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De Havilland DHC-4 CARIBOU, Maintenance Manual

The De Havilland DHC-4 Caribou Maintenance Manual is now available for free download on our website. This comprehensive manual provides detailed instructions on how to maintain and troubleshoot your aircraft. Ensure the longevity and performance of your Caribou by downloading the manual from manualshive.com.

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Summary of Contents for DHC-4 CARIBOU

Page 1: ...THE DE HAVILLAND AIRCRAFT OF CANADA LIMITED Downsview Ontario 1 JULY 1963 Revised 1st February 1972 ft PSM 1 4 2 DHC 4 CARIBOU MODEL DHC 4A MAINTENANCE MANUAL THE DE HAVILLAND AIRCRAFT OF CANADA LIMI...

Page 2: ...ent revision THE DE HAVILLAND AmCRAFT OF CANADA LIMITED DOWNSVIEW ONTARIO A Revised 1 February 1972 DHC 4 CARIBOU MAINTENANCE MANUAL LIST OF EFFECTIVE PAGES Insert this page and latest revised pages D...

Page 3: ...revis ion THE DE HAVILLAND AIRCRAFT OF CANADA LIMITED DOWNSVIEW ONTARIO B Revised 1 February 1972 I DHC 4 CARIBOU MAINTENANCE MANUAL LIST OF EFFECTIVE PAGES Insert this page and latest revised pages...

Page 4: ...nt revision THE DE HAVILLAND AIRCRAFT OF CANADA LIMITED C DOWNSVIEW ONTARIO Revised 1 February 1972 DHC 4 CARIBOU MAINTENANCE MANUAL LIST OF EFFECTIVE PAGES Insert this page and latest revised pages D...

Page 5: ...nt revision THE DE HAVILLAND AIRCRAFT OF CANADA LIMITED Revised 1 February 1972 DOWNSVIEW ONTARIO D DHC 4 CARIBOU MAINTENANCE MANUAL LIST OF EFFECTIVE PAGES Insert this page and latest revised pages D...

Page 6: ...nt revision THE DE HAVILLAND AIRCRAFT OF CANADA LIMITED E OOWNSVIEW ONTARIO Revised 1 February 1972 DHC 4 CARIBOU MAINTENANCE MANUAL LIST OF EFFECTIVE PAGES Insert this page and latest revised pages D...

Page 7: ...Frs 71 VAl OilS S P 73 2 209 14 SEP 73 2 2 10 Z fE 7 8 24 1 September 1970 Page No T R Index Page 1 T R Ser No 1 15 7 18 DHC 4 CARIBOU MAINTENANCE MANUAL ITEMPORARY REVisION INDEX l I Insert following...

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Page 9: ...ook Hamilton Standard Propeller Manual Aircraft Registration _ Manufacturer s Serial No Manual No i INTRODUCTION This manual has been prepared by the De Havilland Aircraft of Canada Ltd to assist civi...

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Page 11: ...ix I Reference Publications Appendix II Special Order Equipment Appendix III Inspection Schedule iii PART PART 1 PART 2 PART 3 PART 4 PART 5 PART 6 PART 7 PART 8 PART 9 Table of Contents TABLE OF CONT...

Page 12: ......

Page 13: ...Lubrication 1 28 1 29 Cleaning 1 28 SPECIAL TOOLS AND EQUIPMENT 1 30 General 1 33 1 1 _ _ _ _ _ _ _ PART I Part 1 Table of Contents GENERAL INFORMATION Paragraph 1 1 1 2 1 3 1 4 1 5 1 6 1 7 1 8 1 9 1...

Page 14: ...1 1 I tJ III 0 1 Ul t l III JQ 1 III S I n t 07 K l I y j J ii 93 00 I ___ a_ _A_ f 1l 4 OO d III 1 I N I j JQ C 1 1 I tJ III 0 1 Ul t l III JQ 1 III S I n t 07 K l I y j J ii 93 00 I ___ a_ _A_ f 1l...

Page 15: ...agraph 5 98 for hot fuel priming system and paragraph 4 56 for winterized cabin heating sys tem 1 3 GENERAL 1 1 GENERAL DESCRIPTION T he DHC 4 Caribou manufactured by The de Havilland Aircraft of Cana...

Page 16: ...O INDICATE THAT AN IDENTICAL ACCESS IS LOCATED IN SIMILAR POSITION ON OPPOSITE SIDE OF AIRCRAFT 1 Pl I 0 1 til 1 p t 1 1 1 0 0 1 JQ 1 I N 1 til til Pl P P P til 0 1 0 p l 1 0 til 0 P til Ui p 1 1 0 N...

Page 17: ...HAT AN IDENTICAL ACCESS IS LOCATED IN SIMILAR POSITION ON OPPOSITE SIDE OF AIRCRAFT 82 Q 81 0 III 1 I 1 l OQ 1 CD I IV l l CD Ul Ul III l 0 l Ul t l CD l 0 l 0 1 0 Ul 0 l Ul Ui r CD CD IV 0 IV 3 n 52...

Page 18: ...r 6 Fuel Cell SUInP Plate and Tank Unit Mid Flap and Mid Aileron Bellcranks Revised 1 December 1965 Part 1 1 2 3 4 5 6 7 B 9 10 11 12 13 14 15 16 17 lB 19 20 21 22 23 24 25 26 27 2B 29 30 31 32 1 6 Ke...

Page 19: ...echanical means are given in Table 1 1 as a guide to the nominal capacity of the crane required 1 7 Part 1 Paragraphs 1 4 1 to 1 5 1 Key to Figure 1 2 Access and Inspection Provisions Cont 62 63 64 65...

Page 20: ...IN 7 ADAPTER 8 PROPELLER SLING 9 ENGINE ATTACHMENTS Figure 1 3 Hoisting Engine and Power Plant 4MC4 Part 1 1 8 i I M 7 0 _ 1 PROPELLER SHAFT 2 ENGINE SLING 3 ENGINE HOIST 4 QUICK RELEASE PIN 5 REAR LI...

Page 21: ...ied to lower end Refer to paragraphs 2 135 3 and 2 135 4 for preparation of rudder for hoisting 1 9 Part 1 Paragraphs 1 5 2 to 1 5 4 TABLE 1 1 APPROXIMATE WEIGHTS OF COMPONENTS ITEM Power Plant Engine...

Page 22: ...RUBBER CUSHION SECURING P CRADLE 4MC5 Figure 1 4 Hoisting Wing and Empennage Units Sheet 10 2 1 10 Part 1 VERTICAL STABILIZER SLIN RUDDER SLING IS L __ELEVATOR SLING 1 RUBBER CUSHION SECURING P CRADL...

Page 23: ...H i i ii iii Figure 1 4 Hoisting Wing and Empennage Units Sheet 2 of 2 FWD Part 1 4Mce 1 11 H i i ii iii Figure 1 4 Hoisting Wing and Empennage Units Sheet 2 of 2 FWD Part 1 4Mce 1 11...

Page 24: ...inches EXTENDED HEIGHT MINIMUM 50 inches 10 feet 8 inches 10 inches 11 inches Revised 1 June 1970 I Part 1 Paragraphs 1 5 5 to 1 8 Note Before the support cradle can be slid under rudder horn the rudd...

Page 25: ...ropeller levers to HIGH PITCH b Mixture levers to IDLE CUT OFF Revised 1 February 1969 Part 1 1 12A of heading must be into the wind whenever pos sible and the following controls must be set to the po...

Page 26: ......

Page 27: ...ure 1 5 Jacking Sheet 1 of 2 Revised 1 February 1969 Part 1 REAR FUSELAGE JACK ADAPTER PAD 1 13 __ _ iI ii dI Figure 1 5 Jacking Sheet 1 of 2 Revised 1 February 1969 Part 1 REAR FUSELAGE JACK ADAPTER...

Page 28: ...e that tie down ropes are at an angle of approximately 45 degrees to ground Revised 1 February 1969 Part 1 Paragraphs 1 8 1 to 1 10 4MC17 VI EW SHOWING METHOD OF USING JACKING BEAM AND ADAPTER 0 MAIN...

Page 29: ...ust locks are properly en gaged otherwise damage to control surfaces and linkages may result 1 14A _ Figure 1 6 Leveling Brackets Revised 1 February 1969 Part 1 b Allow sufficient slack in rope to com...

Page 30: ......

Page 31: ...SELAGE TIE DOWN POINT 6 MAIN WHEEL CHOCKS 7 MAIN GEAR TIE DOWN 8 NOSE GEAR TIE DOWN I 2 4 U II Ii rt Ut Isj OQ 1 1 I 0 0 1 t 1 OQ 1 n 1 II l n 1 NOSE GEAR GROUND LOCK 2 MAIN GEAR GROUND LOCK 3 REAR FU...

Page 32: ...el Lifting Dolly HEIGHT TO RUDDER TIP 31 feet 9 inches 25 feet 4 1 2 inches Revised 1 February 1972 Part 1 Paragraphs 1 11 to 1 12 1 Note If gust locks have been inadvertently left disengaged during h...

Page 33: ...LD 16 ENGINE AIR INTAKE SHIELD 17 CABIN HEATING INLET COVER 18 CABIN HEATING AIR EXHAUST COVER 1 17 4MCIO Figure 1 8 Covers Part 1 i iii iii i WINTERIZATION KIT ITEMS 1 EXHAUST AUGMENTOR TUBE SHIELD 2...

Page 34: ...0 QUICK RELEASE PIN 11 TRUNNION PIN 12 TRUNNION L 3 10 liiii iii 1 7 6 4MC1t Figure 1 9 Towing 1 18 Part 1 1 TOW BAR 2 QUICK RELEASE PIN 3 LIFTING HEAD 4 NOSEWHEEL DOLLY 5 LOCKING LEVER 6 HYDRAULIC AC...

Page 35: ...9 NATO SYMBOL F18 SHELL ESSO TEXACO Aviation Gasoline 100 130 CAPACITY GALLONS u S IMP 414 345 1 19 1 13 EXTERNAL POWER RECEPTACLE A dc external power receptacle is lo cated on the left hand side of t...

Page 36: ...T INDICATING SYSTEM MOISTURE TRAPS 4MCI2 Figure 1 10 Se rvicing Diag ram 1 20 Revised 1 August 1963 Part 1 22 16 12 20 1 GROUNDING JACK 2 FUEL TANK BOOSTER PUMP AND MANIFOLD WATER DRAIN VALVES 3 FUEL...

Page 37: ...plug from free end of hose connected to refuel vent valve figure 5 41 and lead hose out 1 21 _ __ _ Part 1 Paragraphs 1 16 2 to 1 16 3 TABLE 1 4 Cont Capacities Usable Fuel Cont APPROXIMATE WEIGHT POU...

Page 38: ...each tank Alternatively disconnect the ferry fuel de livery line 8 figure 5 46 from fuel crossfeed Part 1 Paragraphs 1 16 4to 1 16 7 of aircraft and into a suitable container to collect any fuel whic...

Page 39: ...il 100 467 Engine Engine RD2472B 0 Oil 100 Oil 100 DTD 585 H 515 Aeroshell fluid 4 Univus J 43 1 23 line 7 at tee connection in left side of wing cen ter section connect suitable hose to line and lead...

Page 40: ...P AIR VALVE PSI 1 030 1 090 1 030 1 090 1 030 1 090 1 030 1 090 1 030 1 090 Revised 1 February 1969 Part 1 Paragraphs 1 18 2 to 1 20 1 When filling bleeding or draining the hyd raulic system take care...

Page 41: ...gen or dry air to 1 030 psi through high pressure HP air valve Revised 1 February 1969 Part 1 1 24A structions on the strut nameplate or in structions contained herein could result in serious injury o...

Page 42: ......

Page 43: ...5 150 150 175 180 205 250 275 400 425 HP AIR VALVE PSI 750 810 750 810 750 810 750 810 750 810 1 25 Always charge high pressure HP air valve first to avoid damaging strut Do not use any bottled gas ot...

Page 44: ...slide replacem mt wheel on axle f Install washer and nut Tighten nut firmly Revised 1 February 1972 Part 1 Paragraphs 1 22 to 1 23 zero operations Increase tire pressures to 40 psi for main wheels and...

Page 45: ...cent by weight solution of boric acid and water and reinstall the jar in the bracket 1 27 _ _ _ _ _ then back off sufficiently to allow wheel to turn freely without side play Lock nut with new cotter...

Page 46: ...d to a minimum in order to avoid da mage to this type of equipment Whenever pos Revised 1 June 1970 Part 1 Paragraphs 1 27 to 1 29 1 holder If no contamination is indicated but pad has dried out remov...

Page 47: ...TABLE OF LUBRICANTS LETTER SYMBOLS SEE SHEET 4 AND FOR SPECIAL SERVICE NOTES SEE SHEET 3 s w 1 II 1 0 1 rn 1 0 i 1 0 l o I N 0 rj JQ 1 1 I t 0 1 II n o ij tJ Il JQ 1 PJ 3 r n ij 1 1 o FREQUENCY SYMBO...

Page 48: ...Part 1 I I 4MC14 Figure 1 11 Lubrication Oiag ram Sheet 2 of 4 1 30 Revised 1 February 1969 Part 1 I I 4MC14 Figure 1 11 Lubrication Oiag ram Sheet 2 of 4 1 30 Revised 1 February 1969...

Page 49: ...isassemble to lubricate Refer to paragraph 2 139 2 for disassembly and 2 139 3 for assembly 0 II 1 1 0 CD J CD 0 fotj CD t T 1 s II 1 0 I IoN fotj IJQ s 1 CD I t s t T 1 l II 0 0 l tJ p IJQ 1 II 3 gi...

Page 50: ...LECTRIC CO J GREASE G300 Figure 1 11 Lubrication Diag ram Sheet 4 of 4 1 32 Revised 1 February 1969 Part 1 Nita 4MC16 TABLE OF LUBRICANTS SYMBOL TITLE CANADIAN SPEC US SPEC BRITISH SPEC AEROSHELL TEXA...

Page 51: ...n Landing Gear Bolt Acorn Rudder Sling Vertical Stabilizer Sling Horizontal Stabilizer Sling 1 33 I sible cleaning should be limited to wiping clean with cloths moistened with a dry cleaning solvent e...

Page 52: ...e Extinguisher System Revised 1 Februa ry 1972 I I _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _c _ _ Part 1 PART NO SD5534 1 SD5537 3 SD5538 1 SD5539 I SD5540 1 SD5545 1 SD5551 1 SD555Z 1 SD5553 1 SD55...

Page 53: ...ontrol Cables 2 55 Control Columns 2 59 Aileron SysteITl 2 64 Ailerons 2 66 Aileron Cables 2 68 2 1 Part 2 Table of Contents PART 2 AIRFRAME Paragraph Page 2 1 2 2 2 3 2 4 2 5 2 6 2 7 2 8 2 9 2 10 2 1...

Page 54: ...2 158 Main Gear 2 161 2 159 Main Gear Shock Strut 2 164 2 160 Main Gear Shock Strut Cylinder 2 164 Part 2 Table of Contents Paragraph Page 2 78 2 79 2 80 2 81 2 82 2 83 Rigging of Aileron System Aile...

Page 55: ...15 Landing Gear Warning Horn 2 211 2 213 2 213 2 213 2 214A 2 215 2 216 2 216 2 217 2 218 2 218 2 3 Paragraph Page 2 161 Main Gear Retraction Actuator 2 167 2 162 Main Gear Shortening Mecha 2 163 2 16...

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Page 57: ...he inside walls and roof are covered by sections of vinyl coated nylon upholstery with fiberglas 2 5 2 1 GENERAL This part covers airfralTle sylTllTletry the body group nose section center fuselage an...

Page 58: ...ING POINT TOP OF SKIN INTERSECTION MEASURING POINT CENTER OF OUTBOARD FLAP ARM HINGE BOLT U I oj tv tv I 0 l JQ i Cl IV I i i I 3Cl til 3 3Cl i t l Jg i I 3 t n l _ _ ___ 0 A I E __ o C MEASURING POIN...

Page 59: ...inged at its forward edge and is held in the closed position by a tapered bolt which fits into 2 6A insulation which are held to the structure by Velc ro nylon tape fastener s hook and pile Sixteen el...

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Page 61: ...ENT FLOOR HATCH JETTISON HANDLE 25 PILOT S RELIEF TUBE Figure 2 2 Body Group Revised I June 1970 2 7 a recess on the aft edge of the hatch well The bolt action is controlled from either oftwo handles...

Page 62: ...D ROTATING SPINDLE 14 HINGE 4MC3Z Figure 2 3 Flight Compartment Floor Hatch 2 8 Revised 1 June 1970 Part 2 Paragraph 2 8 2 and wash surface using a clean cloth soaked with Toluol or naptha gas Dry wit...

Page 63: ...n extend beyond the edge of the frame into holes in the cabin wall The lock is the same type as 2 9 2 6 8 ADD Part 2 Paragraphs 2 8 3 to 2 9 1 DOOR LOCK COVER 2 RUBBER SEAL 3 INNER HANDLE 4 LOCKING PI...

Page 64: ...the center position to pull the tie rod down and withdraw the hinge pins Rotating the quadrant also Part 2 Paragraphs 2 9 1 to 2 10 that used for the flight compartment floor hatch paragraph 2 8 but i...

Page 65: ...INGE PIN 11 SLOT 6 LOCK 12 TUBE 7 QUADRANT 13 PLATE 4MC34 Figure 2 5 Right Hand Passenger Door 2 11 repositions the compression spring which pres ses against the quadrant and prevents it inadvert entl...

Page 66: ...c Discormect door at upper hinge attachments by removing two cotter pins washers and flat head pins Part 2 Paragraphs 2 10 5 to 2 12 1 doorway to gain access to jettison mechanism quadrant b Insure hi...

Page 67: ...CARGO DOOR JETTISON Q 0 W B O oit OCS O 15 13 11 12 Figure 2 6 Draftproof Door AL l 9 j 4MC3 5 2 13 Part 2 1 CABLE PULLEY 2 DRAFTPROOF DOOR CABLE 3 CABLE DRUM 4 STRAP 5 DRAFTPROOF DOOR CABLE 6 GUIDE P...

Page 68: ...ction a bottom skin reinforced by stiffeners a cor rugated end plate and a reinforcing beam between Part 2 Paragraphs 2 12 2 to 2 15 d Remove two track extensions at bottom of doorway frame by removin...

Page 69: ...UNIT 25 LATERAL TORQUE TUBE 26_ RAMP DOOR ACTUATOR 16 Figure 2 7 Ramp Door Part i j II 1 4MC36 2 15 1 DISCONNECT KNOB 2 RH BEVEL GEAR UNIT 3 RAMP DOOR SCREW JACK 4 FORWARD BEVEL GEAR UNIT 5 HOUSING 6...

Page 70: ...carried out with an external source of electrical power plugged into the external power receptacle Part 2 Paragraphs 2 15 1 to 2 16 1 the floor and bottom skin Molded seals of sili cone rubber are ba...

Page 71: ...CTUATOR C C A NO LIMIT SWITCH UNACTUATED RAMP AND CARGO DOORS CLOSED WEIGHT ON NOSE GEAR d III Ii N N J l JQ Ii en N I 00 0 III 3 0 III l a l III Ii JQ o tJ o o Ii C t 1 en l Ii l III CIl l J en 3III...

Page 72: ...ey washer 3 bearing retainer 4 spring washer 5 lock ring 11 bearing housing 10 and spring 9 ReInove Part 2 Paragraphs 2 17 to 2 18 2 TABLE 2 1 TROUBLE SHOOTING RAMP DOOR OPERATING GEAR INDICATION OF T...

Page 73: ...3 OUTER TUBE 24 HALF HOUSING 25 ROLLPIN 26 BEARING RING 27 LAMINATED WASHER 28 LOCK RING 4MC38 2 19 13 16 I 21 I i 22 I C 2 I I I I I I I I I I I I I I 24 25 o 17 18 26 3 19 2J C 20 21 I I 1 _ _ _ _ _...

Page 74: ...ove screws connecting unit to center transverse torque tube and to handcrank horizontal torque tube Part 2 Paragraphs 2 18 3 to 2 19 4 lock ring 6 bearing retainer 7 and bearing 8 from bearing housing...

Page 75: ...misc eilaneous hardware Replacement of parts should be accomplished with the door removed but 2 21 b Remove rivet connecting unit to microswitch shaft c Remove ramp door actuator as detailed in parag...

Page 76: ...NAL JETTISON HANDLE 26 SPRING 39 JETTISON CONTROL ROD 4MC39 Figure 2 10 Cargo Door Sheet 1 of 2 2 22 art 2 CARGO DOORS FORWARD SWITCH PANEL CARGO DOORS REAR SWITCH PANEL 1 CONTROL ROD 14 ALIGNMENT HOL...

Page 77: ...Figure I Sheet 2 of 2 2 10 Cargo Door Parr 2 4MC40 2 23 Figure I Sheet 2 of 2 2 10 Cargo Door Parr 2 4MC40 2 23...

Page 78: ...push rod pulls the door up wards and the latch is withdrawn from its recess Revised 1 December 1965 Part 2 Paragraphs 2 22 3 to 2 23 no special removal and installation procedures for the parts are ne...

Page 79: ...chain guard e Release tension from operating gear cables and chains by slackening turnbuckles 2 25 2 23 1 TROUBLE SHOOTING CARGO DOOR OPERATING GEAR Carry out trouble shooting Part 2 Paragraphs 2 23...

Page 80: ...cally actuate door through full range Dis connect external electrical power Revised 1 December 1965 Part 2 Paragraphs 2 24 2 to 2 24 4 f Remove two bolts nuts and washers securing manual control handl...

Page 81: ...f each windshield which absorb vibrations as the windshield slides on spacers installed at the 2 27 2 24 5 ADJUSTMENT OF CARGO DOOR OPER ATING GEAR a Adjust cargo door operating gear cable turnbuckles...

Page 82: ...be replac ed both wind shields must be removed to install center post gasket Revised 1 August 1963 Part 2 Paragraphs 2 26 1 to 2 26 3A screw positions Note If a windshield is replaced by a windshield...

Page 83: ...TALLING WINDSHIELD Figure 2 11 Windshield Replacement Sheet 1 of 3 Revised 1 August 1963 4MC41 2 29 REMOVE SUFFICIENT SKIRT AND RETAINING STRIP SCREWS TO PERMIT LEFT WINDSHIELD REMOVAL APPROX SIX INCH...

Page 84: ...ASKING TAPE MASKING TAPE Figure 2 11 Windshield Replacement Sheet 2 of 3 2 30 Revised 1 August 1963 Part 2 3 INSTALLATION POSITION TAPE EC 1202 ALL ROUND EDGE OF WINDSHIELD A POSITION TAPE EC 12023 4...

Page 85: ...tion for the windshield wiper arms The rotary windshield wiper switch has four speed settings 2 30A ADHERE REAR GASKET TO FRAME AND FORWARD GASKET TO OUTER RIM OF WINDSHIELD FORWARD GASKETS PUNCH 1 4...

Page 86: ......

Page 87: ...s the speed of the wiper motor Refer to paragraph Z 27 1 for speed settings and current supply 2 31 FAST 3 4 l Z and SLOW and two positions marked PARK and OFF the PARK position being spring loaded to...

Page 88: ...SWITCH ADJUSTMENT TO CONVERTER CAM 4MC43 Figure 2 12 Windshield Wiper System 2 32 _ _ _ _ _ _ _ _ _ Part 2 1 WINDSHIELD WIPER ASSEMBLY 2 CONVERTER 3 WINDSHIELD WIPER SWITCH 4 WINDSHIELD WIPER BLADE ST...

Page 89: ...and g c U Sing an Allen wrench loosen cam screw Rotate cam until m icroswitch clicks to closed 2 33 2 29 1 REMOVAL a Disconnect electrical power disconnect sev en quick release fasteners on center sw...

Page 90: ...rame and retaining strips using Toluol and a piece of plastic or soft metal Revised 1 February 1972 Part 2 Paragraphs 2 31 to 2 33 3 position Hold cam to keep from turning and tighten cam screw d Oper...

Page 91: ...WINDOWS Left and right canopy windows slide on nylon bearings between channel section tracks 2 34A b Where necessary remove sealant from win dow using Toluol and a piece of plastic or lint free rag c...

Page 92: ......

Page 93: ...oval procedure c Fill gaps between butt joints of outer frame with sealing compound Bostik 292 2 35 and may be opened and closed from the inside Hand operated latches lock the windows in the closed po...

Page 94: ...seat A special order shoulder harness and inertia reel can be installed on each Revised 1 June 1970 Part 2 Paragraphs 2 85 3 to 2 39 2 35 3 REPLACEMENT OF SIDE WINDOW SEAL To replace a side panel seal...

Page 95: ...ng extending between fixed brac ket on underside of seatpan and control lever con necting arm 2 36A flight compartment seat Special order safety shields can be supplied as part of the seat struc ture...

Page 96: ......

Page 97: ...UIDE LoL 18 l h 5ii 1 SEAT VERTICAL ADJUSTMENT 14 16 4MC44 Figure 2 13 Flight Compartment Seat 2 37 Part 2 i ii S SEAT ATTACHMENT 1 SEAT ATTACHMENT SCREW 2 SPACER 3 NUT 4 SLIDE 5 SLIDE TRACK 6 SHOULDE...

Page 98: ...sides of seat 2 39 15 INSTALLATION OF SEAT BELT Re verse removal procedure Revised 1 February 1969 Part 2 Paragraphs 2 39 6 to 2 39 15 c Remove bolt attaching end of control lever to seat pan d Remov...

Page 99: ...nly M dification S O O 4067 the floor cargo tie down fittings consist of three rows of 5000 lb 2 38A 2 39A AUXILIARY SEAT FOR THIRD CREW MEMBER To special order only a folding auxiliary seat can be pr...

Page 100: ...CRO STRIP DOOR FRAME 4MC 412 Figure 2 13A Auxiliary Seat for Third Crew Member Revised 15 July 1969 Part 2 I SEAT IN STOWED POSITION 2 38B STOP STOWAGE PANEL ooii ir f VELCRO STRIP DOOR FRAME 4MC 412...

Page 101: ...allation b When Mod 4 1129 or Mod S O O 4067 is em bodied rem ove 5000 pound tie down fittings Z 39 fittings with 18 per row at ZO OO inch pitch this configuration also incorporates the eight 5000 lb...

Page 102: ...t In its stowed position the ladder may be used for exit through the flight Revised 1 February 1972 Part 2 Paragraphs 2 45 2 2 51 c When plywood overlay panels are installed remove skid strips or chan...

Page 103: ...ilot s rear window The co pilot s case is at tached directly to the fuselage structure by two 2 40A compartment roof hatch or may be lowered and used for entrance or exit through the flight corn partm...

Page 104: ......

Page 105: ...t comprises a main firewall assembly a top struc ture inboard and outboard curtain walls and a 2 41 clips at the top and two screws Inating with anchor nuts at the bottoIn 2 57 AIR DELIVERY PROVISIONS...

Page 106: ...X 24 RETRIEVER WINCH INSTALLED 25 RETRIEVER WINCH STOWED 26 BLACKOUT CURTAIN STOWAGE BAG d III Ii N N I N l Q Ii CD N II CD Ii t l CD CD Ii tl Ii o l en o s en 3 1 TROOP JUMP PENDULUM RELEASE CONTROL...

Page 107: ...9 MAIN LANDING GEAR FITTINGS 10 MAIN FIREWALL 11 NACELLE 12 FRONT SPAR ATTACHMENT ANGLE l I PJ 1 N N I j VJ I Ij JQ I j 1 N Ul l JQ 1 a 1 I j Jl 1 n o s n 10 1 8 1 WING JOINT FITTING 2 REAR SPAR ATTA...

Page 108: ...oth wings using 5 16 inch diameter rigging pins e Jack wing not being removed at wing jacking point Part 2 Paragraphs 2 61 to 2 63 1 nacelle rear structure Six hinge fittings for the attachment of the...

Page 109: ...BOLT ITEMIZED 1 2 AND 11 BUT ONLY IF PLAIN SHANK IS SHOWING Figure 2 16 Wing Joint Part 2 4MC47 2 45 I 171 FRONT SPAR ATTACHMENT ANGLE 1 U REAR SPAR ATTACHMENT ANGLE BOLT NUT AND WASHER IDENTIFICATION...

Page 110: ...ter section flap shroud and at wing joint rib Tie one end of a length of cord approximately 20 feet Part 2 1 OUTBOARD HINGED LEADING EDGE 2 INBOARD HINGED LEADING EDGE 3 STALL FENCE 4 OUTER WING FIXED...

Page 111: ...celle p Connect rubberized fabric strips between root and inboard flaps with attachment screws 2 47 long to each inboard cable and other end to its corresponding outboard cable to facilitate routing o...

Page 112: ...end to front spar angle h Remove six bolts securing leading edge out board rib to front spar angle Part 2 Paragraphs 2 64 to 2 64 1 q Check rigging of wing flap system Refer to paragraph 2 96 Rig ail...

Page 113: ...o the front edge of the tip The tip is secured to the outboard rib of the outer wing by screws 2 49 Note A second man IIlUSt support leading edge from this point until removal is comple ted i Working...

Page 114: ...FRONT ATTACHMENT FITTINGS RUDDER SHROUD RUDDER HINGE FITTING 4MC49 Figure 2 18 Vertical Stabilizer Part 2 Paragraphs 2 65 1 to 2 67 1 2 65 1 REMOVAL E3 Extreme care must be taken to avoid dam aging s...

Page 115: ...ps system to the horizontal stabilizer causing stabilizer incidence to vary with flap movement 2 51 Part 2 Paragraphs 2 67 2 to 2 69 1 f Attach vertical stabilizer sling Refer to para 2 68 1 REMOVAL g...

Page 116: ...30 1 22 30 p 15 1 15 1 Bottom surfaces of aileron and geared tab in alignment 3 1 24 1 4 1 40 30 1 Part 2 Paragraphs 2 70 to 2 71 2 70 GENERAL RIGGING INSTRUCTIONS The rigging of each control system...

Page 117: ...T Revised 1 February 1972 40 1 22 1 40 1 22 1 31 1 2 30 1 3P 1 21 1 10 p 25 0 Minimum 5 1 20 1 2 53 Part 2 TABLE 2 3 Cont SURFACE DISPLACEMENT ANGLE TOLERANCE AILERON RUDDER INTERCONNECT TAB Measured...

Page 118: ...3 32 in 7x7 3 32 in 7x19 TENSION iLB 90 70 70 70 110 35 35 35 TOLERANCE LB 15 15 15 15 17 10 10 10 Part 2 Paragraph 2 72 TABLE 2 3 Cont SURFACE DISPLACEMENT RUDDER SPRING TAB Rudder Locked Neutral LE...

Page 119: ...es are clipped level with the cable to prevent fouling No broken wire is permissible in 1 x 19 2 55 Part 2 Paragraphs 2 72 1 to 73 TABLE 2 4 Cont CABLE CIRCUIT RUDDER Front Fuselage Rear Fuselage Spri...

Page 120: ...z w 60 I 50 40 30 20 115 110 100 90 80 70 en C Z l 60 0 Il Z 50 0 Vi z w 40 I 30 20 10 0 115 4MC 50 Part 2 2 56 10 0 10 20 30 40 50 TEMPERATURE 0 F AILERON FUSELAGE CABLE CIRCUIT 30 40 TEMPERATURE 0 F...

Page 121: ...n z w I TEMPERATURE of RUDDER FRONT CABLES 4MC 1 Figure 2 19 Cable Tension Charts Sheet 2 of 3 2 57 Part 2 160 150 140 130 120 110 100 90 80 70 60 L 40 o 10 20 30 40 SO 60 70 80 90 100 110 115 TEMPERA...

Page 122: ...TOP CABLE AND CABLES AFT OF AILERON GUST LOCK Figure 2 19 Cable Tension Charts Sheet 3 of 3 W 4MC 2 Part 2 ELEVATOR TRIM RUDDER TRIM AILERON RUDDER INTERCONNECT ELEVATOR GUST LOCK NOSEWHEEL STEERING C...

Page 123: ...ide cable in groove in control wheel below handgrip h Draw cable into position and ease switch 2 59 cables A simple method of detecting broken wires is by running a lint free rag along the cable The r...

Page 124: ...52 BOLTS 53 CENTER SPROCKET 54 CENTER MOUNTING 55 COVER 56 WASHER 57 NUT 58 COTTER PIN 1 J III i N N I a o I rj JQ i ro N I N o o i o o 3 s ngo 49 48 47 1 COTTER PIN 2 NUT 13 14 12 11 8 3 WASHER LOCK...

Page 125: ...at connec tor and remove clip 33 FORWARD _ J 6 30 4MCts4 Figure 2 21 Control Colulnn Geometry 2 61 housing into position in control wheel Lock hous ing by tightening two set screws through holes in h...

Page 126: ...to approxi mately their installed position Hold spacer 21 between rear sprocket and bearing 22 and Part 2 Paragraph 2 74 7 c Remove plug 29 cotter pin I nut 2 washer 3 and wheel hinge bolt 28 d Withd...

Page 127: ...the columns about bearings in four hinge fittings suspended from the flight com partment floor 2 63 I I spacer 7 between front sprocket and bearing 5 Recheck that chains are correctlydisposed around s...

Page 128: ...to correct ten sion Refer to paragraph 2 72 Reduce chain tension at turn buckles Trace and rectify Part 2 Paragraphs 2 74 10 to 2 75 1 2 74 10 MINOR REPAIR OF CONTROL COLUMN TORQUE TUBE Minor repairs...

Page 129: ...ILERON BELLCRANK OUTBOARD AILERON BELLCRANK OUTBOARD AILERON 4MC SS Figure 2 22 Aileron System 2 65 o 13 14 ___ 15 16 11 18 19 20 21 22 23 24 25 26 27 28 29 1 FAIRLEAD 2 AILERON WING OUTBOARD REAR CAB...

Page 130: ...tboltto 60 85 pound inches and nut for inboard and out board attachment bolts to 30 40 pound inches Part 2 Paragraphs 2 76 to 2 76 2 TABLE 2 5 Cont INDICATION OF TROUBLE PROBABLE CAUSE CORRECTIVE ACTI...

