 14 Perm Splice ALTERNATOR D 7977 rhru D 8264 Issued January 1970 ...

Страница 758: ...8A18 D8265 thru D8417 D8418 thru D8526 P21A20N 3 P32A16 P17 516N P22Ar8NI GND E BAT 4 P10A6 i Bus Bar 7 Overvoltage Indicator 2 Alternator Circuit Breaker 8 BatterySwitch 3 Overvoltage Relay Circuit Breaker 9 Suppressor 4 Alternator 10 Alternator Switch 5 Voltage Regulator and Overvoltage Relay 11 Connector 6 Connector ALTERNATOR D 8265 thru D 8526 6 82 Tssued January 1970 ...

Страница 759: ...9AB0 P21A20N P1 A1GN P32B16 P22A18NI 98 BAT P10A6 I 1 C33A 369 36 1 Bus Bar 7 Overvoltage Indicator 2 Alternator Circuit Breaker 8 BatterySwitch 3 Overvoltage Relay Circuit Breaker 9 Suppressor 4 Alternator 10 Alternator Switch 5 Voltage Regulator and 11 Connector Overvoltage Relay 12 Fuse 6 Connector ALTERNATOR D 8527 thru D 8598 Issued September 1971 _ 6 82A ...

Страница 760: ...STALLED ON D 8699 AND AFTER AND ON PRIOR AIRCRAFT SERIALS MODIFIED P22A18N1 P40A18 GND BAT m P10A6 I I i Bus Bar 7 I Ller nator Out Indic tclr 2 Alternator Circuit Breaker 8 Battery Switch 3 Ovfrvoltage Relay Circuit Breaker 9 Suppressor 4 Altr rn tor 10 Alternator Switcli 5 Voltaffc Rcfflllatorr anti Overvoltage 11 Connector Relay 12 Alternator Out Relay C Connector 13 Fuse 14 Resistor ALTERNATOR...

Страница 761: ... F2 r P22A18N P51A20 1 L F1 mi 3A 7 P32Cf8 P32A18 sc_ 1 Bus Bar 8 Battery Switch 2 Alternator Circuit Breaker 9 Suppressor 3 Overvoltage Relay Circuit Breaker 10 Alternator Switch 4 Alternator 11 Alternator Out Relay 5 Voltage Regulator and Overvoltage Relay 12 Fuse 6 Connector 13 Resistor 7 Alternator Out Indicator 14 Capacitor V35A 369 37 ALTERNATOR D 8883 thru 0 8947 Issued September 1971 6 83 ...

Страница 762: ...8 b If P32C18 cL AUX C F2 r P22A18N P51A20cl _L I F1 3A 1P PI P32C1 P32A18 7 i Bus Bar 7 Alternator Out Indicator 2 Alternator Circuit Breaker 8 BatterySwitch 3 Overvoltage Relay Circuit Breaker 9 Suppressor 4 Alternator 10 Alternator Switch 5 Voltage regulator and Overvoltage 11 Alternator Out Sensor Relay 12 Fuse 6 Connector 13 Capacitor V35A 369 38 ALTERNATOR D 8948 thru D 9068 6 84 Issued Sept...

Страница 763: ...INDICA rOR L49A20 A P14A16 X 3A i OFF P13A20 B P12A20 v V P13B20 C I P17A20N1 I ON m J r F33 369 99 i Bus 2 Alternator Field Circuit Breaker 3 Navigation Lights Circuit Breaker 4 Alternator Out Circuit Breaker 5 Alternator Circuit Breaker 6 Alternator 7 Alternator Master Switch 8 Fuse 9 Overvoltage Relay 10 Low Voltage Sensor 11 Alternator Out Light 12 Warning Light dim Relay 13 Diode 14 Warning L...

Страница 764: ...0 TOLANDLNGOEAR L49Aa0 Ir POSITION INDICATOR A J I P14A16 P13A20 i B P12AZ P13A20 1 C k f m P17A20N 1 F33n 369 sen 1 Bus 2 Alternator Field Circuit Breaker 3 Navigation Lights Circuit Breaker 4 Alternator Out Circuit Breaker 5 Alternator Circuit Breaker 6 Alternator 7 Alternator Master Switch 8 Fuse 9 Overvoltage Relay 10 Low Voltage Sensor 11 Alternator Out Light 12 Warning Light dim Relay 13 Dio...

Страница 765: ...0A20N F2 L P9B20 TO LANDINGGEAR L48A20 tl POSITION INDICATOR A I 14A16 T P19 L 20 i 3A B P12A20 y P13A20 C i t m P17A20N I F33A 369 10 A i Uus 2 ield Circuit Breaker 3 Ni vigation I igh s Clrc uil Brc kcr 4 Out Circ uil Breaker 5 Allern torCircuil Breilker 6 Alternator 7 I ltern lor M lster Switch H I use 9 10 I ow Sensor 11 Allcrnalor ul 12 l lrnin I iahl dilll fiL IB 1 1 V lrninU I iCl lsSwjlcl ...

Страница 766: ... G EA R P O SITIO NINDICATOR I_ P9B20 A P14A16 X 3A P13A20 B u P12A20 P13AZO I i C T sl m P17A20N 1 i Bus 2 Alternator Field Circuit Breaker 3 Navigation Lights Circuit Breaker 4 Alternator Out Circuit Breaker 5 Alternator Circuit Breaker 6 Alternator 7 AlternatorMaster Switch 8 Fuse 9 Overvoltage Relay 10 Low Voltage Sensor 11 Alternator Out Light 12 Warning Light dim Relay 13 Diode 14 Warning Li...