Page 131: ...ON 30 AILERON TRIM TAB RIGHT WING ONLY 14 01 13 11 12 4Mcse Figure 2 23 Wing Flaps and Ailerons 2 67 30 29 28 27 I OUTBOARD AILERON HINGE ARM 2 OUTBOARD FORE FLAP HINGE ARM 3 OUTBOARD FLAP ATTACHMENT...

Page 132: ...use lage and the cord is positioned ready for pulling through a serviceable cable on installation I Part 2 Paragraphs 2 76 3 to 2 77 1 d Check mid aileron movements on completion of installation Refer...

Page 133: ...is correc tly seated on pulley install pulley guard flathead pin and lock with new cotter pin 2 69 2 77 2 INST ALLAT ION OF AILERON CAB LES IN FUSELAGE a To install forward cable untie cord used for...

Page 134: ...and outboard aileron idler bellcrank h Install wing access panels and install up holstery in cabin Part 2 Paragraphs 2 77 5 to 2 77 6 e Remove cord from cables install turnbuckle and adjust to obtain...

Page 135: ...y removing one fair1ead attaching screw loosening other screw and rotating half fairleads clear 2 71 I i Close inboard and outboard hinged leading edges Refer to paragraphs 2 64 4 and 2 64 7 2 77 7 RE...

Page 136: ...of the aileron geared tab adjustable actuating beam to accomplish step j Do not alter beam setting Part 2 Paragraphs 2 77 10 to 2 78 f Working through wing access opening 54 remove flat head pin and...

Page 137: ...UADRANT STOP 10 AILERON QUADRANT 11 TURNBUCKLES 12 AILERON LEVER t J 13 AILERON INBOARD RIB III i N N J VJ 1 JQ s I j 1 N N 1 I j 0 D JQ JQ D JQ t l III JQ I j III S 9 ESTABLISH GAGE ZERO REFERENCE BY...

Page 138: ...agraphs 2 83 I and 2 83 2 Replace indicator Refer to paragraphs 2 84 I and 2 84 2 Trace and rectify Part 2 Paragraphs 2 79 to 2 79 1 k Remove all rigging pins fitted in steps b through d 1 Position ri...

Page 139: ...link 14 to actuator arm 2 2 82 AILERON TRIM TAB SWITCH The aileron trim tab switch on each con 2 75 Part 2 Paragraphs 2 80 to 2 82 TABLE 2 6 Cont INDICATION OF TROUBLE PROBABLE CAUSE CORRECTIVE ACTION...

Page 140: ...rews 3 and washers f Slide transmitter outboard to clear clamp and mounting bracket and lower clear Part 2 Paragraphs 2 82 1 to 2 83 1 2 3 4 5 6 1 8 idlE i i 12 11 4 PINCH NUT 5 AILERON TRIM TAB POSIT...

Page 141: ...y coat tab hinge with sealing and insulating compound Refer to Lubrication Diagram figure l ll 2 77 2 83 2 INSTALLATION To install aileron trim tab position transmitter reverse removal pro cedure Inst...

Page 142: ...6 5 4MCS9 Figure 2 26 Aileron Tabs and Aileron Rudder Interconnect Tab System Rigging Diagram 2 78 Part 2 AILERON TRIM TAB RIGHT WING ONLY 1 AILERON TRIM TAB 2 PUSH PULL ROD 3 PINCH NUT 4 AILERON GEA...

Page 143: ...s of frayed cable s if not in excess of number given in paragraph 2 73 Otherwise renew cables s 2 79 2 87 RIGGING OF AILERON GEARED TABS Note The following procedure must be carried out only when the...

Page 144: ...ough access opening 90 open fairlead on joint rib in manner given in step f Revised 1 February 1972 Part 2 Paragraphs 2 89 to 2 90 3 2 89 AtLERON RUDDER INTERCONNECT TAB The aileron rudder interconnec...

Page 145: ...position A follow up provision in the actuator prevents further actuator movement when the s el 2 81 h Remove pulley guard flat head pins from both pulley brackets immediately outboard of wing joint i...

Page 146: ...34 MID FLAP BELLCRANK 1 111 1 1 35 OUTBOARD FLAP BELLCRANK 4MC60 Figure 2 27 Wing Flap System 2 82 Part 2 1 OUTBOARD FORE FLAP 2 OUTBOARD FLAP PUSH PULL ROD 3 MID FLAP PUSH PULL ROD 4 MID FORE FLAP 5...

Page 147: ...flap selector lever in overhead console in flight cOInpartInent fully down handpuInp selector 2 83 ected flap position is reached An internal lock provision in the actuator locks the flaps in their u...

Page 148: ...fitting in fuselage skin and two nuts washers and boIts securing remaining Revised 1 February 1972 Part 2 Paragraphs 2 93 2 to 2 94 1 qn hydraulic emergency selector panel to NOR MAL SYSTEM and by op...

Page 149: ...rigging gage SDSS79 1 See figure 2 28 With flaps up adjust up stop until it just makes contact 2 85 two hinge arms to hinge fittings in nacelle rear structure f Lower root fore flap clear 2 94 2 INSTA...

Page 150: ...bearings must be retained as described in paragraph 2 186 2A for Mod 4 1299 Revised 1 February 1969 Pa t 2 Paragraphs 2 94 7 to 2 95 e Check mid aileron movements Refer to para graph 2 78 steps h and...

Page 151: ...r applied Flaps must not droop u Lower flaps until root fore flaps are 15 degrees 1 degree down 2 87 2 96 RIGGING OF WING FLAP SYSTEM a Disconnect horizontal stabilizer system front torque tube by rem...

Page 152: ...BOARD FACE OF INBOARD HINGE ARM o 31 4MC61 Figure 2 28 Wing Flaps Rigging Diagram Sheet 1 of 2 2 88 Part 2 10 9 FRONT SPAR r 51N 7 i l fi 5 I JF I ESTABLISH GAGE ZERO REFERENCE BY ATTACHING GAGE TO OU...

Page 153: ...CTION I____ REAR SPAR 21 19 Figure 2 28 Wing Flaps Rigging DiagraITI Sheet 2 of 2 Part 2 4MC62 2 89 1 OUTBOARD FACE OF MID FLAP CENTER ATTACHMENT ARM 2 OUTBOARD FACE OF FORE FLAP HINGE ARMS MID FORE F...

Page 154: ...Flap Actuator and Horizontal Stabilizer Screw Jack Installation 4MC63 2 90 Revised 1 February 1972 Part 2 Paragraph 2 97 v Check that selector pin assembly 1 2 of wing flap selector lever is engaged...

Page 155: ...d 18 g Select actuator lever 13 to pOSition m arked FLAPS UP SETTING POSITION Insure handpum p 2 91 reached A elief valve m ounted below the actua tor has its inlet connected to the piston rod side of...

Page 156: ...H ACTUATOR RETRACTION STATIC FLUID Figure 2 30 Wing Flap Actuator Schematic 2 92 RETURN FLUID 4MC64 Part 2 1 ACTUATOR FULLY RETRACTED AND LOCKED SELECTOR VALVE ROTARY SPOOL SPRING LOADED SPRING EXTEND...

Page 157: ...Take tension out of rudder trim cables by cut ting locking wire removing pulley guard bolt from 2 93 selector on hydraulic emergency selector panel is at NORMAL SYSTEM and operate handpump h Remove tr...

Page 158: ...ry in cabin roof 2 103 WING FLAP POSITION INDICATOR SYS TEM Movement of the wing flap actuator bell Part 2 Paragraphs 2 102 2 to 2 103 rudder trim pulley bracket at station 415 00 and pressing caoles...

Page 159: ...Y 27 DUST EXCLUDER 28 DIAL 29 BASE PLATE 4MC6S Figure 2 31 Wing Flap Position Indicator System 2 95 crank figure 2 31 is transmitted through cables and a reduction unit to two wing flap position in di...

Page 160: ...ng of wing flap position indicator system Refer to paragraph 2 106 g Close nose section upper hatch Part 2 Paragraphs 2 104 1 to 2 104 4 nected to the indicator drive cable leading from the reduction...

Page 161: ...removing cotter pin washer and flat head pin Withdraw front portion of cable 6 from forward end 2 97 I 2 105 REDUCTION UNIT The reduction unit of the wing flap posi tion indicator system reduces the a...

Page 162: ...ach ment The actuator converts the rotary motion of the torque tubes into linear motion to raise or Part 2 Paragraphs 2 105 4 to 2 107 2 105 4 INS fALLATION OF CABLE FROM WING F LAP ACTUATOR BELLCRANK...

Page 163: ...MENT 31 ELEVATOR SPRING TAB MECHANISM 23 Figure 2 32 Empennage 5 6 9 10 11 12 Part 2 2 3 4MC66 2 99 1 RUDDER HORN TIP 2 RUDDER 3 RUDDER HINGF 4 RUDDER TRIM TAB 5 RUDDER TRIM TAB ACTUATOR 6 RUDDER TRIM...

Page 164: ...NNION BELLCRANK 23 HORIZONTAL STABILIZER SCREW JACK 24 WING FLAP ACTUATOR BELLCRANK I 1 11 d II I N N o o Ij JQ I ro N I W W r o I o aII l II cJ ro I l OJ ro 8 3 n 1 UNIVERSAL JOINT 2 UNIVERSAL JOINT...

Page 165: ...aph 1 5 6 Take weight of stabilizer on a crane b Transport stabilizer complete with elevators 2 101 lower the rear of the horizontal stabilizer and vary its incidence Part 2 Paragraphs 2 107 1 to 2 10...

Page 166: ...and outboard ends of leading edge to stabilizer ribs to 60 85 pound inches Revised 1 February 1972 Part 2 Paragraphs 2 109 to 2 109 2 to a positior approximately six inches above its installed positi...

Page 167: ...izontal stabilizer system on comple tion of installation of actuator Refer to paragraph 2 114 2 103 I 2 110 HORIZONTAL STABILIZER SCREW JACK The horizontal stabilizer screw jack is pivot mounted at on...

Page 168: ...tly installed and install new cotter pins in torque tube and universal joint shaft at tachment bolts n P c rt 2 Parag_raphs 2 112 to 2 113 3 2 112 RIGHT ANGLED GEARBOX The right angled gearbox figure...

Page 169: ...agraph 2 118 for the operation of the elevator spring tab mechanism A cable operated elevator 2 105 2 114 RIGGING OF HORIZONTAL STABILIZER SYSTEM Not The following procedure must be carried out only w...

Page 170: ...UP 2 D 10 LESS THAH REFEREHCE AHGLE W WIHG FLAPS DOWN 2 15 MORE THAN REFEREHCE AHGLE 6 4 1j III i N N o CJ JQ i 1 N I lIJ r 0 i t I 0 e CIl t I 1 1 0 JQ JQ l l JQ tJ III JQ 1 III 3 n g 1 2 3 4 5 6 7 H...

Page 171: ...operations f Working through access opening 5 and in board access opening 87 remove two nuts 2 107 trim tab system trims the elevators and is dis cussed in detail in paragraph 2 122 Part 2 Paragraphs...

Page 172: ...ATOR TRIM NEUTRAL CONFIGURATION SHOWN BOTTOM CABLE 13 ELEVATOR FRAME 12 FRAME 8 FRAME 5 FRAME 2 1 N N o 0 0 rj JQ 1 1 N I VJ Ul M 1 0 til til 1 8 28 28 10 11 2 SEE FIGURE 3 1 2 39 4 5 0 f ____ I 12 6...

Page 173: ...tall upholstery in cabin roof install fairing and map case On left side of flight compart ment 2 109 I I four washers and two bolts attaching torque tube to elevator inboard rib g Remove nut two washe...

Page 174: ...layshaft secondary torsion bars tab operating levers and adjustable actuat Revised 1 February 1972 Part 2 Paragraphs 2 117 3 to 2 118 1 2 117 3 REMOVAL OF ELEVATOR REAR CAB LES To remove either of el...

Page 175: ...TO BELLCRANK ELEVATOR LEVER TAB MECHANISM LEVER PRIMARY TORSION BAR LAYSHAFT I v ii I I 1 1 III 1 N Tj Oti s 1 CD N I J t I CD III 0 1 til d 1 i l OQ 1 3 III 0 til Ul CD El N I I CONTROL COLUMN NEUTR...

Page 176: ...tube and spring tab mechanism revers e removal procedure Note following points during installation Pat t 2 Paragraphs 2 119 to 2 120 4 ing rods to deflect the spring tabs and provide aerodynamic assi...

Page 177: ...Using rigging gage SD5564 1 in manner shown the circuit Movement of each trim tab actuator is 2 113 a Bonding leads at elevator inboard hinges must be serviceable and correctly connected In stall eac...

Page 178: ...TURNBUCKLES 12 ELEVATOR QUADRANT 13 ADJUSTABLE CONN ECTING ROD 14 CONTROL COLUMN STOPS 1 J Pl 1 r N N i 0 CI C l CI p t rj CI 0 1 s III 1 0 J N t rj o Q s 1 CI N I v J M CI I r 0 1 0 I Q I Q 9 I I Q 1...

Page 179: ...ndle in one direction causes the slide screwto extend and in the other direction to retract A 2 115 transmitted by an adjustable connecting rod to its corresponding elevator trim tab 2 122 1 Paragraph...

Page 180: ...ES ON LH ACTUATOR DRUM TRIM TAB UP CONFIGURATION SHOWN Figure 2 38 Elevator Trim Tab Actuator 4MC72 Pa t 2 Paragraphs 2 124 1 to 2 124 2 fork end threaded into and riveted to the slide screw is Lolted...

Page 181: ...trim tab handwheel assembly clear _ 2 125 2 DISASSEMBLY a Remove cover See item 10 figure 2 39 2 117 cable drum spindle 1 and remove slide screw complete with stop cover 4 b Remove bearing 7 c Remove...

Page 182: ...IM CABLES 17 CABLE DRUM 18 SHAFT 19 BOLT 20 BEARING 21 KEY 22 BEARING RETAINER LOCKING RING U I 1 N N 00 Tj JQ I j 1 N I v D t 1 CD 0 I j I j 8 III 0 r III CD CD til til CD 80 22 21 20 l 0 1 PEDESTAL...

Page 183: ...ulkhead g Working through access opening 45 remove cable guard nuts washers screws and spacers 2 119 b Remove nut 8 and washer and tap out bolt 19 C Withdraw trim tab handwheel 9 and remove key 7 d Re...

Page 184: ...e fitting from cable drum and unwind cable from drum k Withdraw cable clear Revised 1 February 1972 Part 2 Paragraphs 2 126 2 to 2 127 1 from elevator trim cable drum bracket and re move bridge piece...

Page 185: ...cable end is at the front b Draw cable into pOSition from front end Con nect rear turnbuckle 2 121 2 127 2 INSTALLATION OF ELEVATOR TRIM CABLES IN FLIGHT COMPARTMENT a Thread cable fitting end of cab...

Page 186: ...rough k Insure cables are correctly routed around pulleys Install new cotter pins in flat head pins Part 2 Paragraphs 2 127 5 to 2 127 6 c Install pulley guard flat head pins and fair leads by reversi...

Page 187: ...leys g At side of horizontal stabilizer with un attached cable end wind cable around elevator 2 123 f Install turnbuckle and adjust to take slack out of cables g Remove fiber clamps from cables at ele...

Page 188: ...to rudder 4 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ Part 2 Paragraphs 2 128 to 2 129 trim tab actuator drum and engage cable fitting with drur Cables mu...

Page 189: ...ke rod attachment bracket 11 clear e Withdraw pedal 14 complete with arm 10 and brake lever 18 2 125 I movement The rudder trim tab system is dis cussed in detail in paragraph 2 141 Part 2 Paragraphs...

Page 190: ...S RUDDER PEDALS 25 RUDDER PEDALS INTERCONNECTING ROD AND BELLCRANKS Figure 2 40 Rudder System 4MC74 Part Z 1 CO PILOT S RUDDER PEDALS 2 RUDDER TRIM TAB HANDWHEEL ASSEMBLY 3 RUDDER TRIM CHAIN RUBBING S...

Page 191: ...KEY 18 BRAKE LEVER 19 BOLT 21 BOLT 21 YOKE ASSEMBLY 4MC7 Figure 2 41 Rudder Pedal Assemblies 2 127 2 130 2 DISASSEMBLY OF RUDDER PEDALS a Remove nut washer and bolt 19 figure 2 41 securing brake leve...

Page 192: ...RANK HUB ASSEMBL Y Figure 2 42 Rudder Pedals Interconnecting Rod and Bellcranks 4MC76 __ _ _ _ _ _ _ Part 2 Paragraphs 2 131 2 to 2 132 1 b Dis connect heater ducts and relTlove pilot s foot panel c D...

Page 193: ...attachment bolts b Wirelock hub bolt to channel c Back off stops and adjust stops so that they 2 129 g Remove trunnion nut retaining plates 7 by removing attaching nuts washers and bolts and remove tr...

Page 194: ...bulkhead to immediately aft of wing center section rear spar Lower upholstery to right of aircraft Part 2 Paragraphs 2 135 to 2 136 1 jus t contact N hen rudder pedals are fully deflected with suffic...

Page 195: ...le at turnbuckle aft of wing center section rear spar Turnbuckle must remain with front cable 2 131 centerline immediately aft of wing center section rear spar d Slacken appropriate aileron rudder int...

Page 196: ...olt g With spring tab still supported remove hinge pin which attaches top end of spring tab and bot Part 2 Paragraphs 2 136 4 to 2 138 1 d Tie ontO end of a length of cord approximately 39 feet long t...

Page 197: ...ABLE ASSEMBLY RETAINING NUT 23 RETAINER 24 GUIDE 25 COIL SPRING 26 GUIDE 27 CABLE ASSEMBLY tl P 1 N N I W W l JQ 1 CD N I I IJ 0 0 0 C 1 1 s 00 1 J OJ C S 3 n RUDDER PEDALS NEUTRAL RUDDER NEUTRAL SPRI...

Page 198: ...ctly routed c Rig rudder and spring tabsystemoncomple tion of installation Refer to paragraph 2 140 Pz rt 2 Paragraphs 2 138 2 to 2 139 4 tom end of rudder trim tab by withdrawing from bottom er d h C...

Page 199: ...to para graph 2 146 step d Slacken cables to correct tension Refer to paragraph 2 146 step d 2 135 d Check aileron rudder interconnect tab sys tem rigging on completion of rigging of rudder control s...

Page 200: ...GAGE TO ANY RIB GEARED MOVEMENT _ _ 20 0 ___ 7 4 1 _ tl 20 8 RUDDER AND SPRING TAl SYSTEM I 1j rt N N V J 1 JQ I I N I tI tI p p I I 00 JQ l 00 0 III 00 I III 3 3 n 1 RUDDER TRIM TAB HANDWHEEL 2 TURNB...

Page 201: ...of a length of cord approximately six feet long to each bottom cable end and other end to its 2 137 I Part 2 Paragraphs 2 142 to 2 143 1 TABLE 2 13 Cont INDICATION OF TROUBLE PROBABLE CAUSE CORRECTIV...

Page 202: ...rudder trim tab handwheel in overhead console in flight compartment is set in its neutral position Part 2 Paragraphs 2 143 2 to 2 143 5 FORWARD CABLE 2 3 4 WRAPS ON DRUM ACTUATOR NEUTRAL 10 AFT SHORT...

Page 203: ...R 7 CHAIN GUARD 14 NUT 21 MOUNTING BOLTS 4MC80 Figure 2 46 Rudder Trim Tab Handwheel Assembly 2 139 f h Adjust turnbuckles equally to obtain correct cable tension paragraph 2 72 while maintaining hand...

Page 204: ...ssembly by removing attaching nuts and washers i Disconnect chain from Iiandwheel assembly sprocket Part 2 Paragraphs 2 144 2 to 2 145 1 i Disconnect right hand pitch control rod at its forward end an...

Page 205: ...l from rudder trim front cable and tie cord to appropriate cable end of cable being installed 2 141 j Draw chain and cables through from front k Untie cords from cables and tie cords to handwheel asse...

Page 206: ...fety measure against inadvertently taking offwithgust locks engaged The aileron elevator and rudder Part 2 Paragraphs 2 146 to 2 147 Note For the right hand cable the right hand threaded end is to the...

Page 207: ...N GUARD 41 TENSION SPRING 18 HUB PIN 19 BOLT 20 PIVOT BOLT 21 ELEVATOR TORQUE TUBE 22 LOCK ARM 28 l N lIJ 1 JQ i CD tv I J Cl Ol t o n cr Ol CD S 1 GUST LOCK HANDLE ASSEMBLY 23 SPRING LOADED PLUNGER 2...

Page 208: ...nd aft to decrease gust lock engaged rpm available f Set throttle levers to position established in Part 2 Paragraphs 2 147 1 to 2 148 1 gust lock mechanisms are discussed in detail in subsequent para...

Page 209: ...NGER END FITTING 20 NUT 21 ELECTRICAL CABLE 13 14 4MCB2 Figure 2 4H Gust Lock Handle Assembly 2 145 step b and pull gust lock handle to locked posi tion Handle must make light contact with throttle le...

Page 210: ...r to paragraph 2 72 n Check gust lock system rigging Refer to paragraph 2 153 0 Wirelock turnbuckle Part 2 Paragraph 2 148 3 in cabin roof aft of flight compartment rear bulk head g Remove guard pin f...

Page 211: ...er sprocket 29 from its mounting suf ficiently to permit disengagement of chain from sprocket 2 147 p Install overhead console panels install up holstery in cabin Push in undercarriage circuit breaker...

Page 212: ...ccess opening 1 Working inside rear fuselage remove sproc ket hub bolt 40 cotter pin nut and washer Part 2 Paragraphs 2 150 2 to 2 151 1 j Disengage chain from sprocket and tie chain to mountinJ appro...

Page 213: ...re aft of handle assembly j Remove chain guard pin from sprocket for ward of gust lock handle 2 149 Slide sprockets 38 forward disengage chains and remove sprockets m Withdraw push rod 35 Do not alter...

Page 214: ...nds to aileron gust lock lever 13 figure 2 47 and secure with bolt 12 washer nut and new cotter pin Part 2 Paragraphs 2 152 2 to 2 152 4 k Draw gust lock chain and top cable through from front end Unt...

Page 215: ...T LOCK CHAIN AND CABLE ASSEMBLIES a Insure gust loi k handle is in unlocked for ward position 2 151 b Pass front portion of cable through open fair lead in cabin roof forward of wing center section fr...

Page 216: ...position of elevator gust lock mechanism See figure 2 49 for overtravel configuration ot mechanism Part 2 Paragraphs 2 152 8 to 2 153 b Remove access panels See items 5 and 84 figure 1 2 c Insure fla...

Page 217: ...LOCKED 0 10 0 20 INCH UNLOCKED 0 90 1 10 INCHES 4t 1C83 Figure 2 49 Gust Lock Rigging Diagram 2 153 Part 2 1 GUST LOCK HANDLE 2 FRONT FUSELAGE TOP CABLE 3 FRONT FUSELAGE BOTTOM CABLE 4 TURNBUCKLE 5 AI...

Page 218: ...1 2 through 2 161 5 Remove clean and rein stall filters Refer to paragraphs 2 161 2 through 2 161 5 Part 2 Paragraphs 2 154 to 2 154 1 f Select gust lock handle to its forward un locked position g Che...

Page 219: ...2 158 4 Adjust or replace applicable microswitch Refer to para graphs 2 208 1 through 2 208 3 2 155 INDICATION OF TROUBLE Landing gear will not retract Green down lock lights will not go out when gear...

Page 220: ...consists of a Replacement of faulty seals causing external leakage b Replacement of faulty solenoid Part 2 Paragraphs 2 155 to 2 156 2 TABLE 2 15 Cont INDICATION OF TROUBLE PROBABLE CAUSE CORRECTIVE A...

Page 221: ...cal connector according to figure 2 51 and cover joints with an electrical insulating varnish 2 157 9 LANDING 8 GEAR DOWN LINE CONNECTION 1 2 2 7 3 4 5 SOLENOID SOLENOID 13 12 11 Part 2 Paragraphs 2 1...

Page 222: ...22 O RING 23 WASHER 24 O RING 25 VALVE SPINDLE 26 VALVE SPRING r _ 16 rw f 18 SOLENOID A 1 II 1 1 N N I J1 00 l JQ 1 1 t N I J1 t II l l 0 c 1 t II 1 1 Ul t t l o 1 1 II t J SOLENOID B SOLENOID A ELEC...

Page 223: ...R n Reduce pressure to 4 350 psi and with sole noid A still energized energize solenoid B to 2 159 e After varnish is dry rotate electrical con nector through two revolutions to take up slack wire an...

Page 224: ...procedure Make sure that lever engages properly with master spline on shaft Revised 1 February 1969 Part 2 Paragraphs 2 lS6 9 to 2 lS7 4 operate its pilot valve Evidence of operation will be a slight...

Page 225: ...ors completely enclose the unit 2 158 1 REMOVAL To remove a main gear unit proceed as follows 2 161 13 I J I o I I I I I 12 il 6 11 l I I It 8 10 9 Part 2 Paragraphs 2 158 to 2 158 1 1 COVER 2 QUICK D...

Page 226: ...in gear door actuator for either left or right doors Refer to paragraph 2 186 7 Revised I June 1970 Part Z Paragraphs Z 158 Z a Insure all aircraft electrical power is off b Jack aircraft clear of gro...

Page 227: ...RAULIC DOWN LINE CONNECTION Figure 2 53 Main Gear Revised 1 February 1969 Part 2 16 6 15 4MCB7 2 163 1 MAIN GEAR EMERGENCY RELEASE LEVER I 2 RETRACTION ACTUATOR 3 HYDRAULIC UP LINE 28 So 1 4 HYDRAULIC...

Page 228: ...d with shock strut JH5640 9 the restrictors and rebound plate have been reo Revised 1 February 1969 Part 2 Paragraphs 2 158 3 to 2 160 TABLE 2 16 MAIN GEAR ATTACHMENT TORQUE VALUES LOCATION Drag strut...

Page 229: ...strut cylinder in position shown in figure 2 S3B and using a soft lead pencil mark outline I Z 164A moved and a fixed sleeve and floating plate are added two floating pistons a fixed tube and a I floa...

Page 230: ...GEA LIMIT SWITCH WEIGHT SWITCH Figure 2 53A M ain Gear Electric W iring 2 164B Revised 1 J une 1970 Part 2 1 WINGC 2 DOWNL NECTOR 3 MAIN GEA LIMIT SWITCH WEIGHT SWITCH Figure 2 53A M ain Gear Electric...

Page 231: ...even coat of adhesive resin to bonding area of cylinder and to contact surfaces of indicator 2 164C INNER CYLINDER llM IS08 MAIN GEAR SHOCK STRUT I EXCESSIVE STROKE INDICATOR BRAKE SPOOL FLANGE Figure...

Page 232: ......

Page 233: ...E BACKLASH 1 50 Figure 2 54 Rigging Main Gear Revised 1 February 1972 Part 2 DATUM LINES 4MC88 2 165 0 010 __ INCH t THESE FACES MUST BE PARALLEL WITHIN 0 020 INCH WHEN IN CONTACT I UP LOCK ROLLER 1 i...

Page 234: ...NLY 62 METERING PIN 4MC112 Figure 2 55 Main Gear Shock Strut Sheet 1 of 3 2 166 Revised 1 June 1970 Part 2 1 HEAD 2 SHOCK STRUT 3 METERING PIN 4 RESTRICTOR 5 MAIN PISTON HEAD 6 REBOUND PLATE 7 UPPER F...

Page 235: ...E ARM ASSEMBLIES AND ATTACHMENTS Figure 2 55 Main Gear Shock Strut Sheet 2 of 3 Part Z 4MC113 2 166A Ilb REVERSE VIEW STRUT MAIN ATTACHMENT POINT 57 i lll i AXLE ASSEMBLY AND ATTACHMENTS Revised 1 Jun...

Page 236: ...Part 2 62 Figure 2 55 Main Gear Shock Strut Sheet 3 of 3 2 166B 58 59 60 61 Revised 1 June 1970 Part 2 62 Figure 2 55 Main Gear Shock Strut Sheet 3 of 3 2 166B 58 59 60 61 Revised 1 June 1970...

Page 237: ...se disassembly procedure and note the following a Use new gaskets immersed in hydraulic fluid 2 167 r I i Within 1 or 2 hours of completion of step h place indicator in position on cylinder To in sure...

Page 238: ...the wing rear spar Its pur pose is to provide a down lock for the main gear Revised 1 February 1969 Part 2 Paragraphs 2 11 1 5102 162 1 UP PORT CONNECTION 2 FILTER SCREEN 3 OUTBOARD RESTRICTOR UP PORT...

Page 239: ...r Exp 0 RetractlOn Main Gear 26 ROD EN 1343 27 CYLINDER N FITTING MOD 4 LUBRICATIO 28 L 2 57 Figure 27 2 1 BEARI R HEAD 2 CYLIN RESTRICTOR 3 4 SPRING RESTRICTOR 5 ONE WAY 6 PACKING 7 FITTING 8 SCREEE...

Page 240: ...rs and bolts Take care to retain locating rollpin at upper attach ment bolt Revised 1 February 1969 Part 2 Paragraphs 2 162 1 to 2 163 1 to release the down lock and initiate the folding sequence of t...

Page 241: ...ER MOD 4 1343 27 CYLIN ION FITTING 28 LUBRICAT Retractlon Actuator Exploded View Part 2 4MC91 2 169 2 4 28 5 27 7 28 19 1817 U 16 15 r BEARING 1 DER HEAD 2 CYLIN 3 RESTRICTOR 4 SPRING RESTRICTOR 5 ONE...

Page 242: ...rs and bolts Take care to retain locating rollpin at upper attach ment bolt Revised 1 February 1969 Part 2 Paragraphs 2 162 1 to 2 163 1 to release the down lock and initiate the folding sequence of t...

Page 243: ...RING 25 SEAL HOUSING 26 SPACER SLEEVE Figure 2 58 Main Gear Shortening Mechanism Part 2 4MC92 2 171 11 12 13 1 SPRING GUIDE 2 RETURN SPRING 3 HYDRAULIC UP LINE CONNECTION 4 PISTON 5 UPPER ASSEMBLY ADA...

Page 244: ...LUBRICATION FITTING 22 LUG END 4MCG3 Figure 2 59 Main Gear Drag Strut 2 172 Revised 1 December 1965 Part 2 Paragraphs 2 163 2 to 2 163 4 2 163 2 DISASSEMBLY To disassemble a main gear drag strut see f...

Page 245: ...K UP RING 16 O RING 17 RESTRICTOR 18 O RING 3 4 5 6 7 8 9 4MC94 Figure 2 60 Main Gear Up Lock 2 173 2 163 5 INSTALLATION To install a main gear drag strut reverse removal procedure Use acorn 505529 fo...

Page 246: ...ller and hook and adjust by moving positions of roller within slotted brac ket Revised 15 July 1969 Part 2 Paragraphs 2 165 1 to 2 165 6 ector lever is selected down hydraulic pressure is fed to the t...

Page 247: ...R 38 CONNECTING ARM 44 BOLT 45 BOLT 46 BOLT 4MC9S Figure 2 61 Main Gear Up Lock Exploded View 2 175 Part 2 10 4 46 45 45 23 44 40 41 1 EMERGENCY RELEASE LEVER 2 SELF LOCKING NUT 3 WASHER 4 ELBOW 5 BAC...

Page 248: ...nd out nicks and imperfections up to 0 06 inch deep and one inch long in area 6 Revised 1 June 1970 Part 2 Paragraphs 2 166 to 2 167 1 2 166 MAIN GEAR EMERGENCY EXTENSION SYSTEM The main gear emergenc...

Page 249: ...int 11 Since the removal of material in areas 2 3 5 and 7 will shorten the ultimate roll life 2 176A Part Z 3 7 3 3 6 3 Figure Z 61A Main Wheel Inboard Half Inspection and Rework Areas 7 Inspect regis...

Page 250: ...es or an approved tire machine separate edges of tire from wheel hub beadings Revised 1 June 1970 t Part 2 Paragraphs 2 167 lA to 2 167 3 Figure 2 61B Main Wheel Outboard Half Inspection and Rework Ar...

Page 251: ...lator Refer to paragraphs 2 171 1 and 2 171 2 Replace check valve Refer to paragraphs 2 177 1 2 177 c ReInove bolts holding halves of hub together d Carefully separate hub halves and reInove packing r...

Page 252: ...ING 10 OUTER BRAKE LINING CARRIER 11 INSULATOR 12 WHEEL 4MCge Figure 2 62 Goodrich Wheel Brake Unit Part 2 Paragraphs 2 169 to 2 169 2 2 169 WHEEL BRAKE UNITS The wheel brake units can be either Good...

Page 253: ...o rework areas that are opposite one another g Blend out iITlperfections up to 0 03 inch deep 2 179 b Jack aircraft clear of ground c ReITlove wheel Refer to paragraph 1 22 d unit ReITlove bolt holdin...

Page 254: ...TO DISK BRAKES APPLIED 0 360 INCH 0 125 INCH 11 32 INCH Figure 2 63 Goodyear Wheel Brake Unit 4MC97 Part 2 A B C 2 180 1 BRAKE HOUSING 2 OUTBOARD ANVIL SIDE BRAKE LINING 3 BRAKE DISK 4 INBOARD PISTON...

Page 255: ...CHANGING GOODYEAR BRAKE LIN INGS a Remove wheel brake unit as described in paragraph 2 169 8 2 l80A in area 7 Do not rework opposite areas In area covered by mounting bolt washers blend out nicks or...

Page 256: ...5 9 5 Figure 2 63A Main Wheel Brake Housings Inspection and Rework Areas 2 1S0B Revised 1 June 1970 Part 2 2 6 3 Ff 5 9 5 Figure 2 63A Main Wheel Brake Housings Inspection and Rework Areas 2 1S0B Revi...

Page 257: ...g air at charging valve c Disconnect air line from back of gage Cap and plug open connections 2 181 l b Cut lockwire between threaded bushings and slacken threaded bushings c Remove three linings from...

Page 258: ...el Brakes Hydraulic Accumulator and Emergency Air Bottle Installation 2 182 Revised 1 February 1972 Part 2 Paragraphs 2 172 2 to 2 173 d Remove bolts from flange of gage and re move gage 2 1 72 2 INST...

Page 259: ...the center bellcranks and control valves and between the outer bellcranks and the pedal 2 183 _ _ _ 2 173 1 REMOVAL a Relieve hydraulic pressure from accumul ator by operating wheel brakes b Disconne...

Page 260: ...TOP 28 BELLCRANK STOP 4MC99 Figure 2 65 Wheel Brakes Control Valves Linkage Revised 1 February 1972 Part 2 17 2 184 14 3 8 INCH DIA ROD USED DURING RIGGING ONLY r ANGLE OF PEDAL IN NEUTRAL POSITION 3...

Page 261: ...hich is spring loaded against the emergency air inlet to allow free passage of the hydraulic 2 184A arms are rigged as described in paragraph 2 175 2 The interconnecting push rods between bellcranks a...

Page 262: ......

Page 263: ...ure for shuttling must be between 25 and 100 psi f Plug brake unit connection and apply fluid 2 185 I orr 12 0 11 8 00 10 6 1 1 SHUTTLE VALVE RH SHOWN 2 VALVE SEAT 3 GASKET 4 FILTER 5 BOLT FITTING RH...

Page 264: ...hing length of 2 180 PARKING BRAKE clear plastic hose The parking brake is hand operated from 2 1B6 Part 2 Paragraphs 2 176 6 to 2 180 pressure of 5 psi to fluid inlet port After a three minute waiLng...

Page 265: ...USTING SCREW 12 PULLEY 13 PULLEY 14 STOP 4MC 10 I Figure 2 67 Parking Brake Cable Installation 2 187 a handle on the pylon inunediately in front of the pilot s position See figure 2 67 A cable bolted...

Page 266: ...ak with soap and wate r solution and rectify Replace valve Refer to para graphs 2 185 I and 2 185 2 Part 2 Paragraphs 2 180 I to 2 181 I control valve levers to releas e the brakes 2 180 1 REMOVAL OF...

Page 267: ...r outlet A drain valve fitted in the adapter may be opened to allow mois ture to be blown out 2 189 Part 2 Paragraphs 2 182 to 2 183 TABLE 2 18 Cant INDICATION OF TROUBLE PROBABLE CAUSE CORRECTIVE ACT...

Page 268: ...cotter pins shaft collars 8 and extension springs 34 from connecting rod 31 Revised 1 February 1972 Part 2 Paragraphs 2 183 1 to 2 186 1 2 183 1 REJ 10VAL a Wo king through access opening 46 figure 1...

Page 269: ...COHHE 32 BOLT CTIHG ROD H GEAR DOOR 35 RUB SPRIHG 36 SCREW OP 37 BOLT 38 BOLT 39 BOLT 4MC 102 2 191 2 1 BOLT SSEMBLy 4 COLLAR 5 BOLT 6 PUSH ROD RASSEMBLy 9 ROLLE 10 BOLT R ASSEMBLY g I ER PLATE 13 BOL...

Page 270: ...bber stop 35 from frame assembly 7 c Remove bolts l0 and 12 washers striker Revised 1 February 1972 Part 2 Paragraphs 2 186 2 to 2 186 5 b Remove cotter pin nut washer and bolt 19 and disconnect conne...

Page 271: ...h MECHANISM To assemble a main gear door anism reverse removal procedure Revised 1 June 1970 2 192A plates 11 and 14 nuts screws 26 and 28 plates 27 and rubber bumpers 25 from act uator assembly 15 d...

Page 272: ......

Page 273: ...ues given in paragraph 2 187 3 b Lubricate nose gear Refer to Lubrication Diagram figure 1 11 2 193 2 186 9 ADJUSTMENT a Jack aircraft clear of ground and remove ground safety locks b lnsure leg strap...

Page 274: ...DOWN AIR BOTTLE 29 ADJUSTABLE STAY 15 ADJUSTABLE CONNECTING ROD 30 NOSE GEAR FAIRING 1 III i r t N N 0 I zj 30 dQ s O j 1 N I J 0 Z 0 m 1 Cl 1 III O j 13 16 _ I r I _ I IY ___ r J ___ _ 1 COLLAR ASSE...

Page 275: ...0 660 780 30 40 C l STEERING ACTUATOR r UM AllOWABLE BACKLASH 4MC 104 Revised 1 February 1969 2 195 c Compress nose gear shock strut sufficiently to eliminate self centering action and operate nosewhe...

Page 276: ...removed apply a protective coating of Alodine solution No 1200 and repaint Revised 1 February 1972 Part 2 Paragraphs 2 188 to 2 188 3 2 188 NOSE GEAR SHOCK STRUT The operating principle of the pneu d...

Page 277: ...CE FINISH ALODINE REWORKED AREA Figure Z 70B Repairs to Nose Gear Torque Arm 1 500 IN RADIUS 2 1q6A 2 188 4 ASSEMBLY To assembly nose gear shock strut reverse disassembly procedure Note following poin...

Page 278: ......

Page 279: ...G MOD 4 1289 20 Revised 1 February 1972 18 19 Figure 2 71 Nose Gear Shock Strut Part 2 4MC105 2 197 1 FLUID CHARGING VALVE 2 OUTER CYLINDER 3 METERING PIN 4 DRAG STRUT ATTACHMENT 5 PISTON HEAD 6 UPPER...

Page 280: ...r I I I I I I I I I I I I I I I I I I I I I I I Shock Stru ReVise t Exploded View d 1 February 1972 Par 2 Pre Mod 4 1332 Figure 2 72 Nose Gear 2 198 r I I I I I I I I I I I I I I I I I I I I I I I Sho...

Page 281: ...occupied by the up and down lock segments The switch operating pins extend into the recesses 2 199 Part 2 Paragraphs 2 188 5 to 2 189 KEY TO FIGURE 2 72 1 Fluid Charging Valve 22 Washer 42 Nose Strut...

Page 282: ...MENTS 1 1 13 J 14 1 L 2 a 1 1 3 1 4 5 12 J o 7 1 1 1 Figure 2 73 Nose Gear Drag Strut 2 200 4MC 107 Par 2 1 MICROSWITCH 2 HYDRAULIC SHUTTLE VALVE 3 NOSE GEAR UP LINE CONNECTION 4 NOSE GEAR EMERGENCY D...

Page 283: ...1 REMOVAL OF NOSEWHEEL STEERING CABLES To remove nosewheel steering cables proceed as follows 2 201 and are actuated by the segments Emergency ex tension of the strut is provided by an air bottle stra...

Page 284: ...UNIVERSAL BOLT 34 GASKET 35 ORIFICE 17 Figure 2 74 Nose Gear Drag Strut Exploded View 2 202 4MC 108 Part 2 1 PRESSURE GAGE 2 GASKET 3 GASKET BACK lIP RING 4 FLARED NUT 5 SCREW 6 SPHERICAL BEARING 7 FI...

Page 285: ...e nosewheel pressure line to return 2 192 1 REMOVAL a Select nosewheel steering switch to OFF 2 203 a Open nose section upper hatch and re move access covers 49 and 75 figure 1 2 b Working through nos...

Page 286: ...on of bolt b Lubricate as required Refer to Lubrication Diagram figure 1 11 Revised 1 February 1972 Par 2 Paragraphs 192 2 to 2 193 4 b Insure 111 aircraft electrical power is off c Working through ac...

Page 287: ...ACTUATOR SERIAL NO JH32 AND SUBSEQUENT Figure 2 75 Nosewheel Steering Actuator Part 2 4MC 109 2 205 23 21 20 19 18 12 13 3 4 5 6 1 8 9 10 1 INPUT OPERATING LEVER 2 RELIEF VALVE SPRING 3 RESERVOIR END...

Page 288: ...Blend out and polish imperfections up to 0 015 inch deep maximum in area 2 Revised 1 February 1972 Part 2 Paragraphs 2 194 to 2 196 1 c Operat _ steering actuator through full travel at least five ti...

Page 289: ...es remain the same as for the 7 50 x 10 tires 2 196 2 MAINTENANCE Refer to paragraph 2 157 2 2 206A 5 4 5 3 Part 2 Paragraphs 2 196 lA to 2 196 2 8 3 Figure 2 75A Nosewhee1 Inboard Half Inspection and...

Page 290: ...arate edges of tire from wheel hub beadings taking care not to pinch inner tube Revised 1 June 1970 Part 2 Paragraphs 2 196 3 to 2 196 4 5 4 4 3 3 5 6 3 Figure 2 7 SB Nosewheel Outboard Half Inspectio...

Page 291: ...deflate tube then reinstall valve core and inflate tire to pressure given in paragraph 1 21 2 206C c Rem ve bolts holding halves of hub together d Carefully separate hub halves and remove tube and ti...

Page 292: ......

Page 293: ...hour by noting pres gage after a period of approximately one hour Sure on gage Wirelock valve 2 207 2 197 NOSE GEAR EMERGENCY DOWN SYS TEM The nose gear emergency down system figure 2 73 uses compress...

Page 294: ...EAR DOOR MECHANISM Repair to nose gear door mechan ism consists of replacement of damaged parts and Part 2 Palagraphs 2 201 to 2 201 6 2 201 NOSE CEAR DOORS Th nose gear doors figure 2 76 pivot from t...

Page 295: ......

Page 296: ...appropriate columns of the TEMPORARY REVISION INDEX provided at the front of the m anual Page 1 of 1 Part 2 PSM 1 4 2 TEMPORARY REVISION Serial 16 dated 12 September 1973 Insert in Part 2 facing Page...

Page 297: ...32 BOLT 33 BOLT 34 STOP 35 BOLT 36 BOLT 37 CAM BLOCK MOUNT 38 NUT 39 BOLT 40 BOLT 41 LINK 1 d P i N I i I I i rJ I JQ 1 I N I 0 Z 0 Ul I C I P 1 t J 0 0 1 Ul N H I N 0 11 0 21 BOLT 22 CAM BLOCK 23 RE...

Page 298: ...function test of the landing gear must be made whenever a compon nt in the Revised I June 1970 _ _ Pa rt Z Paragraphs 2 Z01 7 to 2 Z03 renewal of bearings RerrlOve bearings using an arbor presS and s...

Page 299: ...riate columns of the TEMPORARY REVISION INDEX provided at the front of the manual Page 1 of 1 _ _ _ PSM 1 4 2 Part 2 TEMPORARY REVISION Serial II 17 dated 12 September 1973 Insert in Part 2 facing Pag...

Page 300: ......

Page 301: ...nd re rnove landing gear ground safety locks b Connect 28 volt dc external power to aircraft 2 210A e rnc rgency syste rn has been replaced or adjusted and at such other ti rnes as prescribed in Appen...

Page 302: ......

Page 303: ...on ground Power is available through nose gear weight switch and nosewheel steering switch 2 211 I c Connect a hydraulic ground servIcIng rig to hydraulic ground test connections through access openi...

Page 304: ..._ _ _ 40 G I 3 INDICATOR LIGHTS Figure z 77 Landing Gear Electrical System Schematic 2 212 4MC 111 L K ABCDEF R IG T W T SW f ABCDEF T5 17 1 L L T6 4 _ KrKi r A NC UP _ 1 If _ 1 0 g T6 15 16 IF E lF...

Page 305: ...08 1 REMOVAL MICROSWITCHES NON REVERSIBLE PROPS a Insure all aircraft electrical power is off 2 213 to nosewheel steering shutoff valve froIn HYDR circuit breaker Landing gear down lock Inicr o switch...

Page 306: ...OVAL MICROSWITCHES REVER I SIBLE PROPS a Insure all electrical power is off Revised 1 February 1969 Part 2 Paragraph 2 208 2 1 SEMICIRCULAR BRACKET 2 LANDING GEAR WARNING HORN MICROSWITCHES 3 THROTTLE...

Page 307: ...er is directed to the landing gear control lever to ener gize the selector valve up solenoid 2 214A b Open cabin roof upholstery on left hand side of monorail to gain access to microswitchmount ing pl...

Page 308: ......

Page 309: ...y connected across pins Band E No 1 test laInp across pins C and F and No 2 test laInp acroSs 2 215 2 209 1 REMOVAL To reInove a Inain gear weight switch proceed as follows a Insure all aircraft elect...

Page 310: ...a lug attached to the inner cylinder and is actuated When weight is on the Revised 1 February 1969 Part 2 Paragraphs 2 211 to 2 212 pins A and D Connect plug to microswitch re ceptacle c With main ge...

Page 311: ...l connec tor to micro8witch and carry out function test h Wirelock microswitch retaining nuts 2 217 nosewheel the microswitch is in the tripped position and supplies emergency dc power from the UNDERC...

Page 312: ...ing horn test switch on electrical switch panel after reconnection of bat tery Revised 15 July 1969 Part 2 Paragraphs 2 214 to 2 215 2 i Reconnect nos e g ear doors 2 214 NOSE GEAR UP LOCK MICROSWITCH...

Page 313: ...Selector Valves 3 20 3 25 Emergency System Filter 3 23 3 26 Emergency System Relief Valve 3 23 3 1 PART 3 Part 3 Table of Contents HYDRAULIC SYSTEM Paragraph 3 1 3 2 3 3 3 4 3 5 3 6 GENERAL General D...

Page 314: ......

Page 315: ...ll cycles collecting fluid from UP line in a suitable container Reconnect UP line to drag strut 3 3 GENERAL 3 1 GENERAL DESCRIPTION The hydraulic system supplies hydraulic power to operate the landing...

Page 316: ...system if necessary Refer to para 3 3 Establish reason for leak and rectify Revised 1 February 1972 Part 3 Paragraphs 3 4 3 4 1 Handpump must not be used when landing gear is selected UP unless UP lin...

Page 317: ...R ITl TRANSMITTER 4MCI30 NORMAL SYSTEM ON OFF NOSEWHEEL DOWN HANDPUMP SELECTOR P EMERGENCY SYSTEM E SWITCH PRESSURE _____________________________ _ RETURN ______________________________ _ SUCTIO _____...

Page 318: ...ure 3 1 Hydraulic System Schematic Normal System She et 1 of 2 R evbed 1 Febr uary 1972 Pd rt 3 3 5 HOSEwHEE L SrEERING VALyE nHYDRAULI C PRESSURE SHUTOFF VALVE MAIN GEAR RETRACT ON ACTUATOR HOSEwHEEl...

Page 319: ...VALV E Cf C2l RESTR ICTOR Figure 3 1 Hydraulic System Schemati c Handpurnp Operation Sheet 2 o f 2 P art 3 4 H 1 I 3 0 OIL MERGENCY SWITCH SE L EC T OR N O RMAL SYSTEM SY STEM PRESSURE SWI TCH ON OFF...

Page 320: ...GENCY BUS GRAUL IC GROUND ST CONNECTION EM E RG E NCY L ANDING ON GEAR DOWN SELECTOR OFF ECK VALVE I j i J Jv F t RE IHE DRIVEN PUMPS r L 1 B I B Y I i I II ru m IC I sHu irvU LEVE H t J _____ __ _ DO...

Page 321: ...reason hydraulic reservoir is re moved flush with the solvent and dry with a filtered air supply 3 7 Part 3 Paragraphs 3 5 to 3 5 2 TABLE 3 1 Cont INDICATION OF TROUBLE PROBABLE CAUSE CORRECTIVE ACTIO...

Page 322: ...at prescribed in spection intervals as follows a Cut locking wire and unscrew head from filter body Part 3 Paragraphs 3 5 3 to 3 7 2 3 5 3 MINOR REPAIR Minor repairs to the hy draulic res ervoir consi...

Page 323: ...FILLER CAP CHAIN _19 21 4MC 132 Figure 3 2 Hydraulic Components on Flight Compartment Bulkhead 3 9 30 I iiil _ i I II III 27 _ I Ir Part 3 1 FILLER CAP 2 VENT TUBE 3 HYDRAULIC RESERVOIR 4 RESERVOIR S...

Page 324: ...bricated with hydraulic fluid b Fill pump with clean hydraulic fluid before commencing installation Part 3 Paragraphs 3 7 3 to 3 9 3 b Remove filter element c Flush filter body and head with a dry cle...

Page 325: ...gency Shutoff Valve and Hydraulic Pressure Switch Installation Revised 1 February 1969 3 11 _ _ _ _ c Fit new pump gasket d Temporarily place suitable container below connections during line connectio...

Page 326: ...e 3 2 d Select hydraulic pressure shutoff valve OFF at lever 7 above filter Revised 1 February 1969 Part 3 Paragraphs 3 10 2 to 3 12 2 3 3 from emergency shutoff valve d Place container below valve to...

Page 327: ...on for one minute to remove readily removable con tamination particles from surface of element 3 13 e Run an engine to bleed pressure line f Replenish reservoir g Select hydraulic pressure shutoff val...

Page 328: ...ERGENCY SYSTEM RELIEF VALVE 4MC 134 Figure 3 4 Hydraulic Ra nel Below Flight Compartment Floor 3 14 Part 3 1 EMERGENCY HYDRAULIC SYSTEM FILTER 2 SPACERS 3 WING FLAP HYDRAULIC CIRCUIT FILTER 4 FILTER A...

Page 329: ...tW position disk type valve controlled by an operating lever and cables A label alongside the 3 14A b Install unit in suitable housing and flow unit in reverse direction for one hour minim1lm using h...

Page 330: ......

Page 331: ...e two screws Remove these two screws and a third screw atbase ofindicator and remove indicator 3 15 lever reads HYDRAULIC PRESSURE SHUT OFF VALVE and indicates the ON and OFF positions of the lever 3...

Page 332: ...be replaced by a serviceable item transfer union from unserviceable switch Revised I Fe bruary 1972 Part 3 Paragraphs 3 16A 2 to 3 18 2 3 16A 2 INSTALLATION HYDRAULIC SYSTEM PRESSURE INDICATOR Reverse...

Page 333: ...rom relief valve It is not necessary to back off nut immediately above reducer Blank openings 3 l6A to replacement switch using a new O ring lub ricated with hydraulic fluid b Fill switch with clean h...

Page 334: ......

Page 335: ...e landing gear selector valve sticking in the UP selection Provision is made to lower the nose 3 17 3 19 2 INSTALLATION a Obtain a new O ring for each reducer and lubricate with hydraulic fluid b Asse...

Page 336: ...er to paragraph 3 2 Clear obstruction and install line Flush systemifnecessary Refertoparagraph 3 3 Part 3 Paragraph 3 21 1 gear by air pres sure in the event of failure of both normal and emergency h...

Page 337: ...with handpuInp selector at NORMAL SYSTEM by operating flaps g Close nose left hand access door 3 19 Part 3 Paragraphs 3 22 to 3 22 2 Figure 3 7 Hydraulic Emergency Selector Panel 3 22 HYDRAULIC HANDPU...

Page 338: ...ency landing gear down selector is a m anually opera ted three way disk type valve but with greater Part 3 Paragraphs 3 23 and 3 24 FLIGHT COMPARTMENT FLOOR STRUCTURE 1 HYDRAULIC HANDPUMP 2 BOLT 3 HAN...

Page 339: ...dpump charging selector valve bleed wheel brakes system in manner given in paragraph 2 178 3 21 _ _ fluid capacity than the other three way valves 3 24 1 REMOVAL The following procedure ap plies to ea...

Page 340: ...GASKET 4Me 139 Figure 3 9 Hydraulic Emergency Selector Panel and Selector Valves Installation 3 22 Part 3 1 HYDRAULIC SELECTOR 17 HANDPUMP SUCTION PANEL LAMP BRACKET SELECTOR VALVE 2 WASHER 18 BOLT 3...

Page 341: ...luid Tighten line connection while fluid is flowing d Wipe dry drip tray below hydraulic panel 3 23 but using handpump with handpump selector at EMERGENCY SYSTEM and brake accumulator handpump chargin...

Page 342: ......

Page 343: ...ishing Systems 4 71 Heater Fire Extinguisher Bottles 4 71 Hand Operated Fire Extinguishers 4 72 4 1 Part 4 Table of Contents PART 4 UTILITY SYSTEMS Paragraph Page 4 1 4 2 4 3 4 4 4 5 4 6 4 7 4 8 4 9 4...

Page 344: ...97 4 97 4 98 4 98 4 99 4 99 4 100 4 102 4 102 4 102 4 103 4 104 4 104 4 104 Revised 1 February 1972 Part 4 Table of Contents Paragraph OXYGEN SYSTEM AND POR TABLE OXYGEN EQUIPMENT 4 72 4 73 4 74 4 75...

Page 345: ...are located in the heater outlet reducing duct 4 4 2 Temperature is automatically controlled at 4 3 4 1 GENERAL This part gives description trouble shooting removal installation minor repair and adjus...

Page 346: ...to paragraphs 4 16 1 and 4 16 2 Clear blockage or replace lines Revised 1 February 1969 _ _ _ _ _ _ Part 4 Paragraphs 4 4 3 to 4 4 4 the temperature set on the temperature selector The flight compartm...

Page 347: ...NT 27 FLIGHT COMPARTMENT AIR SELECTOR VALVE LlN 2B FLIGHT COMPARTMENT COMBUSTION EXHAUST STA Revise 1 CABIN OUTLET LOUVERED GRILL lA AFT GROUND IlENilLATION FAN MOD S O O 4100 2 CABIN HEATER DISTRIBUT...

Page 348: ...EATER FUEL SYSTEM 4MC 150 F igure 4 1 Heating and Ventilating Systems Revised 1 Feb ruary 1969 4 5 I 8 10 SEE FIGURE 4 13 11 SEE FIGURE 4 10 36 35 34 ANEL VALVE HANDLE H OUTLET LOUVERED GRILL H HOT DA...

Page 349: ...TMENT THERMOSTAT Figure 4 2 Flight Compartment Heating System Schematic 4 6 Revised 1 February 1972 Part 4 _ RAM AIR COMBUSTION COMBUSTION EXHAUST B lHEATED AIR _ RETURN AIR MECHANICAL LINKAGE ELECTRI...

Page 350: ...AL INSTALLATION FLIGHT COMPARTMENT COOLING FANS r T IC A B D V I V CYCLING SOLENOID FUEL CONTRe UNIT ___3 VENTILATION RAM AIR INTAKE ___ MICROSWITCH o SECONDARY BUS A COCKPIT AIR SELECTOR ill FLIGHT P...

Page 351: ...B C 0 E G I H HEATER IGNITION UNIT TO SPARK PLUG MS3106B18 IS TEMPERATURE CONTROL BOX MS3106B18 1P j o o IDARY BUS IE HEATER HEATER MASTER SWITCH I ___ _ L_ T I COMBUSTION AIR FAN VENTILATION AIR FAN...

Page 352: ......

Page 353: ...Re place if necessary Refer to paragraphs 4 17 1 through 4 17 3 Clear blockage or replace lines 4 7 INDICATION OF TROUBLE No heat indicating light on Selected temperature not maintained TABLE 4 1 Cont...

Page 354: ...ct Check and correct Check electrical circuit or replace fan Refer to para graphs 4 23 3 and 4 23 4 Part 4 INDICATION OF TROUBLE Selected temperature not Inaintained Backfi ring pulsating combustion o...

Page 355: ...Replace ram air pressure switch Refer to paragraphs 4 13 1 and 4 13 2 Replace high limit switch 4 9 INDICATION OF TROUBLE Low or no airflow through outlets Heater shuts down light off Warm airflow bu...

Page 356: ...pushed in 3 Pull out handle below air control handle marked COCKPIT AIR SELECTOR to GROUND position Part 4 Paragraph 4 4 5 INDICATION OF TROUBLE Heater does not start light off For special order groun...

Page 357: ...t sealed to meter fuel to the heater unit e A fire extinguisher bottle and flood valve assembly 4 11 4 Switch fuel pump switch to FUEL 5 Select temperature selector to 80 6 Switch heater master switch...

Page 358: ...WITCH 31 BOLT 32 OVERFL OW DRAIN FLEXIB LE HOSE 33 FUEL CONTRO L UNIT MOUNTI NG BRACKE T B 5 0 I 0 H N IJQ s 0 H I Vol J I s 0 I 0 0 IJQ r o I 0 S g r 0 0 I n i I IJQ 5 m I o s 1 FUEL CONTRO L UNIT 2...

Page 359: ...t compartment heater packag e proceed as follows a Insure all aircraft electrical power is off 4 13 f Thermostats temperature sensitive switches and a fire detecting element g A junction box containin...

Page 360: ...BOLT 38 OVERFLOW DRAIN FLEXIBLE HOSE 39 FUEL CONTROL UNIT MOUNTING BRACKET B 6 34 18 15 15 1 1 I I i IrJ JQ I i CD C1l d CD I 0 I i Ilo CD I i Cl I i UgI l Ilo 1 l CD Ilo 1rJ l l JQ I r I C1l o l l CD...

Page 361: ...perate valve Stow cable and arm clear of pack age y Move heater package forward and tilt front 4 15 b Open nose section upper hatch c Remove clamps securing cables to cable harness strap above package...

Page 362: ...ue load inlet and outlet reducing duct special clamp couplings to 50 pound inches d Wirelock straps Part 4 Paragraphs 4 5 4 to 4 6 2 of package to clear electrical cables Raise left hand end of packag...

Page 363: ...tracking is evident check ignition lead spring loaded end for distortion be fore re install ng 4 17 4 7 FUEL SPRAY NOZZLE The flight compartment heater fuel spray nozzle is screwed into the combustion...

Page 364: ...Mod4 1187 is embodied repeat step f with ignition switch selected to EMERG Return switch to NORMAL Part 4 Paragraphs 4 8 3 to 4 10 1 b Wipe out inside of plug well with clean cloth dampened with carb...

Page 365: ...ducing duct to heater and to ducts Slide clamps clear of inlet reducing duct and withdraw duct 4 19 4 10 2 REMOVAL To remove flight compart ment heater ignition unit proceed as follows a Open nose sec...

Page 366: ...ON To install fuel control unit reverse removal procedure Note fo11owing points during installation Part 4 Paragraphs 4 11 3 to 4 12 2 4 11 3 REMOVAL OF OUT LET REDUCING DUCT a Insure all aircraft ele...

Page 367: ...tion 4 16 2 INSTALLATION To install a flight com partment heating system relay reverse removal 4 21 a Make sure all joints are air and fuel tight b Wirelock electrical connector c Test fuel control un...

Page 368: ...e OHMS 10 PERCENT Infinite o to 0 5 o to O 5 224 224 217 208 208 1520 Infinite o to 0 5 150 217 208 Part 4 Paragraphs 4 17 to 4 17 2 procedure Test operation of relays and ground test system on comple...

Page 369: ...ent f Remove cotter pin washer and flat head pin securing cable end to valve pivot shaft lever 4 23 Part 4 Paragraphs 4 17 3 to 4 19 1 TABLE 4 2 Cont CONNECTOR PINS OHMS 10 PERCENT MS3102A lS IS I to...

Page 370: ...to the right of the flight compartment heater package through the side of the aircraft nos e The de Part 4 Paragraphs 4 19 2 to 4 21 g Unscrew nut securing handle to pylon and draw handle and cable as...

Page 371: ...from air selector valve pivot shaft lever on top of air return branch of inlet r educing duct 4 25 flector is fitted externally and to the rear of the stack to deflect the gases away from nose and fu...

Page 372: ...g area d Disconnect air selector valves connecting rod from air selector valve pivot shaft lever be Part 4 Paragraphs 4 23 to 4 23 3 by removing cotter pin washer and flat head pin b Back off locknut...

Page 373: ...the fan are of stainless steel and the ducting aft of the fan is of fiberglas or polycarbonate 4 27 low air return branch of inlet reducing duct e Remove elbow between fan reducer and air return branc...

Page 374: ...6 PLASTIC DUCT 1 CLIP 8 RUBBER OR FIBER STRIP 3 6 4MC nus Figure 4 7 Typical Heating Duct Couplings Part 4 Paragraphs 4 25 1 to 4 26 4 25 1 REMOVAL AND INSTALLATION Remov 4 25 3 REPAIR OF POLYCARBONAT...

Page 375: ...ings forcing ducts into stres s with sub sequent damage to plastic ducts during s ervic e life 4 Z9 The lateral duct incorporates two risers The left riser terminates at two foot warmer outlet grills...

Page 376: ...pply The valve operating supply pressure is ad justable by varying the pressure on the valve spring Part 4 Paragraphs 4 27 4 to 4 30 4 27 4 CABIN VENTILATING AIR EXHAUST SYSTEM The cabin ventilating a...

Page 377: ...BOLT 16 BOLT 6 FU EL LINE 17 BOLT 13 I ji ii i 4MC157 Figure 4 8 Heater Fuel System Components 4 31 4 30 1 REMOVAL a Remove two access panels from right wing See items 67 and 82 figure 1 2 b Working t...

Page 378: ...d through an inlet in the leading edg e of the left wing and through ducts to the heater combustion Part 4 Paragraphs 4 31 1 to 4 33 The filter is retained by two bolts screwed into captive nuts attac...

Page 379: ...E Of RISE CONTROL MOD 4 1321 AND CYCLING SWITCHES AND fiRE DETECTING ELEMENT L J COMBUSTION EXHAUST I SPECIAL GROUND AND fLIGHT SYSTEM COMPONENTS ONLY AIR CONTROL VALVE W _ _ to _ _ _ i _ _ _ 1 _ e OU...

Page 380: ...c Sheet 1 of 2 Part 4 HEATER ELEMENT VENTILATION RAM AIR INTAKE 4M C I i8 Revi sed 25 July 1968 4 33 __ NG HEET I HEATER IGNITION UNIT COMBUSTION EXHAUST RAM AIR PRESSURE SWITCH CABIN AIR II I CABIN E...

Page 381: ...BASIC OR ALTERNATE Figure 4 9 Cabin Heating System Schematic Sheet 2 of 2 4 34 Revised 1 June 1970 Part 4 TO AIR PUMPS SOO MOD 4099 GROUND VENT FAN BLOWER UNITS 20A AI R SELECTOR VALVE CONTROL RELAY...

Page 382: ...URGE LIMIT SWITCH CYCLING SWITCH C F D E A B I TEMPERATURE CONTROL H BOX G J J H G F E 0 B A 4MCl59 T FAN rs FANS VENT f j r IT G ES SECONDARY BUS PUSH TO START RAM AIR PRESSURE HIGH LIMIT SWITCH SWIT...

Page 383: ...will stop the valve at an intermediate posi tion Cooler conditions can be selected similarly 4 34A chamber Ventilating ram air is supplied through an inlet in the leading edge ofthe right wing Stale...

Page 384: ......

Page 385: ...r Refer to paragraph 4 38 1 Clean or replace spark plug Refer to paragraph 4 37 1 Check wiring 4 35 by use of the MAN COLD position Heated air is delivered through eight outlets along each side of the...

Page 386: ...gh 4 31 3 Remove and test temper ature control box Re place if necessary Refer to parag raph 4 51 1 Part 4 INDICATION OF TROUBLE No heat indicating light on 4 36 TABLE 4 3 Cont PROBABLE CAUSE Defectiv...

Page 387: ...o paragraphs 4 38 2 and 4 38 3 Replace fuel control unit Refer to paragraphs 4 43 1 and 4 43 2 4 37 INDICATION OF TROUBLE Selected temperature not maintained Backfiring pulsating combustion or smoky e...

Page 388: ...holes in manner given in para graph 4 45 2 step e Replace high limit switch Refer to paragraph 4 46 Part 4 INDICATION OF TROUBLE Backfiring pulsating combustion or smoky exhaust Low or no airflow thro...

Page 389: ...2 Check and correct Replace relay Refer to paragraphs 4 54 2 and 4 54 3 Check wiring and correct I f INDICATION OF TROUBLE Heater shuts down light off Warm airflow but light off Heater does not start...

Page 390: ...ioning If faulty trouble shoot temperature control system k Select control selector to MAN COLD and Part 4 Paragraph 4 33 4 INDICATION OF TROUBLE TABLE 4 3 Cont PROBABLE CAUSE CORRECTIVE ACTION For gr...

Page 391: ...on air inlet and slide clamp aft onto plastic duct h Disconnect upstream air line 38 at exhaust 4 41 check that air mixing valve actuator operates con tinuously until heater bypass line is fully open...

Page 392: ...RPORATING MOD 4 1321 4 42 4MC 160 Figure 4 10 Cabin Heater Package Installation Revised 25 July 1968 art 4 i jii iii i INCORPORATING MOD 4 1321 4 42 4MC 160 Figure 4 10 Cabin Heater Package Installati...

Page 393: ...Cycling Switch Mod 4 1321 High Limit Switch Mod 4 1321 Fire Detecting Element Mod 4 1321 4 42A 4 42B Part 4 Key to Figure 4 10 Cabin Heater Package Installation 1 Fire Extinguisher Bottle 2 Fuel Outle...

Page 394: ......

Page 395: ...rews Z d Disconnect fuel supply fler ible hose 19 by removing special bolt 4 and two gaskets 5 4 43 stack and at elbow Disconnect line attachment clips and remove line i Release two clamps on sleeve r...

Page 396: ...stalled then install thimble gage in spark plug hole Do not use a spark plug gasket on thimble gage Part 4 Paragraphs 4 36 2 to 4 37 1 1 FUEL DRAIN BOX COVER 2 SCREW 3 GASKET SPECIAL BOLT 5 GASKET 6 N...

Page 397: ..._____ FEELER GAGE 1 1 33 I 0011N REMOVE Figure 4 lZ Spark Gap Feeler and Thimble Gages 4MCISZ 4 45 b Push feeler gage into heater until it contacts ground electrode and check that area Bongage is in...

Page 398: ...s and bolts securing cabin heater air bypass duct to mixing valve as sembly 27 Revised 25 July 1968 Part Paragraphs 4 40 1 to 4 41 1 tinguishing system the duct end being connected by a special coupli...