Страница 767: ...T L6820 C SELECTOR LIGHT F 3 369 31 FUEL SELECTOR LIGHT ModelV35B D 9274 thru D 9537 ro ALTERNATOR r L6820 WHITE WHITE LIC ON 4 FUEL SELECTOR LIGHT LIA1ON I 33 369 311 FUEL SELECTOR LIGHT D 9538 thru 0 9817 810 6 868 ...

Страница 768: ...ock 6 Slip Ring 7 Deice Boot PROPELLER DEICE TWO BLADED D 8407 thru D 9068 s eFH3B10 3 H4B10 BI n HSB1D i i D tt H8B14 7 P L FI I I n r _ 1 HllB14 C H12B14 A E H9B14 C H10B14 IB cl I 1H13B14N C L J AL H6B14N T r i Bus Bar 2 Prop Deice Circuit Breaker f f 3 Ammeter 4 Timer C 5 Brush Block 6 Slip Ring 7 Deice Boot J PROPELLER DETCE THREE BLADED D 8532 thru D19068 Issued January 1970 6 87 ...

Страница 769: ...mer 5 Slip Ring Assembly L y 6 Deice Boot 7 Brush Block 8 Bus PROPELLER DEICE THREE BLADED 0 9089 thru P9817 LH25A101 ftH14A107 tH15A10 IB I I 1 H17A14 C H18A14 D H19A14 E H21A14 F H23A14N L B CH20A1 A I H22A14 C H16A1BN 7_ i Prop Deioe Circuit Breaker 2 Ammeter 3 Connector 4 Timer 5 Slip Ring Assembly 6 Deice Boot 7 Brush Block 8 Bus PROPELLER DEICE TWO BLADED 0 9096 thru 0 9817 6 88 B10 ...

Страница 770: ...D I TEMPERATURE E31A20N L E32A20 YI GROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N CYtlNDER HEAD E42A20N AND E44A20N FUEL QUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT E33A20N j i Cylinder Head and Oil Temperature Circuit Breaker 2 Cylinder head OilTemperature and Oil Pressure Indicator 3 Oil Temperature Transmitter Bulb V358 369 45 OIL TEMPERATURE 0 9069 thru 0 992 1 IJsue...

Страница 771: ...OWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N OIL 35 569 74 TEMPERATURE E39A20N CYLINDER HEAD TEMPERATURE E42A20N AND E44A20N FUEL QUANTITY DO NOT GROUND ANY OTHER WIRES AT THIS POINT i Circuit eroal or 2 Oil lrsrluro Indicator 3 Oil T5mp rotut Indico or 4 Oil Prerrure lranrmittor 5 OilTemp rolture O1L TEMPERATURE AND OIL PRESSURE Vertical Instruments Model V35B D 9222 thru D 9390 Issued Decemb...

Страница 772: ...ATURE D 7977 thru 0 9068 E5A20 AD B PI E41A20 E31A20N E40A20N 1_ E32A20 I J OIL TEMP Y GROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT 831A20N CYLINDER HEAD E42A20N AND 844A20N FUEL QUANTITY DO NOT GROUND ANY OTH ER WIRES AT TH IS POINT i Cylinder Head and Oil Temperature Circuit Breaker 2 Cylinder Head OilTemperature and Oil Pressure Indicator 3 Cylinder Head Temperature Transmitter Bulb ...

Страница 773: ... POINT E31A20N OIL TEMPERATURE E39A20N CVLINDER HEAD TEMPERATURE E42A20N AND E44A20N FUEL QUANTITYJ DO NOT GROUND ANY OiHER WIRES AT THIS POINT I Cir uit r oL r 2 Cylind r H od mp ratur Indito or 3 Cylind r H od 51 349 73 CYLINDER HEAD TEMPERATURE Vertical Instruments Model V35B D 9222 thru D 9390 Isoued December 1972 6 90A ...

Страница 774: ...NSMITTER IIULB CYL HEAD TEMP 3 C E41A20 OIL TEMP 4 E40A20N OIL IEMP I E32A20 TRANSMITTER BULB E33A20N e GROUND THE FOLLOWING INSTRUMENT WIRES AT A SINGLE POINT E31A20N CYLINDER HEAD E42A20N AND E44A20N FUEL OUANTIT I DO NOT GROUND ANY OTHER WIRES AT THIS POINT F33n 3ea2es CYLINDER HEAD AND OIL TEMPERATURE D 9391 thru D 9817 6 90B B10 ...

Страница 775: ...30A20i BLACK 4 E29A20 RED 5 E28A20 L70A20 WHI fO ENGINE INSTR VMENT LIGHTS i Circuit Breaker 2 iManifold Indico or 3 Monifold Tran duc r 35 369 72 MANIFOLD PRESSURE Vertical Instruments Model V35B D 9222 thru D 9390 losued December 1972 6 90C ...

Страница 776: ...ACK 4 C E24A20 RED 5 E25A20 L71A20 WHITE TO E N GINE IN ST RUM ENT LIGHTS i Circuit Bleaker 2 Fuel Flow Indicotor 35 369 71 3 Fu el Flew Transducer FUEL FLOW Vertical Instruments Model V35B 0 9222 thru 0 9390 6 900 laued December 1972 ...