Page 399: ...e flight com partment ram air pressure s tCh 4 42 1 REMOVAL a Insure all aircraft power is off 4 47 e Support bypass duct by hand and releas e clamp securing bypass duct to bypass air transi tion duct...

Page 400: ...urled screw from base of glass bowl c Pivot wire strap clear of bowl Remove bowl empty and wipe dry Part 4 Paragraphs 4 42 2 to 4 44 1 b Lower upholstery in cabin roof aft of cabin flight compartment...

Page 401: ...icro8witch a Slide cable into positionthroughhandleopen nuts washers and screws oving attaching 4 49 I d Replace gasket Reinstall bowl and retain by wire strap and screw Insure bowl is positioned corr...

Page 402: ...raph 4 40 2 b Remove nuts washers and screws securing switch and remove switch Revised 25 July 1968 Part 4 Paragraphs 4 45 5 to 4 47 1 c Remove screws attaching each valve to it shaft withdraw shaft a...

Page 403: ...ther of the cabin heating system relays proceef as follows a Insure all aircraft power is off 4 50A 4 47 2 INSTALLATION To install surge limit switch reverse removal procedure 4 48 CABIN DUCT THERMOST...

Page 404: ......

Page 405: ...intake ant ICIng wires from terminal strip on rib inboa d of intake Remove cord binding wires 4 51 b Lower cabin roof upholstery aft of cabin flight compartment bulkhead to right of aircraft centerli...

Page 406: ...S63 4 Rivets CRS63 5 5 32 inch may be used if necessary b Torque load inner clamp to 35 pound inche Part 4 Paragraphs 4 52 4 to 4 53 2 d Slacken clamp securing intake to elbow duct e Remove screws att...

Page 407: ...r Selector Valves Actuator and Linkage of Speci lOrder Ground and Flight System 4MC 163 4 53 ____t_ 4 54 CABIN AIR SELECTOR VALVES ACTUA TOR AND LINKAGE For the special order ground and flight system...

Page 408: ...rical power g Close nose section upper hatch and reinstall cabin upholstery Revised 1 February 1969 Part 4 Paragraphs 4 54 1 to 4 54 5 stale air to ahnosphere 4 54 1 The selector valve actuator is an...

Page 409: ...reverse removal procedure On completion of installation check operation of relay as follows 4 55 _r 4 54 6 RIGGING OF CABIN AIR SELECTOR VALVE LINKAGE With cabin roof upholstery lowered forward of win...

Page 410: ...r fan assembly from mounting socket c Cap electrical receptacle on mounting Revised 1 February 1969 Part 4 Paragraphs 4 55 3 to 4 55 7 a Connect an external source of electrical power to aircraft b Pu...

Page 411: ...no structural or ducting chan es arenecessaryon changeover The heavy duty an circuits contain 4 56A bracket if fan is not replaced im m ediately 4 55 8 INSTALLATION OF GROUND VENTIL ATION FAN To inst...

Page 412: ......

Page 413: ...and 16 to other lever at bot om of air selector valve shaft in manner shown n figure 4 l3 with 4 57 heavier Wlrlng and higher rated circuit breakers than the normal fan circuits When an aircraft is wi...

Page 414: ...o fans v Replace VENT fan circuit breaker on heating control panel with one of 20 ampere rating and Part 4 Paragraphs 4 56 3 to 4 56 4 one washer positioned between the two rod ends and another under...

Page 415: ...n sisting of interconnected fire etecting elements t o power amplification an controller units 4 59 COMB fan circuit breaker with one of 5 ampere rating w Install push pull rod 3 and connect push pull...

Page 416: ...TMENT PREHEAT INLET Figure 4 14 Engine Preheating Special Order Winterization Kit Installed 4MC 164 Part 4 4 60 2 PRIMARY METHOD OF ROUTING PREHEAT DUCT ALTERNATE METHOD OF ROUTING PREHEAT DUCT IF ACC...

Page 417: ..._ _ _ _ _ _ _ _ _ _ _ _ _ O_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ j _ _ _ _ _ _ __ Part 4 warning lights and electrical wiring The sys tem in each nacelle is divided into three zones...

Page 418: ...ement end fitting at each end of element d Unscrew and disconnect both end fittings from connectors Part 4 Paragraphs 4 59 to 4 59 2 TABLE 4 4 Cont INDICATION OF TROUBLE PROBABLE CAUSE CORRECTIVE ACTI...

Page 419: ...UNT LOWER STRUT Figure 4 15 Engine Fire Detecting System Pre Mod 4 1277 Revised 1 February 1969 4 63 I iii i TYPICAL ZONE 2 ELEMENT CONNECTION AUXILIARY FIREWALL Part 4 14 Im iii TYPICAL lEW OF ZONES...

Page 420: ...FOR CLARIT 4MC176 Figure 4 1SA Mod 4 1277 1969 Detecting System Revised 1 February EngIne Fire 4 64 Part 4 DETECTING ELEMENT DETECTING ELEMENT MAIN FIREWALL ELECTRICAL CABLE ASSY CONNECTOR CONNECTOR I...

Page 421: ...Close acces s doors 4 60 FIRE DETECTION CO TROLLERS Four fire detectio controllers two for 4 64A 1 r _r e Progressively release element from mount ing clips by removing screw and hinging clip free of...

Page 422: ......

Page 423: ...ns label are the two fire marked FlRE 4MC 1 Figure 4 16 Emergency Panel Revised 1 December 1965 4 65 each system are fitted for the left and right hand fire detecting systems each being interchangeabl...

Page 424: ...ng h Place electrical heater in direct contact with a four inch section of installed zone I fire de Part 4 Paragraphs 4 61 1 to 4 63 PULL which contain the fire warning lights for zones 2 and 3 A fire...

Page 425: ...ture 4 65 2 PRELIMINARY CIRCUIT CHECK To car ry out a preliminary circuit c eck of engine fire 4 67 tecting loop After approximately 30 seconds check that warning light glows i Repeat steps g and h fo...

Page 426: ...l power source 1 Remove test lamps from fire extinguisher bottle connectors Revised 1 February 1972 Part 4 1 MAIN FIREWALL CONNECTION 2 ZONE 3 DISCHARGE NOZZLE RH ENGINE 3 SINGLE SHOT DISCHARGE LINE T...

Page 427: ...ISHER BOTTLE FLOOD VALVES remove flood valves from fire extinguisher b ttle proceed as follows 4 69 m Check color coding on connector leads and attach leads to respective valves on left and right hand...

Page 428: ...trical connectors from LH fire extinguisher bottle Pull LH fire extinguisher Revised 1 February 1972 Part 4 Paragraphs 4 66 5 to 4 67 a Insure battery and external power source are disconnected b Work...

Page 429: ...l plug is fitted and is sim lar to that fitted in the engine fire extinguisher ottles Refer to 4 71 control handle and turn RH fire extinguisher control handle to second shot position and pull Check t...

Page 430: ...lve in the mask while exhaling re verses this process These movements automati Revised 25 JulY 1968 Part 4 Paragraphs 4 70 1 to 4 73 1 paragraph 4 66 It is necessary to weigh heater fire extinguisher...

Page 431: ...I charging or servicing the consta t flow oxygen system observe precautions to prevent damage 4 73 cally start and stop oxygen flow so that only the amount of oxygen demanded is delivered 4 73 2 REMO...

Page 432: ...TLET 13 PILOT S CONSTANT FLOW OUTLET 5 OXYGEN MASK CONTAINER 14 REGULATOR VALVE RELIEF VALVE 0 PI Ii I 1 0 1 J Ul 1 c 1 1 r Ii PI Ii 0 C1 0 1 OQ s Ii 1 I 0 s rn PI a 1 0 OQ 1 s t Il rn 1 S a 13 1 I 1I...

Page 433: ...As an alternative method of cha ging to this pres sure the bottle can be remo ed charged away 4 75 to aircraft or injury to persons by fire and ex plosion as follows a Make sure personal clothing han...

Page 434: ...e reverse removal procedure On com pletion of installation proceed as follows Revised 1 August 1963 Part 4 Paragraphs 4 75 1 to 4 76 2 from the aircraft and reinstalled Should the pressure fall to les...

Page 435: ...red from the regulator to t e outlet and with a mask connected to the outlet the check valve is 4 77 a Charge system Refer to paragraphs 4 74 1 and 4 74 2 b Check for leaks at connections with bubble...

Page 436: ...e same as those given for the constant flow oxygen system in paragraph 4 74 1 Revised 1 August 1963 Part 4 Paragraphs 4 79 1 to 4 BOA 1 opened and oxygen flows to the mask Discon necting the mask from...

Page 437: ...20 SPLASH GUARD 21 OXYGEN SHUTOFF VALVE 22 OXYGEN SUPPLY LINE TO CREW _ CHIEF S REGULATOR tJ PI 1 r c 1 01 1 0 JQ s 01 r 0 0 W I I 00 t 1j JQ s 1 CD I 00 tj aCD 1 tj CD SPI l 0 JQ CD l en Ul r CD S 1...

Page 438: ...from self opening oxygen valve in cylinder neck Blank coupling and valve port Revised 1 August 1963 Part 4 Paragraphs 4 BOA 2 to 4 BOB 1 4 BOA 2 CHARGING The diluter demand oxygen system is charged th...

Page 439: ...to e ght parts water Wipe off thoroughly on comp etion with damp cloth Turn off oxygen supply 4 78C IWARNING I Handle a charged cylinder with care A brok en self opening oxygen valve can cause cyl ind...

Page 440: ...olate cylinder pres sure from system and dissipate pressure from system lines Revised 1 August 1963 Part 4 Paragraphs 4 80E to 4 80F 1 4 80E OXYGEN REGULATORS Three identical oxygen regulators are pro...

Page 441: ...tem and regulator indicators should read zero d Repeat steps a through c at least three times 4 78E c Discormect lines from check valve d Discormect clamp and remove check valve Blank opening s 4 S0F...

Page 442: ...o z i u z w J X o Z 0 E a a I ECIl Figure 4 1SB 32 Passenger Oxygen System Revised 1 February 1969 Part 4 4 7SF w I J o Z w J X o I a w o z i u z w J X o Z 0 E a a I ECIl Figure 4 1SB 32 Passenger Ox...

Page 443: ...REGULATOR COPILOT REGULATOR SHUTOFF VALVE VALVE L u un t ut n uv Lot i CREW OXYGEN CYLINDERS tl 1 1 0 CIl Q 1 go 21 1 0 0 1 0 O n n s til 0 fIl a s til 0 g S S 1 1 Il l 1 1 I J O a N tl 1 1 fIl CIl s...

Page 444: ...equired according to the alti tude of the aircraft No external adjustments are Revised 25 July 1968 Part 4 Paragraphs 4 801 to 4 80J IWARNING I Aircraft must be in a well ventilated area with aircraft...

Page 445: ...al On completion of installation turn on oxygen system shutoff valve and chec connections for 4 781 provided and the regulators require no servicing other than to keep clean and free from oil and grea...

Page 446: ...at relays are energized power is applied from the secondary bus through two 70 Revised 25 July 1968 Part 4 Paragraphs 4 80M to 4 82 1 leaks with bubble fluid LAC598 Turco Products Ltd using one part f...

Page 447: ...N ENTS IN NACELLE 23 PROPELLER DE ICING SLINGER RING AND NOZZLE 24 RH WING PRESSURE MANIFOLD ItJ I 1 0 It III It Ilo t I It 0 It It 1 0 0 Ut J 0 H I j OQ 1 It I 0 a I 0 sOQ I s Ilo t I It I 0 til III...

Page 448: ...deliver output power to the windshields to maintain a constant operating 4 80 Revised 1 August 1963 Part 4 Paragraphs 4 82 2 to 4 83 ampere circuit breakers to the inverters Each inverter output is fe...

Page 449: ...MINAL 12 OUTPUT BLOCK 13 COVER TRANSFORME g CcR TRA N W TOR PLUG CL ontrolled Inverter 4MC 170 4 81 2 I 3 Figure 4 20 Windshield C 1 COVER 2 3 TRANSlfy000LING FIN COVER RS 4 FUSE ASSEMBLY Part 4 4 _ 5...

Page 450: ...D CIRCUIT RESISTANCE EQUIVALENT 40 0 45 1 ohms 44 1 49 9 ohms 48 9 54 0 ohms Revised 1 January 1965 Part 4 Paragraphs 4 83 I to 4 83 3 temperature of 105 5 F the power required being proportional to o...

Page 451: ...h A i c t D t _ E __ B MS310IB 24 IP M53110111 22 MHID Figure 4 20A DC Power Test Box IIMC In 4 82A 4 83 4 AIRCRAFT WIRING TESTS Prior to in stalling the windshield controlled inverters per form the f...

Page 452: ...efer to paragraph 4 88 4 84 WINDSHIELDS Provision is made for a plastic wind Revised 1 January 1965 Part 4 Paragraph 4 83 5 to4 84 to the NORM position and check that the light on the test box comes o...

Page 453: ...ete with Iwires f Unsolder wires from relayrrminalS Identi fy wires to facilitate reconnecti n 4 83 shield pre mod 4 1151 or a glass windshield Mod 4 1151 Power is supplied for windshield heating by o...

Page 454: ...RELAY To remove either pitot relay proceed as follows a Insure all aircraft electrical power is off Part 4 Paragraphs 4 87 6 to 4 89 1 4 87 6 INSTALLATION OF WINDSHIELD SENS ING CONTROL RELAY To insta...

Page 455: ...s and the suction action of t e air pumps is nullified Simultaneously the sol noid of the dual 4 85 b Lower cabin roof upholstery aft of cabin flight compartment bulkhead to left of aircraft centerlin...

Page 456: ...MCt7t Figure 4 21 Wing and Tail De icing System Schematic Sheet 1 of 2 4 86 Revised 1 December 1965 Part 4 PR URE rmli MANIFOLD TO OPPOSITE WING ENGINE AIR SUPPLY DISTRIBUTOR VALVES AND BOOTS ENGINE D...

Page 457: ...172 Figure 4 21 Revised 1 December 1965 Wing and Tail De icing System Schematic Sheet 2 of tl 4 87 Part 4 I I 11 C I I OUTER B U l r i OUTBD OFF r Ah LLl r iI INNER on OUTER I 0 INBD OFF RH OUTBOARD...

Page 458: ...witches to inflate and deflate the boots in any sequence and for any period Revised 1 December 1965 Part 4 Paragraphs 4 91 2 to 4 91 4 purpose valve is energized both pre and post Mod 4 1 262 and the...

Page 459: ...shaft Reconnect hfse to boot I Replace distfibutor valve Refer to par graphs 4 93 1 and 4 93 2 4 89 4 91 5 TROUBLE SHOOTING WING AND TAIL DE ICING SYSTEM TABLE 4 9 Part 4 Paragraph 4 91 5 TROUBLE SHOO...

Page 460: ...4 100 3 and 4 100 4 Replace pUIIlp Refer to paragraphs 4 98 2 and 4 98 3 Revised 1 DeceIIlber 1965 Part 4 INDICATION OF TROUBLE Pressure indicator reads low with both engines running Pressure drops r...

Page 461: ...ed to the wing and horizontal stabilizer lead ing edges with cement EC 14031 Minnesota Mining 4 90A 4 91 6 TESTING At periods defined in the in spection requirements and when it is anticipated that th...

Page 462: ......

Page 463: ...ximately 0 50 inch beyond repair patch I i o not inflate boot for fot r hours repaIr following 4 91 and Manufacturing Co Each boot edge is sealed with cement A 56 B B F Goodrich Two boots are bonded t...

Page 464: ...transducer Left and right hand outboard sections of wing leading edge only Revised 1 February 1972 Part 4 Paragraph 4 92 3 4 92 3 INSTALLATION TcHnstall a de icing boot see figure 4 22 and proceed as...

Page 465: ...s TEMPLATE AIR COt lNECTORS ALIGNEp WITH HOLES I AIR CONN ECiJ ORS INSIDE LEADING ED E 4MC 173 4 93 Part 4 DE ICING BOOT CENTERLINE 5 COMPLETE BONDING V BY REACTIVATING REMAINING AREAS OF BOOT AND LEA...

Page 466: ...e icing boot control circuit Function test wing and tail de icing system Refer to para graph 4 91 6 Part 4 Paragraphs 4 93 to 4 94 2 t Install stall fence and stall bar on wing leading edge Left and r...

Page 467: ...c Disconnect flexible hose from elbow fitting at suction relief valve Blank disconnected hose 4 94A I 4 95 DE ICING SUCTION RELIEF VALVE A suction relief valve is fitted in each air supply for the en...

Page 468: ......

Page 469: ...union fitted to the top of tpe valve body is connected by flexible pipes to th pump outlet and 4 95 d Remove lockwire and remove four bolts at taching suction relief valve to mounting bracket Remove v...

Page 470: ...gure 4 23 Wing and Tail De icing System Components in Nacelle 4MCt74 4 96 Revised 1 December 1965 r Part 4 1 PRESSURE MANIFOLD 2 SUCTION MANIFOLD 3 PRESSURE LINE CHECK VALVE 4 PRIMARY OIL SEPARATOR 5...

Page 471: ...g from rear of air pump remove gasket and fi ter c Wash oil filter in a dry cl aning solvent in 4 97 to the primary oil separator Air is relieved over board through an elbow union and a rubber hose co...

Page 472: ...oa d adapter pipe 4 100 2 MAINTENANCE OF COMBINATION UNIT FILTER The filter in the combinatiQn unit Part 4 Paragraphs 4 98 2 to 4 100 2 suring that all foreign particles are removed Rins e filter in c...

Page 473: ...blade shank The pres sure supp y pump is driven by an electrical motor which s controlled by a 4 99 once removed cannot be reinstalled Maintain the unit as follows using a replacement filter at period...

Page 474: ...p to which is attached the air supply line pressurize de icing tank to 3 psi Close air supply valve Part 4 Paragraphs 4 102 1 to 4 103 2 propeller de icing switch mounted on the de icing panel 4 102 1...

Page 475: ...TLET 20 FLUID SUPPLY LINE TO fROPELLER 4MCI75 Figure 4 24 Propeller De icing Tank and Package 4 101 20 _ PROPELLER BLADE 16 1 DE ICING TANK 2 CRADLE STRAPS 3 SPILL TRAY 4 PUMP 5 MOTOR 6 RELIEF VALVE 7...

Page 476: ...and persons must be protected from fumes ariSing from the liquid Any taken orally may cause death T Part 4 Paragra phs 4 103 3 to 4 106 1 Note After pressurization a fall or rise inpres sure may occur...

Page 477: ...on but before insta1 The propeller de icing pump is fitted ling outer wing fixed leading e4ge 4 103 e If a new filter is not available examine filter for evidence of damage Examine seals for deterio r...

Page 478: ...hut down engines Check surface of pro peller blades for satisfactory distribution of de iCing fluid Part 4 Paragraphs 4 lOB to 4 110 d Check for leaks then install outer wing fixed leading edge Refer...

Page 479: ...embly 5 72 Carburetor Hot Air f evers 5 73 Carburetor Hot Air ontrol System Push Pull R ds 5 74 5 1 I Part 5 Table of Contents PART 5 POWER PLANT AND RELATED SYSTEMS Paragraph Page 5 1 5 2 5 3 5 4 5 5...

Page 480: ...ntrol Relay Box 5 160 5 161 5 165 5 167 5 167 5 167 5 167 5 168 5 168 5 168 Revised 1 December 1965 Part 5 T able of Contents Paragraph 5 68 5 69 5 70 5 71 5 72 5 73 5 74 5 75 5 76 5 77 5 78 5 79 0 80...

Page 481: ...ting Syste Servicing of Reversible Part 5 able of Contents Page Propeller System 5_ 170 1 5 170 5 ZA Paragraph 1 5 146 5 147 Propeller J unction Box Reversible Propeller Reversing System Revised I Dec...

Page 482: ......

Page 483: ...ss reo Check booster pump pressure Check fuel lines connections joints and clamps for tightness 5 3 5 1 GENERAL The information contained in this part provides the neces sary instructions for the oper...

Page 484: ...20 FUEL PUMP DRAIN LINE Figure 5 1 Power PLant Arrangementl Sheet 1 of 2 5 4 Revised 1 June 1 70 I Part 5 2 1 CARBURETOR 20 19 18 17 2 CARBURETOR AIR INTAKE ADAPTER 3 INDUCTION VIBRATOR 4 CARBURETOR...

Page 485: ...ELLERS ONLY 1 Figure 5 1 Power Plant Arrangement Sheet 2 of 2 Revised 1 December 1965 Part 5 LEX 5 5 37 21 HYDRAULIC PUMP 30 FIRE DETECTING ELEMENTS 22 MANIFOLD PRESSURE LINE 31 PROPELLER GOVERNOR 23...

Page 486: ...plines for g lling and cracking Reinstall prop ller and tighten propeller retaini Replace propeller Pa rt INDICATION OF TROUBLE Improper idling I iluJ tu start Huugh f urol1Jng HOIJgh running 1 tiluJ...

Page 487: ...eck latch adjustll lent Adjust as necessary on shear pin nut until correct tension is achiE ved 5 7 Part 5 Paragraphs 5 3 to 5 4 2 TABLE 5 1 Cont INDICATION OF TROUBLE Rough running PROBABLE CAUSE Unb...

Page 488: ...18 ACCESS DOOR ENGINE BREATHER DRAIN BOX 19 BOTTOM COWLING Figure 5 2 Engine Cowlings 8 lj J 4M 192 Part 5 i II ii i c 1 HINGE ARM STUD 2 HINGE ARM 3 HINGE BRACKET 4 ROCKER BOX 5 EYE BOLT 6 CHECK NUT...

Page 489: ...sing step e of paragraph 5 6 1 b Connect electrical cable 6 figure 5 3 to actuator receptacle 14 5 9 c When replacing a fastener remove Cherry rivets as necessary from inner skin to provide access to...

Page 490: ...UATOR 15 MOUNTING BRACKET 1 Figure 5 3 E ngine Accessory C 4MC 1 3 a lOn System ompartment Ventil t Pait 5 5 10 UPPER VENT DOOR HINGE ARM 3 TENSION SPRING 4 CABLE 5 CABLE CONDUIT ELECTRICAL CABLE 8 LO...

Page 491: ...freight loading steady strut to external attach ent on underside of fuselage at station 414 00 5 11 c Connect an external source of electrical power to aircraft and extend actuator fully by selecting...

Page 492: ...nect oil tank vent oil pressure el pressure manifold pressure carburetor va Revised 1 February 1 69 Part 5 Paragraphs 5 8 2 to 5 8 3 IWARNING I Always support the rear fuselage when re moving a quick...

Page 493: ...d Route propeller de icing lOne if applicable from rear of cylinders to spinn r afterbody posi 5 13 vent and oil dilution lines at main firewall Dis connect propeller de icing and air pump sur tion a...

Page 494: ...ent nut pOSitions d Loosen screws holding rotate adapter to required screws Revised 1 February 1969 Part 5 Paragraphs 5 8 5 to 5 8 7 tion passing through seal and between cylinders No 6 and No 7 Clip...

Page 495: ...asket fro m fuel pwnp mounting pad clean mou ting pad and place a serviceable gasket over stud 5 14A e Clean face of generator mating surface and install generator on engine Tighten nuts to a torque o...

Page 496: ...1 1...

Page 497: ...gasketo to carburetor e Install main fuel inlet elb w to carburetor f Install carburetor super 5 15 d Clean face of fuel pump mating surface and install fuel pump on engine 11 5 8 9 Install propeller...

Page 498: ...d Specification MIL C 16 73 Grade 2 Nuts must be installed wit out lubricant Revised I Februar 1969 Part 5 Paragraphs 5 8 15 to 5 8 18 charger throat mounting face and secure with bolts Tighten bolts...

Page 499: ...der d Disconnect propeller con rol at governor on aircraft with nonreversible propellers then 5 l6A b Rig engine controls Refer to paragraphs 5 45 5 54 5 63 and 5 73 c Jpen fuel oil and hydraulic syst...

Page 500: ......

Page 501: ...r doors Closed m3 Do not lock passenger doors fter closing q Emergency exits Closed a d secure 5 17 rerrtove support brackets frorrt rrtagneto and clips frorrt No 3 cylinder exhaust valve pushrod cove...

Page 502: ...3 Do not prime prior to this stage as an in take manifold fire may result Revised I Februar 1969 I Part 5 Paragraphs 5 9 2 to 5 9 3 r All switches Off s Circuit breaker panel Check All circuit breake...

Page 503: ...both en gines are running satisfactor 1y continue as follows a Fuel booster pump switches OFF 5 19 Not With the engines either hot or cold hold the pri mer and vibrator switches on steadily and maint...

Page 504: ...ck and adju t tnix ture strength as instructed in paragraph 5 96 4 and 5 96 5 Revised 1 Ju e 1970 I Part 5 Paragraph 5 9 7 b External power unit Order disconnected Check clear of aircraft c Battery tn...

Page 505: ...ure lever AUTO RIC Throttle Advanc e to full hrottle Rpm 2 700 rpm Manifold pressure 50 in Hg 5 20A j Idle speed check Throttles Closed Mixture levers AUTO RICH Rpm 550 25 Generator warning lights sho...

Page 506: ......

Page 507: ...rse rubber in solvent as excessive use of s lvent will dam age bond between rubber and me 1 5 21 1 I r I Part 5 Paragraph 5 9 7A to 5 11 3 5 9 7A FLIGHT COMPARTMENT CHECK AND external power supply if...

Page 508: ...to engi e rigid mounting bracket Do not tighten nut 4MC f95 Figure 5 5 Vibration Isolator 5 22 T I Part 5 Paragraphs 5 10 4 to 5 10 5 b Wa h metal parts with dry cleaning solvent c Magnaflux housing...

Page 509: ...when closed to div de the engine in stallation into two compartme s for fire control purposes 5 23 b Screw thread protector bullets on vibration isolator bolts Install engine in engine mount as sembl...

Page 510: ...AL 4M 196 Figure 5 6 Auxiliary Firewall Engine Mount and Seal Assembly 5 24 Revised 1 February 1969 Part 5 2 ASSEMBLY OF ENGINE MOUNT AND FIREWALL MOD 4 1140 INSTALLATION OF OUTER AND INNER ENGINE MOU...

Page 511: ...Refer to para graph s 5 2 1 1 an 5 21 2 Check and replac Refer to para graphs 5 21 1 an 5 21 2 5 25 r 5 13 1 REMOVAL a Open engine cowlings b Disconnect Zone 1 fire detecting elements at aft side of f...

Page 512: ...Inagneto and Inagneto to en ine tiIning Refer to paragraphs 5 16 4 and 5 16 5 for these procedures Pc rt 5 Paragraph 5 15 to 5 16 2 TABLE 5 2 Cont INDICATION OF TROUBLE PROBABLE CAUSE CORRECTIVE ACTI...

Page 513: ...NAL NETO BEFORE INST a Remove breaker c 4MC 197 Figure 5 7 Location of Magneto to Engine Timing 5 27 I 5 16 3 LOCATION OF MAGNETO TO ENGINE TIMING POSITION a Remove front spark plug from No 1 cylinder...

Page 514: ...r and notch If c ting pointer is on early side of notch tu Figure 5 8 Magneto to Engine Timing 5 28 Part 5 Paragraph 5 6 5 b Connect timing light B 1 across breaker points by attaching a red lead to b...

Page 515: ...center 5 17 1 REMOVAL a Disconnect electrical conn ctor b Slacken four nuts securing top plate 5 29 justing ratchet clockwise two serrations for each mark between notch and edge of pointer Not Because...

Page 516: ...di tri butor block housings ignition leads and scre ned covers The harness is designed to permit re Part 5 Paragraphs 5 17 2 to 5 18 c Slacken four nuts securing body flange then undo four mounting st...

Page 517: ...o and four bolts atta hing distributor housing to manifold d Remove spark plug spring c sleeve 5 31 placement of faulty individual leads The mani fold is bolted to the front crankcase section studs an...

Page 518: ...ces s hole in auxiliary firewall ull conduit over wire from front of engine Revised 1 February 1 69 Part 5 Paragraphs 5 18 6 to 5 20 2 adapter spark plug elbow elbow grommet con duit and manifold outl...

Page 519: ...barrel Place a rotector cap over spring connector c Rem ove spark plug PWA316S special wrench 5 33 Part 5 Paragraphs 5 20 3 to 5 21 1 1 ADAPTER 5 IN ULATING TUBE 2 INSULATING SLEEVE 6 C NTACT 3 TERMI...

Page 520: ...ends of the slots and lift ing over the loosened nuts 5 23 1 MAINTENANCE AND REPAIR To in ure 5 34 Part 5 Paragraphs 5 21 2 to 5 23 1 d If spark plug is seized in cylinder make a conical metal funnel...

Page 521: ...air will mix proportionately to lever selecti 5 25 2 TROUBLE SHOOTING TION SYSTEM AIR INDUC 5 35 1 proper operation of the starter make following checks periodically a Visually examine starter for fa...

Page 522: ...CTUATOR 12 ALTERNATE AIR VALVE ADJUSTABLE TIE ROD 13 ALTERNATE AIR VALVE 14 HOT AIR INLET 0 Pl 1 J1 i Jl I W 0 trj Q 1 I 1l 1 5 0 o o l C l I S t J o 0 o i l Q 1 RAM AIR VALVE ADJUSTABLE TIE ROD 2 RAM...

Page 523: ...or oper ates the raIn air valve while t e right hand actu ator operates the alternate ai valve 5 37 Part 5 Paragr phs 5 26 to 5 27 TABLE 5 4 TROUBLE SHOOTING AIR INDUCTION SYSTEM INDICATION OF TROUBLE...

Page 524: ...6 ALTERNATE AIR VALVE 4 90 Figure 5 12 Air Induction System Schematic 5 38 Revised 1 December 1965 Part 5 ____ I 6 2 RAM AIR UNFILTERED 6 FROM SIDE DUCTS THROUGH FILTERS FILTERED AIR 2 3 5 T CARBURET...

Page 525: ...9 1 REMOVAL a Remove two screws s curing cover at both ends of valve b Disconnect actuating li 5 39 5 27 1 REMOVAL OF RAM AIR VALVE ACTU ATOR a Raise top cowling and remove actuator access panel locat...

Page 526: ...end of rod and adjust tie rod length by turning tie rod up to two complete t rns Revised 1 December Part 5 Paragraphe 5 29 2 to 5 30 3 c Relnove two screws securing hinge bracket at each end of valve...

Page 527: ...ose lower valv Connect tie rod to each valve lever insuring va ves are maintained in position 5 41 1 tie rod has left and right hand threads If adjust ment requires more than two turns readjust rod to...

Page 528: ...BLE TIE ROD 9 VALVE OPEN STOP 10 BEARING HOUSINGS 11 VALVE CENTER TUBE 12 SHAFT END PLUGS 1 ru 1 J1 I J1 I N t j Q 1 1 J1 I W 1 S L o o 1 C l 01 1 S 1 Q III 1 01 S01 III e o 1 n N o 2 I VALVES SHOWN I...

Page 529: ...14 and 1 k Torque load front and rea port flange nuts to 125 170 po cylinders exhaust d inches 5 43 I k If tie rod bearing ends do not align with levers release locknuts and adjust tie rod length main...

Page 530: ...FORWARD SECTION 18 STRAP ASSEMBLY 19 ANGLE MOUNT n l 15 1ID II itIIIm 7 8 I 10 1 r CYL NO 8 C P t 01 I I U1 I t j JQ 0 1 01 I trI X r IIJ en C en 1 S 0 0 IIJ s JQ 1 S 1 18 19 1 EXHAUST AUGMENTOR TUBE...

Page 531: ...Retens on and rig contro system Refer t paragraph 5 54 Retension cable Refer to para gr ph 5 45 5 45 1 Take up slack on remaining hardware through system Do not tighten m Run engine for 30 minutes to...

Page 532: ...45 and 5 45 4 Check carburetor control arm slow running adjustment stop push pull rod if necessary Part 5 INDICATION OF TROUBLE Control movement feels rough and erratic Control creep Not applicable t...

Page 533: ...i Operate gust lock contr 1 lever until gust lock quadrant is clear of fri tion disk retaining 5 47 Ir Part 5 5 35 to 5 35 1 TABLE 5 5 Cont INDICATION OF TROUBLE PROBABLE CAUSE Propeller control feels...

Page 534: ...Propeller Mixture and Friction Levers A sembly Nonreversible Propellers 5 48 Revised 1 December 965 Part 5 shaft and push shaft to right to free it from its left hand outboard hanger fitting j Note di...

Page 535: ...ropeller Mixture and Friction Levers Assembly Reversible Propellers Revised 1 December 1965 5 48A t ahaft and secure with screw Part 5 Paragra ph 5 35 1A 5 35 lA REMOVAL LEVERS NONREVERSIBLE PROPS See...

Page 536: ...fts Install eight bolts through cha els and hangers secure with washers and Revised 1 December 19 5 Part 5 Paragraph 5 35 2 15 35 2 INSTALLATION LEVERS NONREVER SIBLE PROPS a Insur e each control leve...

Page 537: ...cy lever mounting holt from attachment on front spar and allow lever to hang clear on c Ole i 1 5 49 To avoid fouling of controls the eight bolts retaining hangers to console structure must be inserte...

Page 538: ...LE FULCRUM M 18 6 Figure 5 16 Engine Controls Arrangement Sheet 1 of 4 5 50 Revised 1 December 1 65 Part 5 I STATION 108 1 THROTTLE PROPELLER MIXTURE LEVERS 2 PUSH PULL RODS 3 IDLEF PULLEYS TOP CABLES...

Page 539: ...T iu M Figure 5 16 Engine Controls Arrangement Sheet 2 of 4 Revised 1 December 1965 4MC207 5 51 _ _ Part 5 CARB HOT AIR TOP THROT BOT CARB HOT AIR BOT PROP TOP 0 0 MIX TOP PROP BOT MIX TOP j CARB HOT...

Page 540: ...PROPELLERS M 1818 Figure 5 16 Engine Controls Arrangement Sheet 3 of 4 5 52 Revised 1 December 965 Part 5 RH MIXTURE I lm FRONT FACE OF WING CENTER SECTION FRONT SPAR RH PROPELLER RH THROTTLE _ LH CA...