Страница 777: ...0 41 1 BL CK L72A20 _I WHITI TO ENGINE INSTRUMENT LIGHTS 1 Circuit 2 Tothometerlndica or 3 Tachometer Pickup Probe 3 69 77 TACHOMETER Vertical Instruments Model V35B 0 9222 thru 0 9362 Issued Decamber 1972 6 90E ...

Страница 778: ... 2 EllA20j 4 BLACK I I ii I P L72A20 _1 WHITE I TO ENGINE INSTRUMENT LIGHTI i Circuit Bie Lor 2 3 7 chometer robe 35 369 774 4 Rsri lor TACHOMETER Vertical Instruments Model V35B D 9363 thru D 9390 6 90F Issued December 1972 ...

Страница 779: ...TO INSTRUMENT FLOOD LIGHTS L20B18N k L21A18 i L21B18 L20D18N L20Cr8N k L21C18 L20E18N 1 Oil Temperature Radio Instrument and Cabin Lights Circuit Breaker 2 Cabin Light Switch 3 Cabin Light 4 Reading Light Switch 5 Reading Light CAB LIGHTS D 7977 thru D 8598 Issued January 1970 6 91 ...

Страница 780: ...L8B18 TO INSTRUMENT I FLOOD LIGHTS L8C20 k i L32A20 L7B20N L31A20 L 0 L41A20 L31B20 L32B20 koC 1 Oil Temperature Radio Instrument and Cabin Lights Circuit Breaker 2 Cabin Light Switch 3 Cabin Light 4 Reading Light Switch 5 Reading Light CABIN LIGHTS D 8599 thru D 9068 6 92 Issued January 1970 ...

Страница 781: ...L31A20 L32A20 I L41A20 O L32B20 L31B20 i Cabin and Map Lights Circuit Breaker OPTIONAL 2 Compass and OAT Light S itch 3 OAT Light 4 Clareshield Connector 5 Compass Light 6 Ca in Light Switch 7 Ca Jin Light 8 Reading Light Switch 9 Reading Light 10 Map Light Switch 11 Map Light V SI 69 50 CABIN AND MAP LIGHTS D 9069 thru D 9286 Issued September 1971 6 92A ...

Страница 782: ...l CII Y I Bl d l 2 Cabin Lights SwilCh L10oC20 LIOICZON 3 Cabin Light 4 Reading Light Switch 0 L 08 20 FOVRTH SEAT 5 Reading Light a Coiled Cord READING LIGHT I Light Switch B Glarerhield Connecror 9 Colnpasr Light 10 O T Indicator Light 11 Mar Ligh P Llooozo Llolozo I t c READING LIGHT OPTIONAC Oct SWITCH SIXTH SEAT READING LIGHT OPTIONAL Ej 1 1 1 LIIOAZO CABIN AND MAP LIGHTS 0 9287 thru 0 9817 B...

Страница 783: ...IOR LIGHTS L6A20 L5A18 If TO CABIN L3B18L3A18 t L16A18N I L34 18 O r L4A18N L9A18N CO Ir 1 Oil Temperature Radio nstrument and Cabin Lights Circuit Breaker 2 Dim ControlRheostat 3 Fuel Select Light 4 Engine Instrument Lights 5 Glareshield Lights 6 Compass Light 7 Trim Tab Indicator Light 8 LG Visual Indicator Light 9 Resistor INSTRUMENT FLOOD LIGHTS D 7977 thru D 8598 6 94 Issued January 1970 ...

Страница 784: ... BY VENDOR ARE NOT CODED L16A20N L6A20 I _ L5A20 e L34 18 I i Instrument Light Rheostat 2 Fuel Panel Light 3 OAT Light 4 Landing Gear Visual Indicator Light 5 Trim Tab Indicator Light 6 Compass and OAT Light Switch 7 Compass Light 8 Engine Instrument Lights 9 Glareshield Instrument Flood Lights 10 Oil Temp Radio Instrument and Cabin lights Circuit Breaker INSTRUMENT FLOOD LIGHTS D 8599 thru D 8892...

Страница 785: ...J L16A18N IL4B20 iis L L6A18 L5 L34 18 IL2C20 I II u I P L21B20N L9A18N I 1 1L2D20 1 Oil Temp Radio Inst and Cabin Lights Circuit Breaker 2 Dim Control Rheostat 3 Compass and OAT Light Switch 4 OAT Light 5 Fuel Selct Light 6 Engine Instrument Lights 7 Trim Tab Light 8 Landing Gear Visual Indicator Light 9 Glareshield Connector 10 Glareshield Lights 11 Compass Light INSTRUMENT FLOOD LIGHTS D 8893 t...

Страница 786: ...0 3r L2E 20 I I L21B20N O I L2F20 L2G20 I I I I I i Flood Lights Circuit Breaker 2 Dim Control Rheostat 3 Dim Control Transistor 4 Trim Tab Light 5 Landing Gear Visual Light 6 Fuel Select Light 7 Clock Light Optional 8 Glareshield Connector 9 Glareshield Flood Lights INSTRUMENT FLOOD LIGHTS D 9069 thru D 9286 Issued September 1971 _ 6 96A ...

Страница 787: ... L102C20 L102D20 L102E20 I I L103B20N 0 I I L102F20 L102G20 1 Flood Lights Circuit Breaker 2 Dim Control Rheostat 3 Dim Control Transistor 4 Trim Tab Light 5 Landing Gear Visual Light IC1 6 Not Used 7 Not Used 8 Glareshield Coiinector 9 Glareshield Flood Lights INSTRUMENT FLOOD LIGHTS Model V35B D 9287 thru D 9559 6 968 86 ...

Страница 788: ...102 C20 L102 D20 L102 E2 I I L103B20N 0 I L102F20 L102C20 i Flood Lights Circuit Breaker 2 Dim ControlRheostat 3 Dim Control Transistor 4 Trim Tab Light 5 Landing Gear Visual Light 6 Not Used V358 369 54 7 Not Used 8 Glareshield Connector 9 Glareshield Flood Lights INSTRUMENT FLOOD LIGHTS 0 9560 thru 0 9817 6 97 B10 ...

Страница 789: ...GHTS AND FUEL L8OBPO BL CK WHITE 00 TACHOMETER OMNII OMN12 BLACK 1 WHITE N lo ol LH FUEL OUANTITY BLACK i WHITE O O RH FUEL OUANTITY IIACK jo o WHITE I I dio nd nl ul nl Ll ht Cl ult r L 00 2 Dim Control Ilh o ot 3 Dim Control Tlonli lor 4 Omni Liphh 5 Wodgo Lightl 6 luc No 5 T ul No 4 a DIIIIM1NO WHEN OPTIONAL FLIOHTINSTRUMENT LIOHTSINITALLED 033 36986A ENGINE INSTRUMENT WEDGE LIGHTS OPTIONAL D 9...

Страница 790: ...lOW L75120 1 1 0IO LIGHTS O L73110 110120 IFLIGHT INSTIUMENT O TICHOMETER F L72A20 I DimmiNe a OIL TEMP L69 20 FUEL FLOW L71 L73C20 LB0 20 IL MMITII L6 i I P EGT L74C 20 L7 D10 LH FUEL OU N71TI LbS O Y L3O120 omNI II L73E10 CYLINDEII HE D TEMr L67 20 7 1 IH FULL OUANTITI L66 10 I Cir uii r oL r 2 Ih oilo lodio nd tngin Inr rum n Dimminp i Iran iitor lodio ond Inpin In trun nl Di ming 35 369 16 Q I...

Страница 791: ...00 WHITE TACHOMETER OMNI1 OMNI 1 I LACK WHITE I I II O 01 LH FUEL QUANTIT I BL CK WHITE 00 RH FUEL OUANTITY BLACK lo ol WHITE I I dio nd Inllrun nl Li ht Ci uil LI o r 00 16n2av 2 Dim Control Ihooltot AMMETIR r 3 Dim Control 4 Omni Liehh 5 W do Lioh 6 I u No 3 7 3ul No 4 n OMN L T CONNECTED TOFL HT INSTRUMENT DIMMINO WHEN OPTIONAL FLIGHT INSTRUMENT LIGHTS INSTALLED 633368364 ENGINE INSTRUMENT WEDG...

Страница 792: ...INSTRUMENT MANIFOLD LIGHTS AND FUEL PRESSURE BLACI 00 WHITE Bk TACHOMETER OMNI 1 OMNI BL CK WHITE O O LH FUEL OUANTITY BLACK8 WHITE 00 RH FUEL oun Jrl7v BLACK B o o WHITE i lodio nd In lru n nt Li hr Cirluit r ol r O O L86 ON 2 Dim Control Ih o tat MMETZR 3 Dim Control Omni Lilhlr 5 Widg Lishti 6 lu No 3 i OMNI LIGH11 CDNNICTID r0 r tHT INSIIIUMINI DIMMING WHEN OPTIONAL FLIGHT INSTRUMENT LIGHTS IN...

Страница 793: ...L81B20N LO J LB A2ON VERT1CAL SPEED 1 L12B20 BLAEK t L12020 WHITE LI C2D L6F20 L82C20N LbD10 AIR PRESSURE L12P 20 L12C20 L47A20 L30A20N L I W dg Light 6 Landing G ar Vi uol Light 2 Bu No 1 7 Clo k L 5A2ON L46820 3 Bu No 8 Dimminp Traniiilor u b 4 EIap porition 9 Rh oitot OFF L L41A20 5 Irim Tob Light 10 Radio and Initrum nt Light Cir ui Br a r cC 11 Omni Lamp TO ENGINE INSTRUMENT LIOHTZ G33 369 86...

Страница 794: ...I AIR SPEED TURN AND BANK AOF PRESSURE GIRO B B L TE OF CLIMB I B HORILON FLAP POSITION CLOCK L80A20 DIRECTIONAL GYRO LB0B20 1 BUS NO 1 2 BUS NO 2 OMNI 2 OMNI I 3 POST LIGHT 4 RADIO AND INSTRUMENT LIGHT CIRCUIT BREAKER 5 RHEOSTAT 6 DIMMING TRANSISTOR i u FLIGHT INSTRUMENT POST LIGHTS Model V35B 0 9069 thru 0 9559 88 8 888 ...