Page 541: ...ENT Figure 5 16 Engine Controls Arrangement Sheet 4 of 4 Revised 1 December 1965 Part 5 M 1819 5 52A PROPELLER CONTROLLER MECHANICAL HEAD REVERSIBLE PITCH PROPELLERS i ii PROPELLER PITCH CONTROL TELEF...

Page 542: ......

Page 543: ...from e ch front pulley and remove spacer and pulleys from each outer torque tube splined end 5 53 r_ f At engine remove cooling duct from engine driven generator and air pump g Disconnect torque tube...

Page 544: ...re us ed for the right engine the inboard inner torque t and rear inboard pulley are used Revised 1 Part 5 Paragraphs 5 36 5 to 5 37 f UsinE mallet tap each pair of inner and outer torC ue tubes free...

Page 545: ...throttle friction lever from outer pivot shaft by releasing set screw and with drawing lever 5 54A 5 38 THROTTLES I On aircraft with nonreversible propell ers each throttle figure 5 15 is a lever of...

Page 546: ......

Page 547: ...upper guide roller from bra ket at rear end of console to left of ca buretor hot air levers 5 55 r_ d Remove external ring lock ring spacer washer and hanger e Remove adapter and left hand throttle th...

Page 548: ...rs and cable guard pin if pulley remove is one of several on a single shaft Revised 1 December 1 65 Part 5 Paragraphs 5 39 2 to 5 40 3 5 39 2 n TALLATION To install a throttle con trol system push pul...

Page 549: ...s be fore fitting cable guard pin ee figure 5 16 Do not use lubricant on pulle s or pivot bolt 5 57 5 40 4 To remove a throttle cable attachment pulley from rear end of a torque tube proceed as follow...

Page 550: ...is found b Inspect terminal ends for damaged thr ads First two threads may be cleaned up if dam ged Part 5 Paragraphs 5 40 8 to 5 41 2 c Attach cable terminal ends to turnbuckle barrels d Rig and tens...

Page 551: ...e bolts attaching damaged rubbing block to structure frame c Cut rubbing block free of cable s 5 59 Reject cable if more threads are damaged c Inspect swaged ball end for damage and in sure that ferru...

Page 552: ...ips d Check throttle control system push pull ro s in overhead console for a nominal length of 28 5 Part 5 ParagraphE 5 43 to 5 45 Note Rubbing blocks are in one piece and are as sembled to the airfra...

Page 553: ...ine Controls Overhead Console Rigging Fixture Nonreversi Ie Propellers Revised 1 February 1969 5 61 inches Do not adjust rod length at this time of reasonably close to normal measurement e Install rig...

Page 554: ...65 TEMPERATURE of 4MC21 Figure 5 18 Engine Controls Cable Tension Chart 5 62 Revised 1 February 196 Part 5 1 RIGGING FIXTURE AFT PORTION 2 RIGGING FIXTURE CLIP 3 LEVER ALIGNING PIN 4 CARBURETOR HOT AI...

Page 555: ...5 45 3 Check that spring bac at each end of throttle travel is 0 2 inch m asured at center 5 62A j Adjust as necessary See figure 5 20 for air craft with nonreversible propellers or figure 5 20A for...

Page 556: ......

Page 557: ...19 Engine Controls Torque Tube Control Levers Rigging Fi ture Revised 1 December 1965 411C211 5 63 of throttle control knob If spring back is non existent or excessive at one end of throttle travel c...

Page 558: ...I1 t tr Hf 4 0765 I Ii t THROTT LE CLOSED _ I i CARBUR ETOR I I I J L i i I I i PLATE 1 PJ rt r 111 111 I a 1 JQ 1 1 VI N T 1 0 0 s 1 0 C I III S c JQ JQ s JQ 0 S sIII 0 sIII Z0 s 1 0 1 III C III p 1...

Page 559: ...I_CARBURETOR I J i I I I THROTTLE OPEN rTH L E e y PUTE CARBURETOR THROTTLE ARM SETTING tI II 1 U1 I I I I rI I I 0 CD rn CD 0 o Dil CD 1 CD CD U1 CD N 1 0 0 1l iT 1 C CD 0 g 1 0 J rn CD S 0 IJQ IJQ...

Page 560: ...tube and rear pulley From the actuating arm at the forward end of the orque Revised 1 December 965 Part 5 Paragraph 5 46 b Insure that all rigging pins fixtures and other ha rdware used for check are...

Page 561: ...n pulleys in a similar m anner to those of t e throttle control system Refer to paragraph 5 41 5 65 tubes the system movement is transmitted by I teleflex control to each propeller governor on aircraf...

Page 562: ...ts and kinks and insure t at special teleflex conduit test ball bearing pas Revised 1 December 1 65 Part 5 Paragraphs 5 50 1 to 5 53 2 5 50 1 E MOVAL CHECKING AND INSTAL LATION Removal preinstallation...

Page 563: ...k propeller levers for synchron zation Adjust ad justable idler arm fulcrum rad s as necessary 5 67 through conduit easily If new teleflex control is to be installed bend conduit with cable inserted t...

Page 564: ...I l 1 _ 7 _or CENTER LINE f OF GOVERN OR RM SETTIN G GOVE R NOR CONT ROL ARM SETTIN GS U PJ 1 rl U1 J1 cr 00 JQ I 1 IJI N 1 1 i 0 d 1 1 i 0 I rt i 0 Ul III rt 1 S 0 JQ JQ I JQ t SCD I III 0 I III Z0...

Page 565: ...s incorrect rig and ten s ion propeller control system Refer to paragraph 5 54 Revised 1 December 1965 _ Part 5 Paragraph 5 54 1 to 5 54 Z i Check spring back at both ends of propeller lever travel Sp...

Page 566: ...E IDLER ARM SETTIN G PROPE lLER CONTR OL ARM SETTIN G m 0 II 1 Cl fit Cl 0 l I q tJ 1 Cl Cl 0 Cl U1 S I N 0 Cl 1 0 J 1 0 0 U1 Cl Cl 1 0 s 1 0 Ul Ul Cl 3 I q I q sI q tJ 3Cl s Ul 0 s Ul Cl Cl 1 Ul 0 Cl...

Page 567: ...od is 28 37 inches measured betwee centers of bear ing ends Do not use lubric nt on bearings 5 69 t 5 54 3 To insure that range of travel of airframe mounted propeller controls agrees with 103 Idegree...

Page 568: ...anual mixture control arm dIe cut off position If it is necessary to spr g Revised I De cember 1 65 Part 5 Paragraphf 5 58 to 5 63 5 58 MIXTURE CONTROL SYSTEM PULLEYS The mixture control system pulley...

Page 569: ...NSIONS BETWEEN ARROWS ARE IN INCHES POSITION 5 5 r L t _ MANUAL MIXTURE CONTROL ARM SETTING d I 1 U1 Xl II til II a t II n II II 1 t j 0 a I Q U1 U1 I I s 1 II U1 I N N s 1 II 0 1 0 en til II 3 Xl I Q...

Page 570: ...is completed function te t carburetor air induction switches and panel light Revised 1 December 196 Part 5 Paragraphs 5 63 1 to 5 65 2 control red to insert bolts adjust as necessary e ReITlOVe riggin...

Page 571: ...ACKET 11 CARBURETOR AIR IN UCTION SWITCH 4MC2U Figure 5 23 Carburetor Hot Air Levers Assembly 5 73 5 66 CARBURETOR HOT AIR LEVERS The carburetor hot air levers figure 5 23 are of the bellcrank type a...

Page 572: ...stem Re fer to paragraph 5 42 5 70 1 REMOVAL AND INSTALLATION 0 FAIRLEADS Refer to paragraph 5 42 1 Part 5 Paragraphs 5 66 3 to 5 70 1 friction disk spacer tube assembly compres sion washt r spacer tu...

Page 573: ...contr 1 rod conduit end clamp and or bearing ends C eck bearing ends for safety if adjusted 5 75 r 5 70 2 REPLACEMENT OF RUBBING BLOCKS Refer to paragraph 5 42 2 5 71 CARBURETOR HOT AIR CONTROL SyS T...

Page 574: ...CONTROL LEVER SETTINGS 4MCZI Figure 5 24 Carburetor Hot Air Control System Rigging Dimensions 5 76 Part 5 1 67Y VERTICAL LINE OVERHEAD CONSOLE FORWARD I FRAME f I L I i f L 2 18 1 I I IY 750 1 REF lj...

Page 575: ...icator Replace transmitter Switch electrical connector to opposite indicator Replace indicator 5 77 e Check carburetor hot air levers for friction loading Refer to paragraph 5 66 3 f Reinstall all pan...

Page 576: ...ALING FUEL CELLS MC217 Figure 5 25 Fuel System Arrangement Sheet 1 of 2 5 78 Revised 1 Decembe 1965 Part 5 16 VENT FROM NO 10 FUEL CELL 17 FLEXIBLE COUPLING 18 INTERCONNECTING MANIFOLD 19 BOOST ER PUM...

Page 577: ...i il IM Figure 5 25 Fuel System Arrange 11 1 21 22 ment Sheet 2 of 2 Part 5 18 19 20 4MC2t8 5 79 i il IM Figure 5 25 Fuel System Arrange 11 1 21 22 ment Sheet 2 of 2 Part 5 18 19 20 4MC2t8 5 79...

Page 578: ...e pressure switch Check circuit breaker lamp l wir ing Replace as necessary Replace pressure switch Part 5 TABLE 5 6 Cont INDICATION PROBABLE OF TROUBLE CAUSE No fuel pressure engines Defective fuel t...

Page 579: ...OVAL a Drain fuel from affected tank b Remove acces s panel from appropriate cell comea rtment 5 81 Part 5 Paragraphs 5 75 to 5 77 1 TABLE 5 6 Cont INDICATION PROBABLE CORRECTIVE ACTION OF TROUBLE CAU...

Page 580: ...do not occur in the immediate area fittin or radius reinforcement Damage in Revised 1 February 969 Part 5 Paragraph 5 77 2 4MC219 PRE MOD 4 1162 MOD 4 1162 Figure 5 26 Fuel Panel c Discc nnect electr...

Page 581: ...UMP PLATE NO 1 FUEL CELL 39 FUEL BOOSTER PUMP 40 SNAP FASTENER FEMALE PORTION J lI 5 4 d III Ii U 1 V1 I X W I lj JQ r Ii 1 V1 I IV l I lj r 1 C1 1 In Ii Ii JQ 1 8 1 s en r 1 1 o IV 1 FLOAT 10 BODY 2...

Page 582: ...Part 5 co I C I M on I I 4M 221 Figure 5 27 Fuel Cells Arrangement Sheet 2 of 2 5 84 Part 5 co I C I M on I I 4M 221 Figure 5 27 Fuel Cells Arrangement Sheet 2 of 2 5 84...

Page 583: ...inimum of one inch from rib flange to prevent cell from coming in contact with angle of flange 5 85 areas or any cut exceeding one inch in length must be repaired by the manufacturer Repairs will be a...

Page 584: ...electrical connectors at ce Is d Disconnect bonding strip and cut and rem ve Revised 1 February 969 Part 5 Paragraphs 5 77 8 to 5 78 2 d Insure that tape is removed from vent tube holes in ribs and fa...

Page 585: ...drain pipe fitting as follows a Drain fuel tank h Remove filler neck Refer to paragraph 5 79 1 5 87 lockwire at interconnector manifolds Unscrew manifold flexible couplings including 3 4 inch coupling...

Page 586: ...flight maneuvers The fuel manifold branche in to two pipes to circuITlvent the access openi g in I Part 5 Paragraphs 5 79 4 to 5 82 c Disccr nect upper hose connection from drain pipe Cover open end...

Page 587: ...85 2 INSTALLATION To install a fuel booster pwnP reverse removal procedure then function pwnp 5 89 the compartment between cells No 5 and 6 and an interconnecting fuel feed pipe also joins cells No 5...

Page 588: ...uel tank selector switch on the fuel pan 5 89 1 REMOVAL a Operate wing flaps to fully DOWN position Part 5 Paragraphs 5 86 to 5 89 1 5 86 ENGINE DRIVEN FUEL PUMP An engine fuel pump is mounted on the...

Page 589: ...d reopen all fuel valves at least once during test e Repeat steps a through d for opposite side 5 91 b Connect external power supply place fuel tank selector switch in OFF position and fuel emergency...

Page 590: ...cell end until u tricted flow is apparent Remove restrictio reconnect piping Revised December 1965 I Part 5 Paragraphs 5 3 to 5 94 3 f On ccmpletion of test remove all blanks from venting system outl...

Page 591: ...ir temperature bulb and primer solenoid elec trical connectors by reversing removal pro cedure 5 93 c Install blanking plugs in open ends of venting system then pressurize to 10 psi Check all con nect...

Page 592: ...TER PIN 12 CASTLE NUT 12 11 10 9 8 7 Figure 5 30 Idle Mixture Adjusting M into the 2 3 4 5 6 4MC224 Part Paragraphs 5 96 3 to 5 97 Figure 5 29 Idling Speed and Idling Mixture Strength Adjusting Points...

Page 593: ...fuel priming unit is installed with fan to rear 1 Secure all lines and hoses between hot fuel 5 95 supercharger throat Excessive priming fuel is drained off to atmosphere through a supercharger drain...

Page 594: ...ASSEMBLY Figure 5 31 Special Order Hot Fuel Priming System Schematic l IGNITION ASSEMBLY ES MC22 5 Part 5 SOLENOID OPERATED CYCLING FUEL PRIMER VALVE SWITCH I III CARBURETOR PRIME CONNECTIONS FUEL DE...

Page 595: ...trical power connected to aircraft and booster pump and fuel prime switches set ap propriately 5 97 priming unit and carburetor in manner shown in figure 5 32 j Uncap and untie binding of electrical c...

Page 596: ...IILAI 21 FLEXIBLE HOSE 62410005 0160 LEn HAND HOT FUEL PRIMING SYSTEM INSTALLATION SHOWN I 1 J l V1 V1 I 00 JQ s 1 ro V1 I W N c o s ro d 1 S s JQ en 0 r t ro S El0 r t ill o s en r ro ro r t o N I 1...

Page 597: ...NNECTOR 46 NUT AN924 S 47 UNION AN81S 5D 48 GASKET MS29S1lo5 E R OID 8 l O o Ir i_ V 25 U III 1 111 Ul I 0 0 I j JQ 1 1 111 I N r o I j 1 U 1 S s JQ en III 1 3 s III III III o s en p 1 1 N o N 22 DUAL...

Page 598: ...f elect ical power to aircraft e Have appropriate booster pump switc on fuel panel switched to HIGH Part 5 Paragraphs 5 99 to 5 99 5 o Label drain and store unit and associated lines and connections 5...

Page 599: ...connection Check switch Check 400 cycle wiring to tank units and 400 cycle output of inverter 5 101 f Have prime switch on engine switch panel held over to appropriate L or R position and check that f...

Page 600: ...each tank unit and carry ut a capacitance test The capacity of each tank unit should be as follows Part 5 Paragraphs 5 100 3 to 5 100 6 TABLE 5 7 Cont I l DICATION OF TROUBLE PROBABLE CAUSE CORRECTIV...

Page 601: ...5 103 1 DC power Z7 5 volts is provided from the aircraft Z7 5 volts dc emergency bus through 5 103 No 1 18 4 0 5 mmf No 2 34 5 0 5 mmf No 5 31 1 0 5 mmf No 6 23 7 0 5 mmf No 9 24 1 0 5 mmf Total Emp...

Page 602: ...NO I FUEL CELL 4 1 228 Figure 5 33 Fuel Low Level Warning System Adjustment Revised 1 December 1 65 Part 5 Paragraph 5 103 2 to 5 103 3 the ENGINE INSTRUM circuit breakers on the MISCELLANEOUS electri...

Page 603: ...sure switch reverse removal procedure then proceed as follows a Connect external power source 5 105 a Drain fuelfrom tank on affected side of air craft b Pump 24 48 gallons US 20 40 gallons Imp of fue...

Page 604: ...mmed sliding valve or defective thermostat Clean val e or replace thermostat Revised I December 965 Part 5 Paragraphs 5 106 to 5 106 1 b Move mixture lever to IDLE CUTOFF c Move fuel tank selector swi...

Page 605: ...OX 26 ENGINE BREATHER LINES 27 HIGH PRESSURE OIL FEATHERING LINE 24 23 22 21 20 19 18 17 t II 1 r 11 xl ID III ID Po t l ID n ID ID i 0 11 11 o 0 I j JQ i ID 11 VJ 0 en III II 3 i s JQ II 3 II s Z0 s...

Page 606: ......

Page 607: ...ENGINE DRAIN AND BREATHER BOX 21 ENGINE BREATHER LINES 7 1 8 9 10 D 11 12 I I 13 C I 14 tJ III Ii U1 0 CD CIl CD P t I CD n CD g CD 1 0 0 lit VI o J z I OQ Ii CD lit Ul 0 Ul UI CD a 1 1 III OQ CD aCD...

Page 608: ...118 2 The oil pre sure may be adjusted only after the ent door has been adjusted and the il changed Part 5 INDICATION OF TROUBLE Oil temperature persistent ly low Oil pressure normal Oil temperature h...

Page 609: ...I a Run engine if practicable to warm oil so that oil will flow freely from tank when drained 5 109 INDICATION OF TROUBLE Oil pressure low indication at normal and or idling speeds Oil temperature nor...

Page 610: ...ER WALL 26 FEATHERING OIL RESERVOIR 27 HOPPER OUTER WALL 28 COVER SEAL RING Revised 1 December 1965 Part 5 1 J 24 21 20 ON TANKS USED WITH NONREVERSIBLE PROPELLER INSTALLATION ONLY SLIDING VALVE 17 TA...

Page 611: ...light compartment near the engine controls warning persons of condition of engine oil system 5 l10A b Drain oil from system by connecting a suit able hose to drain valve at bottom of oil tank and open...

Page 612: ......

Page 613: ...t exceeding three quarter inch in depth and hav ing a smooth contour showing no cracks may be 5 111 5 107 1A REMOVAL OIL TANK REVERSIBLE PROPS a Run engine if practicable to warm oil so that oil will...

Page 614: ...and ground ite chalk Allow mixture to dry and pour a thin ture of engine oil and kerosene into tank Part 5 Paragraphs 5 107 4 to 5 107 6 rectified without removing the oil tank Refer to paragraph 5 10...

Page 615: ...ested with or without the sequence valve installed a Seal off tank vent and dipstick aperture 5 113 k Attach nitrogen pressure rig paragraph 5 107 10 to filler neck and pressurize tank to a pressure n...

Page 616: ...sequence valve Refer to paragr ph 5 109 2 b Unscrew feathering oil adapter pipe Revised 1 December Part 5 Paragraphs 5 107 11 to 5 108 1 b Close drain valve c Seal off tank base or if sequence valve...

Page 617: ...ture Two bleed holes connect the hot and cold sides of the valve to insure that the oil level 5 115 tank base and remove c Remove 24 screws and washers from access plate 5 figure 5 35 and remove acces...

Page 618: ...of nacelle See item 39 figure 1 2 b Cut and remove lockwire and remove p g Revised I December I 65 Part 5 Paragraphs 5 109 1 to 5 110 1 in the feathering well of the tank is maintained I on aircraft...

Page 619: ...Fill and prime sys tem with correct specification and grade of oil Refer to paragraph 5 119 5 5 117 from top of oil cooler to allowventing when drain ing oil c Working inside main gear well cover com...

Page 620: ...hydr emergency shutoff valves The switch is gua ded to prevent inadvertent operation of the va ves p rt 5 Pilragraph 5 110 5 to 5 112 5 110 5 When oil cooler is not in stalled in the aircraft it is p...

Page 621: ...ED POPPET VALVE OPEN 4MC23 t Figure 5 36 Oil Cooler and Temperature Regulator Valve Schematic 5 119 CHECK VALVES PARTIALLY CLOSED NO FLOW THROUGH OIL COOLER THERMOSTATIC BYPASS VALVE CLOSING r fEE lZE...

Page 622: ...TE WIRELOCK BOLTS ON INSTALLATION 4 C232 Figure 5 37 Oil Emergency Shutoff Valve Installation 5 120 Part 5 Paragraphf 5 112 1 to 5 112 2 IWARNING I If the oil emergency shutoff switch is selec ted off...

Page 623: ...6 BOTTOM ATTACHMENT BRACKET 9 DRAIN VALVE 4r 1C233 Figure 5 38 Engine Drain and Breather Box 5 121 hon of valve paragraph 5 112 3 then fill and prime oil system with correct specification and grade o...

Page 624: ...lution procedur s de tailed in paragraph 5 116 m ust be strictly ad ered to Revised 1 December 1965 Part 5 Paragraphs 5 113 1 to 5 114 P main fin wall by three bolts The box is a welded stainless stee...

Page 625: ...ugh the valve body Both valves are locat ed adjacent to the oil tank in each main wheel well 5 122A 5 114B OIL DILUTION SYSTEM AIRCRAFT WITH REVERSIBLE PROPELLERS Aircraft fitted with reversible prope...

Page 626: ......

Page 627: ...on 5 116 2 OIL DILUTION OF OIL PRESSURE INDI CATING LINES Dilute oil pressure indicating line 5 123 5 115 1 REMOVAL The following procedure is typical for all oil dilution valve s a Disconnect feather...

Page 628: ...reheat using hot air is re quired to insure that the air pu p is heated to avoid shearing pump rive Part 5 Paragraph 5 116 3 for each engine at oil pressure switch bleed con nection on aft face of mai...

Page 629: ...to be obtained This requires the prevention of Qirt abrasives and other particles from enter 5 125 g At end of boil off period run engines upto take off power and check each engine drain and breather...

Page 630: ...l tank drain valve open valves and allow oil to d rain into a suitable container It is advisa Ie to P rt 5 Paragraphs 5 119 1 to 5 119 4 ing the oil 5ystem by oil contamination use of dirty conti irle...

Page 631: ...om the wing and tail de icing system when in stalled Otherwise two air pumps are installed by 5 127 vent oil cooler by removing oil cooler access panel and removing blanking plug from top of cooler b...

Page 632: ...NK NOTE UORMAL FUEL TRANSFER SHOWN Figure 5 40 Scheme 4 Long Range Ferry Fuel System Schematic 5 128 rt 5 DE ICER PRESSUR2 SHUT Of F VALVE CHECK VALVE PRESSURE GAGE r VENTTO ATMOSPHERE PRESSURE RELIEF...

Page 633: ...e all tie down straps from around ferry fuel tanks e Remove sight gages from ferry fuel tanks 5 129 S O O Mod 4099 The Scheme 4 system is com pletely removed from the aircraft when not in use with the...

Page 634: ...E Figure 5 41 Scheme 4 Lqng Range Ferry System Fuel Management Panel 4 C236 Revised 1 February 1969 P rt 5 o 5 130 LEFT HAND WING TANK SHUT OFF VALVE FERRYING SYSTEM FUEL MANAGEMENT PANEL IIt Ab J _ P...

Page 635: ...ings D3 and D5 with two bolts and wash ers Wirelock bolts to cradle with 0 041 inch lockwire 5 l30A f Roll ferry fuel tanks out of aircraft g Roll up cargo tie down straps and remove from aircraft h R...

Page 636: ......

Page 637: ...place in position as shown in figure 5 45 steps 2 and 3 with one on top of each tank and one 5 131 Not Cargo tie down locations used in this in stallation are shown in figure 5 44 Al though floors ar...

Page 638: ...FUELING VENT HOSE 26 VENT OVERBOARD HOSE 27 FUEL MANAGEMENT PANEL 27A AIR PUMPS PANEL 18 11 1J j U1 U1 VJ N r 1 JQ 1 CI Jl I N Ul l r CI 3CI t o s JQ 0 III s JQ CI r 1 ro 1 1 r 1 ro Ul m ro 3 5 m III...

Page 639: ...8 BOLT 39 GASKET 40 SWIVEL FLANGE FITTING 41 FLANGED SWIVEL ELBOW 42 BOLT 33 34 35 36 tJ III I j U1 U1 V V I Jq s I j U1 N til o T S ro t o s Jq aIII s Jq ro I ro I j ro til til ro S s til III III o s...

Page 640: ...OIL TANK CRADLE J 11 FIRE EXTINGUISHER 12 HAND OPERATED ROTARY PUMP 13 SELECTOR VALVE r d III 1 rt n n I iJ IT JQ 1 1 n I I iJ Ul o p 1 S 1 t o JQ 0 JQ 1 IT 1 1 1 o I Ul OJ 1 S 1 1 OJ III I I III o 1...

Page 641: ...DOWN FITTINGS Figure 5 44 Scheme 4 Long Range Tanks Tie Down Locations in Cabin Floor 411C240 5 135 to front of each tank with loops in strap towards tank surfac e k Secure rear tank first as follows...

Page 642: ...RT STRAPS ONE LOOP 4 1 Z41 Figure 5 45 Installing Scheme 4 Long Range Ferry Fuel Tanks Sheet 1 of 2 Part 5 5 136 STEP 2 SECURING REAR TANK 1 THROUGH 3 DOUBLE LENGTH STRAPS 4 THROUGH 10 SINGLE LENGTH S...

Page 643: ...NAL STRAPPING 4MC242 Figure 5 45 Installing Scheme 4 Long Range Ferry Fuel Tanks Sheet 2 of 2 5 137 Part 5 STEP 3 SECURING FORWARD TANK 10 000 POUND TIE DOWN FITTING STEP 4 FINAL STRAPPING 4MC242 Figu...

Page 644: ...hose 1 fo hand main oil tank 13 Lead hose 5 alongside side faCing tni itary Revised 1 Februar 1969 Part 5 situated on abin floor at front and rear spars In sure straps do not foul transparent sight g...

Page 645: ...sure gage With pressure relief valve set to 6 psi c J ck that valve opens and relieves excess 5 139 seat upper rail and tie to rail with plastic lacing In vicinity of front spar rerrlOve existing blan...

Page 646: ...ery line prevents fuel from ing the ferry tanks during normal system tr sfer Revised 1 Februar 1969 Part 5 Paragraphs 5 122 to 5 122 1 pressure eset regulator to supply 5 psi to ferry fuel tank g Fuel...

Page 647: ...el booster pump 26 When employing either method correct grounding procedure must be observed 5 l40A in the event of the ferry fuel shutoff valve failing open The booster pump switch operates the boos...

Page 648: ......

Page 649: ...D FERRY FUEL TANK Figure 5 46 Scheme 2 Long Range Ferry System Installation Part 5 13 4 C 243 5 141 1 RH FERRY OIL SUPPLY LINE 2 MAIN FERRY FUEL TANK 3 AFT FERRY FUEL TANK 4 FUEL VENT HOSE 5 DRAIN LIN...

Page 650: ...arily disconnect fuel delivery line at eac main firewall with a suitable container below con ection Part 5 Paragraphs 5 122 4 to 5 122 5 Do not allow booster pump to run dry c Disconnect ferry fuel de...

Page 651: ...gure 5 47 Propeller and Spinner Installation Nonreversible Propellers Revised I December 1965 5 143 to receive fuel spillage to check fuel flow Re connect lines i Switch AUX BOOST PUMP and selector sw...

Page 652: ...handle d Remove cotter pin and lockscrew from dome retaining ring nut Support weight of dome a d re Part 5 Paragraphs 5 123 1 to 5 123 2 creases th blade angle high pitch 5 123 1 TROUBLE SHOOTING PROP...

Page 653: ...y of the propeller that the shipping and pre installation precautions have been complied with 5 145 lease ring nut e Withdraw dome assembly over distributor valve and place in a suitable container to...

Page 654: ...retaining nut by hand to insure t cross threading occurs then tighten to a using nut wrench and bar Part 5 Note The propeller may be delivered in a crate with one or all blades removed to facilitate t...

Page 655: ...erration equals 1 degree Install e____12 14 13 4 lC24S Figure 5 48 Distributor Valve Assembly 5 147 w Attach hydratorque wrench installing ball armin a pair of wrench holes that will allowmaxi mum mov...

Page 656: ...e is at VUiIU 1 7 1 l A _ lJl v V I v u i J t f c 1 J f Figure 5 50 Installing High Pitch Stop R ng Par 5 Palagraph 124 4MC246 Figure 5 49 Installing Low Pitch Stop Ring high pitch stop ri ng over dom...

Page 657: ...wing each wrapping to overlap and extend approximately 0 5 inch on each side of cemented area 5 149 tached to the rear of the propeller hub by eight special bolts The afterbody is a separate part of t...

Page 658: ...ith take off manifold pressure it is not always possible to obtain take off rpm on the blocks 5 150 Part 5 Paragraphs 5 124 3 to 5 125 1 o Usin a rubber roller roll out any ripples or air bubbles Air...

Page 659: ...is plugged d Position gasket over four attachment stud s with raised screen section facing up 5 151 Part 5 Paragraphs 5 125 2 to 5 125 4 TABLE 5 12 Cont INDICATION OF TROUBLE PROBABLE CAUSE CORRECTIVE...

Page 660: ...lease locknut and adjust high rpm g ver nor stop screw until it butts against stop Ti hten lock nut Part 5 Paragraphs 5 125 5 to 5 125 7 Note If a running in period is required fit a gasket having a s...

Page 661: ...nes for foreign material and bleed line Replace pump Refer to para graphs 5 131 1 and 5 131 6 5 153 c Thi S sl tting is takt off rpm setting How t v r minor adjustments may bt required after flight tt...

Page 662: ...Figure 5 51 Autofeathering System Schematic Nonreversible Propellers 5 154 Revised 1 December 1965 Part 5 NOT E Air pressure from LH pltot closes contacts A C on differential pre ure switch and feath...

Page 663: ...r Feathering Button 24 LH Propeller Feathering Button 25 LH Propeller Feathering Button Light 5 155 Part 5 Paragraphs 5 126 2 to 5 126 4 TABLE 5 13 Cont INDICATION OF TROUBLE PROBABLE CAUSE CORRECTIVE...

Page 664: ...h mounting studs clear of br cket turn switch and lower free from structure m ving switch rearwards Part 5 Paragraphs 5 127 to 5 129 1 5 127 THRUST SWITCH DIFFERENTIAL PRESSURE The thrust differential...

Page 665: ...s 1 2 1 MOTOR 4 NUT 2 EXTENSION 5 WASHER 3 PUMP 4 tC249 Figure 5 52 Propeller Feathering Pump 5 157 f Remove switch from aircraft 5 129 2 INSTALLATION To install propeller feathering button reverse re...

Page 666: ...thering button and propeller gOY rnor pressure cutout switch circuit Each rela is a 28 volt dc type Part 5 Paragraphs 5 131 2 to 5 132 on pump c Ver Install blanks quickly to avoid draining system Use...

Page 667: ..._ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ __ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ J 5 132 1 REMOVAL a Insure that the battery and any external elec trical power source is disconnected...

Page 668: ...l further forward the cam continues to rotate and the blades go into rev rse Revised 1 December 1965 Part 5 Paragraphs 5 134 1 to 5 136 1 sures thE resultant in inches of water As a pre caution agai n...

Page 669: ...rsible propellers 5 137 1 REMOVAL To remove propeller see fig ure 5 53 and proceed as follows 5 161 pitch until a low pitch stop ring on the cam stops its rotation 5 136 2 PROPELLER CONTROL UNIT The p...

Page 670: ...Lay dome down gently in a horizontal p tion to keep rotating cam from moving Revised 1 December 965 Part 5 1 DRIVE BRACKET 8 FRONT CONE 15 SEGMENT LOCK WIRE 2 REAR C NE 9 PROPELLER RETAINtNG NUT 16 PR...

Page 671: ...Insert sleeve socket through power wrench and base plate assembly until it contacts propeller 5 163 Note If propeller was not at the feather or full reverse position when dome was removed mark positio...

Page 672: ...ither 0 005 or 0 015 inch thick as indic ted by 5 or 15 following part number on Revised 1 Jun 1970 Part 5 retainin6 nut Rotate knurled collar on input shaft ofpovrer wrench until splines on sleeve so...

Page 673: ...er connection is made to the timer the auxiliary pump relay for the pump on the propeller con 5 165 u Check serial number on face of fixed cam to insure that it agrees with propeller serial number on...

Page 674: ...T SWITCH PROP OIL LOW Figure 5 54 Reversible Propellers Circuit Logic 5 166 Revised 1 December 1965 Part 5 PROP FEATHER 27 5VOC 10 R I G H T____________________________________________________________...

Page 675: ...aircraft with reversible propeller system is the same as that described in paragraphs 5 132 1 5 167 troller is energized and power is supplied for the propeller feather or unreverse solenoid valve The...

Page 676: ...he operational sequence of the relays for the three functions is as follows Revised 1 February 1969 Part 5 Paragraphs 3 143 to 5 145 and 5 1 2 2 for aircraft with nonreversible pro peller system 5 143...

Page 677: ...ized When blade movement actuates switch o 1 to disconnect a ground circuit relay F and PROP 5 168A a When UNFEATHER PULL is selected and blade switch No I is tripped relay A is ener gized to apply ma...

Page 678: ......

Page 679: ...peller auxiliary pump unreverse feather solenoid and the relay box electrical lock on circuit 5 169 REVERSE light are deenergized pump circuit is cycled and reconnected through relay D energized and r...

Page 680: ...the filler plug to 100 125 pound inches of torque and secure with lockwire Revised 1 December 1965 Part 5 Paragraphf 5 148 to 5 149 Not If the propellers do not corne out of reo verse when the thrott...

Page 681: ...figure 5 56 and turn minimum adjusting screw in or out as required to obtain desired minimum 5 171 j During the first engine runup the propeller shall be reversed unreversed and partially feathered a...

Page 682: ...EEDER SPRING RACK MINIMUM RPM ADJUSTING SCREW Figure 5 56 Speeder Rack Assembly Revised 1 June 1970 P rt 5 Paragraphs 5 149 5 and 5 149 6 rpm setting One full turn of adjusting screw is equal to an rp...