Страница 795: ...AND BANK AO PRESSURE GIRO El R T Or CLIMB HORIZON ELAP POSITION P CLOCK L80A20 PI roll TCIIONIII r g ia0e20 i BuS NO 1 2 BVS NO 2 OMN12 OMNII 3 POST LIGHT 4 RADIO AND INSTRUMENT LIGHT CIRCUIT BREAKER S RHEOSTAT G33 369 B38 6 DIMMING TRANSISTOR FLIGHT INSTRUMENT POST LIGHTS D 9560 thru D 9817 B10 6 99 ...

Страница 796: ...L5B20 L5C20 RED RED RED BLA BLACK RH CENTER CIRCUIT SWITCH PANEL BREAKER PANEL PANEL V358 369 57 i Flood Lights Circuit Breaker 2 ElectrolumiAous Panel Lights Dim Transistor 3 Dim ControlRheostat 4 Inverter 5 Electroluminous Panel ELECTROLUNrNOUS PANEL LIGHTS Model V35B D 9069 thru 0 9537 6 100 88 ...

Страница 797: ... RED RED rLSE20N RED BLACI L5FZON BLACK BLACK 1 t 1 LH RH E L CIRCUIT CIRCUIT PANEL BREAKER I I BREAKER PANEL PANEL i Flood Lights Circuit Br aker 2 Electroluminous Panel Lights Dim Transistor 3 Dim ControlRheostat 4 Inverter 5 Electroluminous Panel ELECTROLUMINOUS PANEL LIGWTS 0 9538 thru 0 9817 B10 6 100P ...

Страница 798: ... 1 TOOIrlaN1L YiO Oi FLIGHT rL OA20 INSTRUMENT MANIFOLD LIGHTS AND FUEL PRESSURE 180820 BL CK 00 WHITE OMNI LIGHTS TACHOMETER OMNI 1 OMNI BLACK WHITE O O LH FUEL QUANTITY BLAC WHITE O O RH FUEL QUANTITY BLACK Illo o WHITE LB4B20 00 L86A20N AMMETER r INSTR LTS 7 LT GND 8 L861 20N p INOINI L OMNI LIGHTS EONNECTTD rO LICIHI INIIIUMINI INSTRUMENT DIMMING WHEN OPTIONAL FLIGHT INSTRUMENT CLUSTER LIGHTS ...

Страница 799: ...TO O TIONPIL O O FLIGHT y1B0A20 I INSTRUMENT MANIFOLD AND FUEL LIGHTS PRESSURE LB0B20 OMNI LIGHTS BLACK WHITE B O O TACHOMETER OMNI 1 OMNI 1 BL CK WHITE 00 LH FUEL OVANTITI BLACK WHITE 00 RH FUEL OUANIITY BLACK N o 31 WHITE LB4B20 03 AMMErER r INSTR LTS 7 GND B L86820N PI INOINI OMNI L1OHrS EONN CIID TO rllOHT INSrlUMtNr INSTRUMENT DIMMING WHEN OPTlONAL FLIGHT INSTRUMENT CLUSTER LIGHTS INSTALLED F...

Страница 800: ...l Column Coil Cord C21A18 3 Trim Control Switch 4 Trim Actuator RED ELEVATOR TRIM 0 8599 thru D 9068 NOSE DOWN r 1 I A YELLOW DI C1A20 CrB20 BLUE 10A 2 B F BROWN 20CiA i_C S G A IC V 1 Pitch Trim Circuit Breaker ICBA20 BLACK NOSE UP 2 Control Column Coil Cord 3 Trim Control Switch C7A20 0 4 Trim Actuator 5 Pitch Trim Switch RED ELEVATOR TRIM 0 9096 thru 0 9817 B10 6 101 ...

Страница 801: ...A20N C42A20N 1 OFF BLACR WHITE PCLLD E OFF PRIOR TO D 9069 i Avionics Bus 2 Constant Copilot Solenoid Valve 3 Constant Copilot Switch 4 Constant Copilot Wheel Switch 5 Constant Copilot Autopilot Circuit Breaker CONSTANT COPILOT 0 7977 thru 0 9817 810 6 102 ...

Страница 802: ...E BLACK RED rl_l I Strobe Light Circuit Breaker 2 Power Supply 3 Strobe Light STROBE LIGHT BULLOCK D 7977 thru D 9068 E L76A20 L76B20 23 4 L79B20N WHITE BLACK RED i Strobe Light Circuit Breaker 2 Power Supply 3 Strobe Light STROBE LIGHT BULLOCK I D9069 thru D 9817 810 6 103 ...

Страница 803: ...sA I d L37A14 er d C 1 5 BLACK BC WHZTE IB A I t RE D I A i Strobe Light Circuit Breaker 2 Power Supply 3 Strobe Light STROBE LIGHT HOSKINS D 7977 thru D 9817 6 104 B10 ...

Страница 804: ...WHITE E BLACK WING LAMP CABLE ASSEMBLY t i cs Al RID B WHITE CI _ I _ BLACK WING LAMP CABLE ASSEMBLY A RED WHITE d REFER TO NAVIGATION LIGHTS C BLACK L3 827C20 POWER SUPPLY BLAC RE D OR NOE WHITE BLUE 33A 369 96A TAIL CONE LAMP ASSEMBLY STROBE LIGHT GRIMES 0 9294 thru 0 9817 B10 6 104A ...

Страница 805: ... Courtesy Light Fuse 3 Courtesy Light Switch 4 Courtesy Light COURTESY LIGHTS Model V35B D 9069 thru D 9559 L81B20 ZR L81D20 c BLACK BLACK 3 F L8IEPO C O V35836967 1 1 Battery Bus 2 Courtesy Light Fuse 4 Courtesy Light COURTESY IdOHTS 0 9560 thru 0 9817 6 105 610 ...

Страница 806: ...A2 OVERVOLTAGE RELAY P34D18 I P59E18 AMPLIFIER O Pssnlsru p46818 i P39A18 T81 82 84644 r _r_ P56n18 TRANSPONDER STANDBY 494 COMM NAV COMM NAV GENERATOR 1 z 2 I O O r RESISTOR P91C18 NAV COMM 1 1 RESISTOR PS C18 I I TRANSISTOR ro MGA NAV Z 853818 ZENERDIODE DIODE I I I I _ menpyln Pszn18 L TERMINAL TO BOARD O cn NAV i mcA I TOAVIONICS 841918 TO GROUNDED TO I I II TRANSISTOR MGA COMM 2 STRUCTURE mac...

Страница 807: ...ANDING REF TO ALT OUT LIGHT GEAR POSITION L J H33D1 DIOOE INDICATOR IH33F18LJ H33C18 I I GEAR 70A12 0 LH SOUAT FLIGHT POSITION 40620 SWITCH SWITCH 4 PARTIAL OPEN H3QB1B cToS o 3 RED 11 1 9 H38120 CONDENSORI RC42CF OOR 7 WH rE JACTUATOR H31 18 C H39A20 1 2 CONDENSER P19D20 101 p P19820 8WF LICK RESISTOR L __ OPEN r P19A20 I P20A20 CONDENSER 6 DOOR LH LANDING GEAR OPEN LIGHT POSITION SWITCH r0 5 ITT...

Страница 808: ...SECTION PERIODIC INSPECTION SCHEDULE ...

Страница 809: ...SECTION 7 Periodic Inspection Schedule I ...

Страница 810: ...el the deicer boots on the propeller for the proper sequence of heater operation The presence of local hot spots indicate severe damage to the deicer heaters which should be repaired before more serious damage develops c Remove the spinner dome and open all access doors pertaining to the wiring and components of the deicer system Turn the deicer switch ON and station an assistant in the airplane t...

Страница 811: ...egrees of rotation is over 0 005 inch or in excess of 0 002 inch in any Lt inch are refer to Section 3 for the paragraph on slip ring alignment h Examine the brush mounting brackets and housings for cracks deformation or other indications of damage Check for tight connections and that the leads are not chafed or binding i Check that each brush rides fully on its slip ring over 360 degrees of rotat...

Страница 812: ...g method 1 Remove the compressor inlet duct assembly by loosening the four clamps and removing the two boots Loosen the alternate air duct control as necessary and lower the duct 2 Inspect the compressor wheel for nicks cracks or broken blades Turn the wheel by hand and feel for excess bearing drag or wheel rubbing against the housing 3 Reinstall the air inlet duct and check the rigging of the alt...

Страница 813: ... GUIDE The owner or operator is responsible for maintaining the airplane in an airworthy condition including compliance with all applicable Airworthiness Directives as specified in Part 39 of Title 14 Code of Federal Regulations 14 CFR It is further the responsibility of the owner or operator to ensure that the airplane is inspected in conformity with the I requirements covered in 14 CFR Parts 43 ...

Страница 814: ...ss to the previously noted documents as well as to this Inspection Guide NOTE Any time an airplane is repainted or touched up inspect all placards and decals to assure that they are not covered with paint are easily readable and are securely attached Replace any placards that have been inadvertently defaced or removed In addition to the inspections prescribed by this schedule the altimeter system ...

Страница 815: ...e Service Bulletins mandatory I OPTIONAL and or RECOMMENDED No Border Service Bulletins cover changes modifications improvements or inspections which may benefit the owner Due to the wide range of information covered by the OPTIONAL Service Bulletin each owner or operator is responsible for conducting a thorough review of each OPTIONAL Service Bulletin to determine if compliance is required based ...

Страница 816: ...1 POWER CHECK Refer to NORMAL PROCEDURES in the appropriate Pilot s I Operating Handbook 12 AMMETER Check for proper indication and unusual fluctuations 13 HEATING AND VENTILATING SYSTEM Check for proper operation heat and airflow output Check controls for freedom of movement 14 FIREWALL SHUTOFF VALVE Check for proper operation and freedom of movement 15 IDLE RPM AND MIXTURE SETTINGS Check for bot...

Страница 817: ... to service 30 AIR CONDITIONER Evaporative System Drain unit to remove dirt and other foreign particles from the wick box drain line and overflow line Remove wick assembly from box and flush with water Refer to AIR CONDITIONER EVAPORATIVE SERVICING in Section 3 1 31 AIR CONDITIONER Refrigerant System Operate the air conditioner and verify that the retractable condenser moves to the ground extended...

Страница 818: ...nd for obstructions Check for metal particles or foreign matter on screens and filters Check for proper torque after installation 13 OIL COOLER Check oil cooler lines and fittings for condition security chafing and leaks 14 PROPELLER AND MOUNTING HARDWARE Check for condition and security I I I 1 15 PROPELLER BLADES Inspect the blades for cracks dents nicks scratches erosion I I I I corrosion secur...