Page 683: ...eller by advancing the rpm of the right hand the feathering action engine Revised 1 June 1970 5 173 feather button of the right hand propeller pulls in and the feather button light illuminates Note th...

Page 684: ......

Page 685: ...t High Intensity Stage 6 39 6 45 Adjustment of Short Field Approach Speed Indicator Reading 6 39 6 1 Part 6 Table of Contents PART 6 INSTRUMENTS Paragraph GENERAL 6 1 General Description 6 2 Instrumen...

Page 686: ......

Page 687: ...selector valve located on the co pilot s flight instrument panel When ground and flight heating 6 3 GENERAL 6 1 GENERAL DESCRIPTION This part deals with the aircraft instru ments which for descriptive...

Page 688: ...CATOR PILOT S 19 STALL WARNING TEST SWITCH 20 THRUST INDICATING SYSTEM SELECTOR VALVE 9 1 J ill i M 0 0 1 S Ul 1 0 t J 1 1 1 i I 0 J1 OQ i 1 OQ D M Ul M i 3 1 M 1 J ill 1 Ul 1 J i 1 0 0 N co Ul D 1 1...

Page 689: ...6 1 Flight Instrument Panels Pre Mod 4 1281 Sheet 2 of 2 Revised 1 December 1965 Part 6 4MC32t 6 5 Figure 6 1 Flight Instrument Panels Pre Mod 4 1281 Sheet 2 of 2 Revised 1 December 1965 Part 6 4MC32...

Page 690: ...CATOR PILOT 20 TURN AND SLIP INDICATOR PILOT 21 STALL WARNING TEST SWITCH 11 14 13 12 U III 11 rt 0 0 I 0 0 CD en CD 0 t I CD n CD CD 11 0 0 J1 1 Q P 11 l 0 1 Q r El en 11 P S l l l U III l l l en dl...

Page 691: ...icators With the valve selected to EMERG OFF the pitot free stream pressure to the thrust indi 6 6A system is installed pitot pressure to the fan air pressure switch part of the aircraft heating con t...

Page 692: ...ATOR 7 OIL LOW PRESSURE WARNING LIGHT 8 FUEL AND OIL PRESSURE INDICATORS 4 5 6 REAR VIEW 1 J III 1 0 of 0 I 0 tJj 0 1 til I 0 t J I I 1 1 0 0 U1 J Q s 1 I 0 I t 1 J Q J I J til 1 s 3 I J 1 J III J I 1...

Page 693: ...IGHT Figure 6 2A Engine Instrument Panel Post Mod 4 1281 Revised 1 December 1965 Part 6 3 4 _ 5 6 7 2 3 4 5 ___ 6 7 8 7 1 MAl ll FOLD PRESSURE INDICATOR DUAL 2 TACHOMETER INDICATOR DUAL 3 THRUST INDIC...

Page 694: ...es not drop more than 150 feet in one minute Tap instrument panel lightly to insure pointer freedom Part 6 Parag raphs 6 9 1 to 6 11 2 cators is shut off and the pressure remaInIng in the thrust indic...

Page 695: ...l PITOT c J STATIC MECHANICAL ACTUATION Q MOISTURE TRAP 4MC323 Figure 6 3 Pitot Static System 6 9 _ TYPICAL MOISTURE TRAP RH PITOT HEAD VERTICAL PILOT S INSTRUMENTS VELOCITY RH LOWER STATIC VENT IN AT...

Page 696: ...that leakage does not cause Il10re than one knot decrease in indication during one Il1inute period Part 6 Paragraph 6 12 to 6 12 3 e Release suction very slowly to prevent daIl1 age to vertical veloc...

Page 697: ...Tap instrument lightly and take second reading Check that difference between readings does not 6 11 6 12 4 Test airspeed indicator for scale error at values listed in Table 6 2 The friction test para...

Page 698: ...s mitted through a lever and gear system to a poin ter which indicates the rate of climb or descent Part 6 Ja agr phs 6 13 to 6 14 exc eed 3 0 knots at 20 knot indication and 2 0 knots at all other va...

Page 699: ...ce fuse Replace instrument Check electrical connec tions Replace instrument Replace instrument 6 l3 of the aircraft in feet per minute on a dial that is calibrated from 0 to 2 000 Part 6 Paragraphs 6...

Page 700: ...upplied by 27 5 volt dc power from the emergency bus through 3 ampere cir Revised 1 DeceITlber 1965 Part 6 Paragraphs 6 15 2 to 6 16 6 15 2 TESTING Test the attitude indicator as follows a Switch OFF...

Page 701: ...2 1 Figure 6 5 Wiring Diagram of Test Circuit for Turn and Slip Indicator Power Failure Sensor 6 15 Part 6 K02 19 20PZ POWER FAILURE SENSOR FOR ATTITUDE INDICATOR A 1 SENSITIVE AC VOLTMETER M t 4 II C...

Page 702: ...of sensor connector until test lamp lights Check that sensi tive de voltmeter reads ZO 5 1 volts de P t 6 Paragraphc 6 16 1 to 6 16 5 cuit breakers marked TURN t BANK on the cir cuit breaker panel in...

Page 703: ...al flight position d Mount accurate sighting compass on a tripod behind aircraft when possible 6 17 d Raise dc power supply to pin F to 28 volts and check that test lamp goes out e Vary dc power suppl...

Page 704: ...mpass card a s shown in folloWing example From Example Step b FOR STEER North 0 002 N E 45 043 6 18 Part 6 Paragrarht G 17 9 to 6 17 11 e Insure that operator of sighting compass has no steel articles...

Page 705: ...te assembly installed in place of the second front window assembly in the right hand fuselage 6 18A 6 17A PERISCOPIC SEXTANT PROVISIONS On special order provisions can be made to install a periscopic...

Page 706: ......

Page 707: ...dicator Refe r to paragraph 6 19 2 Replace transITlitter Refer to paragraphs 6 19 3 and 6 19 4 6 19 ENGINE INSTRUMENTS 6 18 GENERAL Two independent sets of engine instru ments one set for each engine...

Page 708: ...nd the oil portion from 0 to 125 psi The systems are supplied 26 volt 400 cycle single phase ac cur P t t 6 P ragraphs 6 19 2 to 6 20 TABLE 6 8 Cont INDICATION OF TROUBLE PROBABLE CAUSE CORRECTIVE ACT...

Page 709: ...ce indicator Refer to paragraph 6 22 1 Replace generator Refer to paragraphs 6 23 1 and 6 23 2 6 21 rent from the instrument transformer through 1 ampere fuses marked ENGINE INSTRUMENTS in the fuse pa...

Page 710: ...have been replaced the trouble is in the electrical power supply or wiring Revised 1 December 1965 Part 6 Paragraphs 6 22 to 6 24 1 TABLE 6 9 Cont INDICATION OF TROUBLE PROBABLE CAUSE CORRECTIVE ACTI...

Page 711: ...ngine instrument panel See figure 6 2 The indicators are of the ratio resistance type and each 6 23 Part 6 Paragraphs 6 24 2 to 6 25 TABLE 6 10 TROUBLE SHOOTING CARBURETOR AIR TEMPERATURE INDICATOR SY...

Page 712: ...proceed as follows a Remove regulator insert screw b Adjust regulator for fast or slow as required Part 6 Paragraphs 6 25 1 to 6 27 2 is electric ally connected to a resistance bulb which is installe...

Page 713: ...t head heater circuit while drain holes in the case are provided to prevent water accumulation 6 25 c Replace regulator insert screw d Test clock on timing machine for daily rate e Wind clock fully an...

Page 714: ...GHT OR EQUIVALENT lIM 2112 Figure 6 6 Test Circuit for Lift Transducer 6 26 Revised 1 December 1965 Part 6 POWER SUPPLY 26 O 1 V 400 4 CPS NOTE USE AN20 WIRING EXCEPT WHERE MARKED OTHERWISE MILLIAMETE...

Page 715: ...e against vane stop in slow direction Check that microammeter M1 reads zero 100 mi croamperes 6 26A 6 30 1 REMOVAL a Insure all aircraft electrical power is off b Remove four attachment screws from wi...

Page 716: ...rated by the wing flaps modi fy the circuit to compensate for flap settings Revised 1 December 1965 Part 6 Paragraphs 6 30 3 to 6 31 Turn off heater switch immediately after one minute reading has bee...

Page 717: ...ts are rotated altering the resistance in the circuit of the variable leg of the lift computer 6 27 thus providing a true indication of an approaching stall Each unit has external adjustm ents marked...

Page 718: ...ECTION MOVES INDICATOR POINTER COUNTERCLOCKWISE SLOW TOWARD PRE STALL WARNING DIRECTION l J ill 1 0 cr N 00 0 CD C l CD P t J CD 0 CD 3 crCD 1 0 cr J1 trj JQ 1 CD cr I o J CD C l 1 0 0 t 0 3 tl CD 1 F...

Page 719: ...s ducer transformer terminals D and E and check output at terminals D and E of low and high in 6 29 bridge circuit to modify the switching movement and compensate for flap position 6 32 1 REMOVAL a In...

Page 720: ...igure 6 8 Stall Warning System Throttle Microswitches 2 3 4 5 M 21 ILl 6 30 Revised 1 December 1965 Part 6 1 SEMICIRCULAR BRACKET 2 THROTTLE SYSTEM PULLEY 3 CAM 4 MICROSWITCH ASSEMBLY MOUNTING BRACKET...

Page 721: ...OPS Reverse removal procedure Adjust microswitches as described in paragraphs 6 34 3 and 6 40 6 30A tensity computer transformers e Check that there is no output between ter minals C and D 6 33 s INST...

Page 722: ...ANCE A 0 750 INCH 0 875 INCH Figure 6 8A Throttle Microswitch Adjustment 6 30B Revised 15 July 1969 Pa t 6 SWITCH IN CLOSED POSITION THROTTLE LEVERS FULLY OPEN r r 0 010 0 020 INCH OVERTRAVEL A 1 SWIT...

Page 723: ...RACKET ASSEMBLY 4MC329 Figure 6 9 Stall Warning System Flap Microswitches Revised 15 July 1969 6 31 6 34 3 THROTTLE MICROSWITCH ADJUST MENT a Insure throttle controls have been rigged Refer to paragra...

Page 724: ...or pointer will simultaneously deflect to beyond the letter L of the SLOW mark Revised 15 July 1969 Part 6 Paragraphs 6 36 to 6 37 bly along the mounting slot until the actuator strikes he cam and the...

Page 725: ...REAR SPAR 1 1 __ MICROSWITCH Figure 6 9A Flap Microswitch Adjustment BRACKET ASSEMBLY Part 6 6 32A HIGH POINT OF CAM COINCIDES WITH 190 FLAP SETTING RAISE ROLLER TO LIMIT OF TRAVEL Revised 15 July 19...

Page 726: ......

Page 727: ...MOD S O O 4073 M 808 Figure 6 10 Emergency Panel Left and Right Sides Revised 1 December 1965 6 33 ing on the indicator dial With no power applied the indicator pointer tip rests between the letters...

Page 728: ...t 16 Figure 6 11 Test Circuit for Short Field Approach Speed Indicator 6 34 Revised 1 December 1965 Part 6 minus 1000 0 plus 1000 microamperes The mil livoltmeter M2 measures 0 100 millivolts and is t...

Page 729: ...e Using tool SDS643 l for aircraft with short field approach speed indicator or SDS643 3 for 6 34A 1 Using ohmmeter check that there are no short circuits between isolated circuits in indica tor Chec...

Page 730: ......

Page 731: ...that indicator pointer deflects fully into SLOW zone as high intensity stick shakers oper ate 6 35 aircraft without short field approach speed in dicator apply load of 3 75 grams in manner given in o...

Page 732: ...WARN TEST switch to left and check that low intensity stick shakers operate Revised 1 February 1972 Part 6 Paragraph 6 39 I 5 Release STALL WARN TEST switch and note that pointer returns to dia mond m...

Page 733: ...lift computer high intensity stage must be in stalled and energized before low intensity stage 6 37 aa Release switch and check that low intensity stick shakers cease to operate abo Lower flaps to bet...

Page 734: ...Should stick shakers not operate within tolerance repeat procedure in steps a through d and recheck Part 6 Paragraphs 6 42 to 6 43 can be checked or adjusted Perform a complete in flight check recordi...

Page 735: ...ft computer adjustment screws and tighten by hand only to insure that settings are not changed 6 39 f In order to eliminate any small defects due to potentiometer interaction between left low and left...

Page 736: ......

Page 737: ...70A I 7 71 7 71 7 72 7 72 7 73 7 73 7 73 7 74 7 74 7 74 7 74 7 76 7 77 7 79 7 79 7 79 7 80 7 80 7 1 PART 7 Part 7 Table of Contents ELECTRICAL SYSTEMS Paragraph 7 1 7 2 7 3 7 4 7 5 7 6 7 7 7 8 7 9 7...

Page 738: ...ircuit Breakers Provisional Wiring Page 7 88 7 89 7 90 7 90 7 90 7 91 7 96 7 97 Revised I June 1970 Part 7 Table of Contents Paragraph 17 71 7 72 7 73 7 74 7 75 7 76 7 77 7 78 7 2 Number 1 Junction Bo...

Page 739: ...he corrective action in trouble shooting table make a continuity check of the associated wiring 7 3 GENERAL 7 I GENERAL DESCRIPTION The electrical system is primarily a 28 volt direct current single w...

Page 740: ...P JUMP PANEL POST MOD 4 1242 Figure 7 1 Circuit Breaker and Fuse Panels 7 4 Revised 1 February 1972 Part 7 MISCELLANEOUS WINDSCREEN HEAT CONTROL CONTROL GYRO PILOT CO PILOT PILOT CO PILOT COMP ASS Jb...

Page 741: ...r to paragraphs 7 25 1 and 7 25 2 Replace current limiter Refer to paragraphs 7 20 1 and 7 20 2 7 5 Part 7 TABLE 7 1 TROUBLE SHOOTING DC POWER SUPPLY SYSTEM INDICATION OF TROUBLE Battery fails to ener...

Page 742: ...or security and cables and wiring for damage 7 6 d Check control panel knobs for security and cracks Part 7 Paragraph 7 2 3 INDICATION OF TROUBLE Generator fails to de liver power to the main bus Fiel...

Page 743: ...Connect external power source to external power receptacle and insure all buses are ener gized 7 7 7 2 4 PERFORMANCE CHECK The following checks for system performance may also be re ferred to for fun...

Page 744: ...r systems Make point to point check between cable connections and ground to Revised I December 1965 Part 7 Paragraph 7 2 5 v Return all switches to off and disconnect external power source applying po...

Page 745: ...4 andX16C18 from ground post Mod 4 1281 in No 10 junction box Set TRANS FORMER switch to MAIN 7 9 I POINT OF MEASUREMENT DC POWER SYSTEM Cont control relay ter minals Xl A2 BI Between terminals and gr...

Page 746: ...point to point check between cable connections and ground to isolate fault Revised 1 February 1972 Part 7 TABLE 7 2 Cont POINT OF MEASUREMENT AC POWER SYSTEM Cont 2 Connector for inverter changeover...

Page 747: ...amp from navigator I s spotlight if installed and set switch to ON ISOLATING PROCEDURE Part 7 7 l0A POINT OF MEASUREMENT NORMAL INDICATION INTERIOR LIGHTING SYSTEM Cont Revised 1 February 1972 TABLE 7...

Page 748: ......

Page 749: ...ec tion lights Make point to point check between cable connections and ground to isolate fault 7 11 TABLE 7 2 Cont POINT OF MEASUREMENT NORMAL INDICATION INTERIOR LIGHTING SYSTEM Cont 5 No 9 junction...

Page 750: ...oint to point check between cable connec tions and ground to isolate fault Revis ed I February 1972 Part 7 POINT OF MEASUREMENT NORMAL INDICATION EXTERIOR LIGHTING SYSTEM Cont I I 3 TBllO 3 Between te...

Page 751: ...to lights Make point to point check between cable connections and ground to isolate fault 7 12A _ _ POINT OF MEASUREMENT NORMAL INDICATION EXTERIOR LIGHTING SYSTEM Cont 2 No 2 junction box terminals 1...

Page 752: ......

Page 753: ...ontrol circuit Make point to point check between cable connections and ground to isolate fault 7 13 POINT OF MEASUREMENT NORMAL INDICATION PANEL AND WARNING LIGHTS Cont 3 No 2 junction box terrninal 1...

Page 754: ...ates short circuit Make point to point check between cable connections and ground to isolate fault_ Part 7 POINT OF MEASUREMENT WINDSHIELD WIPERS Terminal ends of cables M41A16 M39B16 M39C16 No 2 junc...

Page 755: ...nstruITlents Make point to point check between cable connections and ground to isolate fault 7 15 I POINT OF MEASUREMENT NORMAL INDICATION TABLE 7 2 Cont OPERATION OF EQUIPMENT FUEL CONTROL INCLUDING...

Page 756: ...n cable connections and ground to isolate fault As for step 1 As for step 1 Revised 1 February 1969 POINT OF MEASUREMENT 2 LH and RH con nectors for carbu rector air cylinder head and oil tem perature...

Page 757: ...Make point to point check between cable connections and ground to isolate fault As for step l 7 l6A POINT OF MEASUREMENT STARTER AND IGNITION l LH and RH engine disconnects pins B Between pins Band gr...

Page 758: ......

Page 759: ...Make point to point check be tween cable connections and ground to isolate fault As for step I 7 17 POINT OF MEASUREMENT NORMAL INDICATION STARTER AND IGNITION Cont 3 No 1 junction box LH and RH start...

Page 760: ...resistance indicates short circuit in hydraulic pressure or engine oil fuel Revised 1 December 1965 Part 7 POINT OF MEASUREMENT NORMAL INDICATION TABLE 7 2 Cont OPERATION OF EQUIPMENT I AUTOFEATHERING...

Page 761: ...LH down check RH down check Set co pilot s aileron trim switch to LH down check RH down check 7 1SA POINT OF MEASUREMENT connector pins B C D and ground No 10 junction box terminals 21 22 23 24 32 33...

Page 762: ......

Page 763: ...ting controls Make point to point check be tween cable connections and ground to isolate fault 7 19 TABLE 7 2 Cont POINT OF MEASUREMENT NORMAL INDICATION FLIGHT INSTRUMENTS DC AND AC Pilot s and co pi...

Page 764: ...point to point check between cable connec tors and ground to isolate fault Revised 1 February 1972 I Part 7 TABLE 7 2 Cont POINT OF MEASUREMENT NORMAL INDICATION FLIGHT COMPARTMENT HEATING Cont J and...

Page 765: ...trol system Make point to point check be tween cable connections and ground to isolate fault 7 21 I TABLE 7 2 Cont POINT OF MEASUREMENT NORMAL INDICATION CABIN HEATING S O O Cont 2 Limiter F6 2 ter mi...

Page 766: ...t check between cable connections and ground to isolate fault As for step 1 Revised 1 February 1969 Part 7 TABLE 7 2 Cont POINT OF MEASUREMENT 2 No 2 junction box terminal 14 10 Be tween terminal and...

Page 767: ...trol cir cuit Make point to point check between cable connections and ground to isolate fault 7 22A POINT OF MEASUREMENT NORMAL INDICATION TABLE 7 2 Cant OPERATION OF EQUIPMENT ENGINE FIRE DETECTION A...

Page 768: ......

Page 769: ...in battery Set BATTERY MASTE R switch to MASTER Set EMERG BUS SW to EMERG NOMINAL VOLTAGE 24 7 23 I POINT OF MEASUREMENT NORMAL INDICATION TABLE 7 2 Cont OPERATION OF EQUIPMENT Part 7 Paragraph 7 2 6...

Page 770: ...FF Connect external power source As for step 3 NOMINAL VOLTAGE 24 27 5 27 5 Revised 1 February 1972 Part 7 TABLE 7 3 Cont I POINT OF MEASUREMENT DC POWER SYSTEM Cont 2 UTILITY LIGHTS or TROOP JU fP or...

Page 771: ...step 3 As for stell 3 As for step 3 As for step 3 Part 7 NOMINAL VOLTAGE 27 5 27 5 27 5 27 5 7 24A POINT OF MEASUREMENT DC POWER SYSTEM Cont terminal cable P5IB20 LOW ENG OIL circuit breaker terminal...

Page 772: ......

Page 773: ...to ON Reset UTILITY RECEPTACLES FRONT and Part 7 NOMINAL VOLTAGE 27 5 27 5 27 5 27 5 27 5 27 S 7 25 TABLE 7 3 Cont POINT OF MEASUREMENT DC POWER SYSTEM Cont ICING WING TAIL AUTO if fitted circuit brea...

Page 774: ...p 4 and disconnect standby invertp connector check 27 5 27 5 27 5 27 5 27 5 Revised I February 1972 I I I Part 7 POINT OF MEASUREMENT DC POWER SYSTEM Cont No 2 junction box termi nals 9 10 14 17 9 13...

Page 775: ...R circuit breakers and set appropriate electronics switches to ON Part 7 NOMINAL VOLTAGE 27 S 7 26A POINT OF MEASUREMENT 6 7S0VA inverter at Sta 348 8 dc connector pin C Relay K206 terminal Xl Revised...

Page 776: ......

Page 777: ...t Toilet LIGHT SWITCH to ON and check Part 7 NOMINAL VOLTAGE 27 5 27 5 27 5 27 5 6 6 27 5 27 5 7 27 POINT OF MEASUREMENT INTERIOR LIGHTING SYSTEM 1 Cargo doors forward panel light terminal white cable...

Page 778: ...ircuit breaker check Reset NOMINAL VOLTAGE 27 5 27 5 27 5 20 5 27 5 27 5 24 Revised I February 1972 I Part 7 TABLE 7 3 Cont POINT OF MEASUREMENT EXTERIOR LIGHTING Cont 1 Anti collision light conn ecto...

Page 779: ...circuit breaker Rotate SW EMERG ROOF lights switch to BRT Part 7 NOMINAL VOLTAGE 24 27 5 27 5 7 28A TABLE 7 3 Cont POINT OF MEASUREMENT FACILITY PANEL AND WARNING LIGHTS Cont instrument panel lights f...

Page 780: ......

Page 781: ...valve Set landing gear lever to UP check Part 7 NOMINAL VOLTAGE 27 5 27 5 27 5 27 5 27 5 27 5 7 29 POINT OF MEASUREMENT TABLE 7 3 Cont FACILITY OPERATION OF EQUIPMENT PANEL AND WARNING LIGHTS Cont 6...

Page 782: ...cuit breaker Set VENT DOORS switch to CLOSE MAN check NOMINAL VOLTAGE 27 5 27 5 27 5 27 5 27 5 27 5 Part 7 POINT OF MEASUREMENT LANDING GEAR Cont 3 Landing gear selector valve connector pin A Landing...

Page 783: ...switch to HIGH check Part 7 NOMINAL VOLTAGE 27 5 27 5 27 5 27 5 27 5 27 5 27 5 27 5 27 5 27 5 7 31 POINT OF MEASUREMENT VENT DOORS Cont 2 Vent doors control relay terminal X 1 Vent doors actuator con...

Page 784: ...Reset LEFT and NOMINAL VOLTAGE 27 5 27 5 27 5 27 5 27 5 27 5 27 5 27 5 7 32 Revised 1 February 1969 Part 7 TABLE 7 3 Cont POINT OF MEASUREMENT FACILITY OPERATION OF EQUIPMENT AIR PUMPS FERRY FUEL TANK...

Page 785: ...left and right FUEL SHUT OFF switches for valves closed up check Part 7 NOMINAL VOLTAGE 27 5 7 32A POINT OF MEASUREMENT 7 LH af l d RH fuel shutoff valve connectors pins B Revised I February 1969 TAB...

Page 786: ......

Page 787: ...nd B on differential pressure switch connector check 27 5 27 5 27 5 27 5 27 5 27 5 27 5 27 5 7 33 I Part 7 TABLE 7 3 Cont POINT OF MEASUREMENT FACILITY OPERATION OF EQUIPMENT NOMINAL VOLTAGE FUEL AND...

Page 788: ...for LH FEATHER PUSH NOMINAL VOLTAGE 27 5 27 5 27 5 27 5 27 5 27 5 27 5 7 34 Revised 1 December 1965 Part 7 TABLE 7 3 Cont POINT OF MEASUREMENT FACILITY OPERATION OF EQUIPMENT AUTO FEATHERING NONREVERS...

Page 789: ...ck from pins B to ground check Part 7 NOMINAL VOLTAGE 27 5 27 5 27 5 27 5 27 5 27 5 27 5 27 5 7 34A POINT OF MEASUREMENT TABLE 7 3 Cont FACILITY OPERATION OF EQUIPMENT AUTOFEATHERING AND REVERSING REV...

Page 790: ...set INST PWR FAIL circuit breaker check NOMINAL VOLTAGE 27 5 27 5 27 5 27 5 Revised 1 December 1965 I Part 7 TABLE 7 3 Cont POINT OF MEASUREMENT AILERON TRIM TAB FACILITY 1 Aileron trim tab position I...

Page 791: ...Reset heater FUEL circuit breaker switch Part 7 NOMINAL VOLTAGE 27 5 27 5 27 5 13 75 27 5 27 5 7 35 TABLE 7 3 Cont POINT OF MEASUREMENT STALL WARNING 1 Pilot s and co pilots low stick shaker connector...

Page 792: ...fan air pressure switch connector NOMINAL VOLTAGE 27 5 27 5 27 5 27 5 27 5 Revised 1 February 1972 Part 7 TABLE 7 3 Cont POINT OF MEASUREMENT FACILITY FLIGHT COMPARTMENT HEATING Cont 3 PUSH TO START...

Page 793: ...s inverter power in connectors check Part 7 NOMINAL VOLTAGE 27 5 27 5 27 5 27 5 27 5 27 5 7 37 I I TABLE 7 3 Cont POINT OF MEASUREMENT HEATER INTAKE ANTI ICING Flight compartment and cabin intake ant...

Page 794: ...PS circuit breaker NOMINAL VOLTAGE 27 5 27 5 27 5 27 5 27 5 27 5 27 5 27 5 27 5 Revised 1 June 1970 Part 7 TABLE 7 3 Cont POINT OF MEASUREMENT WINDSHIELD ANTI ICING Cont 3 PILOT FAIL light termi nal2...

Page 795: ...the relay function coil terminals location of relay and approximate resistance of relay coil 7 3SA Part 7 Paragraph 7 2 7 TABLE 7 3 Cont POINT OF MEASUREMENT FACILITY SPECIAL INSTALLATION VIP INTERIO...

Page 796: ......

Page 797: ...235 160 70 3 110 300 235 240 110 93 160 160 160 160 160 110 93 10 10 160 235 235 235 235 235 7 39 I Part 7 TABLE 7 4 RESISTANCE MEASUREMENTS DC POWER SUPPLY SYSTEM RELAY Dimming control relay No 1 and...

Page 798: ...y means of a secondary bus reset switch reconnect the second ry bus to the main Revised 1 June 1970 Part 7 Paragraphs 7 t 8 and 7 3 TABLE 7 4 Cont RELAY IBattery relay auxiliary Battery relay ITlain L...

Page 799: ...bus relay b Secure limiter bus bars to main bus bar c Loosen aft terminal nuts of both current 7 41 bus The emergency bus serves the most essential equipment and is normally powered from the main bus...

Page 800: ...Before removing battery observe safety precautions given in paragraph 7 2 1 Revised 1 December 1965 Part 7 Paragraphs 7 7 to 7 10 1 limiters remove forward terminal nuts and swing curr cnt limiters in...

Page 801: ...tis screwed into a bracket holder on the aftwall of the battery compartment which supports and 7 43 I Before disconnecting the battery insure that the BATTERY MASTER switch is set to OFF and that the...

Page 802: ...stallation Dry thoroughly If base metal is exposed recoat the surfaces with an acid resistant paint Part 7 Paragraphs 7 12 1 to 7 13 1 BATTERY POSITIVE CONNECTOR 5 OUTBOARD VENT 2 VENTING SYSTEM INTAK...

Page 803: ...of the shunt field and the generator warn Figure 7 3 AC DC Power and Voltammeter Panels 4MC34Z 7 45 7 14 BATTER Y RELAY The ba ttery relay functions to connect the battery to the main bus and is cont...

Page 804: ...SHES a ReITlove screws and lockwashers attaching jUITlper and brush asseITlblies to box and post as Part 7 Paragraphs 7 16 to 7 16 3 ing lights Ire protected by five 5 aITlpere push to reset circuit b...

Page 805: ...lts 7 17 1 REMOVAL Before removing generator control panel observe safety precautions given in 7 47 semblies use hook to free each brush spring and check jumper assemblies for damage b Insure that all...

Page 806: ...moving generator relay observe safety precautions given in para graph 7 2 1 Revised 1 February 1972 Part 7 Paragraphs 7 17 2 to 7 19 1 paragraph 7 Z 1 a Identify generator control panel on flight comp...

Page 807: ...secondary bus relay only when both generators are delivering power to the main bus Each bus 7 49 _ a Unfasten upholstery and remove cover fron1 number I junction box b Disconnect cables from terminal...

Page 808: ...relay Reinstall termi nal nuts c Remove attaching screws at base of relay and remove relay from box Part 7 Paragraphs 7 22 1 to 7 25 1 control relay is energized when the related gener in accordance w...

Page 809: ...and withdraw cable froIn within box as flag terIninal will not pass through fault transforIner 7 51 7 25 2 INSTALLATION a To install ground test relay reverse re Inoval procedure reconnecting cables a...

Page 810: ...or double throw with or without center off positions and also with momentary or fixed on positions Part 7 Pa ragraph 7 26 5 to 7 28 g ReITlo e transforITler ITlounting screws and nuts froITl bottOITl...

Page 811: ...the 5 ampere INVERTERS RELAYS STANDBY circuit breaker which is energized with standby inverter 7 53 As a precaution against inadvertent operation SOlne switches are fitted with guards 7 28 1 REMOVAL B...

Page 812: ...inverter and standby inverter relay Check inverter switch replace if faulty Revised I December 1965 I Part 7 Paragraph 7 30 1 operation nd an AC F AlLURE light powered from a 3 ampere INVERTERS FAILUR...

Page 813: ...damage Revised 1 December 1965 d Check fuseholders for specific number of serviceable fuses 7 55 I INDICATION OF TROUBLE Standby inverter fails to start with inve rte r switch at STANDB Y ac standby...

Page 814: ...nal Voltage voltage to be ex pected between point of measurement and ground Revised 1 December 1965 Part 7 Paragraphs 7 30 3 to 7 30 5 7 30 3 PET FORMANCE CHECK a Insure BATTERY MASTER both GEN switch...

Page 815: ...t zone 1 and 2 and 3 connectors pins A fire detection control units Revised 1 December 1965 7 57 I I POINT OF MEASUREMENT AC POWER SYSTEM 1 A fJ bus connection RIGHT STALL WARNING fuse jum per bus ter...

Page 816: ...circuit see wiring diagrams in Part 9 and replace fuse c Function test installed fuse in accordance Part 7 Paragraphs 7 31 to 7 35 1 TABLE 7 6 Cont POINT OF MEASUREMENT ENGINE FIRE DETECTION Cont Righ...

Page 817: ...erter control box and with screwdriver adjust poten tiometer to obtain 115 4 5 volts Clockwise 7 59 with performance check for applicable service 7 35 2 REPLACEMENT OF FUSE HOLDER Be fore replacing fu...

Page 818: ...through pins K and L to the ac buses b With the AC INVERTER switch on STBY Revised 1 February 1972 Part 7 Paragraph 37 7 1 MAIN INVERTER 2 OUTPUT VOLTAGE ADJUSTMENT 3 INVERTER CHANGEOVER RELAY 4 STAN...

Page 819: ...e changeover relay box and out on pin P to the standby inverter relay This completes a supply 7 60A pin C supplies the manual standby inverter circuits as in steps a 4 and a 5 c With the switch on MAI...

Page 820: ......

Page 821: ...ht hand side of hatch well and tie open with cord c Identify main or standby inverter relay on 7 61 from the standby inverter circuit breaker on the emergency bus and starts the standby inverter The o...

Page 822: ...SWITCH PANEL MOD 4 1167 Figure 7 5 Electrical and Engine Switch Panels 7 62 Revised I February 1969 Part 7 Paragraphs 7 38 2 to 7 39 1 num ber 6 junction panel and disconnect wiring from relay term in...

Page 823: ...s cargo doors and ramp door replace if faulty Replace switch Refer to paragraphs 7 28 1 7 28 2 7 63 INDICATION OF TROUBLE Utility light will not light Flight compartment floor hatch light will not lig...

Page 824: ...ts switch and check illumina tion and dimming of magnetic standby compass light Revised 1 June 1970 Part 7 Paragraph 7 39 2 to 7 39 3 7 39 2 VISUAL INSPECTION a Check components for security of mounti...

Page 825: ...trance light assembly follow procedure given in para graph 7 47 2 but pull out INTERIOR LIGHTS 7 65 y Rotate pilot and engine Ii ght switch to OFF Set standby compass light switch to EMERG and check t...

Page 826: ...c Disconnect cables from microswitch d Remove two screws and remove microswitch Revised 1 June 1970 Part 7 Paragraphs 7 43 to 7 44 3 CARGO circuit breaker 7 43 UTILITY LIGHTS Four utility lights are p...

Page 827: ...TS Seven cabin dome lights are provided in two rowS on either side of the ITlonorail in the ca 7 67 from mounting bracket 7 44 4 INSTALLATION OF FLIGHTCOMPART MENT FLOOR HATCH LIGHT MICRO SWITCH a Rev...

Page 828: ...lete with cables and lamps 4MC345 Figure 7 6 Cabin Lights and Cargo Doors Forward Switch Panel 7 68 Part 7 ParagraphE 7 47 1 to 7 48 1 bin roof Each dome light contains a red and a clear lamp in a sin...

Page 829: ...system comprises The lamp is clamped to a mounting bracket to per Revised I February 1972 7 69 __ _ 7 48 2 INSTALLATION a Reverse removal procedure reconnecting cables according to figure 9 24 b Funct...