Страница 819: ...for leakage cracks deterioration and damage Check fittings for security 29 ENGINE ACCESSORIES Check for condition security and leaks Check wiring hoses and tubes for chafing security and leaks 30 ENGINE MOUNTS Check for cracks corrosion and security Inspect rubber cushions mount bolts and nuts and grounding straps for condition and security Check engine mount support for cracks and material integr...

Страница 820: ...ean the screens as directed in this shop manual Check for condition mounting and proper operation Install the screen and check for security Inspect for cracks 46 VACUUM SYSTEM AIR FILTER Located forward of the instrument panel Check for security of attachment replace as required 47 ELECTRIC PROPELLER DEICER a Check for service damage to the deicer heaters brush rods springs and brushes Check for a...

Страница 821: ...nt C CABIN AND BAGGAGE COMPARTMENT 1 SKIN Inspect skins for deformation cracks and loose or missing rivets If damage is found check adjacent structure 2 STRUCTURE Check for cracks and deformation Check for loose or missing rivets and concealed damage 3 CABLES PULLEYS AND TURNBUCKLES Check the flight control components cables and pulleys Replace control system components pushrods turnbuckles end fi...

Страница 822: ...d general condition 14 WINDOWS AND DOORS Inspect windows for scratches crazing and general condition Inspect doors for security of attachment Check latching mechanism for proper engagement and ease of operation Check that rotation of the interior door handle without depressing the handle lock release button does not unlatch the door 15 INSTRUMENTS AND INSTRUMENT PANEL Inspect instrument panel sub ...

Страница 823: ... splits bends or cracks Check control cables pulleys and associated equipment for condition attachment alignment clearance and proper operation Replace cables that have more than 3 broken strands in any 3 foot length of cable or evidence of corrosion Check cables for proper tension NOTE It is important to operate controls through their full range so that the cables move away from pulleys and all p...

Страница 824: ...AR STRUT Inspect the shock strut and components for cracks attachment proper inflation and evidence of leakage 3 ACTUATING LINKAGE Check for wear at attach points Check for cracks and security 4 GEAR DOORS AND LINKAGE Check doors for damage and cracks to the structure and skins Check linkage for wear and cracks at the attach points Check for condition and security 5 NOSE GEAR STEERING LINKAGE Insp...

Страница 825: ... attach points Check for condition and security Determine that all clevis retaining pins are in place and secured with cotter pins 7 STRUT FLUID LEVEL Check and maintain the proper hydraulic fluid level in the struts as outlined in Section 2 8 STRUT AND A FRAME HINGE BOLTS Inspect for corrosion and security of attachment G MAIN GEAR OPERATION I WARNING Under no circumstances should the landing gea...

Страница 826: ...ion and operation of the complete landing gear system 11 DYNAMIC BRAKING ACTION Verify proper operation of dynamic brake relay 12 ASSIST STEP If Installed Inspect the retractable step for cable and safety link condition proper adjustment and operation Check fixed link condition proper adjustment and operation Check fixed steps for security I I I I I H NOSE GEAR OPERATION MECH INSP WARNING I II Und...

Страница 827: ...nd associated equipment for condition attachment alignment clearance and proper operation Replace cables that have more than 3 broken strands in any 9foot length of cable or evidence of corrosion Check cables for proper tension NOTE It is important to operate controls through their full range so that the cables move away from pulleys and all portions of the cables are exposed for inspection 5 CONT...

Страница 828: ...rotate with your fingers J GENERAL 1 Airplane cleaned and serviced 2 Airplane lubricated after cleaning in accordance with this shop manual lubrication chart 3 Inspect all placards to ensure that they are easily readable and securely attached 4 Ensure that all AiMlorthiness Directives Beechcraft and Raytheon Aircraft Service I I I I Bulletins and previously issued Service Instructions are reviewed...

Страница 829: ...ENOPERATING IN AREAS OF HIGH DUST CONTENT Nose Landing Gear Shock Clean off and wipe dry exposed polished Routine Strut surfaces Instrument Air Filters Replace instrument line supply filters at or As noted conditions before 100 hours under extremely dusty Alternate Air Door Ensure door is sealed around all edges and Routine there is adequate spring tension on the door CAUTION To avoid damaging the...

Страница 830: ...d rims bearing for wear corrosion fretting and bluing check seals for distortion deterioration and proper fit and security b Brake Units 1 Check cylinders and associated lines for Routine I damage and leaks 2 Check for evidence of overheating Every 100 hours and or annually 3 Check discs for scoring distortion Every 100 hours and or annually damaged plating and evidence of overheating c Shock Abso...

Страница 831: ...ding and before the airplane is certified as ready for further flight The inspections are conducted at two levels The first level consists of determining if any external damage has occurred and looking for evidence of internal structural failure The second level is concerned with a more detailed inspection of any damaged areas which were indicated in the findings of the first level inspection If i...

Страница 832: ...gs for cracks or I structural failure e Check tips of propeller for damage f Check propeller spinner and backplate for evidence of interference with cowling g Inspect wheel well structure for damage or cracks Check area surrounding the landing gear attachment points Wing Carry thru Structure a Check wing attachment fittings for cracks I Perform a Dye Penetrant inspection b Inspect plumbing wiring ...