Page 830: ...ti collision light 7 53 LANDING LIGHTS A 250 watt sealed beam landing light Revised 1 February 1969 Part 7 Paragraphs 7 51 I to 7 53 mit adjustment of filament alignment Beam ad justment is by three c...

Page 831: ...bracket on nose gear fairil1 c Withdraw light as sernbly complete wi th cal Ie and connector 7 70A is set into the leading edge of each wing at a fixed angle The lights are operated by separate T han...

Page 832: ......

Page 833: ...lfY LIGHTS OUTLET RI R R ENTRANCE I crp 0 R LIGHT L OFF BRIGH T5 Figure 7 7 Rear Switch Panels 7 71 7 54 2 INSTALLATION OF TAXIING LIGHT AS SEMBLY a Reverse reITloval procedure Reconnect cables accord...

Page 834: ...fety precautions given in para graph 7 2 1 HINGE CONTACT 4MC347 Figure 7 8 Eyebrow Lighting Fixture Part 7 Paragraphs 7 56 to 7 57 1 7 56 PANEL LIGHTS RHEOSTAT SWITCHES Rheostat switches are provided...

Page 835: ...hts it is necessary to recycle the dimming relays by switching to BRT and then back to DIM 7 73 _ _ a Disconnect cable at terminal strip or splice behind instrument panel It may be necessary to detach...

Page 836: ...ATION a Insure that aircraft and control unit surfaces are clean to provide good electrical contact Part 7 Paragraphs 7 60 1 to 7 64 2 7 60 1 REMOVAL OF DIMMING RELAY Before removing dimming relay obs...

Page 837: ...D E TERMINAL 7 POSITIV B BATTERY E TERMINAL 9 NEGATIV Y Lighting Con Emergenc trol Unit Part 7 7 75 7 Figure 7 9 2 3 5 1 G AL STRIP 2 TNERTIA SWITCH LL TO RESET 3 I WITCH KNOB PU 4 S R 5 COVE 6 PAD E...

Page 838: ...d Remove control unit cover and identify cable to exit light to be removed Revised 1 February 1969 Part 7 Paragraphs 7 64 3 to 7 65 1 b Reverse removal procedure reconnecting cables according to figu...

Page 839: ...ll power and make point to point continuity checks of all wiring associated with faulty system 7 77 e Disconnect cable from terminal strip in con trol unit and withdraw through grommet f Unclip cable...

Page 840: ...JUMP lights at LH andRHpassengerdoors frame number Z from BRIGHT DIM switch Revised 1 December 1965 Part 7 Paragraphs 7 66 2 to 7 66 3 TABLE 7 8 TROUBLE SHOOTING AIR DELIVERY SYSTEM INDICATION OF TROU...

Page 841: ...limiter F6 1 in No Z junction box connects secon dary dc to the BATTERY CONTROL circuit break 7 79 on control panel This signifies that jump lights dimming relay is energized to connect resistors in...

Page 842: ...10 125 175 190 175 190 80 85 40 45 15 20 9 12 Tighten to depress lockwasher Revised 1 February 1972 Part 7 Paragraphs 7 69 to 7 70 1 er for the cuxiliary battery relay When energiz ed the relay connec...

Page 843: ...er feathering relays f Di sconnect wiring from terminals Xl Al and A2 on external power relay 7 80A disconnect the cables at the equipment on the panel and withdraw the panel with its assembled equipm...

Page 844: ......

Page 845: ...as shown in wiring diagram Tighten terminals to wrench torque values given in paragraph 7 70 2 7 81 2 1 STARTER RELAY Part 7 Parag raph 7 71 2 2 PROPELLER FEATHERING RELAY 3 POSITIVE LINE GROUND FAULT...

Page 846: ...BATTERY RELAY 9 TEST JACK CIRCUIT BREAKER 4MC351 Figure 7 12 NUITlber 2 Junction Box 7 82 _ _ tt _ Part 7 5 6 2 1 MAIN BUS BAR 2 LIMITER BUS BAR 3 SECONDARY BUS RELAY 4 ISOLATION TRANSFORMER 5 CARGO...

Page 847: ...arly identified WINDSHIELD HEAT SENSING CONTROL RELAY 4MC3e2 Figure 7 13 Number 4 Junction Box 7 83 d Connect ground jumper Check that there is continuity zero ohms between terminal X2 ground of any r...

Page 848: ...ircraft and junction panel mounting CARGO DOOR RELAYS 4MC353 Figure 7 14 Number 9 Junction Box 7 84 Part 7 Paragraphs 7 72 2 to 7 73 2 d Disconnect incoming cables at terminals and release from juncti...

Page 849: ...ection of the fus elag e It INSTRUMENT TRANSFORMERS 4MCSS4 Figure 7 15 Nurnbe rIO Junction Box 7 85 surfaces are clean to provide good electrical contact b Install junction panel in position and secur...

Page 850: ...r attached through access hole in monorail web and access hole in cabin flight compartment bulkhead P c t 7 Paragraphs 7 74 1 to 7 77 1 contains cargo doors open and close relays ramp door pen and clo...

Page 851: ...OUND FAUL T TRANSFORMER 4 GEN TERMINAL 5 GEN TERMINAL 4MC355 Figure 7 16 Firewall Junction Box 7 87 Part 7 2 1 STARTER TERMINAL 2 MAIN BUS TERMINAL 3 NEGATIVE LINE GROUND FAUL T TRANSFORMER 4 GEN TERM...

Page 852: ...and a dc utility receptacle with all cables connected to an addi tional receptacle behind the panel Part 7 Paragraphs 7 77 2 to 7 79 7 77 2 INSTALLATION Before installing a cir cuit break r panel on t...

Page 853: ...ctrical connectors and wiring along cable run to receptacles on center pylon discon nect panel 7 89 7 79 1 REMOVAL Before removing cabin lights and cargo doors forward switch panel or interior lights...

Page 854: ...ctor at mating plug or receptacle and check for security Wirelock connector Revised 1 December 1965 Part 7 Paragraphs 7 81 to 7 83 1 c Connect electrical connectors to receptacles and wirelock d Faste...

Page 855: ...OF UNITS PER AIRCRAFT 2 3 2 2 AMPERES PER UNIT L 20 Negligible 0 10 0 50 0 04 0 041 0 04 0 04 7 91 Part 7 Paragraphs 7 83 2 to 7 84 h Lace cable auembly and clip into position precautions given in pa...

Page 856: ...g Gear CSK4743 1 1 0 40 Control Valve Nosewheel 109235 1 0 75 Steering 7 92 Revised 1 February 1972 Part 7 TABLE 7 10 Cont EQUIPMENT PART NO OF AMPERES DESIGNATION UNITS PER PER UNIT AIRCRAFT ENGINE I...

Page 857: ...13 70 0 09 0 25 70 00 0 26 0 35 1 0 04 1 60 1 60 0 60 0 20 1 00 1 70 1 60 0 90 17 48 4 30 4 00 7 93 EQUIPMENT TABLE 7 10 Cont PART DESIGNATION HEATING VENTILATING AND DE ICING Fuel Pump FIt Compt 73C6...

Page 858: ...0 04 0 40 6 30 1 20 0 20 0 20 0 15 0 17 0 17 0 67 0 04 0 17 0 17 1 50 0 80 Revised I February 1972 Part 7 EQUIPMENT TABLE 7 10 Cont PART DESIGNATION HEATING VENTILATING AND DE ICING Cont I Relay Air...

Page 859: ...us MS24171 Dl or AN3370 Z 1 0 39 Panel Generator Control GC34 2 2 1 20 Revised 1 February 1972 7 95 Part 7 TABLE 7 10 Cont EQUIPMENT PART NO OF AMPERES DESIGNATION UNITS PER PER UNIT AIRCRAFT LIGHTING...

Page 860: ...sts the ac and de buses and the electrical system supplied by each bus 7 96 Revised I February 1972 I I Part 7 Paragraph 7 85 EQUIPMENT POWER Cont Battery Main Battery Auxiliary Utility Receptacles Re...

Page 861: ...x S O O Mod 4083 For radio equipment provisions and alternative configurations refer to Part 8 7 97 TABLE 7 11 Part 7 Paragraph 7 86 BUS POWER DISTRIBUTION TO CIRCUIT BREAKERS AND FUSES DC MAIN BUS Fm...

Page 862: ......

Page 863: ...s System J2 Compass System Static Discharge Wicks 8 7 8 8 8 8 8 12 8 13 8 13 8 21 8 25 I 8 26B 8 1 PART 8 RADIO Part 8 Table of Contents Paragraph Page Paragraph Page 8 1 8 2 8 3 8 4 GENERAL Radio Sy...

Page 864: ......

Page 865: ...all radio equipment with the use of test equipment where necessary to verify serviceability The 8 3 GENERAL 8 1 RADIO SYSTEMS CONFIGURATIONS Provision is made to install severaldif ferent radio system...

Page 866: ...e RF grounds These should be run to vertical members of radio rack or other main aircraft structure Part 8 Paragraphs 8 2 4 to 8 3 checks sho lId be performed where possible in an area lucated away fr...

Page 867: ...le at rear of panel and wirelock d Ins ert control panel into console and secure Dzus fasteners 8 5 8 3 1 REMOVAL OF COMPONENTS FROM RA DIO EQUIPMENT RACK a Insure that power is switched off b Disconn...

Page 868: ...reception VOR station bearing displayed on RMIs radio_ magnetic indicators Revised 1 December 1965 I Part 8 Paragraphs 8 3 9 to 8 4 8 3 9 REM VAL OF PANEL MOUNTED IN STRUMENTS a Remove screws attachi...

Page 869: ...ption Provides visual and aural indication of position of aircraft when over 75 mc marker beacon 8 7 I I I I I I Part 8 Paragraph 8 5 TABLE 8 1 Cont EQUIPMENT MANUFACTURER AND MODEL FUNCTION AND CAPAB...

Page 870: ...8 1 contain eight receiver toggle switches marked RECEIVERS 1 Z 3 VOR 1 and Revised 1 December 1965 Part 8 Paragraphs 8 6 to 8 7 3 NORM 8 0UT ISO AMP TRANS REO 4MC380 Figure 8 1 Signal Distribution Pa...

Page 871: ...d then fed through a connector on the pilot s signal distribution panel to the co 8 9 _ _ _ _ _ C _ 2 MB and ADF 1 and 2 a rotary transmitter selector switch marked TRANS REC 1 2 3 and I C ONLY an iso...

Page 872: ...ck that receiver audio level can be adjusted by radio set volume control and ISOVOLcontrolonpilot s Part 8 Paragraph 8 7 7 K1 K2 K3 K4 RESISTORS R 1 THROUGH R8 _ K5 _ K6 RESISTOR 100 n CAPACITOR 4000...

Page 873: ...box Measure re sistance of relay coil This should be 400 ohms approxi mately replace if faulty 8 11 signal distribution panel Check that receiver audio is heard with pilot s receiver toggle switch on...

Page 874: ...K4 between terminal 69 andground The resistance should be 300 ohms approximat ely replace if faulty Part 8 Paragrapl J 8 8 to 8 8 2 INDICATION OF TROUBLE No intercommunication from third station No au...

Page 875: ...nder fiberglas cover One antenna for each receiver Forward loop for No 1 aft loop for No 2 ADF 8 13 8 9 MICROPHONE SWITCHES The pilot and co pilot each have a com bined transmit and interphone microph...

Page 876: ...Ins ert antenna element through lightening hole in wing tip cover and thread through hole in angle P lrt 8 Paragraph 8 10 1 to 8 10 5 TABLE 8 5 Cont ANTENNA TYPE POSITION ADF Sense Antenna Antiprecip...

Page 877: ...z z W z I c W Wz W __ I Figure 8 3 Antenna Locations Part 8 I 8 15 z z W z I c W Wz W __ I Figure 8 3 Antenna Locations Part 8 I 8 15...

Page 878: ...om mast assembly o Follow procedure in steps g through i and remove wire from chuck in mast adapter Part 8 Paragraphs 8 10 6 to 8 10 12 fitting inside cover g Place wing tip cover in position secure a...

Page 879: ...end mast assembly and thread cable through h Remove flooring as necessary to gain accen sleeve 8 17 METHOD OF REMOVING WIRE FROM JAWS OF CHUCK ASSEMBLY WIRE RETRIEVER TOOL MAST ADJUSTABLE ASSEMBLY SMA...

Page 880: ...eces sary to gain access and disconnect antenna cable from mast adapter onlead throughmast assembly Part 8 ParagraphF 8 10 14 to 8 10 16 q Unscrew and remove mast end cap and large gasket r Remove sma...

Page 881: ...ANTENNA MAST 20 MAST END CAP I I I 21 LEAD THROUGH MAST ASSEMBLY 22 GASKET 23 MAST SLEEVE 0 I 1 00 00 D I Zj CJQ s 1 CD 00 I U1 cI Zj CD 5 Ii CD e o s 16 1 END CAP 2 WASHER 3 HIGH VOLTAGE SEAL 4 STRA...

Page 882: ...gh e i Insert prepared cable end into other end of strain insulator as described insteps d throughf I 3 rt 8 Paragraphs 8 10 17 to 8 10 18 f Rem e screws and withdraw mast adapter complete with cable...

Page 883: ...cuit breaker panel The ac power is supplied from either of the aircraft inverters the 115 volts 8 21 j Attach tension unit to connector on eyebolt on upper section of vertical stabilizer using flat he...

Page 884: ...switch to MAG Check fuses then measure phase frequency and voltage of ac supply Revised 1 June 1970 Part 8 Paragraphs 8 11 4 to 8 11 7 400cps directly and the 26 volts 400 cps through a 115 26 volts s...

Page 885: ...750 K RESISTOR 1 K Figure 8 6 No 11 Junction Box Part 8 FIXED SYNCHRO SYNCHRO LOCK 4MC38 5 8 23 _ _ CAPACITOR 1250 UF 8 1 II RESISTOR 750 K RESISTOR 1 K Figure 8 6 No 11 Junction Box Part 8 FIXED SYNC...

Page 886: ...electrical connector b Release snap slide fasteners and lift out amplifier Revised 1 December 1965 Part 8 Paragraphc 8 11 8 to 8 11 12 TABLE 8 6 Cont INDICATION OF TROUBLE PROBABLE CAUSE CORRECTIVE A...

Page 887: ...propriate colum ns of the TEMPORARY REVISION INDEX provided at the front of the m anual Page 1 of 4 PSM 1 4 2 Part 8 TEMPORARY REVISION Serial II 18 dated 11 February 1974 Insert in Part 8 facing pag...

Page 888: ...crease voltage and check that fail light comes on within the values listed in Table 8 7 Page 2 of 4 Part 8 PSM 1 4 2 Temporary Revision No 18 8 11 71 POWER FAILURE SENSOR FOR GYROCOMPASS The power fai...

Page 889: ...BLE SUPPLY 18 TO 30V DC Figure 8 6A l Test Circuit for Gyro Compass Power Failure Sensor Page 3 of 4 r 0 Temporary Revision No 18 PSM 1 4 2 _ _ _ _ 1 J WHITE UNDER VOLTAGE SENSOR C4SCIOS2 K02 19 20PN...

Page 890: ...goes out within the values listed in Table 8 7 s Disconnect power supply and voltmeter Page 4 of 4 Part 8 PSM 1 4 2 Temporary Revision No 18 m Increase voltage and check that fai1light goes out withi...

Page 891: ...tADF 2 or 129 113 130 114 VOR 2 VOR 2 8 35 98 115 99 116 105 121 106 122 Revised 1 June 1970 8 24A Part 8 TABLE 8 6A NO II J B RMI JUMPERS INSTAL PILOT S CO PILOT S RED YELLOW BLUE LATION RMI RMI SYN...

Page 892: ...installation No 1 to be removed prior to any installation of 2 through 9 8 24B Revised 1 June 1970 j art 8 INSTAL LATION NO 9 NOTE 1 DESCRIPTION Dual VOR Single ADF See Note 3 PILOT S RMI DISPLAY l A...

Page 893: ...compass amplifier is applied to the flux valve From the flux valve slaving synchro signals are 8 25 8 11 13 INSTALLATION OF SERVO AMPLIFIER AND MOUNTING To install servo amplifier and mounting revers...

Page 894: ...toms probable troubles and correction proce dures is shown in table 8 7B 8 26 Revised 25 July 1968 I atot H P Hagraphs 8 llA Z to 8 llA 6 fed to the course indicator Cb H The slaving synchro signals...

Page 895: ...I Revised 2 5 July 1968 Figure 8 6A J2 Compass System Components Location Part 8 FLUX VALVE 8 26A I Revised 2 5 July 1968 Figure 8 6A J2 Compass System Components Location Part 8 FLUX VALVE 8 26A...

Page 896: ...rope floss extends about one inch so that the fibers of the floss are free to Revised 25 July 1968 Part 8 Parag raph 8 llA 7 to 8 12 TABLE 8 7B TROUBLE SHOOTING J2 COMPASS SYSTEM SYMPTOM PROBABLE TRO...

Page 897: ...with screws and 10ckwashers removed in a above Insure paral led alignment with line of flight 8 26C ionize in the slip stream by virtue of the impressed electrical potential between the electrified ai...

Page 898: ......

Page 899: ...lectronic Equipment 9 11 Electrical and Electronic Symbols Chart 9 13 Wiring Diagram Index 9 13 9 1 PART 9 WIRING DATA Part 9 Table of Contents Paragraph Page P lragraph Page 9 I 9 Z 9 3 General 9 3 W...

Page 900: ......

Page 901: ...rigerator and Liquid containers Ignition and induction vibrator Starting Pitot heaters engine 9 3 I 9 1 GENERAL The information contained in this part is intended to enable the maintenance repalrman t...

Page 902: ...or AN3350 2 MS24509 3 D7270 1 3 Klixon C4E1089 MS3l06B28 11S AN3320 1 C4E1088 Revised 15 July 1969 Pat t 9 Paragraph 9 3 TABLE 9 1 Cont CIRCUIT FUNCTION SYMBOL K L M P Q v W X RC RL RM RN RU RV RZ SX...

Page 903: ...or 3140 1 C450 Bendix AL58Dl105A 30 General Controls AV16B123OC General Controls MS3106B 14S 7S 9 5 INDEX NO 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 O 31 32 33 34 35 36 37 38 39 40 41 42...

Page 904: ...0S PA904SG Aerotec MS28010 5 MS3106A14S 2S MJl U S Gauge MS25123 1 2 C4E1090 Revised 1 February 1972 Part 9 INDEX NO 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 9Z 93 94 95 96 97...

Page 905: ...0 2 AN3027 S or MS35059 31 AN2552 3A 92269 Roller Smith FIL30 Burndy F1L60 Burndy F1L50 Burndy I 9 7 INDEX NO DESCRIPTION 127 Knob 12S Plug 129 Receptacle 130 Position Transmitter 131 Terminal Strip 1...

Page 906: ...025 2 C4SCI025 1 C4SCI024 13 C4SCI024 11 C29C59 Janitrol 25820089 01 Yap air Revised 1 February 1972 Part 9 INDEX NO 9 8 184 185 186 187 188 189 190 191 192 193 194 195 196 197 198 199 200 201 202 203...

Page 907: ...B16S lP 296 Circuit Breaker MP16lA Mech Prod 297 Switch 24002 4S Grayhill Revised 1 February 1969 I Part 9 r INDEX NO DESCRIPTION PART OR TYPE NO 242 Surge Limit Switch C4V1669 l 243 Ignition Unit l1C...

Page 908: ...184 1 STm N VT 24 andHB I VT 24 Crown MS3100K14S 2S MS24041 1 MS3106R20 27P Revised 1 February 1972 I Part 9 INDEX NO 298 299 300 301 302 303 304 305 306 307 308 309 310 311 312 313 314 315 316 317 31...

Page 909: ...Dage 1 317 1 Dage 1 353 1 Dage 1 916 1 Dage 5192 1 Dage 5193 1 Dage 381094 2126 0 Simmonds 9 10A I I INDEX NO 356 357 358 359 360 361 362 363 364 365 366 367 368 369 370 371 372 373 374 375 376 377 37...

Page 910: ...Dage 1 333 1 Dage MS310ZAZO 16P MS3106BZO 16S MS31 00K18 4P MS31 06B 18 4S Revised 1 February 197Z Part 9 INDEX NO 413 414 415 416 417 418 419 4Z0 4Z1 4ZZ 9 1013 DESCRIPTION Tank Unit No 6 Tank Unit...

Page 911: ...100A16S IP 664543 or 6565Z0 Sperry MS3106B3Z 6P 656767 Sperr y C90104 Sperry C4SC I05Z 7 9 11 _ _ _ r INDEX NO DESCRIPTION 4Z3 Adapter 4Z4 Plug 4Z5 Hood 4z6 Capacitor Assembly 4Z7 Light Assembly Toile...

Page 912: ...002 Littelfuse C4R1571 DHC 60020 3 DHC 60021 5 J26B6H6A Filtors Inc C4R1582 1 Revised 1 August 1963 Part 9 INDEX NO 525 526 527 528 529 530 531 532 533 534 535 536 537 538 539 540 541 542 543 544 545...

Page 913: ...Amplifier Revised 1 February 1969 PART OR TYPE NO C4EI0611 C6H ID 250 1783867 1 Sperry Part 9 9 l2A INDEX NO 580 581 582 583 DESCRIPTION No 11 Junction Box Indicator Gyro Compass Indicator Servo Ampli...

Page 914: ......

Page 915: ...9 40 9 42 9 44 9 46 9 48 9 49 9 50 9 51 9 52 9 54 9 55 9 56 9 57 9 58 9 60A 9 61 9 64 9 66 9 67 9 13 Part 9 Paragraphs 9 5 to 9 6 9 5 ELEC TRICAL AND ELEC TRONIC SYMBOLS all sYITlbols used in the elec...

Page 916: ......

Page 917: ...PST RELAY o A A2 0 0 ll SPST ROTARY 0 B3 0 B i I A3 I DPDT J 1 V I L PUSH BUTTON j NORMALLY OP EN i SWITCH SWITCH c SPST PUSH BUTTON SHOWN OPEN NORMALLY CLOSED SPST MOMENT ARILY ON THERMAL i EXTERNALL...

Page 918: ...NA CABLES TWISTED MICROPHONE D GROUND POLARITY DC POSITIVE AC CYCLES NEGATIVE A B PHASE 4MC400 9 15 HEATER PITOTHEAD THERMOMETER BULB ELECTRICAL RESISTANCE TEMPERATURE RESISTOR lOA FIXED RHEOSTAT lOA...

Page 919: ...part 9 390 391 9 16 Figure 9 2 I f 2 Sheet 0 Ca rgo Doors February 1969 Revised 1 part 9 390 391 9 16 Figure 9 2 I f 2 Sheet 0 Ca rgo Doors February 1969 Revised 1...

Page 920: ...4MC401 4MC401...

Page 921: ...1 I _ 0 N X E NOTE 1 RESISTOR ADDED _ MOD 4 1156 Z PRE MOD 4 13Z3 CLOSE 22 21 ARGODOOJ SW1T HJ OPEN 27 CENTER PYLON DISCO J JECT PA EL 0 l JUNCTION BOX 8 ________ NO nm E1 t t i n D 3 9 SEE SEE SEE M2...

Page 922: ...CATION SWITCH 15 LH PASSENGER DOOR UNLOCKED WARNING UGHT SWITCH 4MC402 Revised 1 February 1969 9 17 CARGO VITO PANEL o OPEN RAMP I DOOR SWITCH I I I I AMP DOWN OVERRIDE I SWITCH I I I 54 J 1 1 M28C20...

Page 923: ...M38A16 W M39A16 xl M40B16 M3SD16 29 ELECTRICAL SWITCH PANI 1 ____ O I 8 19 L ____ NO 2 lUNCTION BOX Part 9 WINDSHIELD WIPER MOTOR AND FILTER I I I L _____j 28 IPARK J CR08W1TCH 34 l l CAM i I _ COM i...

Page 924: ...M35B16 M35A16 31 8 21 lOA I ISEE FIGURE SEC BUSI 9 22 27 5V DC ______ l CIRCUIT BREAKER PANEL 4MC403 13 12 14 A6 1 16 WINDSCREEN WIPER SWITCH 30 I _____ J L P201 M35B16 M35A16 31 8 21 lOA I ISEE FIGUR...

Page 925: ...CA 1 ILANDING GEAR I SELECTOR I SWITCH 51 LANDING GE WARNING LIGHT ITHROTTLE SWITCHES L OVERHEAD em LANDING GE WARNING HO I LA INI I I I LAN 3 LOC 10 i 7 1 NOTE ALL LIMIT SWIT AIRCRAFT ON G CHES SHOWN...

Page 926: ...G12E20 0 D NO 2 DIMMING RELAY JL G17A20N X2 j A SEE FIGURE 9 26 L _46__ 5 NO 2 JUNCTION BOX I 1 8 R 35 0 DI0E20 012B20 J GGEAR WARNING HORN AND OR LIGHT TEST SWITCH O A D12E20 HORN TEST 54 GEA l DOWN...

Page 927: ...l8A20N E F 25 A B C D GIM20 E G2A20 F 25 Part 9 26 26 26 26 4MC404 evised 15 July 1969 9 19 J MC405 ALL SWITCHES SHOWN WITH AIRCRAFT ON GROUND LANDING GEAR DOWN AND LOCKED THROTTLES CLOSED P204 ___ IC...

Page 928: ......

Page 929: ...EL ENGINE ACCESSORY COMPARTMENT VENT DOOR ACTUATOR 298 L ___ LH ENGINE 9 20 Revised 1 Decembel 1965 L Part 9 Figure 9 5 Engine Accessory Compartment Ventilation System RH ENGINE 298 ENGINE ACCESSORY C...

Page 930: ...K54AI8N 41 96 97 298 NOTE 1 1GRD IDENT POST MOD 4 1228 I L JI LH FIREWALL MC40S n d 1 DecembeJ 1965 RH ENGINE ENGINE ACCESSORY COMPARTMENT VENT DOOR ACTUATOR CIRCUIT BREAKER PANEL SEE FIGURE 9 i2 27 E...

Page 931: ...3 44 lE31C20 0 lE31B20 43 lE34A20 lE35G 406 L 4117 I I 8 L_ _ __ NO 10 lUNC nON BOX LEFT WING JOINT 1 I I 403 2E34A20 SYSTEM f TEST RIGHT 2E33A20 RIGHT FUEL QUANTITY GAGE 404 404 LEFT FUEL QUANTITY GA...

Page 932: ...404 405 NO 6 TANk 409 UNIT 409 IE34F20 IE34G20 J t t IE3SB IE3SA 407 413 407 407 Revised 1 Decembe GHT WING JOINT I 408 407 407 407 407 2E35E 2E35D 2E35C I N OI 410 NO 2 170R 410 TANk 411 TANk 411 12...

Page 933: ...410 414 418 oR 407 411 409 412 407 409 1158 Figure 9 6 Fuel Quantity Indication Part 9 4NC40e 9 21 NO 6 TANK UNIT 407 407 2E35A 402 2E34G20 413 9 NO 6 TANK 17 407 408 271 UNIT 409 lE34G20 lE35A 407 N...

Page 934: ......

Page 935: ...1 LH WING JC PlOOI 1 J lQ31C20 lQ32C20 tLJ 112 Figure 9 7 Fuel Control 9 22 Revised 1 December 1965 Part 9 I 2Q3ZA20 2Q31A20 Q34A20 Q33A20 t lQ3ZA20 IQ31A20 14 IS Q3oD20 l SWITCH POSITIONS 12 OFF 13 B...

Page 936: ...2D20 T l31____ 32 LR FUlL TANK SBLECTOR VALVE 59 1 11 12 58 r 1965 A B CI OPEN I L ___________ ____ 59 2 i L N 5 NOTE 1 it FUEL SELECTOR WIRING PRE MOD 41 1162 2 FUEL SELECTOR WIRING POST MOD 4 1162 l...

Page 937: ...MTG BOLT NO 2 4MC454 Figure 9 7A Air Pumps Ferry Fuel Tanks Scheme 4 Revised 1 February 1972 9 22A NOTE 1 BASIC WIRING FOR AIR PUMPS 2 SPECIAL INSTALLATION WIRING FOR AIR PUMPS SEE FIG 9 22 SECONDARY...

Page 938: ......

Page 939: ...LH TANK ENGINES ON AUX TANK r LOW OIL LEVEL If E57A2 81 AUX BoOOi PUMP 42 L H ENGINE I R H ENGINE B FUEL SELECTOR SWITCH POSITIONS 12 OFF 13 BOTH ENG 14 NORMAL NES ON RH TANK 15 BOTH E 16 _ AUX B ES O...

Page 940: ...RE JUMPERS Figure 9 8 Auxiliary Fuel Control and Oil Low Level Warning Revised 1 December 1965 9 23 L NOTE 3 AUXILIARY FUEL PANEL __ Q45BI2 _____________________________________ Q47A _________________...

Page 941: ...0 lE5C20 2E4F20 lE4F20 lE4B20 5 6 lE4C20 L No 2 JUNCTION BOX evel Warning Revised 1 D ecernber 1965 Part 9 FUEL LOW LEVEL WARNING I LIGHTS I l CUIT BREA E PANEL 2E18C20 2E4G20 lE18C20 lE4G20 SEE FIGUR...

Page 942: ...EM 37 3 AMPERE PRE MOD 4 1274 0 0 0 0 co t l e l t l t l 83 THERMISTER I I I NO 2 FUEL CELL 4MC409 1 I I 2E5020 OH I I I 2E18A20 oF IEI8A20 OC I IE5020 0E I 5 NO I 0IMM iNG ELAY SEE FIGURE 9 26 FOR RE...

Page 943: ...PANEL 2 IQI4A20N CONNECTED TO GRD 4 AND 2Q14A20N REROUTED POST MOD 4 1228 3 SOO MOD 4053 POST 4 1281 NOTE l WIRING AND EQUIPMENT MARKED THUS ARE APPLICABLE TO MOD 4076 AND THE LOW OIL LEVEL LIGHTS ARE...

Page 944: ......

Page 945: ...3Q15B12 2Q5820 Xl i LBt r FUBL BOC lQ5820 GRD 2 O J PUMP RELAY NO 21UNCTION BOX 4 ro IF lQl4A _ Rev SEE FIGURE 9 32 r H 2Q17B18 2017C i iii 14 4 2E45A20 0 2 458 R 211 43A20 211 438 13 14 2E3A20 1 11 2...

Page 946: ...________ J 8 Figure 9 10 Fuel Oil and Hydraulic Control and Warning ised 1 December 19b5 9 25 tI J Part 9 RIGHT FUEL AND OIL CONTROLS IDENTICAL TO LEFT CONTROLS RIGHT FUEL RIGHT RIGHT RIGHT HYDRAULI...

Page 947: ...SWITCH STARTBR I SWITCH HOT FUEL PRIME iii r I I I I RH MAGNE 10 HT rni NT Revised 1 December 1965 Part 9 9 26 THEORETICAL SCHEMATIC IGNITION SWITCH IGNITION SWITCH m ffi Sun I _____ Vt 8 T I I _____...

Page 948: ...I I WiGNETO 10 SEE FIGURE I __ _ No l1UNCTION BOX HT L ______ HT J LH ENGINE Revised 1 December 1965 Fuel Prime LH MAGNETO I ID ID iii t HT TARTU k3A2 91 INDUCnON VIBRATOR I I PRIMER 13 lID18 Q1D18 I...

Page 949: ...OD 4 1174 3 CABLES AND EQUIPMENT PRE MOD 4 1281 FOR ALTERED CABLES POST MOD 4 1281 SEE FIG 9 12 III 2 V DC KIA16 3 NOTE RELAY TERMrNA HOWN LOCATED AS HIGH LIMIT RELAY POSITIONED ON SIDE OF uy r6 1 I C...

Page 950: ......

Page 951: ...0AI8 x_ STARTI G 21 lob d SEE 127 5 V DC FIGURE MAIN I US 9 2 CiRCUIT BREAKER PANEL P2C Revised 1 I 86 OVERHEAD CONSOLE 1 IGNITION SWITCH SEE FIGURE 9 11 UNIT I __T __ 2J3C20 _ 2J2D20 _ 2J3D20 t 2J2E2...

Page 952: ...I 1 I I I L ___ J 90 J LH ENGINE 4MC412 Figure 9 12 Ignition Analyzer Revised 1 December 1965 9 27 2J3C20 2J2D20 _ IJ2D20 IJ3C20 2J3D20 f 2J2E20 IJ2E20 IJ3D20 1 T r O A B O X_ olOJ 00 ow 3 I I 1 1 I...

Page 953: ...LTERNATE IFILTER IRAM 1 ____ OVERH Figure 9 13 Carburetor Air Valve Actuator 9 28 Revised 1 Decembt Part 9 lL27 8 36 11 109 69 110 69 111 11 109 96 97 NOTE CIRCUIT SHOWN WITH RAM AIR VAl CIRCUIT BREAK...

Page 954: ...El8 I 1 3 K68C18 K68Dl8 0 K68El8 1 4 K69C18 K69Dl8 4 K69El8 97 96 17 I L______J I I L _____________ 11TH RAM Am VALVE OPEN NO 2 JUNCTION BOX 8 PANEL r I I I I t J r I 36 I I I L i N N N t f r I f r r...

Page 955: ...ETOR AlR ACTUATOR 110 r 1 K65ElS If K67A lSN K66E18 69 A C B I IDENTICAL TO RH I J 4MC413 10_2 JU l AIR ACTUATOR l109 jf 1 3 _J K65ElS K66E1S K6SElS K69E18 3 S 69 K65ElS A If K67AlSN K66E18 C B 69 K6S...

Page 956: ......

Page 957: ...RING I FEATHER PU UNFEATHER I1_ I K38A K25E 41 c OFFr AUTO FEATF FEATHER UNFEATHEI L _ EMERGENCY PAN NOTE 1 WIRING CONNECTIONS MARKED THUS REPLACE IRING SHOWN IN DASH LINES POST MOD 4 1167 2 GRD 11 DE...

Page 958: ...RE 9 2 SEE FIGURE 9 9 SEE FIGURE 9 26 B NO 1 DIMMING RELAY NO 2 ruNCTION BOX Revised 1 D ecernber 5 113 OFF i ___ 2Q 20 r r ON I I 0 2Q41A20 A ill I I _ IQ40A20 0 1 _ ol L J lQ41A20 B FEATHER DILUTION...

Page 959: ...UTION VALVE 4MC4t4 Figure 9 14 Autofeathering Non Reversible Propellers Revised 1 December 1965 9 29 PROP FEATHER 10 _ 21 LEFT lK40A18 5 b 27 AUTOM SW K25A20 27 5 VDC 10 21 o _ RIGHT 2K40A18 SEE FIGUR...

Page 960: ......

Page 961: ...SY M I025 Figure 9 14A Propeller Feathering and Reversing Sheet 1 of 2 9 30 Revised 1 February 1969 Part 9 I L 1ALSO APPLICABLE TO MOD 4 1281 FOR AIRCRAFT STANDARDIZATION 2 ALSO APPLICABLE TO MOD 4 12...

Page 962: ...SE SOLENOID REVERSE a PUMP P K27C4 tot IK27B4 I AUX W UNFEATHER F R SOLENOID I K123A4N S U WALL I I RH SAME AS LH 358 357 KIOID22 KIOIC20 H J IKI06AA22 2KI04AA22 B 2KI06AA22 372 12 373 372 372 2KI02AA...

Page 963: ...2AL 4 Y I L a MAIN I BUS I LH I4 IK28C20 LJ 80 lj 8 K29A20N fI I AUX PUMP I RELAYS NO I JUNCTION BOX II PROP JUNCTION BOX CONDUIT ASSY 114 C4EI0074 1209 2KI07BIS jO A F r 2KI07A20 f 2KII7BISN 11 1 B _...

Page 964: ...I MAIN y I BUS 10 I IK28C20 I LH 2 1 I LJ 80 K29A20 N I AUX PUMP Rs LAYS _ NO I JUNCTION BOX 4MC455 1 O 2 2KI07A20 t T 2 1D 2KI06B20 __ _ 11 3 Cl J 2KI08C20 _ __r71 4 2KIOSB20 I1 t 5 2KIIOBI6 IO 2KIIO...

Page 965: ...I A3 H I 361 C CI A r C I REVERSE SOL CONDUiT A REVERSE ASSY 3116F B LH PROP CONTROL RELAY BOX 362 3 6 7 8 9 I 10 RH PROP CONTROL RELAY BOX IDENTICAL TO LH 362 RELAYS A UNFEATHER C REVERSE UNREVERSE...

Page 966: ...o N e If tJj NO 1 lC DIMMING L RELAY AUTO PROp FEATHER 8LOCKING RELAY 115 NO 2 JUNCTION80X 8 o 1 1 P AND K SECONDARY LOW PITCH STOP CONTROL I I i I FOR UNREVERSE SOL WHEN THROTTLES ARE NORMAL IF 8LAD...

Page 967: ...35A2C B H PITOT DIFFERENTIAL 121 PRESSURE SWITCH Figure 9 14A Propeller Feat Revised 1 February 1969 Lt 356 355 J3007 P3007 KIOOEI8 f IKI08820 1 t IKII2B20 f 2KII2B20 IKII4B20 I 2KII4B20 2KI09B20 KIOO...

Page 968: ...gure 9 14A Propeller Feathering and Reversing Sheet 2 of 2 4MC456 Revised 1 February 1969 Page 9 30A Part 9 r r r I I I I I IKII6A2ON I IKI20A20N I A L2KI20A2ON H 1 2 l IKII2A20 330 2 I IKII4A20 330 2...

Page 969: ...D43B20 BRAKE PRESSURE TRANSMITTER SYSTEM PRESSURE TRANSMITTER D44B20 9 30B Revised 1 December 1965 Part 9 122 a D43C20 BRAKE C 1 D41A20 PRESSURE INDICATOR A D D40A20 D42A20N 123 123 SYSTEM D _____ D4...

Page 970: ...1 f D43A20 D44A20 1 1 023 022 I T SEE FIGURE 9 19 FOR ENG INST FUSES 126 NO 10 JUNCTION BOX 4MC411 L o D43B20 BRAKE PRESSURE TRANSMITTER SYSTEM PRESSURE TRANSMITTER D44B20 Revised 1 December 1965 TB...

Page 971: ...9 N L 128 u u U y o L YELLOW F C2A20 GREEN EI C1D20 0 A Q I BLUE D C3A20 121 PILOT S CONTROL COLUMN 128 129 135 75 130 2 341 OR 134l 133J AILERON TRIM TAB SWITCH CO PILOT RH WING DOWN LH WING DOWN AIL...

Page 972: ...4 341 C2E20 Figure 9 16 Aileron Trim Tab Actuator and Indicator 4MC41e Revised 1 December 1965 9 31 CIRCUIT BREAKER PANELS I SECON ARY I sECONDiR I BUS 27 5VDC BUS 27 1 5 B 5 I I AILERON 27 27 AlL TRI...

Page 973: ...9 17 370 370 345 346 truments DC Engine Ins ENGiII ill RIG LE 1 33 RIGH I 2 I L H d 1 Decem RevIse AI SI L A l part 9 330 1 3420R 140 9 32 Figure 9 17 370 370 345 346 truments DC Engine Ins ENGiII il...

Page 974: ...ON LIGHTS 2Q61A2_0____1 CIRCUIT BREAKER PANEL evised 1 December 1965 Non 1 EQUf MOD 2 MOD 3 4 5 DET __ I S RUMENT P E _ I CARBURETOR AIR TEMPERATURE INDICATOR 137 C 2E 20N A 2E 0 l B 2R A20 32 CYLIND...

Page 975: ...EMPERATIJRE BULB E14C18N R 142 E13C18 B 15 CYLINDER HEAD TBMPERATURE BULB E12B18N 141 BI1C18 4MC417 ___ 91 96 2E13B16 E 2E14B16N D I 2E11B16 IC 2E12D16N B 2E9B16 A 2ElOBltjN d 2E15B16 I b 2E16B16 1 2E...

Page 976: ......

Page 977: ...TURN AND SLIP F3A INDICATOR M A FIn C TURN AND SLlP WARNING LIGHT F194 2 FI95 T 137 L ___________ _ NOTE 1 LD GRD 5 DENT POST MOD 4 1228 Z PRE MOD 4 1281 3 rOST MOD 4 1281 4 CONNECTIONS ARE THE SAME T...

Page 978: ...A20 I Jill L___________________________ _ F195A20 F194A20 FID20 F197J20 FI92A20 P207 D Revised 1 De 20N qI 20N 20 20 146 N TURN AND 12 SLIP INDIcqn ATOR A F2C20 L_ F4A PILOT S FLIGHT INSTRUMENT PANEL...

Page 979: ...GYRO COMPASS SEE FIG 9 36 4MC411 Figure 9 18 Flight Instruments AC and DC ised 1 December 1965 9 33 L 26 NCTION BOX IS SEE FIG 9 23 PI002 0 it 52 o FlO9B20 FlO9A20 51 0 F210B20 F21OA20 30 0 FlOilB20 F...

Page 980: ......

Page 981: ...E 148 RIGHT FUEL AND OIL PRESSURE INDICATOR 141 LEFT MANIFOLD PRESSURE INDICATOR 148 ecember 1965 I Part 9 Figure 9 19 Engine Instruments AC 9 34 Revised 1 D ENGINE IN r STRU N PANEL MANIFOLD INDICATO...

Page 982: ...lEVB20 I B lE19G20 150 A 1E29A20N 65 PI 2EIllB20 Ii I lElll820 I R 126 NOTE I PRE MOD 4 2 J POST MOD E INSTRUMENT PANEL IT MANIFOLD PRESSURE INDICATOR FUEL AND OIL PRESSURE INDICATOR A C D 141 B E F G...

Page 983: ...OIL PRESSURE TRANSMITTER FUEL PRESSURE TRANSMITTER MANIFOLD PRESSURE TRANSMITTER LH FIREWALL 4MC419 1 10 10 10 10 10 10 10 0 10 ON ON ON PlOO3 2E19B20 B 2E19A20 2E26A20N A 2E19E20 2E27A20 B C 2E28A20...

Page 984: ......

Page 985: ...f 2 I 535 555 5 55 9 10 11 12 13 U 15 16 17 18 19 1 557 558 55 4MC452 Revised 1 December 1965 9 67 I I Part 9 R 19 YEL L IS OOO I P e WHT BLK RED GRN YEL BRK ORM GY LIL ILK J GY KO OUT Fl 17 PRGHT APl...

Page 986: ...411 Figure 9 40 Audio System Signal Distribution Panels Sheet 2 of 2 9 68 Revised 1 December 1965 I Part 9 YEL BRN AA R2 22 tl R3 VOLUME YEL GY t 2 tl II CONTROL 1 r ELI BLK FI 17 R2 19 2 500 tl 5K GR...

Page 987: ...w Jersey U S A Aviation Electric Ltd 1 P o Box 6102 Montreal P Q Canada Revised 1 February 1972 Al 1 I Appendix I APPENDIX I REFERENCE PUBLICATIONS The following list is provided to help the operator...

Page 988: ...Canada Joy Manufacturing Canada Ltd 208 King St W Toronto Ontario Canada Revised 1 February 1972 I Appendix I REFERENCE PUBLICATIONS Cont COMPONSNT BATTERIES Aircraft Battery AN3 50 2 36 amp Aircraft...

Page 989: ...Dixon Rd Rexdale Ontario Canada J enmar Sales Ltd 38 Racine Rd Rexdale Ontario Canada i I I I AI 3 REFERENCE PUBLICATIONS Cont COMPONENT PUB LICATION REF CARBURETOR PD 1ZF7 19 CARBURETOR AIR TEMP IND...

Page 990: ...DIAN AGENT Railway Power Corp Ltd 197 Eastern Ave Toronto Ontario Canada Revis ed 1 February 1972 I Appendix I COMPONENT DE ICING SYSTEM AIR PUMP S O O I 33E02 5A DE ICIN S STEM DISTRIBUTOR VALVE S O...

Page 991: ...5 Shaft Rd Rexdale Ontario Canada Canadian Pratt Whitney Aircraft Co Ltd Longeuil P Q Canada AI 5 I REFERENCE PUBLICATIONS Cont COMPONENT DE ICING SYSTEM REGULATOR VALVE S O 0 38EOI ZA DE ICING SYSTEM...

Page 992: ...gation and Control Div P O Box 6102 Teterboro N J U S A Montreal p Q Canada Revised I February 1972 Appendix I REFERENCE PUBLICATIONS Cont I I I COMPONENT PUBLICATION REF FIRE EXTINGUISHERS 28X1694 W...

Page 993: ...Ham ilton Ontario Canada A C Appliances 8 Equipm ent Ltd 585 Dixon Rd Rexdale Ontario Canada AI 7 I COMPONENT FUEL PRESSURE TRANSMITTER ST 55A FUEL PUMP Z P R 600 CWXA Z FUEL QUANTITY INDICATOR 393004...

Page 994: ...Montreal P O Canada Aviation Electric Ltd P O Box 6102 Montreal P 0 Canada Revised 1 February 1972 Appendix REFERENCE PUBLICATIONS Cont COMPOt ENT PUBLICATION REF MANUFACTURER GYRO COMPASS SYSTEM ANN...

Page 995: ...1 45 Shaft Rd Rexdale Ontario Canada Brian Engineering Ltd 45 Shaft Rd Rexdale Ontario Canada AI 9 I REFERENCE PUBLICATIONS Cont COMPONENT PUBLICATION REF FLIGHT COMPARTMENT HEATER FANS S O 0 X70Z Z1...

Page 996: ...xdale Ontario Canada Aviation Electric Ltd P O Box 6102 Montreal p 0 Canada Revised 1 February 1972 Appendix 1 REFERENCE PUBLICATIONS Cont CO 1PONENT HYDRAULIC PRESS TRANSMITTER Type MJ l or 7609 37 D...

Page 997: ...Ltd P O Box 6102 Montreal P Q Canada Aviation Electric Ltd P O Box 6102 Montreal P Q Canada AI lOA I I REFERENCE PUBLICATIONS Cont COMPONENT PUBLICATION REF MANUFACTURER HYDRAULIC SELECTOR VALVES Con...

Page 998: ......

Page 999: ...td I 45 Shaft Rd Rexda1e Ontario Canada Aviation Electric Ltd P O Box 6102 Montreal P 0 Canada Al ll REFERENCE PUBLICATIONS Cont COMPONENT ISOLATION AMPLIFIER 346B 1 LANDING GEAR Main sub assy 5500 7...

Page 1000: ...ongeuil P Q Canada Brian Engineering Ltd 45 Shaft Rd Rexdale Ontario Canada Revised I February 1972 Ap endix I COMPO rENT NOSEWHEI LS ND TIRES Nosewheel 95 41743 Tire 7 50 x 10 OIL COOLER 87222 OIL CO...

Page 1001: ...700 North Miles Rd Bedford Ohio U S A Upton Bradeen James 890 Yonge St Toronto Ontario Canada Al 13 Appendix I REFERENCE PUBLICATIONS Cont COMPONENT PUBLICATION REF MANUFACTURER CANADIAN AGENT OIL TEM...

Page 1002: ...rio Canada AIC Applianc e Equipment Ltd 585 Dixon Rd Rexdale Ontario Canada Revised 1 February 1972 Appendix I REFERENCE PUBLICATIONS Cont COMPO ENT PUBLICATION REF PROPELLER FEATHER ING SWITCH N5008...

Page 1003: ...trai Ave Montreal P Q Canada Sperry Gyroscope of Canada Ltd P O Box 710 Montreal P Q Canada AI IS I COMPONENT SYNCHRO BREAKER S O O 11 4810 TACHOMETER GENERATOR 2CM9AAA 6 TACHOMETER INDICATOR 8DJ82 BA...

Page 1004: ...a Canadian Curtiss Wright Ltd 6503 Northam Drive Mississauga Ontario Canada Revised 1 February 1972 I I I I I I A Jendix I REFERENCE PUBLICATIONS Cont COMPONENT PUBLICATION REF MANUFACTURER VIBRATION...

Page 1005: ...C4V100 1 5 C4G1066 C4Gl720 C4GI022 C4Zl04l3 C4B1055 C4B10000 C4B10040 C4Fl186 7 C4F1633 9 A2 l I I I Appendix II APPENDIX II SPECIAL ORDER EQUIPMENT The following table lists items of special order e...

Page 1006: ...1984 6 C4GI091 C4GI09Z EO 43391 C4G1146 C4G1154 C4G1155 C4F1875 7 C4F1875 5 Revised 1 February 1972 I Appendix II A2 2 SPECIAL ORDER EQUIPMENT Cont DESCRIPTION CABIN Cont Cargo Floor Overlay for use w...

Page 1007: ...ks scheme 2 C4GI007 3 Long Range Fuel and Oil Tanks scheme 4 C4G1500 1 Revised 1 February 1972 A2 3 Appendix II SPECIAL ORDER EQUIPMENT Cont DESCRIPTION ASSEMBLY CABIN Cont Airline Type Seats Order to...

Page 1008: ...ASSEMBLY C4Gl147 C4P1749 3 4 Order tires by size C4G1667 C4E 10185 C4G1664 Revised 1 February 1972 I Appendix II SPECIAL ORDER EQUIPMENT Cont DESCRIPTION MISCELLANEOUS Cont A2 4 Wing Inspection Light...

Page 1009: ...air craft aircraft utilization and type of maintenance organization select one of two methods A3 1 Appendix III General Information APPENDIX III INSPECTION SCHEDULE GENERAL INFORMATION INSPECTION REQ...

Page 1010: ...of some phased in spection items at stipulated periodic in spection intervals Revised 25 April 1967 Appendix III General Information Method 1 Periodic Inspection Method 1 is re presentative of the con...

Page 1011: ...34 35 35 35 35 38 39 36 43 43 43 37 44 48 49 40 45 43 47 46 50 55 55 55 5 J 56 56 56 56 A3 3 I I I 50 100 150 200 250 300 50 1 1 1 1 1 1 1 2 2 2 2 2 2 2 5 3 4 I N 7 7 7 7 7 7 7 S 8 9 10 16 8 9 10 P 1...

Page 1012: ......

Page 1013: ...en or miss ing seal and security Fire extinguisher in designated location Revised 25 April 1967 A3 5 ITEM NO 1 2 3 4 PART 1 BETWEEN FLIGHT INSPECTION ELECTRICAL POWER OFF PREPARATION Wheels chocked an...

Page 1014: ...Loose equipment for proper stowage 9 Oxygen cylinder pressure at 1800 50 psi Revised 25 April 1967 Appendix Iil Part 1 Between Flight ITEM NO RH WING AND ENGINE 1 Wing exterior skin for obvious damag...

Page 1015: ...le jar 15 Fuel booster pump for fuel contamination visual use sample jar Revised 25 April 1967 A3 7 ITEM NO LH WING AND ENGINE Appendix III Part 1 Between Flight 1 Wing exterior skin for obvious damag...

Page 1016: ......

Page 1017: ...erior skin for obvious damage 3 Aileron exterior skin for obvious damage Revised 25 April 1967 A3 9 PART 2 DAILY INSPECTION ELECTRICAL POWER OFF ITEM NO PREPARATION 1 Wheels chocked and aircraft groun...

Page 1018: ...vator skin for obvious damage 6 Oxygen cylinder pressure at IBOO 50 psi A3 10 Revised 25 April 1967 Appendix III Part 2 Daily ITEM NO 4 Oil tank for specified quantity Fill to full mark on dipstick 5...

Page 1019: ...1 All antennas and covers as applicable for obvious damage and security Revised 25 April 1967 A3 11 ITEM NO LH WING AND ENGINE 1 Wing exterior skin for obvious damage 2 Flaps exterior skin for obviou...

Page 1020: ...its using test switch 2 Check pitot head heating elements for operation A3 l2 Revised 25 April 1967 Append x III Part 2 Daily RH REVERSIBLE PROPELLER POWER PLANT 1 Check main sump for correct fluid le...

Page 1021: ...ng Microswitch and electrical wiring for damage chafing and security Revised 1 February 1972 A3 13 I r ITEM NO 1 2 3 4 5 6 7 8 9 10 11 1 PART 3 PERIODIC INSPECTION ELECTRICAL POWER OFF PREPARATION Whe...

Page 1022: ...and security Electrical wiring and connectors for damage chafing and security Revised 25 April 1967 Appendix II Part 3 Periodic ITEM NO 6 7 8 9 10 Package No 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17...

Page 1023: ...nstrument panel shock mounts for damage proper clearance and security Revised 1 February 1969 A3 1S ITEM NO Appendix III Part 3 Periodic Package No 3 Every ZOO flying hours 1 Shock strut torque arms f...

Page 1024: ...nd security Acces sible electrical wiring for damage chafing and security Revised 1 February 1972 I Appendix HI Part 3 Periodic ITEM NO 4 Outside air tem perature indicator for damage and security 5 W...

Page 1025: ...damage chafing and security Heater fuel pump for leakage and security Revised 1 February 1969 A3 l7 ITEM NO R2 ckag I _ Every 200 flying hours 1 Wing flaps exterior skin for cracks and wrinkles 2 Aile...

Page 1026: ...pect for cracks and damage Flight control cables for fraying and security Revised 1 February 1969 I Ap l mdix III Part 3 Periodic ITEM NO 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 1 2 3 4 5 Every 200 fly...

Page 1027: ...Engine drain and breather box for damage leakage and security Drain box Revised 25 April 1967 A3 19 Appendix III Part 3 Periodic ITEM NO Package No 12 Every 600 flying hours 1 Visible internal areas...

Page 1028: ...security 3 Air induction system mixing valves for damage and security A3 20 Revised 25 April 1967 I Appendix III Part 3 Periodic ITEM NO 13 14 15 Supercharger drain outlet for damage clogging and secu...

Page 1029: ...age and security 30 Main oil screen for damage cleanliness and security Revised 25 April 1967 A3 21 ITEM NO 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 Carburetor air valve...

Page 1030: ...ackages 24 through 27 These packages have been intentionally left blank A3 22 Revised 1 March 1968 Appendi III l al t 3 Periodic ITEM NO 31 Engine fire detecting elements for damage breaks properly i...

Page 1031: ...anti colli ion light for damage cracked lens cleanliness and security Revis ed 25 April 1967 A3 23 ITEM NO Appendix III Part 3 Periodic FUSELAGE AND EMPENNAGE Aft from bulkhead sta 93 00 to tail of a...

Page 1032: ...owed Ramp door extension for cracks damage and coating of nonskid rnaterial Revised I February 1969 APT endi x III Htrt 3 Periodic ITEM NO 4 1 2 3 4 5 6 7 8 9 10 11 12 Drain holes for clogging Every 2...

Page 1033: ...rior skin for cracks and wrinkles 2 Aileron exterior skin for wrinkles Revised 1 March 1968 A3 Z5 I ITEM NO 18 19 20 21 Cargo tie down rings for damage and security Distributor valves for damage and s...

Page 1034: ...uts blisters smooth spots out 0 round and excessive wear tread worn to cord Revised 1 February 1969 I Appendix III Pvt 3 Periodic ITEM NO 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25...

Page 1035: ...ar attachment bolts and inspect for cracks magnetic particle method Revised 1 February 1969 A3 27 I r ITEM NO Appendix III Part 3 Periodic 3 4 Brake linings for damage and excessive wear Replace brake...

Page 1036: ...e 3 Deicing fluid transfer tube for leakage and security of connectors 1 3 28 Revised 25 April 1967 Appendix III Part 3 Periodic ITEM NO 2 Bushings for damage and scoring Package No 41 Every 1200 flyi...

Page 1037: ...m age and security 10 Generator electrical leads for damage and security Revised 25 April 1967 A3 29 ITEM NO 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Appendix III Part 3 Periodic Propeller m echanical h...

Page 1038: ...r damage chafing cracks and security Clamps for cracks and security Deleted Revised 1 February 1969 A JlPltJNfix ru patt 3 Periodic ITEM NC 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30...

Page 1039: ...ce with Figure 1 11 Z Accomplish S ecial Inspection items as necessary Revised 1 March 1968 A3 31 I ITEM NO 1 Intake pipes for damage leakage packings and security z Push rod housing for damage and se...

Page 1040: ...or unlocked light c Rear entrance light d Passenger warning sign lights A3 32 Revised 25 April 1967 ELECTRICAL POWER ON ITEM NO GENERAL Package No 56 Every 50 flying hours 1 2 3 4 5 6 7 8 9 10 The fol...

Page 1041: ...and inspect for chafing and proper travel b Check fuel system for leaks Revised 25 April 1967 A3 33 ITEM NO 10 11 12 13 14 e Panel lights f Cargo loading light g Emergency lights Anti collision light...

Page 1042: ...or proper operation using carburetor air induction switch and hot air lever Revised 25 April 1967 I Appendix III Part 3 Periodic ITEM NO 12 A3 34 c Carburetor air induction valves for proper operation...

Page 1043: ...ng fretting and distor tion felt grease retainers for deterioration and Revised 25 April 1967 A3 35 ITEM NO 1 2 3 4 5 6 7 8 9 10 Appendix III Part 4 Special Inspections PART 4 SPECIAL INSPECTION REQUI...

Page 1044: ...cture for corrosion Check inlet filters at both pumps for clean lines daily Revised 1 February 1969 I ALJ endix II P t 4 Special Inspections ITEM NO 11 12 13 14 15 16 17 18 19 ZOo A3 36 INSP DUE Durin...

Page 1045: ...t actuator threads for exces sive wear corrosion Clean lubricate re assemble and reinstall A3 36A I ITEM NO 21 22 INSP DUE Every 500 hours in dusty conditions Every 2000 hours or two years whichever c...

Page 1046: ......

Page 1047: ...elines and connections affected by removal or replacement Switch booster pumps on during check A3 37 ITEM NO INSP DUE Appendix III Part 4 Special Inspections POWER PLANT 1 2 3 4 5 6 7 8 9 10 11 Oversp...

Page 1048: ...opeller control replaced if cause of over speed cannot be isolated elsewhere Revised 25 Apri11967 I Appendix HI Part 4 Special Inspections ITEM NO 13 14 15 16 1 1 1 2 3 4 5 6 7 A3 38 INSP DUE Within o...

Page 1049: ...ttles Discharge and recharge cabin and flight com partment heater fire extinguisher bottles A3 39 I ITEM NO 8 9 10 INSP DUE Overspeed in excess of 40 percent above high rpm setting reversible propel l...

Page 1050: ...i i...

Page 1051: ...t 7 Check main landing gear torque arms for ex cessive play and inspect for structural damage A3 41 Appendix ill Part 5 Heavy landing PART 5 INSPECTION AFTER A HEAVY LANDING The following inspection i...

Page 1052: ...14 Inspect wing shroud skin for buckling cracks and loose or sheared rivets Revised 1 February 1972 l ppendix III Part 5 Heavy landhg FOOT PRESSURE 2 J I I Q fiQ IN MAX FOOT PRESSURE 1 AND MARK DECK F...

Page 1053: ...considered essential to carry out an X ray exam ination of the structure However if suitable A3 43 15 Inspect fairing strips on outboard side of engine nacelles for buckling cracks and loose or shear...

Page 1054: ...repaired if applicable and any fur ther remarks pertinent to this inspection Revised 25 April 1967 Appendix II Pdrt 5 Heavy 1anding equipment is available and the responsible engin eer considers such...

Page 1055: ...nation Unit Filter 1250 hours Heater Fuel Pump Filter Element 1000 hours Revised 25 Apri11967 A3 45 Appendix III Part 6 Replacement Schedule PART 6 RECOMMENDED OVERHAUL OR REPLACEMENT SCHEDULE This re...

Page 1056: ...fe At Engine Life At Engine Life 1000 hours 1000 hours 300 hours 2000 hours Revised 1 February 1972 I Appendix HI Part 6 Replacement Schedule ITEM Engine R2000 7M2 Carburetcr Engine Driven Fuel Pump E...

Page 1057: ...evised 1 February 1969 Page A3 49 A3 49 A3 49 A3 49 A3 49 A3 49 A3 5Z A3 5Z A3 53 A3 53 A3 53 A3 47 PART 7 Appendix III Part 7 Special Structural Inspections SPECIAL STRUCTURAL INSPECTIONS Paragraph 1...

Page 1058: ..._ _ _ _...

Page 1059: ...nting brackets for cracks paying particular attention to the areas indicated in figure AIII 3 A3 49 I Appendix III Part 7 Special Structural Inspections PART 7 SPECIAL STRUCTURAL INSPECTIONS 1 GENERAL...

Page 1060: ...are detailed in this Appendix Department of Transport Approved May 1968 A3 50 Revised 25 July 1968 Appendix II Part 7 Special Str ctural Inspections TABLE AIII l F AIL SAFE COMPONENTS AND INSPECTION...

Page 1061: ...ace at 75 000 hours C4BM1430 Replace at 75 000 hours Department of Transport Approved May 1968 A3 5l TABLE AIII 2 Appendix ill Part 7 Special Structural Inspections SAFE LIFE COMPONENTS AND REPLACEMEN...

Page 1062: ...nel item 66 figure Revised Z5 July 1968 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ r_ _ _ _ _ _ _ _ _ _ __ Ap penaix II P6rl 7 Special Strnctural Inspections c Instal wing flap actuator Refer to Pa rt Z of t...

Page 1063: ...and operat ing lever base for cracks as detailed in figure AIII 23 Use dye penetrant mtlthod A3 53 1 Z second panel outboard from nacelle See figure AlII 17 b Inspect for cracks in milled bottom skin...

Page 1064: ...ENTER SECTION REAR SPAR LHS Figure Aill 3 Wing Flap Actuator Mounting Brackets Revised 25 July 1968 Appendix III Part 7 Special St uctural Inspections AREA OF CRACKS AND SHEARED RIVETS ON ALL BRACKETS...

Page 1065: ...TYPICAL BOTH SIDES Figure Am 4 Nacelle to Wing Center Section Drag Angle Revised Z5 July 1968 A3 55 LEADING EDGE OF WING CENTER SECTION LOCATION OF FRONT SPAR DRAG ANGLE Appendix ill Part 7 Special St...

Page 1066: ...Bottom Skin 0 0 C 0 0 C 0 0 C 0 0 C 0 0 C 0 0 C 0 0 C 0 0 C 0 0 C 00 0 C 0 0 C Revised 25 July 1968 Appendix III Part 7 Special Structural Inspections FUSELAGE 0 0 0 0 0 0 0 0 0 0 o C 0 0 0 A3 56 _ 1...

Page 1067: ...LOCATION OF CRACK 0 0 0 0 0 Figure AIlI 6 Wing Center Section Bottom Skin Revised ZS July 1968 A3 57 FUSELAGE 0 0 0 0 0 0 0 0 0 0 0 0 FRONT SPAR 0 0 0 REINFORCING STRAP 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0...

Page 1068: ...nter Section Bottom Skin A3 58 I 0 FUSELAGE t 0 0r 0 0 0 0 0 0 0 0 Revised 25 July 1968 _ _ _ _ _ _ Appendix IJl Pc rt 7 Special Strllctural Inspections 0 0 NACELLE 0 0 O r 0 0 0 0 0 0 0 0 0 0 REAR SP...

Page 1069: ...uctural Inspections o 0 0 Figure AIII 8 Wing Center Section Access Panel Revised 25 July 1968 A3 59 r r ACCESS PANEL 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 o 0 0 0 VIEW LOOKING UP ON UNDERSIDE OF W...

Page 1070: ...0 0 0 0 0 I I Figure Aill 9 Fuselage to Wing Center Section Drag Angle A3 60 Revised 25 July 1968 I Appendix II Part 7 Special St ructural Inspections 0 0 0 0 0 0 0 0 0 0 I I 0 0 0 0 0 0 OUTBOARD o 0...

Page 1071: ...o o o Figure AID IO Wing Center Section Reinforcing Strap o o o o o 0 C o 0 o 0 o 00 o o 0 o 0 A3 61 OUTBOARD o o o o o 0 o o 0 o 0 o o o o o Appendix ill Part 7 Special Structural Inspections FORWARD...

Page 1072: ...OWN FORWARDt Figure AIII ll Fuselage to Wing Center Section Drag Angle A3 62 Revised 25 July 1968 I Appendix HI Part 7 Special Structural Inspections WING CENTER SECTION CRACKS IN BEND OF DRAG ANGLE j...

Page 1073: ...TYPICAL BOTH SIDES Figure AIII 12 Wing Center Section Reinforcing Straps Revised 25 July 1968 A3 63 I o o o o o o o o FORWARD EDGE FORWARD REINFORCING STRAP t FUSELAGE 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0...

Page 1074: ...ON FRONT SPAR LHS HOWNI Figure AnI l3 Wing Center Section Front Spar Cap Angle Revised 25 July 1968 Appendix III Part 7 Special Strl1ctural Inspections RIB NO 3 0 00 0 o FRONTSPAR 0 0 0 0 0 0 0 A3 64...

Page 1075: ...ON O VIEW ON ARROW A Figure AIII 14 Fuselage to Wing Center Section Joint Revised 25 July 1968 A3 65 o Appendix ill Part 7 Special Structural Inspections UNDERSIDE WING CENTER s 00 0 0 FRONT SPAR 0 DR...

Page 1076: ...OF WING CENTER SECTION Figure AliI IS Wing Center Section Ribs in Nacelle Area Revised 25 July 1968 Appendix III Part 7 Special Structural Inspections A3 66 TOP SKIN WING CENTER SECTION TYPICAL LOCATI...

Page 1077: ...Figure AlII 16 Wing Attachment Fitting Failures Caused by Fatigue Tests Revised 25 July 1968 A3 67 I LOCATION OF CRACK LOCATION OF CRACK Appendix ill Part 7 Special Structural Inspections LOCATION OF...

Page 1078: ...OKING UP ON UNDERSIDE OF WING RHSSHOWN Figure AllI 17 Outer Wing Bottom Skin c Revised 25 July 1968 Appendix III Part 7 Special Structural Inspections c 0 0 0 0 0 0 0 0 CI o o o A3 68 000 000 000 o 00...

Page 1079: ...tructural Inspections o 00 00 00 00 Figure AIII 18 Outer Wing Bottom Skin Revised Z5 July 1968 A3 69 f o NO 67 ACCESS PANEL LOCATION OF CRACK NACELLE o 0 o o 0 o o o VIEW LOOKING UP ON UNDERSIDE OF WI...

Page 1080: ...GE ARMS TYPICAL BOTH SIDES 0 0 0 0 Figure AIII 19 Outer Wing Bottom Skin A3 70 Revised 25 July 1968 Appendix III Part 7 Special Structural Inspections u u i 0 U 0 0 U 0 LOCATION OF CRACK 0 0 0 0 o o o...

Page 1081: ...BELLCRANK LOOSE AND SHEARED RIVETS Figure AnI ZO Wing Flap Controls Tube Revised 25 July 1968 A3 71 WING FLAP ACTUATOR CONTROLS TUBE TO LEFT WING VIEW LOOKING ON WING CENTER SECTION REAR SPAR LHSI AR...

Page 1082: ...LING FLAP ARM Figure AIII 21 Inboard Trailing Flap Arm A3 72 LOCATION OF CRACK Revised 2S July 1968 A pendix JlI Part 7 Special St uctural Inspections 0 00000 0 0 0 0 0 0 0 0 0 0 VIEW ON INBOARD SIDE...

Page 1083: ...cket Lug Inspection Revbed 1 February 1969 It l A3 73 _ _ _ _ l _ _ _ _ _ _ I _ _ _ _ _ _ _ _ _ _ _ LOCATION OF CRACKS VIEW LOOKING AFT Appendix III Part 7 Special Structural Inspections Figure AIII Z...

Page 1084: ...AY SHOW CRACKS Figure Aill Z3 Nose Gear Steering Universal Block Inspection Revised 1 February 1972 Appendix III F art 7 Special Structural Inspections A3 74 o o ANY AREA SO INDICATED MAY SHOW CRACKS...

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