Страница 833: ...ound in the first level inspection I Landing Gear a Place airplane on jacks and check shock strut for free up and down movement I b Remove tires and inspect internally for cuts or broken areas I c Disassemble and examine wheels trims for cracks or distortion d Visually inspect axle with 10 power glass If suspect dye check or magnaflux e Remove and replace or magnaflux the landing gear attach bolts...

Страница 834: ...mensions b Test plumbing and wiring for proper I operation Fuselage Center and Aft a Examine stringers frames and sidewalls for I Section deformation structural failure b Test plumbing and wiring for proper I operation c Inspect heating and air conditioning ducts for damage d Examine the control cables and pulley mountings and check for clearance from structure at pass through locations Ensure a s...

Страница 835: ...gh to be considered as negligible a close inspection of the internal supporting structure may reveal serious damage General Appearance Determine that the airframe components I normal configuration wings fuselage and empennage are in their Wing Carry thru Structure a Inspect the external skin surface for cracks abnormal stress wrinkles and loose or m i s s i n g r i v e t s b Check wing attachment ...

Страница 836: ...g rivets b Check the empennage surfaces for damage I and free movement c Inspect for skin wrinkles at the juncture of I the fuselage and empennage SECOND LEVEL INSPECTION As required I I NOTE I Because G loading may be transmitted along one structural member to another carefully inspect the surrounding and supporting structure in any damaged area found in the first level inspection Wing Carry thru...

Страница 837: ...ational test plumbing and wiring d Examine the control cables pulley mountings and the cable clearance at areas the cables pass through the structure Ensure a smooth normal operation I Empennage a Inspect elevator pushrods torque tubes and bellcrank for damage b inspect the attachment of the vertical stabilizer spars to the top of the fuselage for evidence of damage I c Inspect skin surfaces for c...

Страница 838: ...he data provided in the manufacturers manuals prior to returning the airplane to service following any lightning strikes or other impact damage Propeller a At times the difficulty is not in inspecting the airplane but in determining if a strike has occurred Most times an exit location will indicate possible damage to the components The entry point is most often the propeller A darkened area in the...

Страница 839: ...vidence of arcing sooting or pitting b From the point of entry the strike usually spreads aft in a series of small holes or burn marks After the points of entry and exit are found the structure between these points should be carefully inspected Attention should be given to hinges and hinge pins for possible pitting Cables pulleys bearings bolts and all bonding jumpers in the area should be inspect...

Страница 840: ...SECTION ACCESSORY AND CO NIPONENT REPLACEMENT SCHEDULE ...

Страница 841: ...SECTION 8 Accessory and Component Replacement Schedule I ...

Страница 842: ...he item will reach the period without malfunction as the aforementioned factors cannot be controlled by the manufacturer I WAR IEIO I WARNING Use only genuine Raytheon Aircraft Company or Raytheon Aircraft Company approved parts obtained from Raytheon Aircraft Company approved sources in connection with the maintenance and repair of Raytheon Aircraft Company airplanes Genuine Raytheon Aircraft Com...

Страница 843: ...er On condition Main Gear Assembly On condition Leaking or collapsed struts that cannot be corrected by seal replacement will constitute the On condition requirement Any pitting corrosion cracking distortion or visible wear noted during the seal replacement will also constitute the requirement for an overhaul Nose Gear Assembly On condition Leaking or collapsed struts that cannot be corrected by s...

Страница 844: ...oler On condition replace if contaminated I Air Pressure Pump Airborne Pumps refer to Airborne Replacement Schedule SI 300 17 or subsequent See Supplier Data CAUTION at the end of this section Aero Accessories Pumps Part Number AA442CW replace at 500 hours time of operation Aero Accessories Pump Part Number AA216CW Replace at 1200 hours time of operation Standby Air Pressure Pump Airbome Pumps ref...

Страница 845: ...x I first Replace every 500 hours or 1 year whichever occurs Engine Baffle Seals Replace as necessary or every 10 years of service TF1900 Main Engine Fuel Pump TRW or Thompson Model Overhaul every 900 hours Refer to TRW Service Bulletin ESD 182D or subsequent FLAPS AND FLIGHT CONTROLS Trim Tab Actuator 2 000 hours Flap Flexible Shaft 2 000 hours Flap Gearbox 2 000 hours Flap Motor and Drives 2 000...

Страница 846: ...t See Supplier Data CAUTION at the end of I Airspeed Indicator On condition Attitude Gyro On condition Clock On condition Directional Gyro On condition Flap Position Indicator On condition Free Air Temperature Indicator On condition Fuel Flow Gage On condition Gym Horizon On condition Gyro Filter On condition Gyro Filter Pressure System 300 hours Gyro Pressure Gage On condition Manifold Pressure O...

Страница 847: ... or on condition Refer to Section 4 MISCELLANEOUS Seat Belts or Shoulder Harnesses Inspect every 12 months replace on condition Cabin Heating and Ventilating Ducts Inspect every 12 months or on condition Cabin Heating Exchanger Heater Muffler On condition Hand Fire Extinguisher Inspect every 12 months recharge as necessary Oxygen Cylinder 22 0 cu ft Standard Weight Hydrostatically test every 5 yea...

Страница 848: ...MANUAL ICAUTION CAUTION Supplier Data is subject to change Users of this manual should refer to the Parker Hannifin website components www parker com airborne for the latest information regarding Parker Hannifin Airbome I 821 Section 8 Aug 29103Page 7 ...

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